Mercury Capsule

FAMILIARIZATIONMANUAL:

.c_-'_°_c_Gs COPY NO. _-

ASA

SATE LLITECAP SU L E_,"

_ocument contains information_onal

d__ the Espionage

Laws,. ?tie 18__793 and.7?4,-l_._e

nauthorized person-'Tsited by law.

"_ =_Oili##lil_L_&..

AIRCRAFT _?

__ .... . NOV_ 1961

............_ ,_,-_:

PAGE ....

REPORT SEDR 10_

MODEL_ 133

REVISEDST. LOUIS, MISSOURI

REVISED..

INDEX OF EFFECTIVE PAGES

The pages of this Manual currently in effect are

listed below in numerical order.

Page No. Issue

A Basic

B Basic

C Basic

i-i thru 1-29 Basic

2-i thru 2-28 Basic

3-i thru 3-54 Basic

_-i thru4-63 Basic

5-I thruS-22 _'_ ....6-1 thru6-11 _,_ BasicBasic

7-1 thru 7-5 Basic

8-i thru8-10 Basic •

9-1 thru 9-32 Basic

10-1 thrulO-35 Basic

ii-i thru ii-52 Basic

12-1 thru12-29 Basic

13-i thru 13-76 Basic

.}

DATE ,1 November 1961

REVISED

REVISED

ST. LOUIS 3, MISSOURI

PAGE ....... .1_

REPORT 8'_R i0_

MODm. 133

FOREWORD

The purpose of this document is to present a clear,operational description of the various capsule systems

and major components. Two types of usage for the man-ual are visualized. The first is an orientation-in-

doctrination type document. The second use is as a

reference document containing relatively detailed In-

formation on all systems and components.

The manual is divided by capsule systems. The first

part of each section is devoted to the description and

operation of "specification compliance capsule" system.

Capsules numbered 18 and 19 are the specification

compliance capsule. They are manned orbital capsules

and are representative of the Mercury Program. Imme-

di&tely following the specification compliance sys-

tem coverage is the Test Configuration Capsule Cov-

erage. _his area compares the other capsules to the

specification compliance capsule or to a prior cap-

sule. The capsules are compared on a, "like specifi-cation compliance capsule except as follows" bases.

The Test Configuration Capsules are compared to the

specification compliance: capsule system or to anyother preceding capsule depending on which reference

causes the least duplication. The reader will not be

required to refer to more than two prior capsules sys-

team including the specification system. Separate in-

formation is provided for each capsule test configura-

tion, when the information is the same for each cap-sule it will not be repeated. All capsules will be

covered in this manual for one revision after the par-

ticular capsule has been launched successfully. Afterthat date they will be dropped from future issues.

Capsules numbered 2, 3, 4, 5, 6, 7, 11 and 14are

covered in the i February 1961 issue of SEX_ 104

revised I August 1961. Capsules numbered 12, 15, 17

and 20 have been assigned an eighteen orbit mission

and will be covered in a latter publication.

All capsule configurations are not finalized as of

this printing, additional information will appear in

subsequent revisions to th_s document, ::reflecting

changes as they are incorporated in the capsule.

¢

SECTION INDEX

PAGE

SECTION I

INTRODUCTION ........ ...................................................................... 1-1

SECTION II

MAJOR STRUCTURAL ASSEMBLIES .......................................................... 2-1

SECTION II!

ENVIRONMENTAL CONTROL SYSTEM .................................................... 3-1

SECTION IV

STABILIZATION CONTROL SYSTEM ....................................................... 4-1

SECTION V

SEQUENCE SYSTEM, LAUNCH THROUGH RETROGRADE OR ABORT .................. 5-1

SECTION V!

ESCAPE AND JETTISON ROCKET SYSTEMS ............................................... 6-1

SECTION VII

POSIGRADE ROCKET SYSTEM ................................................................ 7-1

SECTION VIII

RETROGRADE ROCKET SYSTEM .............................................................. 8-1

SECTION IX

SEQUENCE SYSTEM, LANDING THROUGH RECOVERY ................................. 9-1

SECTION X

ELECTRICAL POWER AND INTERIOR LIGHTING SYSTEMS .............................. 10-1

SECTION XI

COMMUN ICATION SYSTEM ................................................................ 11-1

SECTION Xll

NAVIGATIONAL AIDS ....................................................................... 12-1

SECTION XIII

I NSTRUME NTATi ON SYSTEM ............................................................... 13-1

illillllil_i IPIIIIIIpIL lnPI • I

1-1

SECTION I

INTRODUCTION

+--.

":,::iiiiiiiiiiiiiiiiiii!iiiiiii++i!!iiiiii====================================

TABLE OF CONTENTS

TITLE PAGE

MISSION DESCRIPTION ........................ 1-3

CAPSULE DESCRIPTION ........................ 1- 3

BOOSTER DESCRIPTION ........................ 1-19

CAPSULE RECOVERY ............................ 1-19

CREW ................................................... 1-19

TEST CONFIGURATION CAPSULES ..... 1-23

•wv m "1 I I 5/Ll_l I I/ii I-

PAGE

REPORT

MODEL.

1-_2

SEDR 104

133

ST.LOUIS. MISSOURI

DATE 1 NOVEMBER 1961

REVISED

REVISED ,,

ESCAPE ROCKET_

PYLON JETTISON ROCKET_

ANTENNA

CAPSULE ADAPTER (REF)

FIGURE 1-1-CAPSULE PREL_AUNCH CONFiGURATiON

SPIKE

PYLON

ET ROROCKET AND

POSIGRADE ROCKETS

PM45.-2C

•:,}

P If"_l INI I=" I I_ I_" m,. "_" • - '- -- o_m.l'w • ial'_il_'_

\

J

DATE i November 1961

R£VISED

REVISED

McDONNE ST. LOUIS 3, MISSOURI

_- ..... 1/" lu7 l'll f ,,

p_s" I-3,

mm_omv SEDR 104

,4oom. 133

I. INTRODUCTION TO PROJECT MER_

i-i. MISSION DESCRIPTION

The possibility of man vesturing into space has shifted quite recently

from the fantasy of "science fiction" to the realm of actuality. Scientific

progress has slowly but surely loosened man's ties to the earth, and recent

technological advances have promised to release him completely. Today, space

flight is considered well within the range of man's capabilities.

Initiated by the National Aeronautics and Space Administration, a space

flight program is now underway. Through the research, design and production

facilities of McDonnell Aircraft Corporation and their many sub-contractors,

an _nerican will venture into space. The program that will put him there

is Project Mercury.

Fundamentally, the mission of Project Mercury is the projection of a

manned capsule into a semi-permanent orbit about the earth, the study of man's

capabilities in space flight, and the subsequent safe return of the capsule and

its occupant to the earth's surface. It is immediately obvious that the mis-

sion, while simply stated, is of tremeadous scope and magnitude, and requires

exceptional coordination of maupower and facilities. The date contained in

this and succeeding sections will provide detailed information on the equipment

and procedures utilized to accomplish that mission.

1-2. CAPSULE DESCRIPTION

1-3. General

See Figures I-I, 1-2, 1-3 and i-_. The Project Mercury capsule is basi-

cally a conical structure containing a pressurized area suitable for human

occupation during launch, orbit, and recovery phases of the mission. The

"base" of the cone contains provisions for attachment to the ATLAS booster,

PAGE

REPORT

MODEL

1-!4

$EDR 104

133

Mc'DONNELL ' ......... ST.LOUIS, MISSOURI


REVISED, ,

REVISED

//

FIGURE I-Z INTERIOR ARRANGEMENT

!!

/

P_,_45-1A

"CC,,;7;DZ;,;, i.-_r_

, Z J

DATE

REVISED

REVISED

1 NOVEMBER 1961 Mc,DONNE_ __ PA_E '-_ST.LOUIS, MISSOURI REPORT .SEDR 104

'_" . -- MODEL 133

t

i

£241.53 _272.48 _303.43 7354.05 _358.05 E389.O5

ESCAPE PYLON

I°752.69 7103.4.4.

ATLAS ADAPTER

1

Ty

RX 12.00 L X12.00

RX - LX

BY 8.75

_Y5ECTI0kl A,_,

FIGL)I2E I-3 _TATION5 E:IIAG2AM

--"" .; .... NT" " "_v i i i,,,/_-- I _1_1,I,,,,,

PH4-s-I_.B

PAGE I-6

REPORT SEDR104MODEL 133

Mc'DONNEL_L_ __ST.LOUIS. MISSOURI

DATE

REVISED

REVISED

1 NOVEMBER 1961

i_ ]_,1,57 (OI2BtT COi',d_'lC_._ -=,J* !

!_ " F.

/

FIGUI_E l-a, C_,PSULE E)INEN_[ON_pH4S-t 5,_,


REVISED ....

REVISED

Mc'DONNE ST.LOUIS, MISSOURI

PAGE

REPORT

MODEL

1-7

SEDR 104

,133

/--

ROLL

Z

+

X

PITCH

/

Y

+

Y

YAW

NORMAL ORBITAL FLIGHT

PITCH

PITCHIS DEFINEDASTHE ROTATION OF THECAPSULEABOUTITS X-AXIS

THE PITCH ANGLE IS ZERO DEGREES t0 °) WHEN THE Z-AXIS LiES IN A

HORIZONTAL PLANE. USING THEASTRONAUTS RIGHT SIDE ASA REFER-

ENCE, POSITIVE PITCH ISACHIEVED BY COUNTERCLOCKWISE ROTATION

FROM THE ZERO DEGREE t0 °) PLANE. THE RATE OF THIS ROTATION IS

THE CAPSULE PITCH RATE AND IS POSITIVE IN THE DIRECTION SHOWN

AS ARE THE CONTROL MOVEMENTS WHICH CAUSE IT. THE CONTROL

HANDLE MOVES TOWARD THE ASTRONAUT AND THE POSITIVE + PITCI"

REACTION JET FIRES.

YAW

YAW IS DEFINED AS ROTATION OF THE CAPSULE ABOUT ITS Y-AXIS.

CLOCKWISE ROTATION OF THE CAPSULE, WHEN VIEWED FROM ABOVE

THE ASTRONAUT, IS CALLED RJGHT YAW AND IS DEFINED AS POSITIVE

(+).THIS MOVEMENT IS PRODUCED BY POSITIVE CONTROL MOTION. THE

CONTROL HANDLE IS ROTATED CLOCKWISE {AS VIEWED FROM ABOVE

THE ASTRONAUT) AND THE POSITIVE t +) YAW REACTION JET FIRES.

YAW ANGLE IS CONSIDERED ZERO DEGREES (0 °) WHEN THE CAPSULE IS

IN NORMAL ORBITAL POSiTiON (BLUNT END OF CAPSULE FACING LINE

OF FLIGHT). WHEN THE POSITIVE Z-AXIS OF THE CAPSULE IS DIRECTED

ALONG THE ORBITAL FLIGHT PATH tRECOVERY END OF CAPSULE FAC-

ING LINE OF FLIGHT), THE YAW ANGLE IS 180%

ROLL

ROLL IS DEFINEDAS THE ROTATION OF THE CAPSULE ABOUT ITS Z-AXIS.

CLOCKWISE ROTATION OF THE CAPSULE, AS VIEWED FROM BEHIND THE

ASTRONAUT, IS CALLED RIGHT ROLL AND IS DEFINED AS POSITIVE (+).

THIS MOVEMENT IS INITIATED BY MOVING THE CONTROL HANDLE TO

THE RIGHT THEREBY FIRING THE POSITIVE (+) ROLL R EA C TIG N JET.

WHEN THE X-AXIS OF THE CAPSULE LiES IN A HORIZONTAL PLANE, THE

ROLL ANGLE IS ZERO DEGREES (0°)..

ACCELEROMETER POLARITY WITH RESPECT TO GRAVITy

WITH THE CAPSULE IN THE LAUNCH POSITION THE Z-AXIS WILLBE PER-

PINDICULAR TOTHE EARTH'SSURFACEAND THE Z-AXISACCELEROMETER

WILL READ +1 "G".

WITH THE CAPSULE IN AN ATTITUDE SUCH THAT THE Z AND X-AXIS

ARE PARALLEL TO THE EARTH*S SURFACE AND THE ASTRONAUT IS IN A

HEAD UP POSITION, THE Y-AXIS ACCELEROMETER WILL READ +1 "G".

WITH THE Z AND Y-AXIS IN A PLANE PARALLEL TO THE EARTH'S SUR-

FACE AND WiTH THE RIGHT SIDE OF THE ASTRONAUT UP, THE X-AXIS

ACCELEROMETER WiLL READ +1 "G".

FIGURE1-5 CAPSULE POLARITY ORIENTATION WITH RESPECT TO ASTRONAUT

_._t_ i_,,_.! r._-.Li.._l _ ,

PM45-233

PAGE i-8

REPORT _DR iO_I.

MODEL 133

ST. LOUIS, MISSOURI

i, , . "

I Novem1:_r i C_lDATE

REVISED

REVISED,,,

through use of special adapters. The "apex" of the cone contains the devices

for recovering the capsule at the conclusion of a mission, end equipment which

would allow the astronaut to escape in the event of an emergency during the

launch phase. Provided in the capsule proper are systems which regulate

environment, flight attitude, data recording and telemetering, and capsule

recovery.

When in place on the nose of the booster, the s_all end of the capsule

is up. The Astronaut is on his back in a sitting position. During launch and

acceleration phase, the Astronaut faces forward with respect to capsule flight

path. When the booster-capsule combination reaches a specific altitude, atti-

tude and velocity, they separate. The booster slows, and returns to the

earth's atmosphere where it is destroyed. The capsule is stablized momentarily,

then rotated 180 ° about its yaw axis. Throughout the remainder of the flight,

whether orbital or ballistic, the Astronaut faces aft with respect to capsule

flight path.

i-4. Cabin

1-5. Arrangement

The equipment within the capsule cabin interior, Figure 1-6, is arranged

so that all operating controls and emergency provisions are accessible to the

Astronaut when in the normal restrained position. Cabin equil3nent basically

consists of an Astronaut's support couch, a restraint system, instrument and

display panels, navigational aids, flight and abort control handles, food and

water supply, waste container, survival kit, cameras, and electronic equipment

required to operate ccmmnunication system.

1-6. Support Couch

The Astronaut support couch (Figure i-7) is designed to firmly support the

Astronaut's body during the capsule launch, re-entry and landing phase_.

+

/ .

SUPPORT C

WATE RCONTAI N ER5

INSTRUMENTATIONEQUIPMENT

FLIGHT CONTROLHANDLE

FOOD EONTAII_

CONIMUN_CATIONSEQUIPMENT

RATE DAMPER

\

INSTRUMENTATION

EQUIPMENT

LARGEBULKHEAD

AMERA COEI_ELkTtONCLOCK

PANELOBSERVER CAMERA

RESTRAINTHARNESS

ABORT CONTROLHANDLE

it

COOLING Duct

ELECTRONICEQUIPMENT

FACE LENS SEALSUPPLY BOTTLE

BAAX.ALT.SENSORBATTERY

ENVIRONMENTALSYSTEM EOUIPMENT

:;e _ O

_ m111 mo o

z

o

0c:

0

-I

iiir" II

-I

t/t

m

"rl

C_

rn

-r

C_

rrIEZ)C

"13

rriZ-i

(.h-r-1'11

FLOOD.

LEFT

FUSE

OBSERVERCAMERA

HELIUN_bOTTLES

TAPE RECORDER

FLOOD LIGHT

WINDOW POLE --_

MAIN PANEL

\

\\

---ASTRONAUT5 WINDOW

.OOD LIGHT

_ CONTAINER.amRIGHT CONSOLE

ESCAPE HATCH

ASTRONAUT ---vTOE GUARDS

PERISCOPE DISPLAY

5MALL PRESSURE5ULKNEAD

rlli}-I

m

E

o;o ;o Dm m ),< < -i

DATE 1NOVEMBER1961

REVISEDREVISED

M_'DONNELL__"_ __ST.LOUIS. MISSOURI

PAGE ,,, 1-1]

REPORT SEDR 104

MODEL 133

"D" SPECIAL INSTRUMENTATION

"B" PRIMATE COUCH

HOIST ASSEMBLY

,,'.._.////I!_%.,,'A////,li:T/G,

, ',_ ' I" f I."

, L 2_IIXIT "V ; .'. "---

, _._;_////////j,._;/,,,;.-_.

f

"C* ASTRONAUT.% SUPPORT COUCH

(CAPSULES " m ;:t s,,16,18 _:lq)

FIGUIRE I-7 _S.IC MlSSION EQUIPMENT

_.._.,_[.- _;fr-I_ll i I/'_ IL

P)A45- I_50

PAGE

REPORT

MODEl.

McDON E SE R REV,SED

ST. LOUIS, MISSOURI

133 ,.__ __ REVISED

The support couch also protects the Astronaut from loss of consciousness during

capsule peak acceleration and from possible injury at capsule impact. The

support couch is centrally located adjacent to the large pressure bulkhead.

The couch is constructed of a crushable, honeycomb material, bonded to a Fiber-

glass shell, and lined with a comfort liner. The support couch is molded to

the contour of a specific Astronaut's body to provide maximum body support

during capsule flight. The couch is fabricated in sections to enable couch

installation through the capsule entrance hatch.

1-7. Restraint System

The Astronaut's restrain system (See Figure 1-8) is designed to firmly re-

strain the Astronaut in the support couch during capsule maximum deceleration.

The restrain system consists of shoulder and chest straps, leg straps, aI

crotch strap, a laB belt, and toe guards. The shoulder straps may be adjusted

to restrain or release the Astronaut, by a harness reel control handle, located

forward of the upper left side of the support couch. The lap belt and crotch

strap firmly support the Astronaut's lower torso, and the chest strap and

shoulder straps restrains the Astronaut's upper torso. The leg straps and toe

guards firmly restrain the Astronaut's legs and feet. The Astronaut's hands

and arms are restrained by gripping the abort and flight control handles,

located near the ends of the support couch arm rests.

1-8. Instrument Panels (See Figures 1-9 And 1-10)

The capsule instruments and controls are located on a main instrument panel,

a left console, and a right console. The main instrument panel is located

directly in front of the Astronaut's support couch, as viewed By the Astronaut,

and is ettached to the periscope housing. The main panel is designed so that

the periscope display scope forms the lower control section of the instrument

-,° -,°- ,,, ,,, ,., C N F:D iii,i

DATE

REVISED

REVISED

1 NOVEMBER 1961 Mc'DONNELL, ST.LOUIS, MISSOURI

PAGE , 1-13

,REPORT. $EDR 104

MODEL 133

]

: >

\_LJ

/

/

/

/"

///

\

\

\\

/

DETAIL A

i

FI_UP_E I-8 ASTRONAUTS I_ESTRAIIqT SYSTE.M <CAP_ULES lO_I3,1G,!g_)£)_._-_,0

"_"''": D___'_-' "vv • i • J Jar a_L

PAGE

REPORT

MODEL

1-1i4

SEDR 104

133"

MIDONNE_ _.__ST.LOUIS o MISSOURI

DATE ....

REVISED

REVISED

1 NOVEMBER 1961

_ = -,_

II I:e::eI"-:l_e .'°,

i_iiii_

.I

2:

n "

.:0

""x

PAGE

REPORT

MODEL

1.15 Mc,I)0NNELL_H._ __ DATE.SEDR 104

ST.LOUIS, MISSOURI REVISED

133 . . / REVISEDL_

1 NOVEMBER 1961

+-,.

/

I ' i ..... _ I

!

!I

It

FIGURE 1-9 MAIN INSTRUMENT PANEL,(CAPSULE 10, 13, 16/t8 & 19i) (SHEET20Fi2)

I[ l lpl I |"

DATE

REVISED

REVISED

1 NOVEMBER 1961 Mc'DONNELL_L_ _ __ST.LOUIS. MISSOURI

PAGE 1-16

REPORT SEDR 104

MODEL 133

_ 7-"°' @

HOT

@_ .._oo_o@

RIGHT CONSOLE

[D CAPSULE 10,13,16, 18& i9

[_[_> CAPSULE 13 ONLY

i

PUSH

ON

LEFT CONSOLE

FIGURE 1-10 RIGHT AND LEFT CONSOLE (CAPSULE 9 10,13,16,18 & 19)PM45-1G115

panel. Navigational instruments are located in the left and center sections

of the main panel. Environmental system indicators and controls are located

in the right upper section of the main panel. Electrical switches, indicators

and communication system controls are located in the lower right section of the.

main panel. The left hand console is located on the left side of the main panel

and is arranged to provide accessibility and visibility to the Astronaut when

in the fully restrained position. The console includes a telelight sequence

and warning panel, and indicators and controls for the capsule autc_atic stabi-

lization control system, environmental control and landing system. The right

hand console, located below the capsule entrance hatch, includes controls for

the environmental control system. A window pole, located adjacent and to the

left of observation window, enables the Astronaut to actuate controls in the

fully pressurized suit.

1-9. Navigational Aids

The capsule is equipped with navigational aids and instruments to enable

the Astronaut to compute factors relative to his flight or landing. The naviga-

tional aids consist of the periscope, satellite clock, earth path indicator,

altimeter, angular rate indicator and the map case. All navigational aids are

located directly in front of the Astronaut, on or adjacent to the main instrument

panel.

i-i0. Controls

Capsule controls are located forward of each arm rest of the support couch.

An emergency escape handle is located forward of the support couch left arm

rest. The escape handle is utilized to initiate the abort sequence. To pre-

vent inadvertent actuation of the escape system, the escape handle is provided

with a manual lock. The manual control handle, located forward of the support

couch right arm rest, is utilized to control fligh t attitude of the capsule in

18

REPORT ,q_.n_ 10h

MOOa_ 133

Mc'DONNE ST. LOUIS, MISSOURI


REVISED

REVISED

the event the automatic system failed. This handle is also normally locked.

i-Ii. Food, Water and Waste Storage

All manned capsules will be provided with food and water sufficient for the

particular mission. (See Figure 1-6). The food will provide approximately

3,000 calories. The 6 pound water supply is contained in two flat bottles) each

fitted with an extendable tube. A waste container is located on the interior

of the entrance hatch.

1-12. Survival Equipment

The survival kit (See Figure 1-11), stowed at the left side of the couch,

contains the following :

1 Life Raft

1 Desiring Kit (for8 pts.)

2 Shark Repellant Packages

3 Dye Markers

1 Tube Zinc Oxide

1 First Aid Kit

1 Bar Soap

3 Morl_hine and Anti-

Seasickness Injectors

i Signal Mirror

i Ultra SARAH Rescue Beacon

! Survival Ration

i Container of Matches

i Whistle

I cord (ioft.)

i Signal Light

i Pocket Knife

A knife, installed in a case, is located on the entrance hatch interior. (see

Figure 1-6). A flashlight is located adjacent and to the left of the observa-

tion window.

1-13. Cameras

One 16 ram. camera is mounted in the lower left corner of the main instrument

panel for viewing the Astronaut's head and shoulders. A second 16 _m. camera is

positioned above and to the left of the Astronaut's couch to record instrmnent

panel readings. These csmeras operate continuously during launc_ and descent,

_ _ /5̧ /

=A_ i November 1961

R_ISED.

REVISE:D.

Me'DONNEST. LOUIS 3, MI_URI

PAGZ, , 1-19

mm_o_ _nR i0_

13MODEL ........

and at programmed intervals during orbit.

1-14. BOOSTER DESCRIPTION

The launch vehicle, or booster, used to project the Project Mercury capsule

into orbit is the ATLAS "D" missile. Capsule adapters replace the nose comes

of the missiles. The capsule "base" is them attached to the adapter with a

segmented clamp ring. At the proper time, explosive bolts in the clamp ring

are fired, releasing the capsule. The adapter remains with the booster.

1-15. CAPSULE RECOVERY

A normal mission is intended to terminate with the capsule landing in a

predetermined area of the ocean. Under normal circumstances, ships and heli-

copters will be standing by with provisions to pick up the buoyant capsule

immediately after landing. Considering the possibility that the capsule could

land in other than the intended area; numerous devices, both electronic and

visual, are automatically energized or deployed at the time of lending to aid

in locating the capsule. Depending upon the weather, possible capsule damage

and the Astronaut's physical condition, etc., he may either stay in the capsule,

or take to the life raft which is provided as part of the survival equipment.

1-16. CREW

1-17. Re%ulrement s

The capsule crew consists of one man representing the peak of physical and

mental acuity, training and mission indoctrination. Much more will be required

of the crewman than is normally required of the modern aircraft test pilot.

The crewman must not only observe_ control and ca_nent upon the capsule system,

but must scientifically observe and comment upon his own reaction while in a

new, strange environment.

-_ 9:1;"; :, _.;,;7,AL

[96L _l:lg W:IAONI.

C13 SI A'=I _..I

Q':I SIA31.1

31¥Q

IIdROSSIIN ' Slno7"IS

CEL

t'OL _a:_s

13aoP_

]

DATE i November 1_@61

REVISED

REVISED

1-18. Selection

.M!DONN ST. LOUIS 3, MISSOURI

PAGE 1-21

REPORT SRI_R 10_

Moore. 133

From the large number of men who volunteered for Project Mercury, a

relatively small group has been selected. Each man in the group has undergone

extensive testing and examination which has proven conclusively that he

possesses the intelligence, stamina and mental stability required for a project

of this type.

1-19. Training

An extensive training program is being conducted for the Astronauts and

other designated personnel associated with Project Mercury. The program will

provide detailed descriptions and operation of all capsule components in such

a manner that the trainee will fully understand the function of each component

and the reasons for selecting a particular design. Supplementary briefings will

be held so that current design decisions can be made known. Initial training

will be of the "group discussion" type, progressing to procedural trainers.

Training aids and equipment will be designed to train the Astronauts to achieve

the highest attainable degree of proficiency in all normal and emergency

procedures. The following objectives will be sought :

a. The Astronaut will be indoctrinated in the general purpose

and plans of the space program.

b. He must be completely familiar with all normal and emergency

procedures. Emphasis will be placed on this Point, so that

normal procedures are performed almost automatically.

c. He must be indoctrinated as far as possible in the environ-

mental and physiological aspects of the mission.

d. Since the Astronaut himself has the highest utility value

and is the most flexible component in the capsule_ he must

be able to handle the normal work load in the capsule and

..... "DE ......

22

REPORT _ lOk.

MODEL_. 133

McDONNE _._,Ltguls _ M_SSOUm

1 November i(:_iDATE

REVISED

REVISED

still function as an efficient scientific observer.

The completion of an adequate training program will assure a far higher level

of reliability with respect to crew function, and of course, increase the

probability of a successful mission.

1-20. Physiological Preparation

To minimize the possibility of the Astronaut having to pass body waste

solids for the duration of a mission, strict dietary control will be maintained

for a considerable period prior to flight. This will allow a nutritional and

physical buildup in anticipation of the stringent demands which will be placed

upon the Astronaut's physical and mental facilities, and at the same time,

control the type of solid waste which will remain in the digestive and elimina-

tion systems. Finally, low residue or non-residue type food will be supplied

for the Astronaut's consumption during flight.

1-21. Aer_nedical Instrumentation

It is extremely important that certain bio-physical functions be measured

and recorded during all phases of the mission. Such measurements will assist in

monitoring the Astronaut's mental acuity and physical fittness, and will

contribute significantly to aeremedicat research. The blood pressure microphone,

respiration rate and volume 3 temperature tranducers and the F2_ pickups'are used

to register the Astronaut's physical reactions. Leads are routed from the

Astronaut's body to teminals which extend through the suit. Capsule wiring

will attach to the suit at these points. The instrumentation will be accomplished

in laboratory facilities at the launching site prior to donning the pressure suit.

The data thus derived is supplied intermittently to the capsule tape recorder

and continuously to the telemetry equipment.

,,.R=VlSED ST. LOUlS 3, Mmsoum nS_,ORT _DR iO_

.wls=o_ ,_ _ ,4oo_ 133

: '_s j

1-22. Astronaut' s Apparel

The Astronaut's apparel will consist of a completely enveloping pressurized

suit with helmet, suitable undergarments, and boots. The helmet face plate

can be opened while the capsule interior is pressurized although normal pro-

cedure will be to keep the face plate closed. Each Astronaut is specially

fitted and trained in the use of his suit. Oxygen, regulated as to temperatu/e,

pressure and humidity, is supplied to the suit for breathing and ventilation.

For Astronaut comfort, ventilating air should be supplied to the suit at all

times.

1-23. TEST CONFIGURATION CAPSULES

The data contained in paragraphs I-i through 1-22 pertains to the

Specification Compliance Capsules. Deviations from this data, as applicable

to the TEST CONFIGt_%ATION CAPSULES, is explained in paragraphs i-2_ through 1-39.

If no reference is made tO a particular system or item it is the same as the

Specification Compliance Capsule.

I-2_. TEST CONFIGbTJtTION NO. 8 CAPSULE

Capsule No. 8 is similar to the specification capsule except in the follow-

ing areas. Refer to Section II for structural differences.

1-25. Mission Description

The flight objectives of Capsule No. 8 combined with an Atlas missile, will

be a single eliptical orbit around the earth, with Re-entry initiated at a pre-

set point on the orbital trajectory. Capsule No. 8 will not be manued_ but will

be equipped with a cre_aan simulator to artifically contaminate the capsule

environmental system to a degree, similar to that which would be experienced

by an Astronaut during an extended flight. This flight will qualify the

following systems:

_A_.mlII-- .m.. °

PAGE.

REPORT

MODEL

1._., MCDONNELL__ _ D,+E....SEDR 104


133 __ REVISED,

1 NOVEMBER 1961

m

ou z

@o :_

Qz

uJ

FIGURE 1-',12 MAIN INSTRUMENT PANEt/(CAPSULE 8)PM45-11qC

WIll! •

DATE

REVISED

REVISED

! NOVEMBER 1961

M 'DONNE ST.LOUIS. MISSOURI

PAGE 1-25

REPORT SEDR 104

MODEL 133

EMER O:

41-EMER -_NORM

RIGHT CONSOLE

LEFT CONSOLE

FIGURE.1_13 RIGHT AND LEFT CONSOLES (ICAPSULES_ 8 )P_J,4S- I _.OB

_""_'_''''_''_''1 & II I Ii i llJli 1 J Ii'il

26

REPORT SE_ 10_

MODEL. 133

M 'DONNE ST. LOUIS, MISSOURI


REVISED

REVISED

a. Capsule-booster separation.

b. Capsule and escape systems.

c. Environmental control system.

d. Automatic stabilization system.

e. Landing re-entry and recovery system.

f. Posigrade and Retrograde rockets systems.

g. Instrumentation end telemetry systems.

In addition the following objectives will be achieved:

a. Demonstrate the ability of the capsule and ground complex to

initiate an acceptable re-entry after an orbital flight.

b. Demonstrate the ability of ground range stations to perform the

necessary monitoring and control functions during flight.

c. Establish the adequacy of the location and recovery procedures

associated with re-entry.

d. Qualify the capsule primary systems for exit and re-entry flight.

e. Determine the capsule full-scale motions and afterbody heating

rates during re-entry.

f. Evaluate the capsule environment for a one orbit flight, using

the crewman simulator. This test will determine the capsule's

environmental systems capabilities, for human inhabitation during

the entire mission frcm pre-launch through the post-landing phase.

1-26. Crewman Simulator

The support couch is not installed in Capsule No. 8. Instead, an instrument

package and a crewman simulator are installed. (See Figure 1-7. ) The crewman

simulator is a box-like structure containing a carbon dioxide tank, water tank,

strip heaters, valves and controls. This device simulates the carbon dioxide

-- __J _J A_ A" £AJ A_ A_ I £_M J4_

1No e be= Mc,DONNE , REVISZD. ST. LOUIS 3. MISSOURi REPOI:rr. S_DR 10_

/.

output, perspiration output, and oxygen consumption of a human being. The

simulator is calibrated prior to flight and is activated automatically when

the capsule special instrumentation package is energized.

1-27. Instrument Panels

Capsule No. 8 instrument panels are similar to the Specification Compliance

Capsules. See Figures 1-12 and 1-13 for Capsule No. 8 instrument panel configura.

tions.

1-28. Food_ Water and Waste Storage

Capsule No. 8 will not contalnfood, water and waste containers.

1-29. Cameras

The camera installation in Capsule No. 8 will consist of an Instrument

Observer Camera, an Earth and Sky Camera and a Periscope Observer's Camera.

(Refer to Instrumentation Section XIII).

1-30. TEST CONFIGURATION NO. 9 CAPSULE

Capsule No. 9 is similar to the specification capsule except in the follow-

ing areas. Refer to Section II for structural differences.

1-31. Mission Description

Capsule No. 9 Mission will be an Atlas_ Three Orbit Flight. The primary

objective of this flight will be aerQmedical instrumentation of the primate and

the primate's behavior in a space environment. This flight will further qualify

the systems listed in Paragraph 1-25 and in addition achieve the following

objectives :

a. Evaluate the effects on a primate and test the capsule environment

for satisfactory conditions during prelaunch period thr_h the

post landing phase of the mission.

b. Determine in detail the heating effects of the launch and re-entry

phases on capsule environment.

_= .--row _ _--,L w,.v,,1 A |

PAGE

REPORT

MODEL_

_..T_ 104 REVISED.... ST, LOUIS, MISSOURI

133 __=_]_ REVISED.

c. Demonstrate the integrity of the capsule structure, ablation

shield and afterbody shingles for a normal re-entry from orbit.

d. Determine the capsule motions during a normal re-entry fr_ orbit.

1-32. Support Couch

The primate support couch utilized in Capsule No. 9 (See Figure i-7) is

designed to contain, sustain and support a medium-sized primate (chimpanzee)

during an unmanned capsule mission. The couch contains an instrument panel and

controls to test the primate's reactions during capsule flight. This unit is

essentially a two-section container. The aft section is the actual couch that

supports and restrains the primate; the forward section contains the instrument

panel, controls, and observation window. The primate couch, including occupant,

is installed just prior to capsule launch. A Hoist Assembly packed in a plastic

bag is attached to the primate couch support structure. This hoist assembly

is used to assist in removing the primate couch from the capsule during recovery

operations. It is located aft of, and to the right of the prlmate's couch and

is accessible through the escape hatch opening.

1-33. Instrument Panels

The instrument panels on Capsule No. 9 are the same as used on the

Specification Compliance Capsule. (See Figure 1-9,)

1-34. Food; Water and Waste Storage

Capsule No. 9 will have food and water dispensers within the couch for the

primate. The waste containers are not installed.

1-35. Cameras

Capsule No. 9 has an Instrument Panel and Primate Observer Cameras installed.

Also an Earth and Sky Observer Camera is installed which will photograph a portion

of the earth and sky through the observation window. In addition a periscope

• \

:. _j/

.,= Aa.-_ll JL JL_kJLa

DATE ! November 1961

REVISED

REVISED

ST. LOUIS s, M,SSOURJ REPomr S_.oR lob

- MOme. 133

-L;. 7

camera is installed which will photograph the view displayed on the periscope.

Refer to Instrumentation Section XIII.

1-36.

unit.

TEST CONFIGURATION CAPSULE NO. i0

Capsule No. i0 is an orbital training simulator and altlt1._lechamber test

The configuration of the capsule is subject to change during various

phases of the test program; therefore, this capsule cannot be accurately

described in this manual. When Capsule No. lO is assigned to a flight mission

the final configuration will be included during a subsequent revision or

reissue of this publication.

1-37. TEST CONFIGURATION CAPSULES NO. 13 AND 16

Capsule No. 13 is the same as the Specification Compliance Capsule.

(Refer to paragraphs i-i thru 1-22).

CC ::-:D-;4T;AL -

ll_ _' _'' '_+_+q_ +_++, + ,-._ • _ ._p_L.<._,ll_,,

,/ \i,

i

SECTION I_

iii.

MAJOR STRUCTURALASSEMBLIES

TABLE OF CONTENTS

TITLE PAGE

INTRODUCTION ....... . ........................... 2-.3

CAPSULE FOREBODY ........................... 2-4

CAPSULE AFTERBODY ........................... 2-5

ENTRANCE HATCH .............................. 2-7

OBSERVATION WINDOW .................... 2-9

RECOVERY COMPARTMENT ................ 2-11

ANTENNA FAIRING ............................. 2-14

IMPACT LANDING SYSTEM ................... 2-16

ESCAPE TOWER .................................... 2-:>0

PYLON-CAPSULE CLAMP RING ........... :>-20

ATLAS MISSILE ADAPTER ..................... 2-21

CAPSULE-ADAPTER CLAMP RING ......... 2-24

TEST CONFIGURATION ..................... :>-26

PAGE

REPORT

MODEL

2-2

SEDR 104

133

ST.LOUIS, MISSOURI

DATE

REVISE_

REVISED

1 NOVEMBER 1961

HEAT

SHIELD

Z_ ENTRANCE

ATCHEXPLOSIVERELEASE)

FOI_EBODY AREAVENT (42)

LARGEBULKHEAD

WINOOW/_

DOOR

AFTERB(W)Y

//_ LAN DIN_,

SKI.RT

GROUND HANDLING

FITTING(Z)

/_ LOWER WINDOW

MAI N ANt

SMALL PRESSURE RESERVEBULKHEAD CHUTE$

NOTE

CAPSULE

ABLATION SHIELD 8,9,10, 1_,I6,18,19

CAPSULE 9tt Up

/_ CAPSULE 8 ONLY

FIBERGLASATTACH

//_ DE_STABILIZE_R_

FLAP

NOZZLE5

SHIELD

DE-STABILIZERFLAP

PERISCOPE _ uMBILICALDOOR

FIGUPE ?.-I CAPSULE" ST_UCTUI_E (SPECIFICATION C.APSULE), ,, ,r , it:

,'" _ _v_, ," .""2.;_v _ . .= m ilmW,

PM 4.5 - ?-07C

DATE_ i November 1@61

REVISED

IREVISIED

,Mc'DONNE ST. LOUIS 3, MISSOURi

PAGK 2-3

MOOL 133

II. MAJOR STRUCTURAL ASSEMBLIF_S

2-1. INTRODUCTION

The Project Mercury capsule, Figure 2-1, is designed to contain an

Astronaut, primate, or crewman simulator during capsule ballistic or orbital

flight, Capsule payload will depend upon mission purpose. (See Figure 1-7,

Section I.) The capsule will also contain recording equipment, environmental

provisions, and equipment necessary to control the capsule durin_ flight.

The capsule is basically of a conical configuration consisting of a forebody

and afterbody. During orbital flight, the capsule forebody is forward with

respect to the capsule flight path. The capsule forebody is the large, dish-

shaped structure forward of the cabin area. The capsule afterbody consists of

a conical mid-section attached to a small cylindrical section. The capsule is

of a eonventional semi-monocoque construction utilizing titanium for the primary

structure. Capsule construction is designed to protect the internal cabin from

excessive heating, noise and meteorite penetration. Provisions are incorporated

in the capsule to permit cabin entry, exterior viewing, normal and emergency

exit.

Prior to capsule flight, an escape tower and antenna fairing are attached

to the capsule afterbody cylindrical section. The escape tower, designed to

aid in capsule-missile emergency separation, consists of a pylon framework

equipped with rockets. The antenna fairing is a cylindrical shaped structure

containing the capsule radio main receiving and transmitting antenna. The

escape tower is Jettisoned during the capsule launch phase or during an escape

sequence. During the capsule landing phase the antenna fairing is ejected

and serves to deploy the capsule main chute.

4

REPORT S_DR 10_

MODEL lq_

MCDONNE REVISED

_ kouls ..M SSOU I_t'_ _" J.._, E _'_ REVISED

2-2. FOREBODY

The capsule forebody, Figure 2-i, mainly consists of a large, blunt, dish-

shaped structure that is supported by the large pressure bulkhead and adjoins

the afterbody conical section. The large pressure bulkhead internally

separates the forebody from the afterbody. The forebody dish-shaped structure

is an ablation heat shield that is designed to protect the capsule from extreme

thermal conditions during re-entry flight. It is also designed to prevent

capsule damage upon landing impact. The heat shield is attached to the heat

shield attach ring, which in turn is riveted to the capsule conical section

inner skin. The heat shield attach ring incorporates elongated holes, for the

installation of the heat shield to the capsule and to allow for thermal expan-

sion. The ablation shield is designed to ablate heat and is constructed of

fiberglass shingles, radially laminated to form a smooth contour. A retrograde

package assembly is attached to the heat shield by means of three straps. The

retrograde package is Jettisoned from the capsule following retrograde rocket

firing, which initiates capsule re-entry.

The forebody area, between the large pressure bulkhead and the heat shield,

is vented to atmosphere through a series of vents located around the periphery

of the capsule forebody, adjacent to the forebody and afterbody Junction. Two

toroldal shaped hydrogen peroxide tanks and six reaction control nozzles, each

covered wlth Min-K heat insulation, are located In the forebody area. The fore-

body area also houses the heat shield release pneumatic system. A landing

impact skirt is also stored in the capsule forebody area. The rubber-cloth

impact skirt, attached to the capsule heat shield attach ring and the heat

shield, is designed to absorb high energy shock loads encountered during a

capsule landing on land or water; and also to stabilize the capsule during

/-- ,

Astronaut's egress, following a capsule landing in water. During the capsule

landing phase, the heat shield is released, and extends the full _length of the

impact skirt. Upon heat shield contact with land, air within the impact skirt

is forced out through a series of holes located in the impact skirt wall which

in turn provides a cushion-like effect. To prevent damage to the large pressure

bulkhead in the event the heat shield strikes the capsule during landing, the

large pressure bulkhead incorporates a reinforced laminated fiberglass shield

assembly. The fiberglass shield assembly is attached to the torus tank support

brackets. Sandwiched between the fiberglass shield and the large pressure bulk-

head are sections of honeycomb. Fabricated of stainless steel and located about

the periphery of the impact landing skirt, are 24 straps which prevent tearing

of the impact landing skirt during high horizontal velocity water landings.

Located inside the impact landing bag and alternately located in relation to

the steel straps, are 2A stainless steel cables. The cables retain the heat

shield to the capsule in the event strap failure should occur. The afterbody

conical section exterior shingle arrangement extends beyond the large pressure

bulkhead, to the forebody heat shield, and encloses the equipment located

between the large pressure bulkhead and the heat shield. Located adjacent to

the capsule forebody and afterbody Juncture, and bolted to the heat shield attach

ring, is a fiberglass attach ring. During capsule-adapter installation, the

fiberglass attach ring and the adapter attach flange are clamped together with

a segmented clamp ring. Receptacles for the capsule retro-package, adapter, and

the clamp ring pneumatic and electrical connectors are located under the forebody

shingles adjacent to fiberglass attach ring. Six spring loaded access doors,

for the receptacles are incorporated in the shingles.

2-3. A_DY

The capsule af_erbody conical mid-section mainly consists of a pressurised

'_-_ _'_ "_ ..... /

_--a_m '_i=_i,Mil | If'Li--

REPORT 8EDR lO_ .... "ST. LOUIS, MISSOURI " REVISED

MODEL_ 133 _z_'_- "_ REVISED

cabin that is Supported between a small pressure bulkhead and the large pressure

bulkhead. The cabin interior wall is lined with channeled frames to provide

additional structural strength and equipment attach points. The mid-section is

constructed of a conically formed inner and outer titanium shell, seam welded

together. The outer skin is beaded to form small sealed pressure panels capable

of withstanding high pressures and structural loads. The outer conical skin is

reinforced with longitudinal hat stringers. A blanket of thermoflex insulation

is bonded, in between the hat stringers, to the outer (beaded) conical skin.

Min-K insulation is also installed over the hat sections and covered with a

shingle arrangement. The shingle arrangement is similar to the shingle installa-

tion used on the recovery system compartment. The forward end of the conical

section is attached to the forebody heat shield. The combination of the conical

section beaded outer skin, the hat section reinforcements, thermoflex insulation,

and external shingle installation provide the capsule with adequate heat, noise

and meteorite protection.

Located in the bottom of the conical section, as viewed during capsule

normal flight attitude, is a retractable door that encloses the periscope lower

lens flange and the capsule ground checkout umbilical receptacle. The door,

mechanically linked to the periscope housing, automatically opens and closes

with periscope extension and retraction. Two auxiliary hoist fittings, attached

to left and right side of the capsule, provide ground handling attach points. The

hoist fittings are removed prior to capsule launch. An explosive door, namely

the snorkel explosive door, is provided in the capsule shingles, between the

small pressure bulkhead and the capsule conical-cylindrical sections Juncture.

This door is exploded from the capsule during capsule landing. The exploding

of the door from the capsule enables cool air to be drawn into the capsule

v ,_

_ILT y"t v "lr_

l._,ks.L, A" A.a._ 4_.Z, _.A_

REVISED ST. LOUIS 3, MISSOURI Ri_ORT SEDR 10,_

REVISED -- _ MOO_L l_'_

through the snorkel valve when the cabin air inlet valve opens.

2-_. Entrance Hatch

An entrance hatch, Figure 2-2, is located on the right side of the after-

body conical section as viewed from the capsule crew member station. Entrance

hatch construction, similar to the conical section construction, consists of

an inner and outer (beaded) skin seam welded together and reinforced with hat

stringers. A waste container and th_ Astronaut's knife are attached to the

hatch. An explosive charge, moulded in the hatch sill, is provided to quickly

release the hatch and enable the Astronaut to egress rapidly from the capsule.

An explosive charge initiator, located in the upper aft corner of the hatch, is

linked to an internal release control initiator. Prior to capsule launch, the

hatch is bolted and _sealed into position with bolts, and two corrugated shingles

are installed over the hatch. The bolts are inserted through the entrance hatch

sill, which incorporates the explosive charge, and threaded into the capsule

sill. A magnesium gasket, with inlaid rubber, forms the hatch seal when the

hatch is bolted into position° Two hatch shingles are attached to the hatch

stringers, but in no manner are they attached to capsule shingles. (This

enables the hatch to separate cleanly, upon ignition of hatch explosive charge. )

Following capsule impact, the Astronaut removes the initiator cap from the

initiator, and the safety pin from the initiator plunger. By depressing the

initiator plunger, the inltiator's two spring-loaded firing pins strike the

explosive charge percussion caps and detonate the explosive charge. This

action explodes the hatch from the capsule. An exterior hatch release control

is also provided to enable ground personnel to explode the hatch in the event

the Astronaut is unable to do so. Hatch retention springs, secured by pip plus,

are incorporated ca the inner side of the entrance hatch to prevent injury to

ground personnel in the event the initiator plunger is accidemtly depressed.

2-8PAGE

REPORT SEDR 104

MODEL 13 :_

Mc'DONNE ST cLLOU IS, MISSOURI

DATE

REVISED

REVISED

1 NOVEMBER 1961

ENTRANCE MATCH%

EXPLOS|VE. CHARGE.

FIGUREZ-Z CA_P5ULE

/

WA_T£

CONTAINER

PRESSURE VALVE

SEAL

ENTP,ANCE HATCH (EXPLOSIVE RELEASE)

/.J

REV'SED S-r.Louis s. MISSOUm ,_,om-. S_I)R 304

R_V,SE_ _ _oomu 133

_, ._ -

Two pressure valves, located in the hatch, enables pressurization and purging

of the capsule, during capsule ground checkout operations.

2-5. Observation Window

An observation window, Figure 2-3, located on the afterbody conical section,

provides the Astronaut with external viewing. The window, located above the

main instrument panel, consists of an inner and outer assembly. The inner

window assembly is made of three glass panes and a fourth image suppression

filter pane. The three glass panes are sealed in a titanium frame that is

attached to the cabin wall. Each glass pane is independently sealed to provide

a pressure seal between the panes. The image suppression filter pane eliminates

secondary (reflected) images. The filter pane is not pressure sealed. The

outer window assembly consists of a glass pane sealed in a titanium frame, that

is attached to the capsule outer skin. The outer window assembly is sealed

separately, from the inner window assembly, to provide a complete seal. The

outer window conforms to the curvature of the capsule conical section. The

observation window is equipped with filters and door llds, enabling the

Astronaut to regulate external light entering the cabin. The observation

window includes a mirror assembly which increases the Astronaut's angle of

observation.

2-6. Small Pressure Bulkhead

The small pressure bulkhead internally separates the cabin pressurized

area from the recovery system compartment and structurally supports the aft

conical section. A sealed escape hatch, Figure 2-4, internally actuated, is

provided in the small pressure bulkhead to enable the Astronaut's exit follow-

ing capsule landing. The dish-shaped escape hatch is constructed of a beaded

aluminum skin spotwelded to an inner skin, that is reinforced with structural

"Z" shaped members. The hatch outer flanged edge fits into the small pressure

--..,.i ii iI--IrI--.i_I • i/-1I--,

P"_E _.1o Mc,DONNELL_,S__ __ D,,TEREPORT SEDR 104 ST.LOUIS, MISSOURI REVISED

MODEL 133 .... ,- REVISED ,

1 NOVEMBER 1961

v//>>///////////,.,

SECTION B-B

bOOR HANbLE

A

GLA,._S PANE._ _ POLA,RO_I_SECTION A-A F',LT_R (IMAC_E

£13 PPR, E $S i O1'_ )

FI&URE 2-3 CAPSULE OBSERVATION WINBOW ph_4.5-14.5.,

C,-, L, _"''-'- :" T ;A_-V I I | i _

R=V,SE_, sv. Louis 3, MisSou,_, .SPORT SEDR 104

.sv,sEo .oo=. ,, 133

bulkhead sill and is held in place with a retaining ring. Expanding the re-

tainer r_g by rals_ the hatch hsoldle, wedges the retainer ring between the

bulkhead sill and the hatch flanged edge and forces the hatch f_e aft to

provide a sealing action. The titanium small pressure bulkhead is seam welded

to the conical section inner skin and bolted to the conical hat stringer flanges.

2-7. Large Pressure Bulkhead

The large pressure bu3_khead supports the forward end of the conical section

and internally separates the pressurized cabin from the forebody heat shield.

The large pressure bulkhead is constructed of a combined inner and outer

titanium skin. The outer skin is beaded and seam welded to the inner skin.

The bulkhead is reinforced with horizontal channels installed on the outer skin.

The bulkhead inner skin is provided with two vertical channels, centrally

located and spaced, that furnish structural attach point for the Astronaut

support couch. Honeycomb shelves are provided on the bulkhead inner skin, out-

board of the two vertical channels, for equipment installation. The bulkhead

outer flange ring is bolted to the conical section inner skin and the bulkhead

is also bolted to the conical section inner attach ring. Vents are provided

in the large pressure bulkhead to enable overboard venting of the capsule

battery vapors and environmental control system exhaust steam.

2-8. RECOVERY COMPARTM_qT

The capsule afterbody, Figure 2-1, basically consists of the short cylin-

drical section and the truncated cone shaped structure. The cylindrical section

is referred to as the capsule recovery system compartment and contains the laud-

ing parachutes, recovery aids, and the reaction control nozzles. The truncated

cone shaped structure, referred to as the capsule afterbody conical section,

encloses the pressurized cabin. The recovery compartment is connected to the

pressurized cabin by a small pressure bulkhead. The recovery system compartment

PAGE

REPORT

MODEL

2-12

SEDR 104

133.... gy:L_llS :_Mrs so UR+._

DATE

REVISED

REVISED

1 NOVEMBER 1961

//

//

RETAIN INg . RETAINING r--t-lATCH _ [,\I_[N_'-_

RING--'_ /--HAT CH RIN6 --_ ,.j/ \

St'lA LL" -P I_-ESSut_E_'_ SHALL PRESSUFIE

I_/LK HF__D-__ _ULKHEAD

"_ RELEA%E HANDLE

HATCH P_ELF.ASED HATCH CLO-_ED A_s_YPRING"--_ _,,_/

5ECTIOM : (_" B HATCH P,ELEASEI2

FIGURE 2-4 CA_ULE ESC_,PE HATCH

I

DATE

REVISED

REVISED

1 NOVEMBER 1961 Mc'DONNEL_L_ __._ST.LOUIS, MISSOURI

11"

PAGE 2-13

REPORT SEDR 104

MODEL 133

CHUTE

POST

_""=_ L " "=''"=_'='='_ '"T'I • IWl _1 l'_- t i/l_ Ill I RI / i J'_ b

51LI?.INGFLAP

PM 45 .t&_P_-

14

REPORT SEDE lO_

MODEL_ 133

MCDONNEL LST. LOUIS, MISSOURI

"_--CC,i'_[':D _ Y:TI_


REVISED

REVISED

is a cylindrical formed titanium skin structure, reinforced with longitudinal

hat stringers, and covered with a corrugated beryllium shingle arrangement. A

layer of thermoflex insulation is installed between the hat stringers and the

external shingles to prevent excessive heating within the compartment. The

shingles are individual panels bolted to the hat sections with allowances for

thermal expansion. A set of reaction control exhaust nozzles are internally

located every 90 ° , between the compartment inner skin and the external shingle

installation. The recovery system compartment interior is structurally divided

into a left and right section. The compartment left section houses the recovery

aids, electrical wiring and plumbing routed through the compartment. The right

section of the compartment houses a fiberglass container, structurally divided

into two sections that contain the main and reserve parachutes. The container

can be removed by the Astronaut from the cabin following capsule landing, to

permit egress through the recovery compartment.

2-9. ANTENNA FAIRING

The capsule antenna fairing, Figure 2-5, is a cylindrical shaped structure

that houses the pitch and roll horizon scanners, and the main receiving and trams-

mitting antenna. The antenna fairing basic structure is of titanium construction

and is covered with '%qene-_l" shingles. An 8 inch window assembly is located

around the outer base of the fairing and acts as a dielectric between the top

of the fairing and capsule. The window assembly consists of a silicone base,

fiberglass insulation, vycor glass and teflon strips. In line with the three

teflon strips and attached to the antenna fairing shingles, are three laminated

fiberglass guides. The fiberglass guides and teflon strips prevent damage to

the antenna fairing when the escape tower is jettisoned. An aluminum bi-conical

horn is internally located at the base of the antenna fairing. An electric

"-..._ v -=.4" = ..,,.a..i .=._1'_ _ .K/"_ JLJ

V IAI31SAS "3NIC]NV7

ku_a3a_u_n_

WNV1

I_IWS 9NIONV_ 10Vd_11

_03SV3138 0131H_ _¥3H

_±31d3Q N011V819n711

310N

1_3H

(d3_ 0N_ HgVliV

$_;V'1983gl_.

/

/

\

\\\

9NIl113 H 3V11"V

_'131H5" 1'_3H

(*'_ dX,)

\\

\\

\

HOVIlV

181_S lOVd_l

££t

f_Ol _O_S

5L-Z:'

7_OO_M_ II " ..........

I ! l.liIN._[qul I.,..]l INV4u# "

I_lnOSSl_l • SlNO-I'/S

t96t _38W3AON l

O_SIA_ _m

Q3SIA_

3.LVO

PAGE,, , 2-16

REPORT SEDR 104

MODEL 133ST. LOUIS, MISSOURI

DATE,,.,t November 1961

REVISED

REVISED

insulator and lockfoam, located above the bi-conical horn, aid lu antenna fair-

ing insulation. A pitch horizon scanner is located at the top of the antenna

fairing. A roll horizon scanner is located lu the side of the fairing, In line

with the pitch horizon scanner. The fairing is attached to the capsule by a

mortar gun located in the capsule recovery compartment. A steel post located in

the center of the fairing is used as a guide when the fairing is Jettisoned.

Three index pins and six support clips, in the antenna fairing lower matlng

flange, align with three holes and six brackets in recovery compartment mating

flange. The antenna fairing also houses the drogue chute. Three cables retain

the drogue chute risers to the fairing when the chute is deployed.

2-10. De-Stabilizer Fla_

A spring loaded de-stabillzer flap is attached to the top of antenna fair-

ing, opposite the pitch horizon scanner. The de-stabilizer flap ensures capsule

correct re-entry attitude during capsule abort and re-entry phases. During cap-

sule launching phase, and up to the capsule-tower separation, the spring loaded

de-stabillzer flap is held flat against the antanna fairing by means of a nylon

cord routed through two de-stablizing flap reeflmg cutters contained within the

antenna fairing housing. Jettisoning of the escape tower actuates the cutters

which sever the cord releasing the spring loaded flap to the outboard position.

When the capsule descends to lO,O00 feet altitude, the antenna fairing is auto-

matically Jettisoned from the capsule by the firing of the fairing mortar gum.

2-11. IMPACT LANDING SYSTEM

The capsule impact landing system, Figure 2-6, is designed to absorb high

energy shock loads encountered during landing; and also to stabilize the capsule

following a landing in water. The impact system basically consists of a heat

shield release mechanism, heat shield retaining straps (24), heat shield reten-

MAC 2:_ICL (27 APR Sg) _.JVJ._I_I. AU4.aJ._I Jl. I_'l. JLI

.!. /

REVISED ST.LOUIS , MISSOURI REPORT

REVISED " _ MODEL

2-17

SEDRI04

133

150L SQL_IB _U_ _Z4V D-C

i Ii I

MAIN gQUII3 _u5

FIGURE Z -7 IMPACT LANDI'NG SYSTEM SCHEMATIC MH45 -.t._l C

_ _ i i i . I I I II I I I

PAGE .2-18

REPORT SEDR 104MCDONNE

REVISED .ST. LOUIS, MISSOURI

MODEL_ 133 _,._ . REVISED

tion cables (24), a rubberized cloth impact skirt and a fiberglass shield

assembly. The impact skirt is stored in the capsule forebody area. During the

capsule normal landing phase, the capsule 10,O00 feet barostats energizes the

Main Deploy Relay to eject the antenna fairing, which in turn deploys the main

parachute. (See Figure 2-7. ) Ejection of the antenna fairing closes the

antenna fairing separation sensing switch, which in turn directs 2_ V D-C

electrical power to the Main Inertia Switch Relay #l (time delay relay). Twelve

seconds later, the Main Inertia Relay #1 energizes to direct electrical power to

the heat shield release system limit switches and also to energize the Landing

Bag Relay. Energizing the Landing Bag Relay directs 24 V d-c electrical power

to ignite the 2 heat shield release explosive squib valves.

Ignition of the squib valves allows 3,000 psig nitrogen pressure to flow

to the 2 heat shield release mechanism actuators. This action moves the heat

shield from the capsule. Simultaneously with the actuation of the release

mechanism, the mechanism 2 limit switches close to energize the Landing Bag

Extension Signal Relay. Energizing the signal relay, directs electrical power

to illuminate the Landing Bag Telellght (green), indicating a safe condition.

When the actuator piston fully travels to the open limit, the actuator is locked

by a spring loaded lock pin.

In the event the heat shield mechanism failed to actuate, and release the

heat shield, the two limit switches will remain open and the Landing Bag Warn-s

ing Light Relay will energize within 2 seconds. This in turn directs power to

illuminate the Landing Bag Telelight (red), indicating an unsafe condition to

the Astronaut. The Astronaut should place the LANDING RAG SWITCH to the "MAN"

position. Placing the landing switch to the manual position energizes the

Emergency Landing Bag Relay, which In turn provides power to ignite the 2 heat

shield release explosive squib valves. Ignition of squib valves will actuate


REVISED

REVISED

ST.LOUIS, MISSOURI

PAGE 2-1'9

REPORT SEDR 104

MODEL 133

DEF..STABILIZING

(CAPSULE 8 ONLY) FIGUI::2E 2-t_

PAGE • 2-20

REPORT SEDR lob,.

MODEL_ 133

Mc'DONNEL LST. LOUIS, MISSOURI


REVISED

REVISED

the mechanism to release the heat shield, and in turn the limit switches will

close to illuminate the telelight (green).

2-12. ESCAPE TOWER

The escape tower (Figure 2-8), designed to aid in Capsule-missile emergency

separation, consists of a pylon framework equipped "with rockets. The pylon is

a triangular shaped structure that is designed to support an escape rocket and

a Jettison rocket. The pylon is constructed of 4130 tubular steel and is

approximately lO feet in length. The base of the pylon structural tubing is

bolted to a steel flanged attach ring. A four foot escape rocket casing is

bolted to the top (apex) of the pylon. Bolted to the bottom of the escape

rocket casing is a Jettison rocket. Electrical wiring is routed through the

structural tubing, from the rockets to connectors, located on the pylon attach

ring. Pylon tubular structure is covered with heat protective material. Prior

to capsule launch the pylon is installed onto the capsule, by clamping the

pylon attach ring to the capsule recovery system compartment with a chevron

shaped, segmented clamp ring. Explosive bolts connect the clamp ring segments

in tension. The bolts are fired to separate the clamp ring when the pylon is

Jettisoned from the capsule. During capsule normal launch the escape rockets

are fired to separate the pylon from the capsule. In the event the capsule

escape system is activated, during launch phase, the escape tower is fired to

propel the capsule away from the missile and then the Jettison rocket is fired

to separate the pylon from capsule.

2-13. PYLON-CAPSULE CLAMP RING

The clamp ring consists of three chevron shaped segments that clamp the

pylon attach ring to the capsule recovery system compartment flange. Three

explosive bolts, with dual ignition provisions, connect the ring segments in

, -77,,¸

MAC 231G (Rev 14 Oct. 55)

DATE i November i_I

REVISED

REVISED

M DONNE ST. LOUIS 3, MISSOURI

PAGz .... 2- 21

REPORT _EDa 104

MOD_ 133

l

+/ '-

tension. The clamp ring is basically the same in design as the capsule-adapter

clamp ring (Figure 2-11), but considerably smaller in size. The clamp ring

retains the pylon to the capsule until the clamp ring explosive bolts are fired

which in turn separates the clamp ring. The exterior of the clamp ring is

covered with a heat shield to protect the clamp ring and explosive bolts from

excessive heating during capsule launch. A layer of thermoflex insulation is

bonded to the interior of the heat shield. The heat shield is attached to the

clamp ring with screws. An aerodynamic stability wedge attached to pylon heat

shield, aids in stabilizing the capsule during the launch phase. Six cable

straps, bolted to the pylon structure and clamp ring stability wedge, aid in

capsule-pylon separation by retaining the clamp ring segments of the pylon when

the explosive bolts are fired.

2-14. ATLAS MISSILE ADAPTER

The Atlas missile adapter I Figure 2-9, is a slightly tapered, cylindrical

shaped structure that is designed to mate the capsule with the Atlas missile.

Upon adapter and capsule •installation to the missile 3 the adapter is bolted to

the missile and the capsule is attached to the adapter. The adapter is of

semi-monocoque construction and is approximately 4 feet in height. The adapter

basically consists of an outer corrugated titanium skin assembly, riveted and

Seam welded to an inner titanium skin assembly and internally reinforced with

two titanium support rings, riveted between the ends of the adapter. A steel

flanged ring is riveted to the bottom, inner surface of the adapter. The

flanged ring is provided with holes to enable the attachment of the adapter

to the missile with bolts. Alignment marks are provided on the ring for proper

adapter-missile alignment. Riveted to the top, inner surface of the adapter

is an aluminum flanged ring. The adapter aluminum ring mates with the capsule

forebody fiberglass attach ring, during capsule to adapter installation.

............ 1rill A 1_" VV| _1|"'• JllmJll1|NI • I_--

/

,o

uJ

:EUA

_J00w co co

< Ill W

- |_

o

ia&aJ

l}-

w o< bJ

k

md_

b-

M!DONNELL..-.-DAT_ i November 1961 . --j_ p_l 2-2B

R_vnsEo. ST. LOUIS S.M,SSOUm REPOWr... SEDR 101;

Ra'VlS_D _ MO_ iBB

An alignment mark on the adapter ring BY axis enables proper alignment of

capsule to adapter. The top of the alum lnum ring is slotted at 120 ° intervals,

to provide adequate clearance for the capsule retrograde rocket assembly attach

straps, when the capsule is attached to the adapter. A metal striker bracket

is riveted internally, every 120 °, to the adapter skin. When the capsule is

attached to the adapter, these striker brackets depress (open) the capsule-

adapter separation sensing switches, located on the bottom of the retrograde

rocket assembly attach straps. The capsule is attached to the adapter by

installing a chevron shaped, segmented clamp ring over the mated flanges of the

capsule forebody fiberglass attach ring and the adapter upper ring.

A retainer assembly, attached to the adapter interior skin, is provided to

prevent the retro-package and the explosive bolt fragments from striking the

Atlas missile adapter LOX tank. The retainer assembly is a cup shaped structure,

that fits over the retro-package dome, and is supported by three metal straps

that are attached to the adapter with cable assemblies. A vent port, located

in the adapter skin, receives the missile boil-off valve tube and enables the

relieving of liquid oxygen from the missile. Opposite the liquid oxygen boil-

off port, is an adapter door installation. The door installation provides

access to the booster and Capsule heat shield area while on the pad. A fiber-

glass shield attached above the vent port opening, streamlines the adapter and

shields the boil-off tube. Two stretch fittings, located 180 ° apart at the

upper section of the adapter, provide a means of supporting (stretching) the

missile while in the vertical position following adapter installation. Six

cable assemblies, attached to fittings spaced around the adapter outer corrugated

skin, are attached to the clamp ring that attaches the capsule to the adapter.

The cables retain the clamp ring to the adapter following capsule-adapter

separation.

_vi ma a_mi _ a ii .m

REPORT _DR lO b" ST. LOUIS, MISSOURI REVISED.

MODEL_ 1_3 J _.T_,A-_ ....... _ REVISED

2-15. CAPSULE-ADAPTER CLAMP RING

The capsule-adapter clamp ring, Figure 2-10, is provided to attach the

capsule to the adapter. The clamp ring secures the capsule to the adapter

throughout the capsule launching phase until the clamp ring is separated by means

of explosive bolts, which in turn allows the capsule to separate from the adapter.

The clamp ring consists of three chevron shaped segments, that when installed,

mate with the capsule forebody fiberglass attach ring and the adapter upper

support ring. Three explosive bolts, with dual ignition provisions, connect

the 3 clamp ring segments in tension. A metal striker bracket is bolted 3 every

120 °, to the inside of the clamp ring. When the clamp ring is installed, the

striker brackets depress the capsule ring separation sensing switches, located

in the outer periphery of the capsule forebody.

The exterior of the clamp ring is covered with a heat shield that protects

the explosive bolts from excessive heating. The heat shield consists of three

fairing assemblies which are located directly over the explosive bolts and three

segmented fairing assemblies which cover the remainder of the capsule adapter

clamp ring. The fairing assemblies which locate directly over the explosive

bolts are a three piece installation. The top piece is fabricated from aluminum

and the two bottom pieces are made from titanium. These fairing assemblies are

fastened to the clamp ring support fittings. The interior of the fairing

assemblies is insulated with thermoflex. The three segmented fairing assemblies

are of a titanium construction whose interior is insulated with thermoflex. The

segmented fairing assemblies are bolted to the adapter clamp ring. Six cable

straps are bolted to the capsule adapter cable fitting. These straps aid in

capsule-adapter separation, by retaining the clamp ring to the adapter when the

explosive bolts are fired. An electrical cable, clamped around the interior of

the adapter, is connected to each of the clamp ring explosive bolts, to two

/- •


REVISED

REVISED

SECTION'(: -C"

FIGUP, E 2 -I0 CAP5ULE ADAPTER CLAMP P,ING PM_5- 26

,_mip_lli'lllimllln_liali Inlml • • __

REPORT BE.DR 101¢ ST. LOUIS, MISSOURI REVISED

MODEL 133 ......... T_nT.._ffm,.. REVISED-- _.4_,..I J. 11 4L" JL.L_ JLr_W-'-.I=--._"'L"I_" ....

receptacles in the capsule forebody area and to two receptacles on the missile.

A pneumatic line is also connected to one end of the explosive bolt and to a

quick disconnect in the capsule forebody.


2-17. TEST CONFIGURATION CAPSULE NO. 8

Capsule 8 differs from the specification capsule in the following manner.

2-18. Forebod[

Capsule 8 does not contain an impact landing skirt. Instead, the heat

shield is bolted directly to the heat shield attach ring (See Figure 2-1).

Capsule 8 capsule adapter clamp ring heat shield has a large frontal area in

comparison to the specification capsule adapter clamp ring heat shield. Capsule

8 does not incorporate a large pressure bulkhead fiberglass shield protector.

Capsule 8 Atlas missile adapter is the same as the specification capsule (See

Figure 2-10).

2-19. Afterbodz

Capsule 8 does not have an explosive entrance hatch (Figure 2-12). The

hatch can only be removed externally. Hatch removal is accomplished by removing

the attach bolts that secure the hatch to the capsule. Hatch sealing is similar

to the specification capsule. The entrance hatch stringers are interlocked

(bolted) with the capsule stringers when the hatch is bolted in place. Capsules

8 and 12 do not contain entrance hatch retention springs.

2-20. Windows

Capsule 8 contains two cabin windows, but does not contain an observation

window (Figure 2-1). One window is located on the upper left side as viewed

from the capsule crew member station, to permit Astronaut's exterior viewing.

Located in the lower right side of the capsule is a window that enables the

. Y

........_ r__,T"__"_"_Wr',_",_--"-"_ -_'-'-''".... A .,.,.a.,_ ._a a,'t A A2"IkJ_

DATE

REVISED

REVISED

1 NOVEMBER 1961


PAGE 2-27

REPORT SEDR 104

MODEL 133

/

\

HATCH SHINGLE

[ INSULATION

INSULATION

HATCH SEAL

PI_2-:ll. C_PSG_E E_I'RAlqC_ HEI"CH

_111 ill/r-----it l l]!_ I--

PM,_,r_2A

REPORT _EDR 10[I - REVISEDST. LOUIS, MISSOURI

MODEL- 133 _ REVISED,_r , , ii I i i II .... _

photographing of the earth and sky during capsule flight. A camera is internally

located adjacent to this window. Each cabin window consists of an inner and outer

window assembly. The cabin inner (main) window assembly consists of four glass

panes sealed in a titanium frame attached to the cabin wall. The glass panes are

spaced and independently sealed to provide a pressure seal between the panes.

The outer cabin window assembly consists of a glass pane sealed in a titanium

frame that is attached to the capsule outer skin. The outer pane conforms to the

curvature of the capsule conical section. Capsule 8 does not incorporate a

snorkel explosive door.

2-21. Antenna Fairing

The antenna fairing destabilizing flap on Capsule 8 does not contain a

horizon scanner cover. (See Figure 2-1).

2-22. TEST CONFIGURATIONS CAPSULES 9, i0, 13 and 16

Capsules 9, I0, 13 and 16 major structural assemblies are basically the

same as that of the specification capsule.

J

• __;Y,,_--'_" 3-1

$£CTK)N Ig

/ ....

. _..J'

ENVIRONMENTAL CONTROLSYSTEM

TABLE OF CONTENTS

ii ii i'i ! i ii _-'-%-.-i__

• :. ::::::::::::::::::::::::::::::::::::::

'::_!::::::!::iii::::::iiiiiii!iiiiii_!ii!i_:

TITLE PAGE

DESCRIPTION 3-3eoeoeqsoeeeeoeeooeooeeoeeeeeeooooeeeeooeoeoe

CABIN ENVIRONMENTAL CONTROL ......... 3-S

SUIT ENVIRONMENTAL CONTROL ............ 3-6

SUIT EMERGENCY CONTROL, .................... 3-.7

OXYGEN SUPPLY ................ , .................... 3--8

COOLING CIRCUIT .................................... 3-8

OPERATION ............................................. 3-9

SYSTEM UNITS ......................................... 3-29

TEST CONFIGURATION..., ....................... 3-53

II_'ILI 1 I lfmlim

PAGE

REPORTMODEL

3-2

SEDR104133

C

M,DONNELL ST.LOUIS, MISSOURI


REVISED ,

REVISED

4p 0

FIGURE _-t EMVIP, ONMENTAL CONTROL SYSTEM

z

l_O-

_d

x0

_0

o_P'3_ rr

--.J _L_

D

[MaC PIJ. O_

_" k0 :I: =_ 'oeo og _o

-e-3

Pi_A_- _-7 D

-?

REVmEO, ST. -outs 3, MiSSOURi REPORT _EDR 104

.EV,SEO. . MO0_ 133

III. ENVIRONMENTAL CONTROL SYSTEM

3-i. DESCRIPTION

The environmental control system Figure 3-!, provides the Capsule Cabin and

the Astronaut with a 100 per cent oxyge n environment to furnish the breathing,

ventilation and pressurization gas required during the capsule orbital flight and

ventilation for a 12-hour post-landing phase. The environmental control system

also functions in the following manner: Removes odors, CO2 and moisture from the

Astronaut's suit circuit; provides an "emergency rate" usage of oxygen in the

event suit circuit pressure drops below 4.0 + .1 psia; maintains cabin and suit- "3

temperature at approximately 80°F; provides an emergency fire extinguishing

capability and operates in "weightless" or "high g" conditions. System function-

ing will be automatically controlled during all phases of flight. In the event

the system automatic control malfunctions, manual controls are provided to insure

system operation.

The environmental control system is designed to be operated in either the

suit mode, cabin mode or emergency mode. The system primary mode, suit environ-

mental control, is normally utilized and enables the Astronaut to function in

the closed suit circuit during cabin pressurized and emergency (depressurized)

conditions. In the event one control mode malfunctions, the remaining control

mode will continue to operate. The emergency mode, suit environmental control,

insures Astronaut survival in the event both the suit and cabin environmental

control modes malfunction. (see Figure 3-2. )

The environmental control system provides a primary and secondary oxygen

supply for both the cabin and suit circuits. Primary and secondary oxygen systems

are basically the same, except the secondary oxygen regulated pressure is lower

than the primary oxygen regulated pressure. A manually controlled cooling circuit,

_vz_li il,d'l_lNI I 1/_ I-"

4

REPORT SEDR 104

MODEL 133

Mc'DONNELL ' ....... -ST.LOU IS. MJ,SSQUR!,_.8

CASIN AII;:I I

INLET J

VALVE J

E

I _t SUITCOM pRE%C-_R

,i

%UI'T

CiI_CUIT

SHUT-OFFVALVE

1COI,APRES_OR J

CO_ ANDODOR

ABSORBE_

- LEGEND-,,,,, , OXYGEN FLOW

WATER FLOW

-"''-- "_' STEAM FLOW

• AE_I'UAT[N(_F_E_URE

CHECKVALVE

_]L_RE _u L Kl.,.,tE.AD

CABIN PRP-._UR ER_.LI EFVALVE

I l,,IIII

,_LI I T

; H EATF-XCHANGE_

CABINHEAT

E_CHANGER

FATE 1::_CCX_LANT

TANK

)...

I'IIIII

I!t

iNVERTER

NEAT EXCNANG=I

(MAIN)

7-

FLOW

J PRESSLIREhELl EFVALVE

t

I !I Itl !

DATE II1 NOVEMBER 1961

REVISED II

REVISED

PRIMARY

OXYGEN OXYGEN

BOTTLE BOTTLE

FLAPPER J

tVENTIL?TIONI

I OuTFLOWII VALVEI

SUIT

1;::_,E G ULATOI:_

I:'IGU_E 3'_. EI,qV_i2.0NI_ENTAL CONT_0L 5"YSTE_ BLOCV.. OIA, GIZ/X, lv_

LAFi_E F::_._SMR,F..,. _ULKH_:AD

PH_S- _3_

::._ y/

.L_'i/'_ll. IFIIr_PL,_- - .


REVISED

REVISED

Mc'DONNE ST. LOUIS 3, MISSOURI

PAGE 3"5

REPORT ,q_l_ 10_ ......

MOCk. .......13_

/

/

\\

for suit and cabin systems, is provided to control suit and cabin temperatures

during capsule flight. The capsule environmental control system components are

located below the Astronaut's support couch adjacent to the large pressure bulk-

head and also on the interior of the small pressure bulkhead adjacent to the

capsule escape hatch. System manual controls are located on the left and right

consoles; system instruments and warning lights are located on the main instrument

panel.

3-2. CABIN ENVIRONMENTAL CONTROL

During capsule normal orbital flight, the environmental control system is

normally operated in both the cabin and suit environmental control mode. Opera-

tion in the cabin control mode permits the Astronaut to open his helmet face-

plate for short periods of time. The capsule primary and secondary oxygen supply

furnished the cabin with pressurization, breathing, and ventilation gas. The

cabin is equipped with automatic and manual controls for cabin ventilation, de-

compression, pressurization, temperature control, landing and post landing

ventilation.

The cabin is cleared of contaminants and a lO0 per cent oxygen environment

is made available by purging the cabin prior to launch. The purging operation

is accomplished by utilizing the Capsule Leakage Tester. During orbital flight,

cabin pressure is automatically controlled by a cabin pressure control valve. The

cabin pressure relief valve prevents excessive pressure buildup within the cabin

and provides a manual means of decompressing the cabin in the event of a fire or

buildup of toxic contaminants. A water coolant supply tank, common to both cabin

and suit circuits heat exchangers, provides cabin cooling. In addition to its

cooling capability, the coolant tank is a source of drinking water for the

Astronaut. Cabin temperature is controlled by a manually controlled selector

valve, which regulates the amount of water entering the cabin heat exchanger, and

_v. mm m_al A |f_k I--

3-6 M ,DONNELL oA, REPORT R_,D_ ].Oh ST. LOUIS, MISSOURI REVISED

MODEL_ 133 _ REVISED

in turn provides cabin cooling by means of water evaporation. The cabin fan,

located on the inlet side of the heat exchanger, forces cabin air through the

exchanger to provide cabin cooling and ventilation. Cabin air inlet and outflow

valves, located on the small pressure bulkhead, provide ventilation during the

"capsule landing and post landing phase.

3-3. SUIT ENVIRONMENTAL CONTROL

During capsule normal orbital flight, the capsule common o_jgen supply

furnishes oxygen simultaneously to the suit and cabin environmental control

circuits. If a cabin circuit malfunction, such as cabin decompression, should

occur at a time when the Astronaut has his faceplate removed, the Astronaut

should immediately close his faceplate. Closing the faceplate initiates the

suit environmental control mode and confines the Astronaut to the closed suit

control circuit.

While operating in the suit environmental control mode, the suit pressure

regulator controls the suit pressure to approximately 5 psia and replenishes

oxygen consumed by the Astronaut, duringnormal suit control circuit operation.

The suit pressure regulator is supplemented by a constant oxygen bleed system

as a supplier of oxygen to the suit circuit. Suit circuit pressure is also

utilized as a secondary means of pressurizing the water coolant tank, in the

event the coolant quantity system fails. The suit environmental control circuit

incorporates compressors, filters, absorbers and a temperature control to insure

Astronaut's maximum comfort. Suit circuit temperature is controlled by means

of water evaporation. A water separator utilizes the common oxygen supply

pressure, to remove moisture from the suit circuit oxygen supply. A compressor,

located on the upstream side of the suit circuit heat exchanger, forces the suit

circuit oxygen supply throughout the circuit, providing suit circuit ventilation.

.... _. =._=, JL JL.-_-1LII, _

DATE ,1 November l_l "J_--_M_DONN_,_k//_/_ __ PAG_ 3-7

REVISED ST. LOUIS 3, MISSOURI REPORT _DR 104

R_,mSED MOZ_. 133

/i'

/

During the capsule landing and post landing phase, atmospheric air is drawn in

through the cabin air inlet valve to provide suit circuit ventilation.

3-4. SUIT EMERGENCY CONTROL

While operating in the suit environmental control mode during orbital flight,

the suit emergency control mode automatically activates when suit circuit pressure

decreases below 4.0 + .1 psia pressure. A control handle is provided to enable.3

manual selection of the emergency mode. During the capsule landing phase, the

emergency mode is automatically activated to increase Astronaut's cooling. The

environmental system oxygen rate valve and the suit circuit shutoff valve actuate

simultaneously to switch the environmental system frum the suit environmental

control mode to the suit emergency control mode. Actuation of these valves may

be either automatic or manual.

Operation in the suit emergency control mode, during orbital or landing

phases, basically consists of eliminating suit circuit oxygen flow through the

suit CO 2 and odor absorber, heat exchanger and water separator units. During the

landing phase, oxygen flow through the Compressor is maintained. During orbital

phase, oxygen flow is eliminated by deactivation of the Compressor. Elimination

of oxygen flow through these accessory components, while operating in the suit

emergency control mode, reserves the oxygen supply to remove the Astronaut's

generated heat, pressurize the Astronaut's pressure suit, and provide a breathing

source for the Astronaut.

An 02 EMERG light, located on the main instrument panel, and a tone generator

indicates when the environmental system is operating in the suit emergency mode.

Manual provision, to activate the suit emergency control, is located on the right

console.

_8 aA,.Jmm*A • • as *ram

Mc,DONN.ELLL z REPORT ,_ ] Oh ST. LOUIS, MISSOURI REVISED

MODEL. 133 " _ REVISED,

3-5. OXYGEN SUPPLY

The environmental system is supplied with oxygen, from primary and secondary

bottles. The primary and secondary oxygen bottles are directly interconnected

by a supply line, that forms a common oxygen supply to the cabin pressure control

valve, suit pressure regulator, emergency oxygen rate valve, and the suit circuit

water separator. The primary and secondary oxygen supply lines incorporate shut-

off valves, pressure transducers, pressure reducers, and check valves. The

pressure transducers transmit oxygen pressure, present in the primary and second-

ary oxygen bottles, to a dual quantity indicator, tape recorder, and to a tele-

metry unit. The primary oxygen bottle pressure is reduced to lO0 + 10 psig, by

a primary oxygen pressure reducer. Two primary oxygen pressure reducers are

provided to insure oxygen pressure reduction, in the event one pressure reducer

fails closed. The secondary oxygen bottle pressure is reduced to 80 psig by a

secondary pressure reducer. The primary oxygen supply reduced pressure, being

greater than the secondary oxygen supply reduced pressure, permits the primary

oxygen supply to be utilized during normal conditions with the secondary oxygen

supply in reserve. The oxygen supply line check valves prevent the loss of

oxygen, in the event either the primary or secondary oxygen pressure reducers

malfunct ion.

3-6. COOLING CIRCUIT

During normal capsule orbital flight, the environmental system cooling circuit

furnishes the cabin and the suit circuit with provisions for independently con-

trolling the cabin and suit circuit temperatures. Water is supplied, under

oxygen pressure, from the capsule water tank to the cabin and suit circuit heat

exchangers which in turn provides cooling by evaporation. The heat exchangers

absorb heat from the cabin and suit circuit oxygen and boil it off as steam.

CC_,_FIDELT_aL


REVISED,

REVIS£D,


P^S_ 3-9,

mm:,OmT _I_R 10b, , ,

• -_ ..... Mo_m.. 133

The cooling circuit contains an independent oxygen bottle that provides

pressure necessary to pressurize the water coolant tank, enabling water flo_ to

the heat exchangers. The oxygen bottle pressure is used as a reference pressure

for the coolant quantity indicator. A llne, interconnected between the suit

circuit line and the coolant tank pressurization llne, insures water coolant tank

pressurization, in the event the coolant quantity indicating system malfunctioned

The cooling circuit basically consists of a water tank, cabin and suit tempera-

ture control valves, heat exchangers, and indicators. A coolant quantity indi-

cator, EXEESS CABIN H20 and EXCESS SUIT H20 lights are located on the main panel.

Temperature control valves are located on the right console.

3-7. OPERATION

The environmental control system is designed to sequentially operate auto-

matically during the launch, orbit, re-entry and post-landing phases of capsule

flight. The mode in which the environmental system is operated is dependent

upon the existing conditions within the cabin and suit circuits.

During the pre-launch phase of operations, the capsule oxygen and water

supply are fully serviced and a capsule preflight is performed. Refrigerated

air is ducted through the capsule hatch to pre-cool the capsule cabin and struc-

ture during capsule preflight. The refrigerated air supply is removed and an

external supply of freon coolant is directed to the cabin and suit circuit heat

exchangers, through the umbilical, to continue pre-cooling the capsule structure

and cabin equipment. The oxygen supply bottles shutoff valves are opened and

the Astronaut is connected to the capsule suit circuit by attaching the suit

circuit personal leads (flex hoses) to the Astronaut's pressure suit. The suit

compressor and cabin fan are activated. The suit circuit is purged with an

external source of low pressure oxygen applied through the suit circuit purge

valve. Following the purging operation, a suit circuit leakage check Is per-

.. .m i _ i am am

s- o .MC,DONNELL REPORT SED_ lO_ ST. LOUIS, MISSOURI REVISED

MODEL. 1_ _ _ REVISED


formed with the Astronaut's faceplate closed. The capsule entrance hatch is

bolted into position and the capsule cabin is then checked for leakage and purged

with oxygen. The suit circuit incorporates provisions for obtaining launch purge

oxygen samples.

Forty-five seconds prior to launch, the ground umbilical plug is dlsconnectec

and freon coolant supply to the capsule ceases. During launch and orbit, the

cabin pressure relief valve maintains cabin pressure at approximately 5.5 differ-

ential (cabin/ambient) psia. During capsule launch, the suit circuit pressure

regulator maintains the suit circuit pressure approximately equivalent to cabin

pressure. The suit circuit oxygen is kept free of contaminants by a solids trap

and a CO2 and odor absorber. The solids trap removes foreign particles such as

food particles, nasal excretions, hair, etc. The CO 2 and odor absorber filters

odors and CO 2 from the circulating oxygen. Moisture from the suit circuit

oxygen is removed from the system by a water separator. The pneumatically

activated water separator deposits the moisture into a condensate tank. Cabin

and suit circuit temperatures are controlled by manually operated metering valves,

that regulate the water flow rate from the water coolant tank to the cabin and

suit circuit heat exchangers. Upon reaching altitudes where the saturation

temperature of water is lower than the cabin and suit circuit gas temperatures,

the cabin and suit circuit heat exchangers will provide cooling by water evapo-

ration.

Prior to capsule re-entry from orbital flight, the Astronaut positions the

temperature control valves to a COLD setting. When the capsule descends to an

altitude of approximately 21,0OO feet, the snorkel explosive door is ejected.

(Door is located on capsule exterior.) At an altitude of approximately 17,0OO

3000 feet, the cabin air inlet and outflow valves open barometrically venting

the cabin to the atmosphere. Operation of the suit circuit compressor draws out-

CO_F_'DEL'TIAL

1 ovember M!DONNELL 3-nREVISED. ST. LOUIS 3, MISSOURI REPORT ._R.T_R 1 04

REVISED • MOD_EL- 1_3

side air into the suit circuit through the ejected snorkel door opening, the

snorkel valve and the open cabin air inlet valve. The air, circulating through

the suit circuit, is relieved into the cabin and in turn flows out through the

cabin air outflow valve. Simultaneously, with the opening the cabin air inlet

and outflow valves, the environmental system mode of operation switches to the

suit emergency mode, but the suit compressor continues to operate. Switching

to the emergency mode provides a greater cooling capacity for the Astronaut.

When the capsule descends to approximately I0,000 feet altitude, the antenna

fairing is ejected. Ejection of the antenna fairing directs capsule power to

ignite explosive squibs, and in turn open the cabin air inlet and outflow valves°

(Opening of the cabin air inlet and outflow valves, when the antenna fairing is

ejected, is provided to supply ventilation air into the cabin in the event of a

capsule low altitude abort (below 17,000 feet) during capsule launch.) An inlet

air snorkel valve and an outflow air diaphragm flapper ventilation valve located

on the unpressurized side of the small pressure bulkhead -- opposite the cabin

air inlet and outflow valves, prevent water from entering into the cabin in the

event the capsule submerges after landing in a water environment. A vacuum

relief valve, located in the flexible ductlng between the cabin air inlet valve

and suit circuit, enables suit circuit ventilation whenever the inlet snorkel

valve closes. During the post-landing phase, the Astronaut may continue to

operate his suit circuit compressor to provide suit circuit ventilation. The

suit circuit compressor draws atmospheric air into the suit circuit, through

the cabin air inlet valve.

3-8. CABIN ENVIRONMENTAL CONTROL

Operation of the environmental control system in the cabin environmental

control mode, (Figure 3-3), after the capsule has entered the orbital flight

path; permits the Astronaut to open his helmet faceplate and be exposed to cabin

.J.J'_/_k IIPILI'_PIL l'l'll A I

REPORT S]EDR 104. REVISEDST. LOUIS, MISSOURI

133 ..........-- -" _" REVISEDMODEL. -,ovJ1z zJ_,.',-_ z *._


environment for short periods. The cabin circuit also provides a manual method

for decampressing and repressurizing the cabin. The cabin pressure relief valve

relieves cabin pressure in excess of 5.5 psia. In the event cabin pressure tends

to exceed the 5.5 psia differential (cabin over ambient), the relief valve will

open to relieve the excessive pressure. In the event the cabin pressure decrease_

below 5 psla, the cabin pressure control valve will sense the pressure drop and

open. Opening of the cabin pressure control valve allows oxygen to flow into the

suit circuit. The suit pressure regulator will sense the increase in suit pres-

sure, and relieve excess pressure into the cabin. Routing the cabin pressure

control valve oxygen supply through the suit circuit, provides a constant purgiug

of the suit circuit. Cabin pressure control valve maintains cabin pressures to

5.1 +. "2 psia..3

During orbital flight, cabin gas is circulated throughout the cabin by the

cabin fan, located at one end of the cabin heat exchanger. The cabin fan forces

cabin gas through the cab_u heat exchanger. The cabin gas circulating through

the cabin, absorbs the heat generated by the cabin electronic equipment and in

turn is cooled when the gas passes through the cabin heat exchanger. Water from

the water tank circulates through the heat exchanger and absorbs the heat from

the cabin gas passing through the heat exchanger. The heated water evaporates

and passes overboard through the large pressure bulkhead steam vent. Regulating

the amount of water entering the heat exchanger provides cabin temperature con-

trol. A cabin temperature control valve, located on the right console, is

manually operated by the Astronaut to control cabin temperature.

In the event of a fire or a buildup of toxic contaminants, within the cabin,

the Astronaut may manually decompress the cabin by actuating the DECOMPRESS "T"

handle, located on the left console. The decompression handle is connected to

the cabin pressure relief valve with a cable. During decompression of the cabin,

, j

2;/¸.

DATE 1 November 1961

REVISED,

REVISED


PA6E 3-13

REPORT SEDR 104

MODEL 133

the cabin pressure control valve closes when cabin pressure decreases to 4.1

psia. Following fire extinguishment, or the removal of toxic contaminants, the

Astronaut may repressurize the cabin by closing the DECOMPRESS "T" handle and

actuating the REPRESS "T" handle. The REPRESS "T" handle is connected to the

cabin pressure control valve with a cable. When the cabin has been repressurized

to 5.0 psia, the REPRESS "T" handle must be manually closed, in the event of a

cabin decompression, due to a metorite penetration or excessive cabin leakage,

the cabin pressure control valve will close automatically and prevent oxygen flo_

to the cabin, after the cabin pressure decreases to 4.1 psia. Closing of the

cabin pressure control valve reserves the remaining oxygen supply for the suit

environmental control circuit, enabling the Astronaut to continue the mission.

Prior to capsule re-entry, the Astronaut should assure that his helmet

faceplate is closed, and pre-cool the cabin structure and equipment by position-

ing the cabin temperature control valve and suit temperature control valve to

the cold settings. During capsule descent, cabin pressure is maintained at

approximately 5 psia pressure, until the cabin altitude is approximately 27,000

feet. At 27,000 feet altitude the cabin pressure relief valve begins to open,

allowing atmospheric air to enter the cabin and equalize capsule internal and

external pressures. When the capsule reaches 17,000 + 3000 feet altitude, the

cabin air inlet and outflow valves open and the cabin fan ceases operation.

Opening of the cabin air inlet valve provides outside air ventilation for the

suit circuit. Suit circuit air is then vented to the cabin and out through the

cabin outflow valve. If the cabin air inlet and outflow valves fail to open

at 17,000 + 3000 feet altitude, the Astronaut should actuate the SNORKEL pull

ring to open the valves. In the event the Astronaut fails to open the cabin

air inlet and outflow valves, the valves will open automatically at lO,000 feet

when the antenna fairing is ejected. Ejection of the antenna fairing directs

-T_9_b.... _-::T:AL

PAGE,

REPORT

MODEL

3-14

SEDR 104

133

M,_DONN_L/z__ ___ST.LOUIS. MISSOURI

DATE ...... 1 NOVEMBER 1961

REVISED ....

REVISED

lge_

_j

/

t.d

a.>

,,/j_-0

Z _

I I 5S

I_>:1 -- d

_ . i _ I

F.--o

FIC_URE S-3 CA_I_ ENVIRONMENTAL CONTR.OL

REVlSEO. ST. LOUIS 3, MISSOURI R_ORT S_R 104

REVISED _: • " Moore. 133

electrical power to ignite the cabin air inlet and outlet valves explosive

squibs, which in turn mechanically open the valves. A snorkel valve, provided

on the inlet side of the cabin air inlet valve and a diaphragm flapper venti-

lation valve provided on the outlet side of the cabin air outflow valve, prevent

water from entering the cabin when the capsule lands in the water. Following

capsule landing, the Astronaut may operate suit compressor for ventilation.

A cabin pressure indicator and a cabin temperature indicator are provided

on the_ main instrument panel to indicate cabin pressures and t_ratures. A

humidity indicator, with an incorporated sensor and amplifier, is also provided

on the main instrument panel to indicate relative humidity content of the cabin

gas. A CABIN PRESS light and tone generator, located on the main panel, indi-

cate when cabin pressure has decreased below _.0 psia pressure.

3-9. SUIT ENVIRONMENTAL CONTROL

The suit environmental control circuit, Figure 3-_, is supplied oxygen from

the environmental system oxygen supply, through the suit pressure regulator and

the cabin pressure control valve. During capsule launch and re-entry phases,

when the Astronaut's helmet faceplate is closed, the suit pressure regulator

utilizes cabin pressure as a reference to control the suit circuit pressure.

While operating in the suit environmental control mode, (helmet faceplate closed):

oxygen from the suit pressure regulator flows through the suit compressor, CO2

and odor absorber, suit heat exchanger, water separator, Astronaut's pressure

suit, and the suit circuit solids trap. In the event the suit circuit oxygen

pressure decreases, (more than 2.5 to 3.5 inches of water below cabin pressure)_

the suit pressure regulator will sense the pressure drop and open, allowing

oxygen to flow into the suit circuit to maintain the suit circuit pressure

within 2.5 to 3.5 inches - water of cabin pressure. When not in operation, the

suit environmental control system is guarded against contamination by a neoprene

L96L 11]SW_IAON I

Q3SIA3_I

O3SIABtl

alyO

=/4T_;,;-: C: J.%' C _I _'II_OSStlN ' SI nO'l"IS

Cl;l

t_Ot 11133S

9l'£

"13Q01_

1}40d3_

17

REVISED ST.LOUIS, MISSOURI REPORT SEDR 104

REVISED w . _ MODEL. |33

txm.os_v,_ . . -_..(, _E#I -" _l_ _ ti _ _..

_pL._ SUPI_LY I t'_---.J) \ I _- ; I I ':" _"_II II PI oxYG.:l,l

, ,REGUL_ TO!_ GIOUND TEST Si_pt£tl _u _,. | . 171 O_IFIC

A I_ c D I IilMD OlllT PI[I_ "rE_I

7-_L/! __ : ,,.-°,I• .- i15 v Ac

"d- -- --

-I T -- :.Eoo......

I )_ el , / I _ I III 7 ¥ I I.Li_ ] I I _*l,T<. I iT ._............. i t III o lii l_ t I I"_" I I I L--c.... to,,_ " -i [ttI I ._._t _o, L I I I I - I " " IF" I I I I I ,"'I'I I I I i --------o_._ _--"" I,T

i P_O_G_A_B_

/ I I _. i i,, .... :<i_,.. I.,_$P"'-I I ' I , UAt__A_ CJ% ,# "'%'2..'._2."--I -- .fd H _t_I.... Illlllllllll ....... ___x_'x_'x._.i_li_: T

............ t_ ft J) •No, z FtC_UR_. _-5 %UI_ Etv_,r_C_t CON'I_OL _i o_,15 300

18

REPORT _ lO4

•'__ 133


•n_'_T_Irlr_nnlr • T._ REVISED

coated nylon closure coupling. The closure coupling is attached to the ends of

the suit environmental control system inlet and outlet ducts.

The suit circuit incorporates two compressors that are installed parallel

to each other. During normal suit circuit operation the #I suit compressor

circulates the suit oxygen from the pressure suit outlet, throughout the suit

circuit. A differential pressure switch is vented to the inlet and outlet duct-

ing of the #I suit compressor. In the event the #I suit compressor malfunctions,

or fails to operate, the differential switch senses the pressure drop across the

#1 suit compressor, and in turn directs power to operate the #2 suit compressor.

A SUIT FAN switch is provided on the main instrument panel, to enable selection

of either compressor. Oxygen flowing from the compressors passes through the

CO2 and odor absorber. The absorber is divided into individual sections that

contain activated charcoal and lithium hydroxide removing odors and carbon

dioxide from the oxygen, to prevent any disccmfor_ to the Astronaut. Filters,

incorporated in the absorber, remove charcoal or lithium hydroxide dust from

entering the suit circuit oxygen.

Suit circuit temperature is controlled by a suit heat exchanger, that

removes heat from the suit circuit oxygen flowing through the heat exchanger.

Waterflow to the heat exchanger is controlled by a suit temperature control

valve, located on the right console. Suit circuit oxygen pressure is also

utilized to pressurize the water coolant tank in the event the coolant quantity

oxygen bottle, normally utilized to pressurize the water tank, malfunctioned.

Suit pressure and temperature sensors, located in the suit circuit, transmit

suit circuit pressure and temperature to the SUIT ERVIRON_ indicator. The

SUIT ENVIRO_ indicator, located on the main panel, is a dual face indicator

and indicates SUIT PRESS and SUIT TEMP. The water separator is a filter-type

sponge, that collects moisture from the suit circuit oxygen flOWlZ_ through the

':....._ C2NFID=NTIA, --

l ove ber Mc,DONNELL C , ,ffi 3-19REVISED ST. LOUIS 3, MISSOURI REPORT _R 10_

REVISED. _<"_ "" ' .... MODEL 133

i _" _ "*"iI

separator. At timed intervals, the sponge is pneumatically compressed to remove

the water from it. Water removed from the sponge is drained into a condensate

storage tank, located adjacent to the water separator. The sponge is compressed

by a piston that is actuated by oxygen pressure. The capsule programmer pro-

rides 24V D-C electrical power to energize the water separator solenoid valve for

30 seconds every 30 minutes. Energizing the solenoid valve, opens the valve to

allow oxygen pressure (lOO psi) to actuate the water separator piston. The

water separator piston incorporates two magnets. The magnets aid in determining

the position of the piston before and after actuation. Oxygen, flowing through

the water separator, flows to the closed emergency oxygen rate valve and through

the Astronaut's pressure suit. Oxygen, from the pressure suit, then passes

through a solids trap, that is provided to remove any foreign matter such as food

particles, hair, nasal excretions, etc., from the suit circuit oxygen supply.

The solids trap incorporates a relief feature, to prevent the possibility of

foreign matter blocking suit circuit flow. The suit circuit shutoff valve,

located downstream of the solids trap, is mechanically locked in the open posi-

tion during operation in the suit environmental control mode.

During capsule pre-launch phase, the suit circuit is purged and saturated

with oxygen from an external low pressure source. Suit heat exchanger is also

supplied with a freon coolant, from an external ground supply, to provide suit

circui¢ cooling. The suit circuit oxygen circulates throughout the suit circuit,

during the suit environmental control mode operation. During capsule flight the

pressure within the suit circuit is autamatlcally maintained at approximately 5

psia by the pressure regulator. During the landing phase, the capsule 21,000

feet barostats close at a capsule altitude of approximately 21,000 feet. Closing

of the 21,000 feet barostats directs 24V D-C electrical power to energize the

inlet air door relay. Energizing the inlet air doo_ relay directs power to

20

REPORT .c_,DR lo4

MODEl 133

McDONNE ST. LOUIS, MISSOURI

F!

/

DATE ' 1 NoVember l_l

REVISED ,

REVISED, ,

ignite an explosive squib, which in turn ejects the snorkel explosive door.

(Door is located on capsule exterior. ) When the capsule cabin descends to an

altitude of 17,0OO + 3000 feet, the cabin air inlet and outflow valves open

barometrically. The suit compressor draws atmospheric air into the suit circuit

through the ejected snorkel door opening, the snorkel valve and the open cabin

air inlet valve. In the event the cabin air inlet and outflow valves fail to

open, the Astronaut may manually open the valves by actuating the SNORKEL pull

ring, located on the left console. If the Astronaut does not open the valves

manually, the valves will open automatically at I0,000 feet when the antenna

fairing is ejected. Ejection of the antenna fairing directs electrical power to

ignite the cabin air inlet and outflow valves explosive squibs, which in turn

mechanically open the valves. Opening of the cabin air inlet valve automatically

switches the environmental system mode of operation to the suit emergency mode,

but the suit circuit compressor continues to operate to provide suit circuit

ventilation. Also, opening of the cabin air inlet valve directs electrical power

to close the suit circuit shutoff valve, which in turn mechanically opens the

emergency oxygen rate valve and provides electrical power to illuminate the O2

EMER light and operate a tone generator. Electrical power is also/_rovided to

energize the emergency air inlet door relay, which in turn directs electrical

power to ignite the snorkel explosive door squib and eject the s_orkel explosive

jdoor. (This provision insures the ejection of the snorkel explosive door, in

the event the door failed to eject at 21,OOO feet. ) Air circulating through the

suit circuit is vented through the suit pressure regulator to the cabin, and in

turn is vented out of the capsule through the cabin outflow valve. During the

capsule post-landlng phase, ventilation is provided by operating the suit circuit

compressor, which in turn draws outside air in through the cabin air inlet valve

and vents cabin air out the cabin outflow valve. In the event the capsule sub-

C ll-i ,_l&TI'_ lr n m---_-- ...... _-. A_A, A lz_klJ

RI:_VISED. ST. LOUIS 3. MISSOURI REPORT _.'_R I0_

R=v,sED. _..................... _oo=L 133

merges momentarily, following a water landing, the ball float in the cabin air

inlet valve and the diaphragm flapper valves in the cabin air outflow valve

will seat. Seating of the valves (snorkel and flapper), prevents water from

entering into the suit circuit and cabin, through the open cabin air inlet and

outflow valves. Operation of the suit circuit compressor with the snorkel valve

closed will create a vacuum in the flexible ducting, located between the cabin

air inlet valve and the suit circuit. The vacuum relief valve, located in the

flexible ducting, will open when the pressure differential between the cabin and

flexible ducting is 10-15 inches of water. Opening of the vacuum relief valve

allows cabin pressure to enter into the suit circuit flexible air inlet ducting,

and unseat the air inlet snorkel valve ball float, if the capsule snorkel valve

is above the water. This action in turn allows outside air to enter into the

suit circuit to continue ventilation. During capsule submersion, cabin air

entering the open vacuum relief valve provides suit circuit ventilation,

3-i0. SUIT E_GENCY CONTROL

The suit emergency control, Figure 3-5, is provided to insure Astronaut's

survival in the event the cabin and suit environmental control circuits mal-

function. Operation in the suit emergency control mode basically consists of

opening the emergency oxygen rate valve, to supply oxygen at a rate greater

than normal; and closing of the suit circuit shutoff valve, which in turn

eliminates oxygen flow through the temperature control and impurity removing

units. !S_luminatiom of the 02 EMERG light and the movement of the EMERG 02

rate handle to EMERG position, indicates environmental system operation in the

suit emergency control mode.

When operating in the suit environmental control mode, during capsule

normal orbital flight, the emergency oxygen rate valve is closed, the suit

circuit shutoff valve is open, suit compressors are operative, and the suit

_T_'7 '_--.._'T'.;L

22

REPORT b-'_DR 10/4•

MODEL_ 133

MCDONNE DATE 1 November 1961REVISED .....

. ST. LOUIS, MISSOURI• " REVISED

circuit pressure regulator is controlling oxygen flow to the suit circuit. The

emergency oxygen rate valve remains closed as long as suit circuit pressure

remains at approximately 5 psia pressure. In the event the suit circuit pres-

sure drops to 4.0 +. .1 psia, the rate valve internal anerlod extends, to offseat.J

a poppet, and allows oxygen from the oxygen supply to flow through the rate valve

and into the suit circuit. The extension of the rate valve aneriod, due to low

pressure, actuates a limit switch that provides electrical power to energize the

suit circuit shutoff valve solenoid and the suit fan cut-off relay, illuminate

the 02 E_RG light, and operate a tone generator. Energizing the suit fan cut-

off relay removes the llSV A-C electrical power to operate the suit circuit com-

pressor. (At an altitude of 17,000 +. 3000 feet, the cabin air inlet relay will

open. Opening of the cabin air inlet relay de-energizes the suit fan cutoff

relay. The de-energized suit fan cutoff relay routes power to the #1 suit cir-

cuit compressor. If the #1 suit circuit compressor fails to operate within 12

seconds, the suit fan selector relay will energize and allow power to be directed

to the suit fan cutoff relay and then on to the #_ suit circuit compressor.)

Energizing the shutoff valve solenoid releases the shutoff valve shaft arm, and

mechanically moves the EMERG 02 handle, right console, to the EMERG position.

Movement of the EMERG 0 2 handle moves a cable, that is connected to the emergency

oxygen rate valve shaft arm, and mechanically actuates the emergency rate valve

to maintain the rate valve in the open position. With the emergency oxygen rate

valve open and the suit circuit shutoff valve closed, oxygen from the oxygen

supply flows into the pressure suit and is discharged through the suit pressure

regulator relief valve.

Actuating the E_ERG 02 handle to the NORM position resets the shutoff valve

to the open position, the emergency oxygen rate valve to the close position,

starts suit compressor operation, extinguishes the 02 EMERG light, and in turn

REVISED ST. LOUIS 3, MISSOURI REPORT _ 10_

REV,sz. MOOE. 133

/

switches the suit circuit operation to the suit environmental control mode. The

suit emergency mode is also automatically selected durin_ capsule landing phase,

when the capsule has descended to an altitude of 17,000 + 3000 feet. At 17,000

+ 3000 feet the cabin air inlet valve opens. Opening of the cabin air inlet

valve actuates a limit switch that provides electrical power to operate the suit

circuit compressor and close the shutoff valve, which in turn mechanically opens

the emergency oxygen rate valve. An inlet power switch, located on the main

instrument panel to the right of the satellite clock, is incorporated in the

environment control system. The inlet power switch allows operation in the

suit environmental control mode in the event the cabin air inlet valve prematurel_

opens (See Figure 3-_). Premature opening of the cabin air inlet valve deacti-

vates the cabin fan and closes the suit circuit shutoff valve which in turn opens

the emergency oxygen rate valve. The suit circuit is now operating in the

emergency mode. To initiate transition back to the suit environmental control

mode, the inlet power switch is placed in the BY-PASS position. With the inlet

power switch in the BY-PASS position, the cabin fan is activated (See Figure 3-3)

and the suit circuit shutoff valve is deactivated. The E_BR 02 handle, right

hand console, is now placed in the NORM position; placing of the EM_ 02 handle

to the NORM position opens the suit circuit shutoff valve which in turn closes

the e_ergency oxygen rate valve. The environmental control system is now operat-

i_ in the suit envi_ntal control mode. To prevent snorkel door separation

upon premature opening of the cabin air inlet valve, the emergency inlet air

door relay is interconnected to the antenna fairing separation relay during

descent. After opening of the cabin air inlet and outflow valves, the inlet

power switch is placed in the NORMAL position.

3-ii. OXYGEN SUPPLY

During the capsule pre-launch phase and prior to installation of the capsule

C9::-:------_: .--:AL

PAGE _-24

REPORT ,_EDR 104

MODEL_ 133

Mc'DONNEL L ST. LOUIS, MISSOURI


REVISED

REVISED,,,

entrance hatch, the capsule oxygen supply shutoff valves are manually opened, by

ground crewmen, to activate the oxygen supply. Opening of the primary and second

ary oxygen supply shutoff valves, Figure 3-6, provides oxygen to the cabin pres-

sure control valve, suit pressure regulator, suit emergency oxygen rate valve,

constant bleed orifice which routes oxygen directly to the suit circuit inlet

duct and the suit circuit water separator solenoid valve.

During operation, when the primary oxygen bottle pressure drops below

approximately 200 psig, due to near depletion of the primary oxygen supply; the

secondary oxygen supply line pressure will override the primary oxygen supply

line pressure and continue to supply the environmental system with oxygen. Two

oxygen flow sensors, one located in the primary oxygen supply llne and one

located in the secondary oxygen supply llne, detect environmental control system

transition from primary oxygen supply to secondary oxygen supply. Used in con-

Junction with the oxygen flow sensors is an oxygen flow switch (See Figure 3-6).

The oxygen flow switch, located on the main instrument panel to the right of the

satellite clock, is a two position switch marked "SEC" and "PRIM". When the

primary oxygen supply flow rate drops to approximately zero pounds per minute

at 80 psig, the oxygen flow sensor will direct a 24 volt d-c signal to illuminate

@

the 02 QUAN light and operate the tone generator. The 02 QUAN light, located

on the main instrument panel, and the tone generator are provided to indicate

to the Astronaut that the secondary oxygen supply is being utilized. The G2

flow switch should now be positioned to the "SEC" position. Positioning the 02

flow switch to "SEC" removes the 24 volt d-c signal from the 02 QUAN light and

tone generator circuits. A quantity indicator gage, located on the main instru-

ment panel, is provided to indicate remaining oxygen supply. Two transducers,

primary and secondary supply, are provided to enable telemetering of oxygen

quantity remaining.

DATE

REVISED

REVISED

I NOVEMBER 1961 Mc,DONNELL_H_,__ST.LOUIS, MISSOURI

PAGE 3-25

REPORT SEDR 104

MODEL 133

,b *':,

t

F LOW

Z _ 4 5 G

SW" I

t_-_.

IN_RUN_ENI_

Y

2 3 4 5 _

OxVGE_

QUA_T_\I N D _CATOI;_ \_

(MAIN I:_ANF.L_ N_

FIGURE 3"_, PP-.IMAR'Y AND SECONDAR_ OXYGEN SUPPLY

26

REPORT _!_ID_ !C'/I.

MODEL 133

MCDONNE oA, REVISED.

ST. LOUIS, MISSOURI

........ ............ . " _. _ REVISED

3-12. COOLING CIRCUIT

The cooling circuit, Figure 3-7, basically consists of a water coolanttank,

cabin and suit temperature control valves, cabin and suit heat exchangers,

inverter heat exchangers, coolant quantity indication circuit, and an excessive

water warning circuit. During capsule pre-launch, after the entrance hatch has

been installed, cabin, suit circuit and inverter cooling is achieved by supply-

ing freon (F-f14) through the capsule umbilical connector and into th_ cabin,

suit and inverter heat exchangers. The freon coolant absorbs heat from the cabin

and suit air flowing through the heat exchangers, and boils overboard through

the environmental system steam vents, located in the large pressure bulkhead.

Freon metered to three inverter heat exchangers absorbs and dissipates heat from

the inverters in the same manner as the cabin and suit circuit heat exchangers.

Forty-five seconds prior to capsule launching, the freon coolant supply is dis-

continued. When the capsule reaches approximately 115,0OO feet altitude, in-

verter, cabin and suit circuit cooling is achieved by water evaporation, that

occurs within the inverter, suit and cabin heat exchangers. The coolant quantity

indicating system pressure relief valve remains open, during capsule launch,

until the pressure decreases to approximately 5-9 psia. The relief valve closes

at 5.9 psia pressure and in turn enables the coolant quantity indicating system

to operate.

Water from the water coolant tank is supplied, under a 5-5 psia pressure,

through the temperature control valves, to the suit and cabin heat exchangers.

Water is also supplied and me'cereal to the main and standby inverter heat

exchangers. Oxygen, stored under a 5OO psig presmxre in the coolant quantity

oxygen bottle, is utilized to pressurize the water coolant tank. A pressure

regulator decreases the coolant oxygen supply 500 psig pressure to 5.5 psia

pressure. A cooling circuit pressure relief valve relieves cooling circuit

C2NI'ID Li',;_-ta,_ .......

RL='VISED ST. LOUIS S, MISSOURI REPORT SEDR 10_

. MOO=. .... .

\

J

pressures in excess of approximately 6 psia. Oxygen pressure within the water

coolant tank tends to move the tank diaphragm, which in turn forces the water

supply out of the tank at a rate dependent upon the position of the temperature

control valves. In the event the coolant quantity oxygen supply should deplete

or malfunction, oxygen, at 5 psla pressure from the suit circuit, will continue

to pressurize the water coolant tank. The temperature control valves control

the amount of water entering the heat exchangers, and in turn controls cabin and

suit temperatures. Water within the heat exchangers absorbs heat from the cabin

and suit oxygen, flowing through the heat exchangers; The heated water evaporates

and flows out through the steam vents, located in the large pressure bulkhead.

Water metered to three inverter heat exchangers absorbs and dissipates heat from

the inverters in the same manner as the cabin and suit circuit heat exchangers.

In addition, heat generated by the Inverters is drawn into the cabin heat

exchangers by means of the cabin fan. Indicator lights are provided on the main

instrument panel to indicate extreme cold conditions in the cabin and suit heat

exchangers exhaust ducts, which could possibly freeze and plug overboard steam

vents. If the heat exchangers exhe_st ducts temperatures drop below 42°F, a

thermal switch, located in each of the exhaust ducts actuates close. Closing of

either thermal switch directs 24V D-C electrical power to illuminate either the

EXCESS CABIN H20 or the EXCESS SUIT H20 light, and operate the tone generator;

thus indicating to the Astronaut of extreme cold temperatures in the heat

exchangers exhaust ducts. The Astronaut must then position the cabin or suit

temperature control valve to a warmer setting, in order to reduce the possibility

of water freezing in the exhaust duct.

A coolant quantity indicator, main instrument panel, is provided to indicate

the quantity of water coolant remaining in the water coolant tank. The indicator

operates in direct relationship to the oxygen remaining in the coolant quantity

28

REPORT SEDR 104

MODEL 133

Mc'DONNEL ST.LOUIS, MISSOURI

DATE ......

REVISED

REVISED

1 NOVEMBER 1961

_,_ TE.ST

_W iTCH

_4v DC

0

DIM._ NI BRT,

E NVI_ON MENTAL WARNING

CONTROL LI6NT SWITCH WATER

24V DC COOLANT TANK

CABIN TEMPERATURECONTROL VALVE

ORIFICE PREON CHECKVALVE

METERING VALVE

(WATER)

WATER CHECK

VALVE.

H

H

[1 METERING 'VALVE

(FREON)

FREON CHECKVALVE

COOLANT QUANTITY

OXYC_ N BOTTLE

(5ooPSi)

FREON CHEC}KVALVE

THERMAL

I SWITCH

I

I

TNERMALSW_TCH I

['

TOPRESSL RE

ORIFICE

'ILARGE PRESSURL

BULKHEAD

NOTESCHEMATIC DEPICTS COOLING

CIRCUIT OPERATION OURIN_

NORMAL CAPSULE FLIGHT

HEAT HEAT HEAT

EXCHANGER E_CHANGER EXCHANGER

_IIN INVERTER (5TBY INVERTER MAtH INVERTER250 _A.) Zso_A_ 150_A.)

I I ICAPSUCEUMBILEALPLU6

FIGURE 3-7 COOLING CIRCUIT

SUIT

CIRCUIT

FLOW

I'{'FREONSUPPLIEDDURING "_

_,GROUNDOPERATION ONLYJ

SUIT HEAT

EXCHANGER

PM4.5 -36B

P/"_ I_1E" I f"_ P" " " -- " -....... • .,.,_1 I I/all, l[--

,.oo....REVISED ST. LOUIS 3, MISSOURI MI_ORT. _D_ 10_.

R_'VISED , . ,i, MODEl.. 133

oxygen bottle, through a pressure transducer and instrumentation package. When

the coolant quantity oxygen bottle is full, (500 psi), the coolant quantity

indicator will read 100%. As the coolant oxygen bottle pressure decreases, as

a result of water being utilized, the coolant quantity indicator reading will

decrease accordingly.

3-13. SYSTEM UNITS

3-i_. PRIMARY AND SECONDARY OXYGEN BOTTLES

The primary and secondary spherical shaped oxygen bottles are located

beneath the Astronaut's support couch adjacent to the capsule conical section

and large pressure bulkhead. Each bottle has a capacity of 4 pounds oxygen,

stored under a 7500 psig pressure at 70°F temperature. Reduction of pressure

for utilization in the environmental control system is accomplished with pressure

reducers. The primary supply is reduced to approximately I00 psig; the secondary

oxygen supply is reduced to approximately 80 psig. Servicing of the oxygen

bottles is accomplished through a quick disconnect filler coupling.

3-15. SUIT CIRCUIT PRESSURE REGULATOR

The suit circuit pressure regulator, Figure 3-8, is provided to regulate

oxygen pressure to the suit circuit and to replenish suit circuit oxygen consumed

by the Astronaut, absorbed by moisture or carbon dioxide or lost through leakage.

The regulator is a demand type diaphragm operated regulator that controls suit

circuit pressure in reference to cabin pressure. Suit circuit pressure is main-

tained approximately 2.5 - 3.5 inches of water below cabin pressure during normal

system operation, under ideal (no cabin leakage) conditions. Cabin pressure is

sensed on the upper side of the regulator control diaphragm and suit circuit

pressure is sensed on the lower side of the diaphragm. The regulator also con-

tains a resilient type diaphragm that is used to relieve excessive suit circuit

30

REPORT SEDR 104

MODEL_ I_

Mc,DONNELL __ DATE !" November l_l

REVISED• ST. LOUIS, MISSOURI

REVISED,,

pressures. Two anerolds are provided to shut off cabin vent port of regulator in

the event cabin pressure decreases below 4.6 + .2 psla. In the event of cabin

leakage, not decreasing below 4.0 + .2 psia, the cabin pressure control valve

will open to replenish cabin pressure to 5.1 + .2 psia. Make up oxygen from the- ,i

cabin pressure control valve will flow through the suit circuit and out through

the suit pressure regulator relief valve sad into the cabin. At this time, suit

circuit pressures will exceed cabin pressures due to pressure differential (suit

above cabin) required to open the suit circuit pressure regulator relief valve.

The cabin leakage rate will determine the amount the suit circuit pressures will

exceed the cabin pressures.

During normal capsule ascent, cabin pressure decreases, and the regulator

relief diaphragm relieves suit circuit pressure to within 2 - 9 inches _0 above

cabin pressure. During capsule normal orbital flight, the control diaphragm

will regulate suit circuit pressure in relationship to cabin pressure. An in-

crease in cabin pressure will act on the diaphragm to offseat a poppet valve and

allow suit Circuit pressure to increase to within 2.5 - 3.5 inches of H20 below

cabin pressure. In the event cabin pressure decreases below 4.6 + .2 psla, the

aneroids will extend sad close off cabin vent port of regulator. Two 60 cc/min

bleed ports will then bypass the poppet valve to the cabin sensing side of the

control diaphragm sad regulate suit circuit pressure to 4.6 + .2 psia. Two

aneroids and two bleed ports are provided to insure regulator operation, in th_

event either aneroid or either bleed port fails to function. Descent operation

of the regulator is the same as an increase in cabin pressure during capsule

normal orbital flight.

3-16. SUIT CIRCUIT SHUTOFF VALVE

The suit circuit shutoff valve, Figure 3-9, is designed to shut off oxygen

,<.

CCNFIDE- _;Tia,.

±IN_

t, Ol llQ_l$

"I3QOIN

J._lO,:t_ld lttFIOSSiiN ' SI FIO-I'.LS

a3Sl^31:l

Q3SIA31:i

_.LVCI

32

REPORT SEDR 104

MODEL 133

Mc'DONNELL ' ST,LOUIS, MISSOURI

_%../I_II IL'/L'-i_i I I/-'ti=' _

DATE

REVISED,

REVISED

1 NOVEMBER 1961

SUIT CIRCUIT

FI(_URE 5-9. SUIT CIRCUIT SHUTOFF .VALVE

5HUTOFP VALVE

PIA45-152 A

pl_Llkl P I _ P IL • -- - " --•.._ v I ". I I I._ I.. i 1 i-'i rt I..

REVISED ST. LOUIS 3. MISSOURI REPORT _DR ].04

aEvlsED ........ MOD_',' .........133

flow to the suit environmental circuit accessory components, whenever the suit

circuit is operating in the emergency mode. Closing of the suit circuit shutoff

valve reserves the remaining oxygen supply for the Astronaut's pressure suit.

The shutoff valve, spring loaded to the close position, is latched in the open

position during normal suit circuit operation. Valve is maintained in the open

position by a solenoid controlled detent pin engaged into the valve spoon arm.

A micro switch, depressed by the valve arm, completes the solenoid circuit when

the valve is latched open. Opening of either the emergency oxygen rate valve

or the cabin air inlet valve directs an electrical signal to energize the shut-

off valve solenoid. Energizing the solenoid retracts the detent pin and allows

the valve spring to rotate the valve spoon to the close position. Closing of

the valve opens the solenoid circuit and opens the emergency oxygen rate valve,

through an inter-connecting cable. The shutoff valve is mechanically opened by

the EMER 02 control handle, located in capsule. The shutoff valve is inter-

connected to the emergency rate valve, so that when the emergency rate valve

closes, the shutoff valve opens.

3-17. EMERGENCY OXYGEN RATE VALVE

The emergency oxygen rate valve, Figure 3-10, is provided to supply a

regulated amount of oxygen directly into the Astronaut's pressure suit, in the

event malfunction occurs in the suit circuit operation. The rate valve is

designed to operate automatically and contains provisions for manual operation.

The valve, closed during normal suit circuit operation, contains an aneroid that

senses suit circuit pressure. Whenever suit circuit pressure drops below 4.0

+ .i psia, the aneroid extends to offseat a spring loaded poppet and allow oxygen.3

pressure to enter the diaphragm chamber. The pressure in the diaphragm chamber

increases and fully strokes the poppet, allowing oxygen to flow into the

Astronaut's suit at a fixed flow of .049 to .051 #/_Lin. Simultaneously with the

_Im,_mLL irmml imll, l,,mL |,mira I At 11

PAGE

REPORT

MODEL

3-34

SEDR 104

133 '

McDO__ __ST.LOUIS, MISSOURI

DATE

REVISED

REVISED

1 NOVEMBER 1961

/

----E.ME.R_F_.NO..YO_ f_ATE VALVE

F_O_ CAPSULE

,_...... ,/--MANUAL CONTROL

POPPET-__ _ CONTROL SWITCH

_o_ -_ _

FIGURE 5-10 EMERGENCY O_ RATE VALVE_h_45-i53

//

MCDONNE , 3-35REVISED ST. LOUIS 3, MISSOURI REPORT., _DR 10_

REVISED of . - ' MODEL 133

offseatlng of the poppet, a control switch is actuated through a lever mechanism,

and directs electrical power to close the suit circuit shutoff valve, illuminate

the 02 EMERG light, and stop suit circuit compressor operation during capsule

orbital flight. Suit circuit shutoff valve is interconnected with emergency

oxygen rate valve. Therefore, closing of the shutoff valve actuates the emergency

oxygen rate valve manual control shaft to close off oxygen flow to valve poppet

inlet. Oxygen then flows directly into suit circuit through the valve aneroid

chamber.

Emergency rate valve control shaft actuation actuates a pin to depress con-

trol switch and also moves EMERG 02 control handle (right console) to EMERG

position. Emergency oxygen rate valve may be opened manually by selecting EMER

position with EMERG 02 control handle. Operation will be same as control shaft

am operation, described above. Whenever the EMER 02 control handle is moved

to NORM, the suit circuit shutoff valve opens and emergency oxygen rate valve

close s.

3-18. SUIT CIRCUIT COMPRESSORS

The suit circuit environmental control system utilizes two electric motor

driven, single-stage, centrifugal compressors (See Figure 3-4). One compressor

is for the normal circulation of gases within the suit circuit; the other is a

standby compressor used in the event of normal compressor failure. If the

normal compressor fails, the standby compressor is activated by a pressure dif-

ferential switch which directs power to the standby compressor electrical connec-

tions. The only time the suit compressor is inoperative is during orbital flight

when the Astronaut is utilizing oxygen from the emergency oxygen rate valve.

When supplementary oxygen from the emergency oxygen rate valve is being used

below 20,000 feet, the suit circuit compressor will continue to operate to

circulate ambient air to the Astronaut.

3-36 Mc,DONNE ., DA, Uow= rREPORT _ I011" ST. LOUIS, MISSOURI REVISED

MODEL_ 13_ L,vJ.,,_. , .... , , REVISED

3-19. CO2 AND ODOR ABSORBER

The CO2 and odor absorber, Figure 3-I1, is provided to remove Astronaut

emitted odors and carbon dioxide frun the suit circuit. The absorber is basl-

cally a metal cannister divided into two sections. The inlet section contains

activated charcoal that removes obJectlonal odors from the suit circuit oxygen.

Lithium hydroxide, located in the center sections removes carbon dioxide. The

outlet section is an exit filter, provided to prevent charcoal and lithium

hydroxide dust frem entering the suit circuit oxygen flow. The charcoal and

lithium hydroxide granules are compressed by a spring force. The CO2 and odor

absorber has an operating life of approximately 31 hours, and to insure proper

absorber operation the absorber should be replaced prior to capsule mls sion.

3-20. SUIT CIRCUIT HEAT EXEHA_ER

The suit circuit heat exchanger (Figure 3-12) is of a plate fin construction

with rectangular offset fins, double sandwich, one pass on the oxygen side and

two pass, single sandwich on the water side. The function of the heat exchanger

is to cool the gases circulating throughout the suit circuit. Water from the

water cooling tank is routed to the inlet side of the heat exchanger at which

point it is directed to a high density woven felt pad. The function of the felt

pad is to evenly distribute the water through the heat exchanger. As water

passes through the felt pad, it comes into contact with the heat transfer sur-

faces on the water side of the heat exchanger. The water then absorbs the heat

from the circulating gases and the water is then boiled off as steam and dumped

overboard.

3-21. WATER SEPARATOR

The water separator, Figure 3-13, is provided to remove moisture, condensed

as a result of suit heat exchanger operation, from the suit circuit oxygen. The

CO _,'FID Z_A'A,A L

DATE

REVISED

REVISED

1 NOVEMBER 1961

Mc'DONNELjL-__ __ST,LOUIS, MISSOURI

PAGE 3-37

REPORT, $EDR 104

MODEL. 133

i I i /

1 II

FiGUP,E.5"I[. CO_ AND ODOR AIBSORBEP,

PAGE

REPORT

MODEL

3-38

SEDR 104

133


DATE ........

REVISED

REVISED ,

1 NOVEMBER 1961

L

_UIT HEAT EXCHA_C_ER

m

[_. ox'_ C___NOX",f C_E N F----Jx, x OUTLET

INLET

(FELT PA, D

FI_, E. ON _N LE.T

_'TE AIv_ _OUTLET

FIGURE 3-12 %BIT HEAT EY,CHAN_EP,

SECTIONSHOWIN_' OPERATION

PM45- _._G

' 'q,.*v m,_ m ! !'

l ov er M¢,DONNE , 3-39R_ISED ST. LOUIS 3, MISSOURI REPORT. _:_ 10t

REVISE=) _ MOOre. 133

separator is basically a filter type sponge that collects moisture from the

oxygen passing through it. The sponge, pneumatically compressed, removes the

condensate from the sponge and deposits it into a storage tank. During suit

circuit operation, the sponge filters moisture from the oxygen flowing through

the sponge. Once every 30 minutes, for a duration of 30 seconds, the capsule

programmer supplies electrical power to energize the water separator solenoid

valve. Energizing the normally closed solenoid valve opens the valve and directs

oxygen from either the primary or secondary supply to the piston stem and the

piston plate chambers.

Due to the difference in area, on each side of piston, the piston raises

the sponge out of the suit circuit oxygen flow and is compressed against the

separator housing plate. Water squeezed out of the sponge drains into the con-

densate tank. Following the termination of squeezing (30 seconds), the water

separator solenoid valve is de-energized and the solenoid valve closes. Oxygen

below the separator piston is vented to cabin through the separator solenoid

valve. Oxygen above the piston, entrapped by a check valve, forces the piston

down, thus returning the sponge into suit circuit oxygen flow. Suit circuit

pressure is also supplied to top of separator to_aid in forcing the sponge down.

Two check valves, located on top of separator, prevent water from entering the

suit circuit and also prevents water backflow into the top of separator. A check

valve is supplied to prevent oxygen depletion in the event separator mechanisms

developed a leak. During squeezing operation suit circuit oxygen flow will not

be affected, as oxygen will continue to flow through area normally occupied by

the sponge. The water separator piston incorporates two magnets. The magnets

aid in determining the position of the piston before and after actuation.

3-22. SOLIDS TRAP

The suit circuit solids trap, Figure 3-14, is located in the pilot's suit

PAGE

REPORT

MODEL.

3-4_0

, SEDR 104

133

M_'DONNELL_'•_ ____ST.LOUIS. MISSOURI

DATE1 NOVEMBER 1961

REVISED ........

REVISED

SPONGE

VRLVE

III

FROMOXY&EM,_UPPLY

OXYGEN SUPPLY

FIGUP.E _-IR W/kTE_ "3EPAtZATOD.

C _ I_1 !_" I I"_ l" _ "-- -

PM,_5-157B

DATE

REVISED

REVISED

1 NOVEMBER 1961 M_'DONNE_"4_ __ST.LOUIS, MISSOURI

PAGE

REPORT ......

MODEL

3-41

SEDR 104

133

/ .,

.FIQIjRE

-- PRIMARY FLOW

-- -- 5ECONDARY FLOW

SOLIDS TRAPpM 4_j- Z'_lh

--Will Ii./r-:-il I lnL

..o. - M_,DONNE___ °_......REPORT, SEDR 10,4


MODEL ] 3 3 r m-_J__ l_ P- L i -P_L.td _ REVISED

1 NOVEMBER 1961

W^$HERS I.,

" _NLI CAP:WE_

FIGURE 5-15 CALVIN HEAT EXCHANGEP-, AND FAN PM_,S-Z_TA

7 j/,'

CC"

REVISED. " ST. LOUIS 3o MISSOURI REPORT SEDR 10)4

REVmEO _ MOOEL l_,!D " ' ' '

oxygen outlet duct. The trap consists of a 40 micron mesh screen filter which

incorporates an integral bypass to insure operation in the event the trap would

become choked with collected solids.

3-23. CABIN HEAT EXEHANGER

The cabin heat exchanger (Figure 3-15), cools the cabin gas in the same

manner as the suit circuit heat exchanger except the cabin heat exchanger employs

an electric driven motor fan to draw in and reclrculate cabin gas. Internal

structure is the same as the suit circuit heat exchanger.

3-24. CAPSULE WATER TANK

The capsule water tank is a pressurized compartmented cylindrical shaped

container (Figure 3-15). Water is displaced from the tank by means of a rubber

bladder which is activated by oxygen from the Coolant Quantity Oxygen bottle.

Water from the tank is directed to two manual control valves which control the

water supply to the suit circuit and cabin heat exchangers. The capsule water

tank also provides the Astronaut with a source of drinking water.

3-25. CABIN PRESSURE CONTROL VALVE

The cabin pressure control valve, Figure 3-17, is provided to maintain

cabin pressure to 5.1 + .3 psla. The control valve contains two aneroids that

sense cabin pressure. Whenever cabin pressure drops below 5.1 + .3 psia, the

aneroids partially expand and unseat the spring loaded metering pins, which in

turn permit oxygen to flow into the suit circuit. The suit pressure regulator

senses the increase in pressure, and relieves suit circuit pressure to the cabin.

Directing oxygen flow through the suit circuit provides constant purging of suit

circuit. When cabin pressure increases to 5.1 +- .3 psia the aneroids contract,

allowing the metering pins to seat and shut off the oxygen flow. In the event

of cabin deccmpression, or whenever cabin pressure drops below _.0 + .2 psia,- .i

....... "_ "I"i #i I

PAGE,

REPORT

MODEL

3-44

SEDR 104

133

_ST,,LC_U_S, M_SSOURI

- qlmJ_.Jl_lli Ii._tJl_l i IX-_t.,.

DATE

REVISED ,

REVISED

1 NOVEMBER 1961

TANK

I

F IGURF. '3-16 CAPSULE WkTE.P, T_NK_M 4-5- Z58

CC.;r;GF_J_i J IAL

3-4_5


REVISED _ MODEL, 133

CABIN PRESSURE CONTROLVALVE

SPRING - LOA£)EDPOPPET

FIGURE 3-17 CABIN 9RESSURE CONTROL. VALVE pM4s-158 A

_vl111 II,,,,/bl"ll i I.r'l.l,,,,_

REPORT Sg'DR 10_ REVISEDST. LOUIS, MISSOURI

MODEL. 133 REVISED

the aneroids fully expand and seat against the inlet port. This prevents oxTgen

flow, through the cabin pressure control valve, and reserves the remaining o_ger

supply for the suit circuit. Two aneroids are provided in the valve to insure

operation in the event that one aneroid fails. A manual control is also pro-

vided to enable cabin repressurlzation in the event cabin depressurization was

manually selected. Actuation of the REPRESS "T" handle, in the cabin, offaeats

a spring loaded poppet in the valve and allows oxygen to flow directly into the

cabin. REPRESS "T" handle should then be pushed in, followin E cabin repressuri-

zation, to enable cabin pressure control valve automatic operation.

3-26. CABIN PRESSURE RELIEY VALVE

The cabin pressure relief valve, Figure 3-18, automatically controls cabin

pressure relative to ambient pressure durin 6 launch, orbit, re-entry and landing

phases. In the event of a water landin6, the valve incorporates provisions to

keep water from entering the cabin. The valve also features means for manually

deconpressing the cabin. The cabin pressure relief valve consists of a cali-

brated spring control section and e. poppet valve control section. The calibrated

spring control section incorporates ambient and cabin seusing chambers separated

by a sensing dtaphra_, spring loaded metering valves and calibrated sprin6s.

The poppet valve control chamber incorporates a manual control am, a check

valve, poppet stem orifices, spring loaded poppet valves, poppet chamber

diap_ and poppet chambers.

After the cabin pur_m 6 operation, cabin pressure will be the same as the

existing ambient pressure. During launch, as ambient pressure begins to de-

crease, the cabin pressure relief valve will relieve cabin pressure until the

pressure differential (cabin/ambient) reaches 5-5 psia. The cabin pressure

relief valve will then prevent cabin pressure build up in excess of 5-5 ps:l.a

• ._::/


REVISED

REVISED

McDONNELL__ __ST.LOUIS, MISSOURI

PAGE 3-47

REPORT .............. SEDR 104

MODEL 133

• /

CABIN P_F-SSU_E _F.L_EFVALVE

l I

f..' - '.N C

F_'Y_" //////////////__V///////////////px/ _'_""--------cH,_B_R"CABIN . _ _ '_. _ _" _ _MANUALDIAI:_RA_M / I_1 21_1 I _ I _ , Y_I _ _CoNTROL"CHAMBER'-'_- _._ - L_I I _ ' I r_l I M _ _RM

_EEP_F0"_ _,_ o_PFPI_Z STEM

CAISIH . F/J I_I' Y//J ,_/_" '11 _ _ _""---CHECKVALVE

- . _-_'_'/_ _ ________._ __ __ CABIN.

F_C)PPET _ _ _'- POPPET

_'_ ......._2_ ,;_:/_........................v,_v_FIGURE _-i8 CABIN P_ES_J_E ._ELIEF VALVE

t_'_Jlt_lllt. Jlllllltllllil|llllll i •

_111_ "II1_ l ]1 l I II/ i111 | I I J--'_ IIII

PM45- _

PAGE

REPORT

MODEL.

McDONNELL z_T_R 104 REVISED

ST. LOUIS, MISSOURI

throughout the orbit, re-entry and landing phases. Cabin pressure will be

vented, through the poppet stem orifices, into the poppet valve chamber. Cabin

pressure will also be vented, through the cabin air filters, into the cabin

sensing chamber. Ambient pressure will be vented, via the ambient port, into

the ambient sensing chamber. The calibrated springs are designed to respond to

differential pressures in excess of approximately 5.5 psi (cabin/ambient). When

the pressure differential between the cabin sensing chamber and ambient sensing

chamber exceeds approximately 5-5 psla (cabin/amblent), the calibrated springs

will retract. The metering valves will then be lifted from their seats, allowing

differential pressures in excess of 5.5 psia to escape through the ambient port.

Due to the ambient port being larger than the poppet stem orifices, the dissipa-

tion rate of the excessive differential cabin pressure (inside the poppet valve

chambers) will exceed the rate of buildup in the poppet valve chambers. This

will momentarily cause the cabin pressure to be greater than the poppet valve

chamber pressure. The greater cabin pressure _-ill act against the cabin dia-

phragm, unseating the poppet valves. The poppet valves will then aid in the

relieving of excessive differential pressure. If the Astronaut executes a manual

decompression of the cabin, the check valve acts as an exhaust for poppet valve

chamber pressure.

During orbit, the cabin pressure relief valve will prevent cabin pressure

buildup in excess of approximately 5.5 psia. Cabin pressure in excess of

approximately 5-5 psia will be exhausted to the outside atmosphere. Upon re-

entry, when the ambient pressure becomes 15 inches of water greater than cabin

pressure, the poppet valves will commence to open allowing ambient pressure to

enter the cabin. Valve relieving operations will then be similar to those dur-

ing launch. In the event the capsule makes a water landing, the poppet valves

will not open until water pressure exceeds cabin pressure by 15 inches of water.

.,j

• k.,IV_.'t,l. Jl. Jl.Jrl:,{'l-_'_l.''_._-_ -

REVISED ST.''f ------_- ---7"-_LOUIS 3, MISSOURI REPORT _..DR 10_

REV,S_O -" _ " ..... Moo_ 133

/

A manual control located on the left hand console and marked "PRESS MEG" manually

closes the poppet valves to prevent water frQm entering the cabin through the

valve.

3-27. SNORKEL AND DIAPHRAGM FLAPPER VALVES

The cabin inlet air snorkel valve and the cabin outflow diaphragm flapper

valve act as water check type valves. During the landing and post landing phases

(often reaching a pressure altitude of approximately 17,0OO ft.) ambient air is

circulated through the valves. In the event the valve parts were under water,

the valves would seat and prevent water from entering the cabin.

3-28. CABIN AIR INLET VALVE

The cabin air inlet valve, Figure 3-19, provides ventilation and cooling

for the suit circuit and cabin during capsule landing and post landing phases.

It is a spring loaded close, spoon type valve and is barometrically controlled.

Prior to capsule launch, the valve is manually latched closed so that one

mechanism spring loaded detent pin rides on the large diameter of the aneroid

plunger (maximum allowable pull to set detent pin is five (5) pounds); and the

valve arm is engaged by the release link, which is engaged by the spring loaded

aneroid locking pin. During capsule launch the aneroid expands due to decreasing

cabin pressure, and forces the aneroid plunger down. The valve mechanism detent

pin then slips off the plunger large diameter onto the plunger small diameter.

During capsule landing phase, when the capsule descends to an altitude

of approximately 17,000 +. 3,000 feet, the aneroid retracts as cabin pressure

increases. Retraction of the aneroid moves the aneroid plunger upward, engaging

the detent pin against the plunger larger diameter, which in turn compresses

the aneroid locking pin spring. This action raises the locking pin from release

llnk and allows spring loaded valve to open. The valve arm is attached to valve

PAGE

REPORT

MODEL.

3-50 MCDONNELL '_ _//_ DATE,, 1 NOVEMBER 1961

ST.LOUIS. MISSOURI REVISED

REVISED

SEDR 104

i33-- vv • |w

EIC-I.URE _>r:19 _CABIIq AIR INLET VALVE

CC;;.;GZN, _A,'PM 4.5-/$4 I_,

:.Z.Y

o mber Mc,DONNE , , 3-51REVISED ST. LOUIS 3, MISSOURI Rli_OR'i" _-_)R 10)4

REVISED . t-' MODEL 133

shaft and moves with closing, thereby disengaging micro-switches. Disengagement

of micro-switches directs electrical power to stop cabin fan operation and close

the suit circuit shutoff valve, which in turn opens the emergency oxygen rate

valve. A manual control arm is provided to enable valve opening in the event

valve failed to open at specified altitude. Actuation of the manual control arm,

mechanically, contacts the locking pin spring and disengages locking pin from

release link, allowing valve to open. In the event of a capsule low altitude

abort, an explosive squib will force the locking pin up, to enable valve opening.

Valve must be manually reset to close position. Opening of the valve enables

suit ccmpressor to draw ambient air into suit circuit to provide suit circuit

and cabin ventilation.

The cabin air outlet valve is basically of the same construction and

functions in the same manner as the cabin air inlet valve.

3-29. VACUUM RELIEF VALVE

The vacuum relief valve, Figure 3-20, is designed to open at a pressure

differential of lO to 15 inches of water, to provide suit circuit ventilation

whenever the inlet snorkel valve closes (ball float seats). The relief valve is

located in the flexible ducting, between the cabin air inlet valve and the suit

circuit inlet duct. In the event the capsule submerges momentarily, following

a water landing, the snorkel valves ball floats will seat (close) and prevent

water from entering into the suit circuit and cabin. The operation of the suit

circuit compressor and the closed air inlet snorkel valve will create a vacuum

in the suit circuit air inlet duct (flexible ducting). When cabin pressure

exceeds the flex duct pressure, by lO - 15 inches of water, the vacuum relief

valve will open. As the valve opens, cabin pressure acting on the valve poppet

surface will be great enough to hold the valve open until the pressure differ-

ential (between cabin and duct) is approximately 2 inches of water or less. Suit

via .u Ita,,Ji-..INI I l_b'IL t-.-*

PAGE

REPORT

MODEL

_'_ Mc'DONNE_ C__ DATESEDR 104 ST.LOUIS, MISSOURI REVISED

133 C,_T_-_ i _ I,,_,,__[_ REVISED

1 NOVEMBER 1961

VACUUM RELIEF" VAL'_..

F SEAL

5_ama-x 8 /

TO C_BINA_N _NLET'VA L'4 £

'_OU NT _½G _OLT

AnD %PP_C_._

VALX/E

DUCTi_ / m-FLEX, BL_

| I r---%_%,_

L J _ CIRCUIT

FIGURE 3-20 _/ACUUM RELIEF VAWE

AA _ I =

mATE 1 November 1961

REVISED

REVISED,

ST. LOUIS a, MISSOURI REPORT SE_R 10_

MOOEL 133

circuit ventilation is provided by the cabin air, entering the opened vacuum reli_f

valve, whenever the inlet snorkel valve ball float is seated (closed). Also, the

opening of the relief valve removes the vacuum in the flex duct to enable the

snorkel valve ball float to unseat (open) whenever the snorkel valve is above

water.

3-30. TEST CONFIGURATION CAPSIK_S


Capsule 8 environmental control system differs from the specification

capsule in the following manner.

Capsule 8 environmental control system is the same as Capsule 2 and 3

except for the following: Capsule 8 will incorporate a cabin 02 pressure warn-

ing light but this warning light will not be supplemented with a tone generator

circuit. There is no indicating system to reflect 02 emergency operation.

Capsule 8 will incorporate a circulation fan to aid in cooling the special

instrumentation package. The air inlet and outlet valves open at 17,000 .+

3,000 feet. The air outlet valve is the ssme as Capsule 2 and 3. Capsule 8

does not contain heat exchangers to cool the main and standby inverters, nor

does it contain manual provisions for closing the cabin pressure relief valve

poppet valves.

3-32. TEST CONFIGURATION CAPSULES NO. 9, !0 AND 13

Capsules 9, I0 and 13 environmental control systems are basically the same

as the specification capsule except as follows: Capsule 9 solids trap is

designed for a primate; it does not contain heat exchangers to cool the main

and standby inverters; the water separator is deactivated; and the water tank

is not utilized as a source of drinking water for the Astronaut. Capsule 9

suit circuit does not incorporate a suit 02 partial pressure system; and the

-__D;.F;D=;4T;AL

PAGE , 3-5_

REPORT SEDR 104

MODEL_ 133

Mc,DONNELL __ DATE 1 November l_lREVISED

._T..Aou!s,. MmSOUm-_v,, ..... _ REVISED

suit circuit does not incorporate a constant bleed oxygen system.


Capsule 16 environmental control system is basically the same as the

specification capsule.

4-1

SECTION IV

STABILIZATION CONTROLSYSTEMS

TABLE OF CONTENTS

/, ,.

i I¸ i),.;'j'

TITLE PAGEIII ii

AUTOMATIC STABILIZATIONCONTROL SYSTEM

SYSTEM DESCRIPTION ....................... 4-- 3

SYSTEM OPERATION .......................... 4-12

SYSTEM UNITS .................................. 4-19

RATE STABILIZATIONCONTROL SYSTEM

SYSTEM DESCRIPTION ...................... 4"-24SYSTEM OPERATION ......................... 4-25SYSTEM UNITS .................................. 4-25

REACTION CONTROL SYSTEM

SYSTEM DESCRIPTION ...................... 4-2'7

SYSTEM OPERATION ........................ 4-29

SYSTEM UNITS ................................. 4-36

HORIZON SCANNER SYSTEM

SYSTEM DESCRIPTION ...................... 4-40

SYSTEM OPERATION ........................ 4- 41

TEST CONFIGURATION CAPSULES ........ 4-55

'_Vlll IlJl_i| I IPI_I,,

'm

c:

.u}

(j,....<

.--.i

cA

ID,ROLL RkTE TR_.NSbUCER

I])VEI2TICALs

IDYAW RATE TRJ

/ //

/

/iI

I

//

/

\

GYRO _,,.

R_°,_ POTENTIOMETEI_[I_OLL') '

_yscs,_W) SCS PO'TENTION_ETF.R

_ITCH)

\,

PITCH RATE TRA_SbUCER<I}

YAW RATE GYRO(i]

PITCH RATE GyRO<ZI

-CALIBRATOR <]]

NOTE5

A$CS CON_ PONENT

RSC5 AND TELEI',_ET_,YCOlViPON ENT

RSCS RATE-DAMgER BOX HORIZON SCANNER (PITCH)

/

[ ;_ "0) I!1 >

m11

-t

4_

in ITI ).

_ m

1

=Arm, I November i_61

REVISED,

REV'ISE:D ,

El'. LOUIS 3, MISSOURI

PAGE _"-3

Rli_PORT. _EDR 104

MOC,_L.....,133

z¸

IV. STABILIZATION CONTROL SYSTEMS

4-1. GENERAL

Stabilization of the capsule in space is accomplished by the Automatic

Stabilization Control System in conjunction with two sub-systems, the Horizon

Scanners and the Reaction Control System. These systems establish and maintain

a stable platform with four basic automatic modes; Damper, Orientation, Attitude

Hold and Re-entry. A redundant rate "back-up" system, the Rate Stabilization

Control System (RSCS), is also provided. The RSCS provides the Astronaut with

an emergency method of controlling the capsule with a "rate-stick" in the event

of a failure in the Automatic Stabilization Control System. In addition, a visual

indication of yaw, roll, and pitch attitude is provided. The following paragraphs

4-2 through 4'56 briefly describe the individual systems and functions involved

for the specification compliance capsule.

AUTOMATIC STABILIZATION CONTROL SYSTEM

SYSTEM DESCRIPTION

The Autcmatic Stabilization Control System (ASCS) is composed of a

Directional Gyro, Vertical Gyro, .05g accelercmeter switch, Rate Gyros (yaw,

roll and pitch), a rate damper, and an Amplifier Calibrator Unit. Location of

the individual components within the capsule is shown in Figure 4-i. Total

weight of the ASCS is approximately 59 pounds.

Three switches are provided in conjunction with the ASCS. The GYRO switch

AD_O/RATE COMD switch, and the NORM-AUX DAMP-FBW switch are located on the

Astronaut's left console. With the NORM-AUX DAMP-FBW switch in the NORMAL posi-

tion and the AUTO-RATE COMD switch in AUTO, stabilization is accomplished in a

completely automatic manner, requiring no assistance from the Astronaut. In the

FLY-BY-WIRE position, the automatic feature is disabled and 24 V d-c power is

_ ' _T r_ ,r, mll, j L ,i

REPORT SEDR 10_ ..... ST:..LOUI$,.. MISSOURI REVISED

MODEL. 13_3 f,_ __n_____.4 REVISED

connected to the Fly-By-Wire limit switches on the Astronaut's control stick.

In this position stabilization is accomplished through an electro-mechanical

arrangement (See Figure 4-9) by movement of the Astronaut's control stick in the

desired plane. Low and high thrust actuation occur at approximately 30% and 75%

of full travel, i.e., 3.9 ° and 9.8 ° for yaw, pitch, or roll. The AUX DAMP posi-

tion disables both the automatic and fly-by-wire function, permitting rate

damping as a singular feature. The GYRO switch is a three position switch in-

corporating a CAGE, FREE, and NORMAL position. In the CAGE position the Attitude

gyros are mechanically caged and the Horizon Scanner slaving function is dis-

abled. In the FREE position theAttitude gyros are uncaged; the Horizon Scanner

slaving function remains disabled. The NORMAL positlon uncages the attitude

gyros and permits Horizon Scanner slaving. The AUT0/RATE COMD switch provides

a method of energizing either the RSCS or ASCS systems as desired. In the RATE

COMD position, the attitude gyros and slaving circuits remain energized although

they are not used to control the capsule. (See Figure 4-12. )

4-4. ASCS Sequencing

The following paragraphs, 4-5 and 4-9, describe the ASCS sequential opera-

tion under normal and abort conditions. Figures 4-2, 4-3 and 4-4 are provided

for clarity and should be followed closely in conjunction with the text concern-

Lug the various modes of operation.

4-5. Normal Sequencing

In Figure 4-2, the progress of a normal orbital mission is shown divided

into eight phases appropriate to the following discussion.

The ASCS is in the "ready" status prior to separation of the escape tower,

its gyros are running and all circuits except the final 12 output relays are

fully energized. RSCS operation is prevented by the AUTO/RAT_ COMD switch being

in the AUTO position. Phase (A), involving gyro slaving to the Horizon Scanner

CCr 2IDZ L

0

I-I_ ,,,J

_ o _< w Co. n,

0

Z

r_._

Z

Q Qhi ILl

I-

Q e¢ e¢

ii

I_11N3-]_9NIWrI(](]NOO3__]d .Zl 01.01 -10::llV_t710_!(]NVONId_VO_11'_tH

_EO"711Nn JGnlllIV 1_1N3-]_(]IOH 9

3al.40_l13tl9Nlari(]3(]nllllV 0_13_ <37o1-13

NOIlY_3_O _3N_35 1N_ISN03 G_V 3GO_ II_0 ]

3_flII11_ 0_i3_ 01 NOIiViO_ _NV 3QOV_NOIi_IN]I_O "D

_3NNV3g NOZl_OR01 SO_XOHDlld ON_ 7]0_ ]ARTS "V

_ NOIL_YOl_, _IS_ IO_LNO3NOII_ZHI_ISOIIY_OI_V

*"+-"-__.,c.+_/_:++L

i I/

.......... 2i ....'II_I0

+o5ILl

_I

,,.v0Z

l",,,,l

l.l.l

j ',(

f

/ ++I

I

+..

. ! i i ,. /"

6

REPORT, _DR 104

M ,DONNELL REVISED

ST. LOUIS, MiSSOURi

MODEL- 1,_3 ""_ _'"_: _, ..__._' _""._ REVISED_ _;""_2_2J" J, _l " " _ _ rr_ ,

pitch and roll outputs during ascent s is to minimize _o errors which may

accumulate while the capsule is being boosted.

Phase (B) starts after capsule separation when a brief, flve-second signal

commands the ASCS to provide rate damping to stop any tendency to tumble.

Phase (C) is initiated at the completion of five seconds of rate damping.

The ASCS is placed in the orientation mode, capsule turn around (180 ° counter-

clockwise Yaw Rotation) is accomplished, and the capsule is pitched-down to the

retrograde firing angle within 30 seconds. Pitch, roll and yaw gyro slaving to

the Horizon Scanners is provided during phase (C) and for the first 4_ minutes

of phase (D) to yield a good yaw-angle reference prior to settling down in orbit.

In phase (D) the capsule is in orbit. An orbit pitch attitude of -34 °

(small end down) is held so that the capsule is ready for an immediate abort.

The attitude gyros are slaved to the Horizon Scanner at a cycle of 8.5 minutes

on, 9-1.5 minutes off, throughout phase (D). During the orbit phase manual con-

trol and fly-by-wlre control may be utilized as desired. Rate damping becomes

optional under manual control conditions by positioning of the ASCS MDDE SELECT

switches and RCS controls. By switch manipulation, rate damping is provided by

either the ASCS or RSCS. See Paragraph 4-3. Rate gyro run-up is continued

throughout phase (D). Another feature utilized in Phase (D) is an automatic

return to the orientation mode. If the capsule drifts (from orbit attitude)

beyond the limits of the retro-interlock sector switches, automatic return to

orientation mode will occur at + 12° pitch, + 30° yaw and roll. The Astronaut

can also place the ASCS back in the orientation mode by manipulation of the

AUTO/RATE COMD switch.

In phase (E) of Figure 4-2, rate gyro run-up is automatically assured by

relay switching lO minutes prior to retrograde attitude. Horizon Scanner slaving

operation becomes constant at this time to obtain a good reference prior to

_, o

ILl

I.-I1 ..,J

ld i1_o c_I11 C

n n, _I

.I

o(/)

,,=,

o8.:I,

,,, _ __I-., > >< Id Iii0 0_ n,

,._o"ld'=t0:JIA,DNWV',I

t

"I_o_ _ _<Inli..u.y

L

(]NVI_NO3 3dOINllg_10 $ 301_1.tA0

GIOH=JOt'llI.LJ._ O_ll]_J

(2-vm_-_'_) S_VNd NOI C_SI_

k _,_aU l u_-" V -.,---i-,

N O I/_ "Zl_l d'O S rJorl NJ.LNO:) .LN-]::_¥-")NI21ha NO A'HVI£1NI

- _100'3 ISV'3

(3_40"Nt_ _'IZ' NO'HIll _'9)S)100] :)lq01_3d

H3ild o_, _-o'l,_-'L (]-IOH 3O_±IIJ.V £1gElO_vA 3' qqo_l o_ _ =o J

H31 Id '__Vk 110_

#'ONWWHO3 3001_llC_O S3(]1_13^0

,,,. X___________,

'3

C_qNO33SS-_ --

dn:Nn_l9_1

8]_V3SNOZI_IOH01 :_AV1S

"OlnV

:_ cj-,.'.L.

llg_lo

0U13_

_]d_VO

0

E

E

g

m

t_

.o

N

t_

£

J

Ix.0

"7 _ _

9If)

!

tD

la_

//

REPORT SEDR 104 ....... ST. LOUIS, MISSOURi REVISED

MODEL 133 ....... ' REVISED

achieving retro-attitude. The Astronaut may change any one or all three of the

capsule attitudes maintained by the ASCS by changing the space reference plane

or planes of the attitude gyros. To maintain the new reference plane or planes,

the Horizon Scanner slaving cc_mand must be stopped by placing the gyro switch

in the Free position. New reference planes may be established by the Astronaut

while the ASCS is in operation by placing the gyro switch in the Free position,

manually turning off the ASCS fuel in the axis or axes affected, utilizing

manual control to position the capsulej and then caging and uncaglng the gyros.

The ASCS may then be returned to fully automatic operation in all three axes

with the exception of Horizon Scanner slaving. To utilize Horizon Scanner slav-

ing, the capsule attitudes must be within the observation range of the scanners

and the gyro switch must be placed in the Normal position.

The ASCS receives Tr signal and maintains capsule in high torque retro-

grade attitude (phase F). Horizon Scanner slaving is discontinued at this time.

Thirty seconds after retrograde attitude command, the retro rockets are fired.

During the period of retrograde rocket firing the ASCS utilizes h_gh torque

action to hold the capsule within one degree of the ideal angles. Retrograde

rocket firing command and ASCS high torque switching command occur simultaneously

Rocket firing is completed in 20 seconds and the high torque switching command is

held for 23 seconds.

Upon completion of retro package Jettison, the ASCS automatically pitches

the capsule to the post-retro fire attitude (phase G) in preparation for re-

entry drag. The ASCS returns to orientation mode with constant scanner operation

to accurately maintain the re-entry attitude.

Finally, when re-entry is sensed by the .05g accelerometer switch, the

eighth and last phase (H) of the ASCS performance starts with the turning off

of the attitude gyro power. During this period the ASCS initiates and maintains

REVISED ST. LOUIS 3. MISSOURI REPORT,,,,I., _F_R 104

.Ev,s_o _ MOrnS. ,,, 133

r'

a constant roll rate of i0*%o 12° pe_ second to minimize touchdown dispersion.

Rate damping is provided to stabilize the re-entry trajectory. ASCS operation

in this phase continues until main chute deployment, at which time all ASCS

power is removed.

Pilot-overrlde provisions permit interruptions of the preceding "normal"

sequence by manual, fly-by-wlre or RSCS stick-steering control manipulation and.

return to the "normal" ASCS MODE. Thus to a significant degree the Astronaut is

the intelligent "back-up" for the ASCS, Full utilization of this reliability

augmentation principle has led to gyro caging and other switching features which

are intended to make the capsule manually controllable. The following table

lists the switch and control positions necessary to achieve the four basic modes

of control after attaining orbit. Variations of the various modes can be

obtained by further switch manipulation. A more detailed discussion of the con=

trol modes available is contained in SEDR 109, Capsule Flight Operations M_nual.

RCS "T" HAttDLE POSITIONSWITCH POSITION

CONTROL MSEE Auto/Rate Cored Norm-Aux Damp-FBW Auto Fuel M_nual Fuel

sys. Sys.

AUTOMATIC AUTO NORMAL PUSH ON RATE COMD

FLY BY WIRE AUTO FLY BY WIRE PUSH ON RATE COMD

RATE-STICK RATE COMD NORMAL PULL OFF RATE COMD

DIRECT AUTO AUX. DAMP PUSH ON DIRECT(With Rate

4.6. Abort Sequencing

In general, abort sequencing (See Figure 4-4) is programmed to correspond

to the safest procedures at all times. The possible abort situations can be

divided into three types, namely (I) abort, before tower separation when ASCS

rate damping is required; (2) abort after tower separation but before the

trajectory is truly orbital; and (3) abort fr_a orbit. The following paragraphs,

¥'_-, .a il./r--i_l | I/_i. -

Mc,DONNELL

REPORT $EDR 104 ST.LOUIS. MISSOURI REVISED

MODEL 133 --_ _'_ _ _ e._i.._P" _ T _J-'_" REVISED

1 NOVEMBER 1961

FIGU_E4-¢ .ASCS EMEI_GENCY OPEI2/kTION DI44_" 39£

_llP v i _ll Illi#

i¸, :

ST. LOUIS 3. MISSOURI

DATE 1 N_z_bel 4 1_1 PAGE_ 4-11

REVmED R_oxr SEDR 104

RSV,SED _ eOO_ 133

4-7 through 4-9_ dlscuss _CS sequencing in each of the abort conditions.

4-7. Abort Before Tower Separation

If an abort mission Is started durln 6 the perto_ when the booster and sus-

talner eng/nes are burnlngj the ASCS Is utilized for rate damping only after the

following external operations have been achieved.

(1) Booster and sustainer engines cut-off.

(2) Capsule separation from adapter.

(3) Escape tower rocket firing.

(4) Retro rocket separation from capsule.

(5) Timed arrival at approximate peak of trajectory.

(6) Separation of escape tower from capsule.

Upon completion of the latter operation, the ASCS is coezuu_led to provide rate

dampinS, using the rate gyros which are continuously energized dur'l]_g the normal

ascent and "abort trajectory" flight. A constant roll rate of 10 ° to 12 ° per

second is employed. Rate dsmping ceases upon deployment of the main chute.

4-8. Abort After Tower Separation

The flrst operation is engine cut-ofT. This is followed immediately by

capsule separatlon_ posl_de firing, and the normal mission post-separation

signal sequence tO the ASCS. The effect Is i_nedlate dsmplng of any capsule

tendency to tumble. After 5 seconds of rate damping, the automatic sequence

co,ands capsule turn around an an attitude angle of 34 degrees. Then either

the Astronaut or Ground Command must initiate retrograde sequencing. Upon

achievSug the proper roll_ pitch and yaw an61es within rather wide "permission"

bounds (See _ph _-Sj Page 4-6)_ the ASCS enables rapid-sequence retro

rocket _ to proceed.

NOTE

ASCS "permission interlock" during retro flre can be over-

i

PAGE _-12

REPORT _. _R _0_

MODEL. 1_

McIDONN_ _4_ DATE ! __ovember l_lREVISED

.....Slr. LOUIS, MISSOURI

_---'_--JCI_T 1C_TT_ ]_ REVISED

ridden at any time by the Astronaut. It is also noted that

the Astronaut may switch to the Rate Stabilization Control

System at any time should a malfunction occur in the Automatic

Stabilization Control System.

After retrograde operation, the abort mission in this case proceeds as in the

normal mission post-retrograde sequence (except for the difference in trajectory

time and distance intervals).

4-9. Abort From Orbit

Whenever an abort from orbit is initiated, the normal automatic or manual

retrograde operations will apply. However, if manual retrograde operations are

utilized the pre-retrograde period of gyro slaving to the Horizon Scanners

("last look") will be eliminated.

4-10. SYSTEM OPERATION

Overall system operation is best explained by Figure 4-5. The Amplifier

Calibrator receives inputs from sensors on the left side of the page and generate

outputs to Display sad Reaction Control devices on the right. The four basic

operations are slaving, repeating, mode switching and torque switching. Data

flow pertaining to the individual Yaw, Roll and Pitch channels is illustrated

in Figures _-6, 4-7 sad 4-8. In general, these diagrams are straightforward

and require no explanation. However, the method utilized in deriving Directional

information is unique to a degree and warrants the following discussion.

The Pitch gimbal (vertical gyro) is processed continuously during the

orbital phase of the normal mission, so that the capsule "local vertical "_

reference revolves 360 degrees during each orbital cycle. The gyro slaving

principles which permit Directional (yaw) information to be derived are as

follows: After initial slaving and settling of the roll sad pitch loops, the

IL._VZ'I i' AU..I_.L_t • JLzeLJLJ

', _j" /

-q

6_C

rn

4:=

L.

cnt_Ln

EDF-0

7_

E_i

j>o_

#,

SENSORS AND.COMMANDS

HORIZON

SCANNER

•ROLL"

IIORIZOH

3CANNER

"PITCH"

"IGNORE" ROLL AND/OR PITCH COMMANDS

CALlBRATOR

MODE

,SWITCHING

! lil ,RATE GYRO cEYAW

RATE GYRO J

p,T_ I_I l

RATE G,YRO cE

ROLL

TORQUE

SWITCHING

DISPLAY' AND RESPONSE

(_-c)

)-¢)

r- ..........I

_IRoL,I

I_i ,,,wI_L_ .......

ATTITUDE DISPL_-Y---

_ PACKAGE "B"

YAW

YA_

I

I ROLL _

I ROLLPITCH

IJ PITCH

HzOtFUEL

HIGH fiElDLOW 14Ee;_TiVETORQUE CHRI,,ABER5 SHOWNFOR YAW RY.i3 ARE TYPIpo._iTIV£ TORQUE _,kl'DROLL ¢ "PITCH P,_E3 #li2.E3IMILRR.

g g _

0C

m0

"oIll >

m

4

I I_AA,STEI_ E] I,<_EQ_JE.t-aC.E._

DEVICES

EC_ E.L E [20MErE _.SWlTC_ !

71

CK]ill

d_

0

xOr)

OJr"0C)

[3}>

°1%

t°!DrT-cI.4 _C

_Y_aoS

PITCHTORQUE

SW)TCHIN_LOgiC ANb

OUTPUTRELA_(S

_I"T'CH

_ORI"ZON <]3SC/_NNER

"lr_ORt" P_'rc_ S_G.----- 1 !

,,_ . ,--_IIL._, I _ pow_

L-E_N¢3

II

,,j

E> NOT PART 09" A$CS

!I 'I I

I

I

I

"7 FIRST PITCH lREPE#,TERI

• J p,,=_ I

l _T,_,_s_-ro,_I

;o -om >

10-i

0

i

m m :><: < .-I

$

DATE

REVISED

REVISED

1 NOVEMBER 1961 Mc,I)ONNE_LLj_.___ PA_EST.LOUIS, MISSOURI REPORT

= : MODEL

4-15

SEDR 104

133

i _

'° iT

_u_

og

T

iii i

_dO

"tit I

0

$0J

2

P

ge

6o

?

II

_ b---

oiJ

Jd J

t_

-Z_l

_1I

.-.-.1

FIGU__E 4-7 YAW AXIS BLOCK-.. IDIA, G_AM

IM

<)-

IJ

I

P

!

16

REPORT SEDR 104

MODEL 133

Mc'DONNEL.__.L_j_ C-_,,_,_ST.LOUIS, MISSOURI

DATE

REVISED

REVISED

1 NOVEMBER 1961

m

IIIC_

u_

Q_IL

P

P

I.J,,¢

_z

oc

o

:i

I

o_

FL1I

t

:2d

,_I°_I

BLOCK DI A&I2A M

___ _A

..... ;C,_";4

/

R_xsEo st. Louis s, Mmsoumx ms_oRv SEDR 104

._,sEo_ Mo_.. ..... 133

_SCS controls the capsule to the command pitch attitude, and to level roll

attitude. Initially, after separation and capsule turn-around, some yaw error

(as great as I0 degrees) may exist due to directional drift during boost. Since

the Roll gimbal of the vertical gyro is the inner gimbal, yaw misalignment of

the capsule causes the Roll glmbal output to contain an error component due to

the constant orbital _itch) angular rate. Thus a comparison of the Roll Horizon

Scanner and vertical gyro roll indications will provide an error signal producing

a roll gimbal torquing rate. This torquing rate which is a direct function of

yaw error is used to slave the yaw gimbal of the directional gyro.

Another area that warrants discussion is that of torque switching, i.e.,

the thrust output of the Reaction Control System in conjunction with the various

modes of ASCS operation.

Figure _-i0 serves as an introduction to the torque switching behavior of

the ASCS. For maximum conservation of control fuel, the behavior varies accord-

Ing to the ASCS mode appropriate at a given time. A so-called "phase-plane" plot

of angular rate vs. angle is shown in the lower right corner of Figure 4-i0

adjacent to a typical Pitch time-history for the "Orbit" mode. Current ASCS

design permits a plus or minus three degree oscillation about the nominal orbital

attitude, which in turn is referenced to the Horizon Scanner's sensed "Horizontal".

The oscillation is non-simusoidal because of the discontinuous torque program;

pitch rate is a square wave, and pitch angle a sawtooth, both having a

characteristic period of 240 seconds. Portrayed on the Phase-plane, the "Orbit"

mode oscillation is a gentle drift from -3 degrees relative pitch angle to +3

degrees relative pitch (-S_ to -Sl ° degrees, referenced to true horizontal).

This drift lasts for approximately one-half-period of two minutes. When the

error becomes +S degrees, a low torque pulse causes the angular rate to reverse

from _2 to _ deg/sec., where upon the second half-period is spent drifting

_" -_|r'%r"lh .m. - -

PAGE

REPORT ....

MODEL

4-18!

SEDR 104

133

Mc'DONNELLL ' .,_J,_.U IS_, MISSOURI

DATE , 1NOVEMBER1961

REVISED

REVISED , ,

,SCS AMP- CAL

O_TPUT RELAYS L

i _

FIGUI2E 4-9 ASCS

//

//

//

NOTESONLY THE YAW MICRO SWI"T'CH_

AND ASSOCIATED CIRCUITRY'

A_E _i40WN, _0LL AN{:) PITCHARE _I_ILA_

[E)_V_/ITCHE_ SktO'cc'N IN %"riCKNEUTRAL POSiTiON LOWTORQUE 5WITCHES CLO_EFIRST

[_ RELAYS ,DE- ENERGIZED I kl

P_W F_OC_l"riON

" UST

CHAMBER GYP.')

FLY-BY- WII2E CONTI_'OL PH,HS-_o_

OAT_ I NoVember I C_l

REVISED.

ST. L,OUIS 3. MISSOURI RE:PORT_ ,,,_--'_[ 104"

Moo=, 133elMmem_,_, ,,,

slowly through zero to -3 degrees error.

As another example of ASCS torque-switching, Figure 4-10 shows the

"Retrograde-Hold" torque logic phase-plane diagram. In this case high-torque

nozzles are utilized instead of the low-torque nozzles which were adequate to

control the gentle orbit oscillation. A series of attitude gyro repeater sector

switches and rate-gyro pickoff sector switches are used to define step-like

boundaries within the phase-plane. A typical contour is shown to illustrate the

motion resulting from a large disturbance torque while in this mode. When the

capsule motion results in a pitch rate value above the right-hand stair step_

high negative torque is applied until the capsule attains a negative rate and

rotates into the "no-torque" region. The inverse occurs if the retro-rocket

thrust eccentricity or other disturbances force the capsule into a situation

calling for positive thrust. The net effect of the torque-switching logic shown

is to maintain rapid and reliable control during the important operation of

retrograde firing.

Other modes of operation requiring torque switching logic are "Orientation"

and "Rate Damper". During orientation mode both high and low torquing is uti-

lized to rotate the capsule to new preset attitudes. Both high and low torque

is also applied during rate damper mode but only rate gyro signals are needed

as a basis for switching logic. In this case 3 torque switching boundaries are

horizontal lines on the phase-plane.

_-Ii. SYSTEM UNITS

_-12. Amplifier Calibrator

The Amplifier Calibrator unit can be "functionally" divided into four

sections. These functional sections are slaving, repeating, mode switching

and torque switching.

PAG E .

REPORT

MODEl.

4-20

SEDR 104

133

/oMCDONNELL___d# _,_

ST.LOUiS, MISSOURI

¢" ¢"__.i_ I_-_,r..L.,-,-,__L..,--

DATE ,

REVISED

REVISED

1 NOVEMBER 1961

I0.0

(=,.0

• 2.0rJLLJO_

LLILLI

LLJ

c_

2.0

IO.O

I

_5.5 =I

......... _q .....

II

A e DEG#EES

-" I TYPICALT_MEH,_'roR'YC_rr_)-_

I +_ -_A

ORBIT(I_TCliA.,YISEXAMPLE')

DURIkTION

0.2.

0.1¢7

0.252

0.437

÷A *-£ 0.755

FIGUI_E 4-10 TO_'QUE L0454C PN/_SE PLANE

rv

+h

• 8 *C *.b

+l ° *;" *Y ,_,.°_,Z_*_.5" *"

pC .,,,..,.,,-..- ..-. -.PH4S- S_,,A

l ove ber l l, MqDONNELL -21RL-VlSEO s'r. Louis s, M1ssoum R_,OR_r _R _0_.

._v,s_ .... _ . Moo_. 133

•i_ -,

i

4-13. Attitude Gyro Slaving

This section contains amplifiers anm summing netvorks which accept roll

and pitch information from the Horizon Scanners and generate currents to torquers

in the attitude gyros. Thus, upon command frcm an external timing device, the

Gyros' Roll, Pitch and Yaw gimbals are aligned with corresponding directions in,

or perpendicular to the orbit plane. (Ref. Para. 4-10. )

_-l_. Repeater Section

The repeater section •is a group of servo-mechanlsms (four in present design,

including two for pitch angle repeating). Attitude gyro outputs, which are

received at the calibrator in proportional or "analog" form, are amplified and

used to drive shafts which serve as roll, pitch and yaw signal sources for both

internal (torque switching) and external (display and telemetry) purposes. The

on-off reaction control of the Mercury Capsule makes it desirable to use con-

ductlve sectors on the shafts of three of the repeaters. The sectors serve as

attltude-level references for torque switching.

4-15. Mode Switching Section

This section of the Calibrator establishes the proper attitude angle bias,

torque switching status, and interlock signals corresponding to the ASCS mode

commanded by external devices.

NOTE

The sum of all such external devices is, for ASCS design

purposes a 'Smaster sequencer" which coordinates all automatic

functions.

The mode-switching section uses compact, solid-state switching circuits. Al-

though these circuits contain many transistors, diodes, and other electrical

components, they are of a class that i8 not critically dependent upon reference

voltage or temperature levels.

_'/_ T_'T!DE;'T. :_

Mc,DONNELL zREPORT _DR lOLl. REVISED

ST. LOUIS, MISSOURIMODEL. !33 * ' _ REVISED

4-16. Torque Switching Section

The torque switching section contains transistor and diode circuits similar

to those in the mode-switchlng section. Torque switching circuits receive the

step-functlon outputs of the attitude gyro repeaters, plus the outputs of the

rate gyros. The latter (rate) signals come from sector switches replacing the

usual proportional rate gyro pickoffs. Using these step-wlse indications of

attitude and rate conditions, along with the mode switching section output defin-

ing the current phase of the mission, "decisions" are made which result in

energizing of the appropriate Reaction Control valves.

4-17. Accelerc_eter Switch

The acceleration switch is a hermetically sealed instrument. The basic

mechanism consists of a centrally located mass supported by a cantilever spring.

The mass is damped by the viscous shear action of the fluid which fills the case.

Switch actuation is caused by the displacement of the mass element. An Acceler-

ation force of .05g, in the axis normal to and in the direction away from the

base, is required to close the circuit. M._chanical stops are provided to re-

strain the mechanism and to protect against damage when subjected to excessive

acceleration.

_-18. Attitude G_ros

The function of the attitude gyros (vertical and directional) is to determinq

attitude augles between a set of fixed axes in the moving capsule and the refer-

ence ax_s which are fixed in the orbital plane but which are moving with the

local vertical. Both attitude gyros are "free" gyroscopes with slaving capabil-

ity. A means is incorporated for caging and for obtaining electrical signal

(synchros) outputs which define the attitude of the gyros with respect to two

mutually perpendicular axes. The attitude gyros possess unrestricted mechanical

freedom in the outer axis and + 83° (minimum) of mechanical freedom in the inner

REVISED. ST. LOUIS 3, MISSOURI REPORT. SF.LDR lO_

REVISED. MODEL lB3

!

_

axis. It is noted that the degree of gyro freedom does not necessarily reflect

the attitudes permissible by manually steering the capsule in orbit. Due to

limitations in the Horizon Scanner system and the repeater section of the

Amplifier Calibrator, manual control of the capsule should be limited to + 30°

in all axes. However, barring equipment malfunction, exceeding these limits

will not prejudice the success of a mission. If these limits are exceeded, it

is recommended that the gyro switch be placed in the FREE position. Input

power requirements are 115 volt 400 cps single phase (gyro motor), and 26 volt,

400 cps (synchro and torque motor).

4-19. Attitude and Rate Indicator

The Attitude and Rate Indicator is mounted on the upper portion of the Main

Instrument panel. The indicator provides visual indications of Capsule Rate and

Attitude in the Yaw, Pitch and Roll planes. The attitude indicators are driven

by the attitude gyro synchro outputs (through the Amplifier Calibrator). The

attitude indicators are calibrated to indicate capsule attitude within a range

of + 180 ° except for Yaw which shall indicate 0°, 80°, and 270 ° In a clockwise

direction. The rate portion of the indicator is driven by the miniature rate

transducers (See Para. 4-26) which also serve as sensing elements for the Rate

Stabilization Control System. The range of rate indication is O to + 6°/sec.

for all three indicators. The roll rate indicator has the additional capability

of being externally switched to a range of 0 to 15°/sec. in order to monitor

re-entry roll rate.

0

4-20. Rate Gyros

The rate gyros perform electrical circuit switching functions at specific

rates of angular velocity about an axis perpendicular to the base of each unit,

referred to as the "input axis". Rate gyros are used in the pitch, roll and

yaw m_es, respectively. Each rate gyro consists of a high speed rotor, mounted

u. 4 MC,DONNEL L . REPORT _DR lO_ REVISED

"_;ST. '_OUIs _ MI$SOURL,.

MODEL- l_ _u-',..=. ....... REVISED

in a gimbal ring, in such a manner that it is free to process about one axis

only (the output axis) which is perpendicular to the spin axis of the rotor.

The output signals are generated by the motion of wipers, attached to the gimbal

ring, moving across the contacts of sector switches. Input power requirements

are met by ll5 volts, _OO cps.

4-P_l. RATE STABILIZATION CONTROL SYSTEM

_-22. SYSTEM DESCRIPrION

The Rate Stabilization Control System provides an excellent alternate means

of capsule attitude control in the event of failure in the Automatic Stabiliza-

tion Control System. It has been shown by flight simulation studies of the manual

control problem that the Astronaut should, by utilizing the Rate Stabilization

Control System, be able to approximate retrograde attitude error performance of

the Automatic Stabilization Control System. In addition, the Rate Stabilization

Control System provides a completely redundant rate-damper and programmed roll

rate during re-entry.

The Rate Stabilization Control System consists of three miniature rate

gyros, three (signal pickup) potentiometers, three channels of electronics (rate

damper) contained in a 300 cubic inch box, one switch, and six solenoid control

valves, which utilize the manual reaction control fuel and thrust chambers.

Figure 4-1 shows the location of the major components within the capsule. Total

weight of the Rate Stabilization Control System is approximately 25 pounds.

Power requirements for the Rate Stabilization Control System are met by 24

volt d-c and ll5 volt, 400 cycle a-c. Power is connected directly to the rate

damper box through the AUTO/RATE COMD switch mounted on the left console. See

Figure 4-12.

REVISED. ST. LOUIS 3, MISSOURI REPORT SEDR 10_

REVISED. .... i MOOE.. _.33

4-23. SYST_q OPERATION

Figure 4-ii is a functional block d/agram of the Rate Stabilization Control

System. A typical channel is shown. In general, the Rate Stabilization Control

System provides the Astronaut with a redundant rate damping and "rate-stlck"

steering feature. The outputs of the rate transducers and the control stick

potentlomenters are combined in the summation networks. The summation net-

works compare the capsule,s angular rate errors and, if errors exceed preset

dea_-zomes, 2 de_sec in Roll and 3 de_sec in Pitch and Yaw, the appropriate

off-on corrective torque is commanded by energlzimg solenoid control valves in

the Mamua_ Reaction Control System. With the control stick at zero deflection

(Rate Stabilization Control System operational) an autcmatic three axis rate-

damper is achieved, including an automatic 7.7 + 2 de_sec constant roll rate

when re-entry is sensed. By manipulation of the control stick, steady-state

angular rate____sother than zero (approximately proportional to stick deflection)

may be attained if desired. This is in contrast to the proportional accelera-

tion (Torque) response which remains as an alternative in event of malfunction

in the Rate Stabilization Control System.

4-24. SYSTEM UNITS

4-25. Rate Damper Box

The rate damper box provides three channels of transistorized electronic

unit caaprlslng the rate-damper portion of the Rate Stabilization Control

System. Each channel contains a summation network, preamplifier and demodulator,

and two trigger circuits. The 5½ x 6 x 9 in. box weighs approximately seven

pounds and is mounted below an_ immediately aft of the control stick. The rate-

damper box mounts two AN type electrical connectors, one for GSE and one for

capsule lnterconnectlon. The dead band adjustments which are provided are a

2 de_sec to 4 deg/see in pitch and yaw axis and a 1.5 de_sec to 3 de_sec in

_,,,, ^ ,k, I--I 11_ Plk I"!" 1 A !

PAGE.

REPORT

MODEL

ST.LOUIS, MISSOURI .REVISED

REVISED

SEDR 104

133 'w.,_./l r ,L./'-:--;T_IInL

. _i_ _II l

II

T,,_ _-- #)))l_"i_ J i'

..... i

CONTROL STICK POTENTIOMETER I

CONTROL 5TtC'_ DEFLECTION FOP., l

_ATE _TICK" CAI_AIS_LI'rY. I I

TWO V/A'/ 5ELECTOR I_

I - --o_.oT_M_:.A.,CA,-CO.._CT,O.I "_-----#_I --_.oT_ _EcT_iCA_CO_._c_,oNI L°:_F- .... YP-_t_

' " ]IEEl> PITCH AND YAWCHANNELS ARE I I L E=_--J

ADJUSTED _'0R A DEAD ZONE J I 1 F _r

OF APPROgI@!ATELY3 OES./SEC. Jl l

...............SUMMATION

I__T_.J' ' ZI NETWORK I-I ...........I...............I _ l' 11[:J_l "-TI I I I F--q_'-F-:T'_°"'_L£.-. L---=L,_ , SUM5 INPUTS AN_LICON TRANSISTOR PRE.-AMP I 5WITCH I , ] --IIF

PLACES CAP'3ULE I COMPUTE'5 CAPSULE AND DEMoOuLAT(::_L, OE_DLIL.ATOR J I I I J %INCONSTANT ANGULAR RATE ERROR. OPERA't'E._ ONE. Of: THE. TWO ELECTRONIC TRAM,SI,STORIZED -,L lif "

7 ole/5_.¢. ROLL J OJT_PUT IF INPUT EXCEED- 5WITCHES, DEPENOIN_ UPON Tt._E POLAR- TRIGGER CI]_CU IT JTO 50LENOID !_RATE TO MINt,_I- I 5 i:¢LESET DEAD ZONE _F ITY OF THE ERROR 51GNAL INTO THE PI_0VIDE$ POSITIVE FONTROLVALVE,qZE TOL_CI-IOOWN AFPROX MATELY _- ,_ AMPL) FI ER.. ,$W!TCHIN& ACTION {¢-EETYPICA_...p',_E)ISPEASION. I °l'('/"'lC" _ OF 50LEMOID J CONFIGUgATION_ L

CONTROL VA,LVE 5

I

_'"-'m I RATE DAMPEI_ I_X (HONEYWELL BG 17/A-I) ........ I• _,,_,.vo.,u.j _ PR_._IMPACT

I A _LC_N

INSTIE_IJMF..MTPANEL IAuT° _ t

_ATE TRANSDUCEIQ _,_,YRo,,I::)I::_VIOE5 OUTPUT I::_:_)PORTIONALTO CAD.SLJLE. AN_ULAR RATE _,¢ORDISPLAY, R5C5 AND T_.LEMET_.Y.

__ _, IOW RELAY

\\\\\LEFT COk_SOLE_'. _'F _

I /ATTITUDE RATE INDICATOR :VPROVIDF,.S VISUAL DISPLAY 011:"C._Pc, ULP,.

ATT}TLtD_- AND AN_UI..A_ !:_ATF...

" F[t_Lr_E4L-ll _SCS IBLOCK OIA_RAM . _

_iNr aur" I_1 i I_L--

PM 4:5-. I_lIB

•,,llmilllllll_'l_ " ;L -'"t_'7-T_: C '

k

• ,j

REVISED ST. LOUIS 3, MISSOURI REPORT _EDR 104

R_m=o. _ MOO_ .... 133

the roll axis. Signals from the rate transducers and stick potentic_eters are

sent to the rate damper box where the two signals are summed together forming

an error signal. The error signal is sent to a two stage voltage amplifier

followed by a double ring diode demodulator. In accordance with the magnitude

and phase of the error signal the demodulator will select one of two transistor

operated relays which applies a 24 volt d-c output signal to appropriate sole-

noid control valve such that corrective torque is applied.

4-26. Miniature Rate Transducers

Each of the miniature rate transducers consists of a gyroscope, an ampli-

fier, and a demodulator. These components function together to produce an a-c

output signal proportional to input rate of change of attitude. All three rate

transducers are identical except for gyro orientation in the transducer base.

A special indexing feature prevents installation in the wrong location. Input

power utilized by the rate transducers is ll5 volts, 400 cycle a-c.

4-27. Control Stick Potentiometers

The three identical 1000 ohm 120 turn potentiometers are connected to the

manual control stick linkage in such a manner that output signals are produced

proportional to stick deflection in the yaw, roll, and pitch planes. Active

sector is equal to 40 degrees with a minimum of lO degrees of over-travel

without electrical discontinulty.

4-28. REACTION COB"I_OL SYSTEM

4-29. SYSTEM _ESCRIPTION

The Reaction Control System is used for capsule yaw, pitch and roll control.J

The system is a pressure fed monopropellant, catalyst bed design. The right

angle thrust chambers obtain thrust by decomposition of 90% hydrogen peroxide

(H202). The system is divided into two individual systems; one for automatic

control (ASCS), and one for manual control (control stick and RSCS). The auto-

P_E _'_ Mc'DONNELL,_ __ D_T_REPORT SEDR 104 ST.LOUIS, MISSOURI REVISED

MODEL 133 REVISED

1 NOVEMBER 1961

II

I

o lI

_EFORE

0

JA_

AFTER I

i

HSVAC

r_ sus A I

MAIN _4 V PCPR_,- |k4PACT B_JS.

I

I --_'

I BF.FOR_- * GNAT* GYROS

1 °%::o I

N

P5A_CS CAL

M ATTITIJDF GYRO_LAVF- COMD.

___GYRO CAGE COMD.

V LOGIC DC

P AFT G'Yr_O PWR

J _.OG|C AC

_I R/G START

H_' AC PWR

D DC PWR

_ Sc ,,_ CAL

FI GURE4- I_, .POWER DISTRI _LITION DIAGRAMPM 4,5-159

,,2J

C C t'; -; F_.,.F_N T i,kL-


REVISED

REVISED

Mc'DONNELL . ST. LOUIS 3, MISSOURI

PAeE_ 4-29

REPORT, SED_ I0_

MODEL 133

matic system consists of a pressurization system, an "electrically" controlled

solenoid fuel distribution system, and twelve thrust chambers. The manual

system is similar to the automatic system except that it consists of only six

thrust chambers. The manual system also utilizes proportional "manually" con-

trolled fuel distribution valves in addition to the electrically operated

solenoid control valves. Figure 4-13 shows the location of all system compon-

ents within the capsule.


The following paragraphs, 4-31 through 4-35, briefly describe the operation

of the automatic and manual systems. Figure 4'18 and 4-19 should be followed

closely in conjunction with the following text.

4-31. Automatic System

The automatic system consists of twelve hydrogen peroxide monopropellant

thrust chambers of fixed thrust levels and their associated valves, lines, H202

tank, pressure regulator and pressurization bottle. (See Figure 4-14.) The

automatic system can be essentially divided into three sections; pressurization

and fuel supply, distribution, and propulsion units. The fuel supply is un-

stable hydrogen peroxide (H202) contained inside a flexible bladder which in

turn is contained in a half toroidal tank. The flexible bladder has a fuel

capacity of approximately 32 pounds of liquid H202. Helium, under pressure,

surrounds the bladder containing the H202 and acts as the pressurization agent.

The Spherical helium tank, pre-servlced to 2250 psi, has a capacity of 265 cubic

inches.

The following sequence of events occurs in producing a thrust output.

Assume the bladder is serviced with H202 and the helium sphere pressurized to

2250 psi. Upon opening the helium regulator manual shutoff valve, helium is

allowed to pass through the filter, regulator, checkvalve, and finally surrounds

_Z;;;-;D--;gY;AL

CI4EC_

HELIUMRELIEF VALVES

G::

p1 /

/

/

YDROGEN PEROXIDENUALSYSTEM)

PRESSURE _WI

HELIUMFILTER

HzOz RELiEr VALVE (=/a',)

I

/I

/i I

R5C5 ,-SOLEta,Ot D

YAW THROTTLING

PITCH

R,_Cfi 5OLENOIDI.CONTROL VALVE

/

[I

t_ANUAL P_B-PULLSHUT OFF VALVE

FlU-DRAIN 5HUT-OF_" VALVE

¢OLL SOLENOID VALVES

THRUST CHAt_BERS

-PRES;URE TRAN,_I)_W:ER

-HELIUM REGULATORS

ELIUM MANUAL SHUT OFF VALVES

TRAN_DUCEI?

MANUAL VENT VALVE_

-HELIUM (Hz)TANK 0,1ANUAL')

(Hz)TANK ('AUTO)

MANUAL PUSH-PULLOFF VALVE

MANUAL PUSI4-PULLSHUT OFF VALVE

C_ECK V_LVE_

r

/

///I

i /

// /

/i/

SOLE|NIOIDVALVES

)ITCHTHRUST CHAMBER(o TO24 LBS.)

THRUST CHAMBER(_ANO2# LBS.)

•_ - C:HAMBEI_(oTo?.._,LBS)

THRUSTCNAMBER .(i ANP ?4.LB_{,)

YA_N SOLENOIDi_ALVE_

//

VENT VALVES

YAW -_0LENO|D

YAW THRUST(!A_P 24 LBS,)

YAW THRUST.{0 TO Zar LBS)

PITCH SOLEVALVE¢o

ITCHTHRUST CHAMBERTo 24 L_)

PITCHTHRUSTCHAMBERSf AND 24 LBS)

"0

r" .

;o ;0 O

1;

0

l November Mc,DONNELLREVISED ST. LOUIS 3, MISSOURI REPORT _ 10t

REVISEO. _ MO0_ 133

the bladder pressurizing it to 480 psi. The helium pressure forces the H202

out of the bladder through the perforated transfer tube and into the down-stream

lines. By opening the manual push-pull shutoff valves the H202 becomes available

at the "electrically" operated solenoid shutoff valves. Upon receiving a 24V

d-c signal from the ASCS or fly-by-wlre control system, the appropriate solenoid

valve opens. H202 enters the solenoid valve through an integral 165 micron

filtration screen and passes into the corresponding thrust chamber where it is

decomposed and produces the desired thrust. See Figure _-20.

System components not directly associated with the preceding explanation

of a thrust output are explained as follows. The helium pressure transducer

provides a means of monitoring (by proper calibration) the percentage of H202

present in the bladder. The perforated tube in the propellant tank (external

of the bladder) is used to prevent the possibility of trapping helium pressure

while servicing the H202 bladder.

_-32. _snual System

The manual system (See Figures 4-15 and _-16) consists of six thrust

chambers of the same configuration as those in the automatic system with pro-

portional thrust output added. The fuel flow in the manual system may be con-

trolled in either of two ways: (1) by manually controlling the proportional

control valves, or (2) by electrical solenoid control valves. A two position

selector valve is provided such that the method of control may be selected.

See Figure 4-19. The manual control valves have a dead band of + 1/16 of an

inch from theoretical neutral and a total stroke of 3/8 of an inch from

theoretical neutral for each thrust chamber. The throttle valve arm assemblies

or bellcranks which rotate these proportional control valves are designed to

shear at less than full Astronaut effort on the manual control system. See

Figure _-29. In the event a proportional control valve should Jam and immobilize

-n

0%C_3rn

!

)>C

o

7>--!

C_U}

ZCn

)>r-t-

OE

HELIUM LOW PRESSURE--_

RELIEF VALVE

r /

HYDRO6EN PEROXIDE O.h.O,-)TANK

II

#

#

\

//

ROEL MANUAL FU£H-PULL

S SHUT OFF VALVE

/

/I#

" ",/_,LV E

FILL DR_,IN %HUT-OFf "V_,L'VE

RELIEF IVALVE (_'a')

SOLENOID VALVES

RUST CHAMBERS 0 AND i_ LBS_

TRANSDUCER

HELIUM REGULATOR

I_AANUAL SHUT-OFF VALVE

HELIUM MANUAL VENT VALVE

,/- HELIUM FILTER

MANUAL PUSH- PULL

SHUT OFF VALVE

MANUAL PUSH-PULL

SHUT OFF VALVE

E_ "VALV E_

SOLENOID

VALVES

i-IELiUl_ RLL AND

VENT VALVE

YAW 50LENOID

VALVE 5

THRUST CHAMBER (

PITCH SOLENOID.VALVES

SOLENO|D

VALVES

CHAMBE_

0LB)I

CHAMBER

(24- LB.1

0 mo4

m Z

(_0

Ili Ill )_< (: -I

_ m

°°10 U

": ) ' i

i ¸ j

/

/

ll

./I

//i

/ !

//l

R_C5 SOLENOID

CONT RO L VAt

YAW T_4 I_OTTLm

VALV

HYDROgeN I:)E ROX_ DE

( N?_OZ. ) TANK

_lTCt-t

VALVE

m m ),

I < < -_

fll I'll

0 0

Z

o

H

E ;_ "U

3 In >

m

_ ,

34

SEDR 104.REPORT ......

MODEL 133

M_'DONNF__f__ST.LOUIS, MISSOURI

//

/'

\\

//

DATE

REVISED

REVISED

1 NOVEMBER 1961

\

//

///

/

FIGURE 4-16 RC5 ,CONTP, OL L%NKAGE PM45-SZ C

!,

(

D,TE _NO_._., MCDONNELL_ __ P,_E.•REVISED ST.LOUIS, MISSOURI REPORT .....

REVISED . MODEL

"1_-- _AFET_'

4-35

SEDRI04

133

\

\

i \ \\\

PITONCONTROLLINKA6F.

YAW

FIGUI_E 4-17 TI-I_EE AXIS HAND CONTROLLEI_

__.all_ _li. IL I _ I II1_ IIIm Ik I i •

REPORT SEDR 104 ST. LOUIS, MISSOURI REVISED

MODEL_ 133 -,_,,.,""7_';DETUTIAL ......... REVISED

DATE I November 1961

the manual control system in one axis, increased Astronaut effort would break the

shear pin in the bellcrank and free the system. The manual control system could

then be utilized for automatic control system fly-by-wire switch operation or

manual control system "rate stick" potentiometer deflection. See Figures 4-9 and

4-11. The remainder of the manual control system is similar to the automatic

system except for fuel capacity, which is 23,_ lbs. of H202 for the manual system.

4-33. SYSTEM UNITS

Due to the simple nature of the system components, a discussion of each is

considered unnecessary. However, two items (thrust chambers and propellant fuel)

do warrant brief explanations.

4-34. Propellant Fue ! (H202)

Hydrogen peroxide is a clear, colorless liquid soluble in all proportions in

water and most substances which are miscible with water. Hydrogen peroxide when

catalytically decomposed releases water vapor, oxygen gas, and heat. H202 de-

composition when properly contained and controlled is capable of producing usable

thrust. One pound of H202 solution (90%) when properly decomposed will produce

approximately 60 cubic feet of gas. Hydrogen peroxide (90%) freezes at ll.3°F,

and boils at 286°F.

_-35. Thrust Chamber

The thrust chamber assemblies (See Figure _-20) consist of a stainless steel

chamber that contains a metering orifice, a distribution disc followed by a

catalyst bed and then a nozzle. The catalyst bed contains a stack of removable

nickel screen wafers. The screen gauge resembles common household screen. The

screen is covered with an electrolytically deposited coating of 99_ silver and

1% gold (called drexite) that enhances the catalytic properties of the nickel.

The open area between the catalyst bed and the right angle nozzle forms a short

/f.,

|1 .

DATE I NOVEMBER 1961

REVISED ,, ,

REVISED

MCDONNELL_I_ __ PA_E.... _-_ST.LOUIS. MISSOURI REPORT. $EDR 104

.............. " MODEL 133

i ":'_';

PAGE

REPORT

MODEL

4-381s

SEDR 104

133

MCDONNELL_ ___/_Z DATE


____ REVISED

1 NOVEMBER 1961

°/I_o_

I

I

SCI-.IEMA'r:I C . OlAGI:::2AM

, _mZ. .....

/


REVISED ..... ., . -v MODEL. 133

/

c _,"

DREXITE COATED NICKEL SC2EEN_- PO;ZOUS STAINLESS STEEL FLOW/-- DISTRIBUTION PLATE -- _ILTEI_

/ VILTERS /,MLET CAP

V/////////////////////.////¢/2_/(//7 _ c,7"y'_ _(¢,.\"q1---"><--_lL"i76_ /

W/ _ 50LEMOID iNLET VALVE

NEAT BAR_(ER

ILB./_ND 6 LB. TIq_UST

DII,_EXITE COATED NICKEL SCREENS- /--_LO#OU_STS_I_UNLIE# _ #LTEAIEL /FILTERS /'-_"L'TEI_.

c_LWS_ cups _ / ,/ _ SCREEN

_ _1,,,I/,,,ll,_ii1,,,!_,I!,gI I It,

L_ HEAT BARRIER

24 LB. T_I_UST

FIGUI_E 4-20 12EACTION CONTIL:k3L TN_UST CHAMBERPP14_-giB

PAGE b,.-Jl.O

REPORT .q_._ 1 Oh

MODEL. !_3

Mc,DONNELL DATE 1 November l_lREVISED

ST. LOUIS, MISSOURI

...... _._, REVISED

plenum chamber to smooth out the flow prior to reaching the nozzle throat.

H202 enters the thrust chamber through a metering orifice upon actuation

of the solenoid valve. The stainless steel porous plate distributes the flow

and presents the catalyst bed with a uniform input. Upon entering the first

stage of the catalyst bed, a violent reaction takes place. Expanding gases

rush through the remainder of the catalyst bed resulting in a thrust output in

the right angle nozzle. The majority of the decomposition (and most violent)

takes place within the first two catalyst cups. Temperatures of approximately

1400°F can be expected in this area. The remainder of the catalyst cups are

to assure a complete decomposition process and to prevent any liquid form of

H202 from reaching the nozzle.

_-36. HORIZON SCANNER SYSTEM

4-37. SYSTEM DESCRIPTION

The Horizon Scanner System incorporates two identical scanning units. The

purpose of the Horizon Scanner system is to provide a roll and pitch reference

during the orbital phase of the normal mission. The scanners produce an output

signal that slaves the ASCS attitude gyros to the proper angles upon command

/

from an external programmer.

4-38. Basic Construction

Figure 4-21 is a photograph of a Horizon Scanner Unit. _ll major components

and "subassemblies are mounted from the large circular plate and include the

scanning prism assembly, prism drive system, infrared detector, electronics,

synchronous switches, electrical connector and cover. The circular plate is

flange mounted so that the scanning prism compartment projects into the space

outside of the vehicle. The elctronics system is completely transistorized and

the various functional sections are fabricated on separate printed circuit

_v _-q T le_ m-_

•,_vJ.'t.a. Am.IJL_I • .ILJ"Ik.JL'r _'*'_"

:M 'DONNE REVISED_ s'r. LOUIS 3, MISSOURI REPORT. _J_DR 104.

RSvisEo _--_ MOm_ 133

:.C._ /

boards. Three of these printed circuit boards are enclosed in the shielded

housing fastened to the circular plate. The remaining boards are fastened to

the four posts mounted on the circular plate. For rapid servicing the four

posts with attached boards can be replaced as a single unit, or individual

boards can be replaced as required.

4-39. S_ecial Features

The Horizon Scanner has a number of special features. It is compact in

size (6 5/32" long x 5 7/8" diameter over-all) and •light in weight (3.02 lbs).

The scanner is equipped with a centrifugally - activated shutter. The shutter

prevents solar radiation from dwelling upon the detector and resulting in

probable damage during those periods when the scanning prism is not rotating.

Another feature is a special circuit which can be used to disconnect the error

signals from the vehicle reaction devices during those periods when the presence

of the sun in the scan path or the loss of horizon would result in erroneous

error signals. The final feature of significance is that only a single power

source providing llO volts, 400 cycles, 3.2 va is required to operate the entire

system. The highly regulated power supply in the system eliminates the need

for the bulky batteries usually required to bias the infrared detector.


OPeration of the Horizon Scanners depend s upon infrared radiation received

from the earth as compared to the essentially zero radiation from space. These

differences in radiation levels provide a sharp radiation discontinuity at the

horizon. The Scanner system uses this discontinuity for both day and night

vertical reference sensing. When the capsule is oriented so that the earth is

present in its scanning path, there will in general be two points where the

scan intersects the earth's horizon (See Figure 4-22). The scanner detects

the thermal discontinuity, or change in radiation level, between the earth and

i

............. |Iv_._.s_a a/md,b.d_ql JL Adr-ka_

42

REPORT SEDR 104

MODEL 133

Mc'DONNEL_LH'_ __ST.LOUIS, MISSOURI

DATE .... I NOVEMBER 1961

REVISED

REVISED

FIGURE 4-211 WIDE ANGLE HORIZON SCANNER

.- : , .,

PM4_-___8 A

'i

'_vi',illl =idliil I I_


REVISED

REVISED

Mc,DONNEL_LH._ __ PA_EST.LOUIS, MISSOURI REPORT

MODEL

4-43

SEDR 104

133

s-

.=

SCAN

\\ \

/ \

',1 I/I I

//

/I

\\

FIG. 4-2.2 I-IOP,J ZON SENGOI:E... SC.$wN PATTIZP,,I_

I

PAGEv- 7-

REPORT b_DR 104 ST. LOUIS', MISSOURi REVISED

MODEL_ i_ __='--_ _ REVISED

space at the two horizon points. The Scanner then bisects the included angle

from itself to the Horizon points, compares the direction of the bisector with

that of a fixed reference in the capsule and generates linear error signals

proportional to the angle between the bisector and the fixed reference. As

previously stated, these error signals (roll and pitch) are used to slave the

ASCS attitude gyros.

Figure 4-23 shows a simple block diagram of the Horizon Scanner. The

following discussion entails a brief explanation of the functioning of each

block as related to the over-all operation.

4-41. Radiation Gradient At Horizon

There is a large difference in the radiation which the detector receives as

it scans across the boundary between space and the upper atmosphere (troposphere)

This change is approximately equal to that from black bodies at 0°K and 200°K.

respectively, and the radiance difference is approximately 0.003 watts/cm 2 -

steradian. The location of this gradient is sharply defined, and it is much

larger than any others that can be encountered during the scan cycle.

4-42. Correction For Reflected Solar Radiation

Sharp radiation gradients do exist because of reflected solar radiation.

Such gradients are found at cloud edges, topographical irregularities on the

earth's surface and the terminator line between night and day. These radiation

changes can be filtered out so that the horizon gradient is the only one that is

detected by the system. Selective filtering can be accomplished since most of

the reflected solar radiation falls in the spectral region between 0.2 and 2.0

microns, while the radiation emitted by the earth and troposphere is at wave-

lengths longer than 5 microns. The filtering is accomplished by a germanium

prism and field lens in front of the detector. As a filter, germanium sharply

cuts off all radiation at wavelengths shorter than 1.8 microns while transmitting

REVISED ST. LOUIS 3, MISSOURI REPORT _DR 10t

R_VlSED MO_EL 133

very uniformly radiation from 1.8 to 20 microns. The use of this filter remove_

over 90 percent of the reflected solar radiation. Signal clipping techniques

in the electronics remove any residual effects.

_-_B. Scanning and Radiation Detection

Details of the scanning prism assembly can be seen in Figure 4-21. The

infrared detector is fixed to the_center of the circular plate and its field of

view extends through the circular opening in the center of the scanning assemblyo

The detector field of view is 2° by 8° and the presence of the scanning prism

has the effect of deflecting it 55° "from the normal. Thus the apex angle of

the scanning cone is llO°. In operation 3 the drive system rotates the scanning

prism and the detector field scans the field of view through the conical pattem_

described previously. Different amounts of radiation strike the detector during

various portions of the scan cycle: and the amplitude of the detector output

changes accordingly. The detector output signal is processed by the electronics

system and the error signal produced is available at the electrical connector.

4-_. Synchronizing Generator

Closely associated with the prism drive system is the reference signal

generator. The output of this generator Is a square wave signal at a frequency

of 30 cycles per second. This signal is the fixed reference against which the

detector horizon signals are compared. The reference signal Is triggered by the

interaction between a magnetic pickup coil and a semi-clrcular steel vane. The

vane is imbedded in a slot cut into the surface of the scanning prism assembly

gear. A pickup is mounted so that the end of its magnetized core comes close

to the surface of the vane. As the scanning prism assembly turns, the ends of

the vane pass by the end of the magnetized pickup •coil core, generating the

reference pulse. A subsequent electronic network converts the pulse to a phase I

locked 30 cycle square wave. The use of this signal will be considered later[

-=::;:-;7.,:;;TIAL

PAGE _-4_

REPORT SEDR 10_-

MODEL., 133

in this section.

4-45. Sun Shutter


REVISED

The sun shutter consists of a pair of spring loaded metal slides which fit

into opposed transverse slots through the tube section of the scanning mirror

assembly. When the scanning mirror assembly is not rotating spring tension

pulls the two slides together and the detector field is obstructed. When the

scanning mirror is turning, the centrifugal force on the slides is sufficient

to open the shutter.

_-46. Infrared Arrangement

Infrared radiation frcm the field of view strikes the infrared detector and

produces the electrical signal which is processed by the electronics system. The

infrared detector is a thermistor bolometer with its active element immersed in

the germanium lens.

The active element is a rectangular flake of thermistor material and is con-

nected in a bridge circuit with a similar compensating flake which is shielded

from radiation. The two flakes are oppositely biased and their Junction is con-

nected to the input of the preamplifier which follows. By immersing the active

element in the rear surface of the germanium lens the over-all detectivity can

be increased by a factor of about 3-5 over an unimmersed detector having the

same field of view. The material in the thermistor flake has a high negative

_emperature coefficient of resistance. That is, when the temperature of the

material is raised, the flake resistance decreases. Since the surface of the

thermistor flake is blackened, it absorbs impinging radiation and its resistance

is decreased. When the shutter is closed, both flakes in the detector bridge

are at the same temperature. Since both flakes have the same linear character-

istics, their resistances are the same. Gradual variations in ambient temperatu_

change the resistances of both flakes by equal amounts and the voltage of their

l ember MCDONNELL REVISED ST. LOUIS 3, MISSOURI REPORT SEDR 104

REVISED ............... MODEL_ 13._

Junction remains the same. When the shutter opens, incoming radiation is

focused on the active element; the compensating element is shielded from out-

side radiation. The temperature of the active element is changed, and its

resistance becomes different from that of the compensating element. As a

result, there is a voltage change at the Junction of the two flakes and this

change is connected to the electronics system. As the scanning prism turns and

causes the detector field of view to cross the horizon, there is a sharp change

in the radiation level striking the detector. The result of the radiation

changes during a complete scan cycle is the generation of an approximate square-

wave signal at a frequency of 30 cycles per second.

Electronics system is physically arranged so that functionally related

parts are located close to each other. The electronics system is divided into

eight major circuits, located on individual printed circuit boards. In some

cases, the requirements of compact and economical construction have resulted

in two or three sub-circuits being located on one board. Thus, the functionally

related booster amplifier, signal centering circuit and phase inverter-limiter

are located on one board which the block diagram (Figure 4-23) shows as divided

by dotted lines. Although the power supply and reference generator circults

are not closely related in function they are both located on the same printed

circuit board.

The paragraphs that follow describe the functions of the major sections

and sub-sections of the electronics system. The description is made with

reference to the waveforms generated by system operation, and these are shown

in Figure 4-24. Functional description will be made at the level of the major

circuits and sub-clrcuits shown in the block diagram Figure 4-23.

_-47. Immersed Detector

The radiation falling upon the detector determines the waveshape of the

REPORT ISEDR lOLl • REVISED.S_!" LOUIS, MISSOURI

detector output signal which is to be processed by the electronics system. The

radiation characteristics are determined by the scanning cycle described previ-

ously, and are shown as the first _aveform, WF-1, of Figure 4-24. The waveform

shows that earth radiation is higher than space radiation and that there is an

abrupt shift from one level to the other as the detector scans across the horizon

The change in radiation requires 200 microseconds to take place because the

detector is of finite size, and this time is required for a complete shift of

radiation level across the entire surface of the detector. Thirty complete

cycles of radiation change take place in one second.

_F-2 shows the detector output signal which results from the radiation

changes taking place at the detector. This signal resembles the radiation signal

with the exception that the shift between the two levels takes a longer time.

The reason for this is that approximately 2 milliseconds is required for the

active detector flake to reach the half-level of its now stabilized output.

The detector output signal has an amplitude in the order of 2 millivolts.

4-48. Pre-Am_llfier and Booster Amplifier _ircuits

The Junction of the two thermistor flakes is direct-coupled to the input of

the pre-amplifier. The pre-amplifier has a voltage gain of 400 at 30 cycles

per second. Direct-coupllng is used between l_m-ampllfier stages to provide good

low-frequency response and to prevent phase shift. Negative feedback is used

_-Ithin the pre_Ifier to provide stable gain, and the RC coupling network in

the feedback loop provides a high-frequency boost to compensate for the long

detector time constant. WF-3 shows the effect of this boost. The rise time of

the waveform has been reduced to approximately 350 microseconds at the half-

level point. The booster amplifier provides an additional voltage gain of 5 at

30 cycles per second. WF-4 shows the output of the booster amplifier. The

peak-to-peak signal amplitude is in the order of 5 volts.

DATE

REVISED

REVISED

I NOVEMBER 1961 Mc'DONNEL LST, LOUIS , MISSOURI

PAGE 4-49

REPORT ..... SEDR 104

MODEL 133

: \

II / ,,oR,'.S'M /--/.4.H_'[,,qS"[Z)

/ /_)£T£CTOR

II

II "

II / ------

Z)ETE'CT/OI_C,'_CZJIT"

8oo, s'7-_,R AMP

_/GNAL

CENTER

CIRCUIT

PI-,/AS£

/N IIE.R TC_

LIMI r£1_

/_c_R iz<3_v

I-IMI _'_D ,..¢',_lV, dL.._:_w£ R /N/_,l_rI/O V ,d<30 _

t

_u_-

p_"

G_Nr_4TOR

r

._//_/. /F/E..q_',RROR _/_N.4t..

R_'F'_'.REA/C_ 5",_A/AIL<3¢/T.=_Ur

FIG 4-_3 _O_.LZO_ _CAh.lhdE.g:_... I_LOC;_ DIA(_g_vl

PAGE

REPORT

MODEL

4-50

SEDR 104

133

Mc'DONNELL ST.LOUIS, MISSOURI

-_Vl_lr il./r--I_l I i ....

DATE

REVISED

REVISED

1 NOVEMBER 1961

WF I-RADIATION ON DETECTOR

WF 2 - DETECTOR OUTPUT

5O%

WF 5- PREAMPUF!ER OUTPUT

WF4- BOOSTER AMPLIFIER OUTPUT ( 0" HORIZON)

V.

WF4A- BOOSTER AMPLIFIER OUTPUT (2,5" DROPPED HORIZON]

__#_ /-_A---4_-_/2-_v.

WF 5- SIGNAL CENTERING CIRCUIT OUTPUT

WF &- LIMITER AMPLIFIER OUTPUT

WF 7-PHASE INVERTED LIMITED OUTPUT ._IGNAL

50-150 _ _EC.

WF 8- IMPUT_ TO PHASE DETECTOR

_RCE VIBRATING ARH NO,7 AT_-SOURCE -_-

AT R 801 _V

AT R 80Z _OURCE

LOAD

WF 9-CHOPPER INPUT (AT K!O.I CONTACT)

I-- LOAD "--'F" 5CURCE--I

KIOI _--_20V

I-.-_0uRCE--I.-- LOAD----I

KID& I

WF I0- CHOPpEP, OUTPUTS (AT NO. 7 CONTACT)

I--LO4D---p SOURCEH -_sv

KI02

INTERNAL SIGNAL WAVEFORM5

o, NO HORIZON

B_ 15 VIX: T t__j_ I_'E 5"8V P/P

0

_. LOW ALTITUDE HdRIZON

I

I I I VOLTS

t i _ -0

_) INSUFFICIENT 'GAIN OR PARTIAL SIGNAL LOSS

J _ _ jIF VOLT_--i - 0I I

, t I i i

c_ NORMAL _IPM_IAL DROPPEDHORIZON

a. NORMALAPPROX. ,

36 _ SEC_

| '/I-ayocl,.g_l tjJITTER MUST aE L-_S

..... •_--__J/THAN 5 U 6EC WITH

,i o RESPECT TO LEADING EDGE

_. MOTOR ._TOPPED(LOSS OF M.,,E-.Nr'T_CF'_CKUPREFERENCE PUL.S,E)

C, PARTIAL FAILURE OF SWITCHING TRANSISTOR

I) DE_c_IVE r_,_ _,,._ . 14. v NORMAL

0

_') DEFECTIVE I I-'' J-- I + I4 V NORMAL

Q 305 rtoy==R= 3vi:x-., __n',_;

J%P-L__J-L-O

] I I,I-7, ,F-l, IF "_°I " I I I U VOLT.5

_, L L _.LJ L___, _0 _. TYPICAL LOCK- OUT SIGNAL

i raT'pM_,-'I I I '>

'_" SUNIN SCaNII)_N AT I'-- IJ1 ir_____[]_.iI'-INCREASED VIDI"H CAUE'ED BY "SUN PUL'_Ei-'--÷?'0 j I LOCK-0UT T0 GROUND

I I vo.TsMORIZ.0N _

__----_ ,_------d, -O

NORMAL H0mZON D_SCONTINUrFY _') li II cI I . ' I U LJ L_ K- OUT TO +14 V2.)BUN IN _ -4,,tI-,--.$UN PUI.._E , _

_J _i_ _L----J _00LTG e.,. IMPERFECT _YNCHRONISM

O T OTATLIMITED SIGNAL OUTPUT AT P-IOtA

FIG-,4-24. HORIZON SCANNER WAVE FORM._ PM_-Z20 A

:i':U

, (:;

l Ii_ .m- - --

CC,;;";,..,_,,, , ,,-,,--

_ IIL/

OAVE I November 1961

REVISED

REVlSL=ID

ST. LOUIS 3, MI_URI RmPORT _DR i0_

Moo,,, 133

4-49. Signal Centerin_ Circuit

In the signal processing considered previously there has been no particular

interest in the voltage level of the average signal. However, this average

signal level is important in system operation. The reason for this is that the

error signal must be determined only by the phase angle between the horizon

and the fixed reference in the vehicle, and amplitude variations in the signal

should have no effect. Amplitude variations will take place because of changes

in earth temperature at different parts of the trajectory or orbit. When these

amplitude variations are combined with the rise-time characteristic of the

detector there is a difference in phase between different portions of the lead-

Lug edge and the fixed reference signal. Error signals would also be affected

by amplitude changes due to changes in amplifier gain and supply voltage.

Limiting can be used to eliminate the amplitude variations but the limiting

slice must be taken at a point of minimum phase variation. These variations

are greatest at the peaks of the wave and least at the center. Using an RC

circuit to couple the signal to the llmiter would balance equal areas of the

signal waveform above and below ground. Changes in the angle of horizon de-

pression would cause a shift in the d-c level of the signal. Hence, a signal

centering circuit is employed before the limlters to assure that the same center

slice is sampled for phase shift under all conditions. The signal centering

circuit consists of two diodes connected back-to-back as d-c restorers. The

diodes conduct on opposite peaks and thus permit the associated capacitors

to charge up to opposite peak values of the signal. The two levels are then

summed in a resistive divided network, and half the sum is sampled by tapping

the divider at its midpoint. An emitter follower couples this signal which is

shown in WF-5 to the llmiter circuit.

REPORT SEDR lOLl • St. LOUIS, MISSOURI REVISED

MODEL. 133 ............. _ _ _ • REVISED


4-50. Limiting and Phase S_litting Circuits

The signal next enters the first of a pair of cascaded feedback amplifiers,

each of which acts as a limiter and phase inverter. The amplifier consists of

a grounded emitter stage which performs the phase inversion s and an emitter

follower. The feedback ratio is about 50:1 and the over-all gain of the section

is about 30. The output swing is lO volts each side of the fixed lO-volt level.

A low output impedance is maintained during the time when the emitter follower

is in cutoff by feeding the signal from the collector of the grounded emitter

stage directly through a shunt diode. The first section of the feedback

amplifier is fed by the signal centering circuit. Its output signal is the

"limited signal output" and sho_u in WF-6. Part of this signal is fed to

another limited amplifier substantially the same as the first, where it under-

goes a second inversion to become a mirror image of the output of the first

section. The output of the limlter section is thus the dual signal shown in

_F-8. While either signal carries the signal information s the presence of the

image signal will be found useful in cancelling out undesirable ripple components

in the rectified signal.

4-51. Phase Detector

A pair of symmetrical s limited signals enter the detector section (WF-8).

From these the detector derives a d-c signal which is proportional to the phase

difference between the reference pulse and the midpoint of the two horizon inter-

cepts. The phase sensitive rectifier consists of two SPDT polarized relayss or

choppers, driven in phase opposition by the reference signal. These are desig-

nated KlO1 and Kl02 (WFg). The use of two choppers provides the advantages of

full wave rectifications notably low ripple.

To understand the action of the synchronous rectifier, it is essential to

know the relative phasing of the drive and horizon signals. Since the two

._j/

_bul_ r l_l_ A A.ak L -

,,ooREVISED ST. LOUIS 3, MISSOURI REPORT _DR 10_

REV,SEO _ MOOEL 133

choppers are driven 180 ° out of phase, the arm of one connects its capacitor

to the source while the arm of the other connects its capacitor to the load.

Swltch-over takes place when the radial sector of the scanning beam crosses the

vertical reference mark of the sensor and switching back occurs 180 ° later.

Thus, when it is connected to the source each storage capacitor receives part

of the sky pulse and part of the earth pulse. The capacitor is charged positively

during the svltched in portion of the earth pulse and negatively during the

switched in portion of the sky pulse. If the sensor horizontal is parallel to

the horizon, eachcapacitor is negatively charged an amount equal to the posi-

tive charge. Therefore, the net charge is zero. If the sensor tilts with re=

spect to the horizon the amount that each capacitor charges positively is not

equal to the amount it charges negatively. The net charge is, therefore, no

longer zero. The net signal at the input of the d-c amplifier is thus positive

for a positive tilt of the sensor (cw as viewed from the sensor along the scan

axis) and negative for a tilt in the opposite direction. WF-9 and WF-IO indi-

cate respectively the voltage of each chopper and the uncombined output.

4-52. D-C Amplifier

The output of the phase detector is combined and filtered in an R-C net-

work at the input of the d-c amplifier. The signal at this point varies

approximately i00 mv per degree of tilt and the average level is - O.15 volts.

The amplifier input is at high impedance to maintain a low ripple factor. With

a gain of approximately three, the output of the amplifier is 286 mv per degree

tilt of the sensor, reversing polarity at zero tilt. Part of the output is

fed back to the emitter of the input stage. The balanced circuit configuration

minimizes the output drift vith temperature fluctuations.

4-53. SP-HL Detection Circuit

There are two conditions under vhich unwanted error signals are generated,

-"-C._'Y:ZZ_:T'AL

54

REPORT SEDR 104

MODEL_ 133

Mc,DONNE REVISED

_-, -_'r._',-.'- -,_?_W_ REVISED,,

namely, when the sun appears in the scan and when the horizon is lost. Signals

produced under these conditions trigger a logic circuit which indicates by its

output that the sun is present or the horizon is lost (hence the designation

SP-HL circuit). This output can be used to disconnect the d-c error output from

the vehicle guidance system. The effect of sun presence is shown graphically in

the waveforms of Figure 4-24. The sun pulse introduces an unsymmetrical element

into the signal train 3 and the horizon information derived from it is likely to

be false. The presence of the sun's radiation is perceived at the detector.

The sun radiation is hundreds of times greater than that of the earth. The stars

and other bodies produce negligible signals. When a sun pulse occurs, the second

stage of the pre-amplifier puts out a negative pulse with a peak amplitude of

three to four volts. This pulse causes the Void Signal Circuit to produce an

output. When a horizon is present in a normal scan a signal of 5 of 6 volts from

the signal centering circuit suffices to keep the void circuit amplifier shut off.

The absence of the signal when the horizon is lost has the same effect as a sun

pulse -- it causes the void amplifier to conduct with a consequent output current

of 4 ma into a load of 2000 ohms or less.

4-54. Phase Reference Sisnal Circuit

A phase reference signal is produced by the scanning system whenever it

passes through its highest point with respect to the Sensor. The reference

signal is generated in the scanning system. It consists of two equally spaced

pulses, one positive and one negative, for each revolution of the scanning

system. These pulses trigger the bistable multivibrator. The two-level detector

section is in synchronism with the scan cycle. The output of the reference

generator under various operating conditions is shown in Figure 4-24.

4-55. Power Su_l 7

All the power required to operate the sensor is derived from the llO volt,

./

..../

/"

DATE ,1,,November 1961

REVISED,

REVISED.


PA_ L55

REPORV SEDR 104

MOI_ZL .....I_

400 cps llne by a built-in power supply. Input to the supply is through the

transformer. The primary of this transformer is tapped like an auto-transformer

to provide low voltage a-c to operate the scanning motor. The transformer

secondary output is full wave rectified to produce, -30, +30 and +16 volts d-c

with respect to ground. The +30 and -30 v01t outputs are fed to the Regulator.

The +16 supplies the reference generator, and void signal circuits. Part of

the transformer secondary voltage is rectified separately to produce unregulated

power for use in the reference generator and the void signal output current

amplifier.

_-56. Power Regulator and super Regulator Circuits

The Regulator circuits convert the outputs of the power supply into

regulated voltages for use in the sensor. Most of the voltages are regulated

by cascaded zener diodes which maintain a substantially constant voltage across

their terminals by an effect similar to break-down in a gas discharge regulator.

The regulator also contains a symmetrical arrangement of transistors connected

as emitter followers. Since the base potential of each transistor is fixed by

zener action, the output voltage is accordingly regulated with reasonably low

noise. This output is filtered and further regulated in the Super Regulator

circuit to provide the highly regulated voltage required by the detector and

pre-smpllfler. This voltage is extremely stable and its noise content is

essentially transistor noise. The zener diodes used in these circuits are 1/4

watt units which regulate within 5%.


4-5@. TEST CONFIGURATION NO. 8 CAPSULE

The Automatic Stabilization Control System for Capsule No. 8 is identical

to the Specification Compliance capsule with the exceptions noted in the follow-

Ing Paragraphs 4-59 through 4-62.

--1 i& iIiiiwllli _1 • i/-lIJImm

: f

i

"T!

CR]m

4_I

p.}Lrl

HELIUM LOW PRESSURERELIEF VALVES

HYDROGEMPEROXIDE zTA_K (AUTOMATICSYSTEM) /

/

MANUAL PITH- PULLSHUT OFF VALVE

NOTEDUMtt Y I_ISTALLATION

[_ HYOROGEN PEROXIDE{HzOz)(MANUAL SYSTEM) HELIUM FILL ANDVENT VALVES

HELIUM FILTERS t-b.Oz3£TTISOIq V4LVE

SQUIg ACTUATED

L

ii /

' _

__AW S_OLENO_D VALV

/ YAW THRUST CHAMBERSJ(I AND 24 LBS,')

PITCH SOLEHOIIPJVALVES

O !11 >

_ m

.4

m

_B _B 0Pl Pl ),

°°10 0

IzI;

-n

G_CX3rn.pI

rao-

c:

HELIUM LOW PRESSURE-

RELIEF VALVE

.J/

HYDROGEN PEROXIDE (HzOt)

TANK /

,' /

ROLL MANUAL FU_;H-PULI.,

SHUT OFF VALVE

RELIEF WLVE (Y,_)

FILL OR_.IN IDL_-..

RELIEF VALVE (_}

-ROLL SOLENOID VALVES

-THRUST CHAMBERS (I AND 6 LB '_')

TRANSDUCER

REGULATOR

MANUAL SHUT-OFF VALVE

IJELIUM MANUAL VENT VALVE

- HELIUM FILTER

/ / MANUAL PUSH- PULL

/I ' SHUT OFF VALVE

/

_0 / / MANUAL PUSH-PULL

SHUT OFF VALVE

-PITCH Hz_ RELIEF VALVE

' YAW H=Oz RELIEF VALVE

P* PITC P. SOLENOID

ii / VALVES

/ -1 CHAmB_ (..B.)@w SOLENOID

i VALVESi

_. _ / CHA_BE_"-" (ILB)

13 /

cn ; '

rn

.//_. e_,._BER

" " " _ " -" {24- LB.)

/ MELIUh_ FILL AND /

CHECK VALVE / VENT VALVE

HELIUM (H_ TANH --/ YAW SOLENOIVALVES

HEAT • _ARRIEP,THRUST CHAI_BER (ILB) CIr. PLACES)

' PITCH SOLENOID THQUST CHAMBER

"_ VALVES (I LB.)

:;0 O

g g m

E,C1

r- 11-t

m

u1

4_

4-58 McDONNE REPORT S_EDR 104 REVISED

ST. LOUIS, MISSOURI

MODEL 133 _ REVISED .......

4-59. Automatic Stabilization Control System

In general the discussion contained in Paragraphs 4-2 through 4-20 applies

to Capsule 8. Two exceptions are the addition of a yaw data converter to permit

telemetry monitoring of vertical roll and yaw torquer command signals, and the

removal of ASCS power after the antenna fairing has been separated.

4-60. Rate Stabilization Control System

Capsule No. 8 is not equipped with a Rate Stabilization Control System,

therefore Paragraphs 4-21 through 4-27 do not apply.

4-61. Reaction Control System

Capsule No. 8 is not equipped with a Manual RCS System with the exception

of the fuel tank which has been installed and connected to the Automatic RCS

System to provide additional fuel. All text contained in Paragraphs 4-28 through

4-35 pertaining to the automatic system applies with the exception of component

location. For automatic system component location and tubing configuration, see

Figure 4-25 and 4-26. Additional differences between Capsule No. 8 and

Specification Compliance include helium regulator output pressure and thrust

chamber composition, helium regulator output pressure for Capsule No. 8 is 460

psi. Capsule No. 8 thrust chambers do not contain the filter and screen shown

in Figure 4-20.

4-62. Horizon Scanner

Same as Specification Compliance. Refer to Paragraphs 4-37 through 4-56.


The Automatic Stabilization Control System for Capsule No. 9 is the same

as the Specification Compliance capsule with the exceptions noted in the follow-

ing Paragraphs 4-64 through 4-67.

\

. j

r__

|

!_

r_

o

ROLL 5HLJT-OFF VALVE.('AUTO

ROLL RSC550LE_Ot DCONTROL

CVALVE5

TO PtTCH AI'_D YAWTHROTTLE VALVE5

(MAN)

I

_B,C¢_PITC_ AND YAW_OL_Om CONT_O_VALV rr-S CMAN)

EAAI4UAL RC_ HYDROGENPErOXiDE (H=O_ TANK

m Ii1< <

m mo o

==

0

.<

=;

;0 "0m >

II-t

m

_E ,-6o M_,DONNE_ __ D_TE,REPORT SEDR 104 ST.LOUIS. MISSOURI REVISED

MODEL 133 ="_..ti"lt =L,,,tI.,, "Ti = ,_,_ REVISED

I NOVEMBER 1961

AUTOMATIC RC_ HYDF_OCtEN PE.P.,O'Y,IDE. (,H'z.Oz,")T,kNK.

MANIJAL RC._SHYbP.OC1EN PEP.OXIDE (HzOz) TANK

FI_LIRE _.Z8 INTERCONNECTION OF AUTOMATIC- AND MANUAL P-,CS FUEL SUPPLY SCHEMATIC (CAPSULE 9)

,_.:j

i • _LI

• I Ii,,/L--i_II i I:PI r---:

r

/

OATE 1 November 1961

REVISED

REVISED

M DONNE ST, LOUIS 3, MISSOURI

PAGE 4-61

REPORT SEDR 104


In general, Capsule No. 9 ASCS system is the same as Specification Complianc_

Capsule. Some slight differences do exist in the area of normal sequencing due

to the different missions involved. For a detailed description of ASCS normal

sequencing, refer to Paragraph 4-5 through 4-9.

Normal sequencing described in the foregoing referenced paragraph is ade-

quate for Capsule 9 with two exceptions. ASCS operation ceases at antenna fair-

ing separation when the ASCS power is removed. Also a yaw data converter has

been added to the system to permit telemetering the command signals generated by

the Automatic Stabilization Control System. Refer to Paragraph 13-145.

4-65. Rate Stabilization Control System

Same as the Specification Compliance Capsule. Refer to Paragraphs 4-21

through 4-27.


The Reaction Control System on Capsule No. 9 is the same as the specifica-

tion compliance capsule with two exceptions. The control stick is not installed

and the Manual Reaction Control System hydrogen peroxide fuel tank is connected

to the Automatic Reaction Control System to provide an additional fuel supply for

the automatic control system. See Figures 4-27 and 4-28. Refer to paragraphs

4-28 through 4-35.

4-67. Horizon Scanner System

Same as specification compliance capsule. Refer to Paragraphs 4-36 through

4-56.


The Automatic Stabilization Control Systems for Capsule 13 are identical to

those discussed in Paragraphs 4-2 through 4-56 which apply to the Specification

Compliance Capsule.

_A_ ,-',_r'h|_', A,

PAGE, 4-62

REPORT _DR lO_

MODEL. 1_3



REVISED ,

REVISED

4-69.

Same as Specification Compliance.





Automatic Stabilization Control System

Refer to Paragraphs 4-2 through 4-20.



4-72. TEST CONFIGURATION CAPSULES NO. IOAND 16

The Automatic Stabilization Control System in Capsules No. i0 and No. 16 is

the same as the Specification Compliance Capsule. Refer to Paragraphs 4-1 throu_

4-56.


Same as Specification Compliance. Refer to Paragraphs 4-2 through 4-20.







,umMp_4m=-_

DATE , I NOVEMBER 1961

REVISED

REVISED

M DONN ST.LOUIS, MISSOURI

PAGE..

REPORT

MODEL

4-63

$EDR 104

133

THROTTLE VALVE

FIGURE 4-Z9 MANUAL RC5 THROTTLE VALVE. AND BF.LLCPh_NK PM45- 7.70

_.A:; .......vv I IIN/r--I1 I I/_ t-

mSEQUENCE SYSTEM, LAUNCHROUGH RETROGRADE

S_CTION v

OR ABORT

TITLE

TABLE OF CONTENTS

PAGE_.___.

NORMAL MISSION SEQUENCE ............... 5-3

ESCAPE SYSTEM ..................................... 5-11


C_.;&:----m -.Ill'liB • I Ilmlliill

(_) fIRE BOOSTERAND 3USTAdNER ENGINE,_.

• - (_ (_) (_ BOOSTEREN6tNE CUTS OFF AND _EPARATES UPON GROUNDCOMMAND.

1"1 _ (_ TWE_T_ _ELO_b_.kTTE.R E,OOSTER.CUTOFF, FIRE TOWER Rim SEPARATIONBOLTS.

C_/ \ _ AFTER SENSING TOWERRI_ SEPARATION.ESCAPEROCKETS

_.(-- -_ "-" FIRE, PARACHUTE L,kNOIN6 SYSTEM IS kRMEB

_- _ (_) CAPSULE ADAPTER 5EPARATIONBOLT5 FIREAFIER THRUS'I I)ECA_'TO .OZC_A,_OiSEt...TINGEDELAX

_> .

f'-_I (_) CA"UIY ROTATES 180 AND A'SL_ES "_'_-°OV"_IT ATTITU DE •

_LI (_ (_ WHEN 'I'_'PP"O_I'P"A_TT'Tt_DE'A_b kFTEP" _O _EC"T'IvIEDELKY' RETRO ROCKET'_ F'REE

V _ (_ SIXTY SECONDS AFTER RETP,.OROCKETS HAVE FIREDs RET_O ROC..KET P/_,CK_kR IS

Z _"_ JETTISONED CJkP._ULEA._S_),AE_AND _AINTA,IN_ RE-E_TP-.Y _,TTITUI)E

m_ \'_ (_ UPOI'_ DE_CENT TO ZI,O00 FEET,DROGUE CHUTE IS DEPLO'YEb .

,__ (_ AT I0,000 FEET, I)ROf_ttECHbTE,,AIITEHNA FA_P.._,_ IS JETTISOhEb t_kIN

_,. _ CHUTE DF.PLO'YEb

_ I_ UPQ_ IMPACT,Mk_N CB_TE IS bI_,CONNEC..TE|)PILOT &Hb KESERVL CHUTE EJECTED,

Q _ RECO_/ERY ._,tbS DEPLO_ED

i/_- --..

\..

RE'VISED

REVISED


pA(; .....:5-3

REPORT _ I0_

Mo_ 133

V. SS_ SYSTEM, _ THROUGH_ OR ABORT

5-2.

5-3.

NORMAL MISSION SEO_:E

LAUNCH T_R(XJGH ST._IIEr

_IPTIONi

The launch through sCs_l.n8 sequence establishes 'baLl.c references at time of

la_ch and then remains inactlve matll _. At sta_L_ the -_satle's

booster engine separates, resulting in the escape tower bolts be_m_ fired after

a twenty seccmds time delay. The escape rockets are fired i_ed£ate_7 after

tower bolt detonation and subsequently the la_iaE system becomes armed.

The sequence system is Initiated by tvo 28 V d-c slgnsls from the atsslle

vhlch occur st 2 inches a_er l£x'toff (See _ 5-2). This ls know: as time

zero reference and ener_zes a T_e Zero latching relay in the No. 3 Launch and

Orbit relay box located within the capsule. _.n Astronaut ocutro].led back-up

switch is provided in the event the 28 V sl_ls from the _ssLle do not reach

the cap_tle. These same sl_aols are also sent to the _ Altitude Sensor

and the Satellite Clock. The s_aal to the _ Altitude Sensor results in

e_l/shi_ the functlc_ of time lift-off versus the ti_e an abort _ay occur.

At &_tel_ 1,35 seconds _sslle sta_n_ will occur whereby the _eeh_n£cal

separation of the booster engine will cause the loss o_ capsule power to the

Booster E_lne Sel_ratlc_ Sensor rely. _awa_h this de-ener_zed rel_ power

be appl£ed to the Tower Jettlson 20 Second Time Delay rely. After the 20

second t_e delay_ power will be _plied to ener_L_e the Tower Sel_ar_lu_ Bolts

Power relay and the Tower Jettlson Warni_ Llsht 2 Second _ Delay relay.

The To_er Sel_ttun Bolts Power rely7 ls ar_ed by both the Main a_ Isolated

_-e s_u£b bus throu_ the _ ARM switch. _en ener_zed, the Isolated _lu_b

PAGE

REPORT

MODEL

5i- 4

SEDR 104

133

/

Mc,DONNELjL__ __ DATE-_-'. ST, LOUIS 'r MISSOURI REVISED

P P_w, !"_ =_I_=Ne_F_ REVISED

1 NOVEMBER 1961

5T_ql NGTWO. _- ETT.W_, L_RT

W_,RN. LT. I_E L/_"_ I

L_O S_aT,D.') I

f

leOOsTaa I I

E._GmE I ^ I

_EPA_'/_T%O_I-_ INTEP, LCX:.K _ FIREREL P<'¢ I I

_lN_ LIMIT P-OCKE_

%V_/ITC.,,_ FiRE _.E.Lk'-([ [ aOq"_'F''{l"

II

I

TW_ 5E_ I I TOWE_.i_OLTS -- _OLT5

H JETTISONRQCKE.T

_///////////////////_

///////////////////'/_

BOOSTERE.Nr=.SE.P.

NOTF_.%/_ USE IF ATLP,% FAIL% TO

PRODUCE. LIFT-OFF 51C.,,_L

/_ LO_ OF ?.B VOLT POWER

z_ IF ESCAPE P.OCKE%'5 FA_LTO F_P.E ANO T_R_T bE.CkW5

TO ,_0 q.

LIFT- OFF

AT L/_% -_B VOLT_ AT

TIME ZERO

_w_TC.H I --

H

4

%._-,T E.LLI-? E

TIME 7-E_,O

MA_MUMALTITUDE

FIGURE 5- ?_.LAUNCN THROUG_ 5"T/kQ_,NG(._LOCK DIA,GR/_'Ni_

%'-/_TEM

r

!4_t

\ -#M'45-? _,5

i_ii _

bus pover flres tvo of the flve squibs (2 boZts) and _ squib bus power flzes

three of the rite squibs (3 bolts)° As the three se_ented Tower Clamp

sepazstes_ the three Tover Claap ring 1t:tt svitches return to the norasl posi-

tim and sJ.lov Iso_ted and Msln squlb bus pover through their contacts. The

Isolated squlb bus pover enerElses both the Emergency Escape Rocket Fire rela_

and the Eaergency Jettison Rocket Flre re/_y, vhtle the )_Ln squib bus p(r_er

energizes both the Escape Rocket Fire relay snd the Jettlsc= Rocket Fire relaT.

£s the contacts of the Eaers_acy JettAs_ and Jettison Rocket Fire relays are

ecanected In paza_el, either relay vl_ fire both s_Llbs Of the _ettlsaa rocket

£rcm the two different power sources. The Emergency Escape and Escape Rocket

Fire relays are cc_ected :In the Identical same :anner and _ fire both squibs

of the escape rocket _ both pover sources. Power to energlze the Eaergency

Jettison and Jettison Rocket Flre felly is routed throv_h the Capsule Separation

1 Seecad Ttae Delay relay. _s the result of the 1 second delay the Tower Clap

sel_rates_ the Escape Rockets flre and separates the rover f_m the capsule

vlth the Jettison Rockets unfired. _en this ls s_ccmpllabed, two electrical

disconnects between the tower s_t cspsule are sepaz_ted and reaove power fr_

the three Tower Separaticm Sensor relays. _ the de-energized No. 1 Tower

Sel_mtion Seuor rels_ the green JETT TOga light on the teleltght panel

l_mLinstes. When the tower and the ca_mxle sepezste_ the No. 1 and No. 2 Tower

8el_mtlc_ Relays are de-energlsed_ _ pover to energize the No. 1 mad No.

2 _ Chute S_stea Arm 2 Second _ De].a,y Rel_rs. A_er 2 seconds deist, 1;he

Chute Rela_rs a:l the 21_000 foot barosvttches and the Nstn C_te Delay 2

Second Tlae Dela_ relays. After two seconds the IO,(XX) foot _mritebes are

armed. _e power clrcult v111 ho_ st these tvo polnts watll the capsule de-

seeads down through the 21,000 foot range, at which ttae the _ sequence

is tattlated. Refer to Sectlc_ IX of thls amnu_.

6

REPORT _ 10_.

MODEL..1.33

Mc,DONNE REVISED

_TLT'J'_U| _!_S_ S'O_U RI REVISED

5-5. SECOND__

5-6. _n_io_i

Second staging is initiated by sus_J_er engine cutoff at which time the

capsule adapter bolts are fired providing acceleration has decayed to .20g. The

three posl_ade rockets and the four explosive electrical disconnects are fired

lnmediately after the bolts are detonated and result in capsule separation.

Capsule separation is sensed and _uitiates five seconds of rate damping which

is followed by orbit orientation in which the capsule rotates 180 ° degrees and

Settles into a 3_ ° orbit attitude.

5-1'. OPm_TION

At approximately 285 seconds after launch, second staging will occur (See

Figure 5-3)- At thie tJ_e a 28 volt d-c signal fran the missile _-1_1 energize

the Sustainer Engine Cutoff Relay. _en the thrust drops below -_)E, the ._0_

switch in the Thrust Cutoff Sensor closes. Power is then suppl_ed through the

Capsule Separation 1 Second Time Delay and _ta_er Engine Cutoff Relays after

the 1 Second Time delay to energize the Capsule Separation Bolts Po_er and the

Capsule Separation Warning 2 Second Time Delay relays. Through the energized

contacts, power from the Main and Xsolated bus fire the Capsule Separation Bolts.

Also Main bus power is suppled through the Warning Light Time Delay relay to

l]._te the Red CapsuZe Separation Sequence Light on the Lef_ Hand Console.

the Tri-se_ented Capm_le-to-Adapter clamp ring separates it a3_lows the

Capsule Adapter Ring Limit Switch to close supply_z_ power to energize the Posi-

grade Rocket l_re, Emergency Pos_rade Rocket Fire and the Capsule Adapter Dis-

connect Squib Fire relays. The Main and Isolated busses supp_ power through the

energized contacts of these relays to fire the Pos_Erade Rockets and the four

Cap_e Adapter Explosive Disconnects, The Posi_pmde Rockets create sufficient

LT_ LT_L T_VlT_TT.L _F_------ - --

DATI_ i November ig61

REVISED

RE_ISi[D

M ,DONNE __ST. LOUIS 3, MISSOURI REPORT _ 1(_

Mo=_. 133L --

\

thrust to separate the capsule from the adapter. This allows the three Capsule

Separation Limit switches which are attached to the retrograde straps to close.

Power from the Isolated squib bus flows through the closed contacts end acti-

e

rates the #1 Capsule Separation Sensor relay which extinguishes the Red Capsule

Separation Warning Light and illuminates the Green Light. Power also flows

the Capsule Separation Sensor relay to the 5 Second Time Delay DeWing Slgnal

relay. Activation of the Dsmping Signal relay actuates the orbit orientation

relay bringing the capsule to a 3_ ° (blunt end up) orbit attitude.

5-8.

5-9. SC IPTZ0a

In order for the capsule to impact at a designated area, the re-entry

sequence must be initiated approximately 3000 nautical miles up range of the

touchdown point. The method Of initiating normal re-entry sequence is by the

closing of the Retrograde Firing Signal switch within the Satellite Clock. The

switch may be activated by the run-out of time pre-set into the clock prior to

launch for a calculated re-entry time. _ starts at booster lift-off. The

time my also be pre-set by the Astronaut or by Ground Co,and when necessary.

The sequence may be started directly by using Ground Command transmitters and the

Capsule Co,and Receivers. The final method is for the Astronaut to manually

start the sequence by pressing the Retro Sequence h_tton. The last two methods

by-pass the satellite clock. A brief res_e of the sequence starts with the

closing of the Retrograde Firing Signal switch, which energizes the Retro Sequence

Fire 30 Second Time Delay relay. After the capsule has attained the proper atti-

tude end the time delay has run out, the three Retro Rockets will fire 5 seconds

apart. _en the Retro Rockets fire end the Auto Retro Jettison switch is in the

"ARM" position the Retro Rocket Asselbly Jettison 60 Second Time Delay Relay is

enerEtzed end at the run-out of the 60 second time delay the retro package is

.......... ""f ff R!

PAGE

REPORT

MODEL

5-8

SEDR 104

133

Mc,DONNE__ PST.LOUIS. MiSSO0'Rr "_'_

C,-,-,,-:_ _,__ilT i I I

DATE

REVISED

REVISED

1 NOVEMBER 1961

®

t---I

iF--

__////////////////////

_o

II

I

_.A .

//////

//////

'//i

Zo_-

(3.

_n,O

z_O..J

bj O-JO

,Po_q o

(j c_ _ N

DJ

.4,._

{Z :"

_o 3

O. ,_,v uJ

IZ0

II z

__ 0_.

_o_

J

!

ojzo

r',,, _ o

FICIURE_-3 SECOND ,STAGIE_ (._LOC_KD(A_I_,M)

ir¢ i _r

¢ 'JI :

I

_Zq

I

/

"i

C'C._:V :='.--, _,,T_-

B//¸_ , \

DAV_ i November 1@61

RE_/ISED

R_ISED


Jettisoned.

.'AGE 5-9

.",'O.V S_m ]._>_,

The retro package separation is sensed and results in the separa-

tion of the three retro package electrical umbilicals.

5-10. OPER_ION (See Figure 5-4)

The satellite clock Retro Fire switch is armed by Main Squib bus power

through the Capsule Separation relay (See Figure 5.-4). With the Retro Delay

switch in the "NORM" position and the Retro Fire switch closed by any of the

three previously mentioned methods, the Retro Rocket Sequence Fire 30 Second

Time Delay relay Is energized. At the same time the Retro Sequence Indicator

Relay is activated illuminating the Green Retro Sequence Indicator light. With

the Retro Delay switch in the "INST" position power is supplied directly to the

contact of the Attitude Permission Relay No. 1 by-passing the 30 second delay.

The Astronaut may manually start the Retro sequence by pressing the Retro

Sequence switch on the lef_ hand console which will energize the Emergency

Retro Sequence Relay and allow the nodal sequence to be followed. The Retro

Interlock switch in the ASCS Calibrator closes allowing power to flow through

the Emergency Retro Fire No. 1 Relay and energize the No. 1 and No. 2 Attitude

PeDaisslon Relays when the capsule is in the proper position for Retro Rocket

firing. The Red Retro Attitude telelight is switched on when the Retro Rocket

Sequence Fire Relay_ 30 second time delay is depleted and the capsule has not

attained the proper re-entry attitude.

Normally, the Attitude Per_sslon Relay exti_u/shes the Red Retro Attitude

telelight, illuminatil_ the Green light and energizing the Retro Signal Latch

and the Retro Rocket Fire Relays. Power from the Isolated Squib bus is nov

routed through the Retro Rocket Fire Relays to the Retro Rockets in turn f_ri_

first the Left (No. 1) Rocket, after a 5 second time dell7 the Bottom (No. 2)

Rocket and 5 seconds later the Right (No. 3) Rocket. Through the Retro Sisal

Latch Relay, a circuit will be ccRpleted to energize the Retro Fire Signal

vvl_a allu_aw • a,lr-Sahm F

1Q

REPORT _ l(_

MODEL. l_

Disengage 23 Second Time Delay Relay. The power to the coil of the Retro Fire

Signal Disengage Relay allows the circuit to be completed to the ASCS Calibrator

resulting in hi-torque RCS operation. This high-torque operation will last for

23 seconds, which is 3 seconds more than the duration of total retro rocket

firing. The high-torque mode holds the capsule in the 3_ O attitude while the

rockets are firing. At the end of 23 seconds, the Retro Fire Signal Disengage

23 Second Time Delay relay will energize removing power from the Retro Fire

Slgnal relay and thus removlng the high-torque signal. With the Attitude switch

in the "AUTO" position the Astronaut may press the Retro Fire switch energizing

the No. 1 Emergency Retro Fire relay allowing Isolated bus power to energize the

No. 2 Emergency Retro relay powering contacts on the No. 2 Attitude Permission

Relay firing the Retro Rockets when the capsule assumes the proper attitude.

With the Retro Attitude switch in the "BY-PASS" position, and pressing the Retro

Fire switch which energizes the Attitude Permission By-Pass relay, the Retro

Rockets will be fired regardless of the attitude of the capsule. _en the Retro

Signal Latch relay is energized, Main Squib bus Power is supplied to energize the

Retro Rocket Assembly Jettison 60 Second Time Delay relay and the Retro Fire

Warning Light 20 Second Time Delay relay. After the 20 second time delay has

run out the Red Fire Retro Telelight is illuminated. When velocity decreases to

2_0 ft./see, the velocity sensor supplies pre-impact, Main bus power to energize

the RePro Rocket Fired Relay, activating the rela_ removing Power from the Red

Fire Retro telelight and illuminating the Green light. With the Automatic Retro

Jettison switch in the "ARM" position, at the end of the 60 second time delay the

Retro Rocket Assembly Jettison 60 Second Time Delay relay allows power to ener-

gize the Retro Rocket Assembly Jettison relay and the Jettison Retro

Light 2 Second Time Delay relay. As the 2 second time delay is expired the Red

Jettison Retro telelight is illuminated. The _etro Rocket AsseRbly Jettison

J

/--- .

DAT£ 1 NoveE_er i_i PAG£ _-ii

REVISED. ST. LOUIS 3, MISSOURI REPORT _E]_ I0_

_zvlsEo. _ MO_. 133

relay directs Main and Isolated bus power to the two squibs of the Retro Rocket

Assembly Jettison Bolt. The bolt will fracture and the package will drop free

of the capsule 2 being assisted by a coil spring installed between the heat

shield and Retro package Asse_ly. T_ dropping of the retro package assembly

from the capsule will allow the three Retro Rocket Asse_7 Separation _nsors

(single pole limit switches) to return to their normal position energizing the

Retro Rocket Assembly Separation re_7. This will allow the Retro Rocket

Assembly Umbilical Separation relay to energize, firing the six squibs of the

three Retro Rocket package tm_ilicals and Jettison the electrical umbilical pluEs

milliseconds after dropping of the retro pack_e. When the Retro Rocket Assembly

Umbilical Separation Relay is activated_ it removes power from the Red Jettison

Retro telelig_t and illuminates the Green light. When the Retro Rocket Assembly

Separation relay is energized, it activates the Accelercmeter Arm 5 Second Time

Delay relay. At the end of the 5 second time delay_ the relay functions suppl_o

lng a ground for Main bus power _lch operates the .05g relays. The energizi_E

of the No. 1 and No. 2.0Sg Retro Sequence Drop, .O_g Jettison Assembly Sequence

Drop, and .O_g Retro Telelight Power Drop rele_s removes po_er from the various

relays and switches involved in the Retro Sequence as well as extin_tishi_ the

Retro telellEht s.

5-11. ESCAPE SYS_

The escape system primarily consists of a tower &ssembly desiEned to pro-

wide a safe means of abort between prelm_ch and sta_inE. By utilizing the post-

grade rocket system, escapes may still be initiated after booster staging and

throughout sustainer operation until orbit. The to_er assembly consists of a

10 foot, tubular steel structure with a _ foot escape rocket mounted to _ts

tapered end. A segmented clamp ring with 3 _xplostwe bolts secures the t_e of

SEre 104 REVISEDREPORT ..... .ST. L.OUiS ,. MISSOURI

MODEL_ I_B _; _i __,_ _j T_.._ ' REVISED

the tower to the recovery con_artment upper flange. Attached to the escape

rocket nozzle adapter plate is a Jettison rocket which is used to Jettison the

tower assembly after the escape rocket has been fired for an abort; however,

under normal launch conditions the escape rockets are fired to accomplish tower

separation at time of booster engine separation.

5-13. ESCAPE BEFORE LIFTOFF _EFORE UMBILICAL DISCONNECT

Only one ground controlled signal will energize the Mayday relays. This

signal is a direct hardline from the blockhouse abort switch through the missile

to the capsule Mayday relays. In the event that the capsule must be aborted on

the launch pad and the missile is unable to transmit the hardline abort signal,

there is one other method which may be selected. Umbilical pins _ and 45 are

abort wired and transmit 28 V power from the blockhouse to the capsule's

Ground Command Abort Signal Latching relay, energizing and locking in the relay.

Through this energized relay capsule 28 V Squib Arm Bus power is transmitted

to the pole of the Ground Test Umbilical relay; however, power will not continue

through this relay until the relay is de-energized. The only way the relay may

be de-energized is by ejecting the umbilical. Therefore, if this abort method

is required to be used it would be necessary for the blockhouse conductor to

first select the Abort switch _ower to pins _ and 45) and then milliseconds

thereafter eject the umbilical.

5-1_- ESCAPE _ LIFTOFF AFTER UMBILICAL DLSCOKIECT

During countdown there will be approximately 50 to 90 seconds between time

of capsule umbilical eject and time zero, which is two inches liftoff. During

this period, the three available methods of abort are: (1) The blockhouse to

missile hardline abort signal as explained in the previous paragraph; (2)

Ground cc_Aud receiver abort signal; (3) Astronaut's Abort handle. These three

/

REVISED ST. LOUTSs, MISSOUR; REPORT _R1:_ 104

REVISED MOI:_L- 133

methods all result in energizing the Mayday relays.

5-15. ESCAPE AFTER LY__FF _EFC_E TO_R SEPARATION

After liftoff, (Time Zero), there are three methods by which an abort may

be initiated. They are: (I) Ground command receiver abort signal and (2) Astro_

naut Abort handle, both of which were possible methods in the previous paragraph,

(3) The Booster Catastrophic Failure Detection system. This third method has

been non-effective in the two previous paragraphs due to the Time Zero relay

being de-energized. However, the Time Zero relay is energized two inches after

liftoff and completes a circuit to the M_ay relays if the Catastrophic Failure

Detection relay is de-energized by loss of power from the missile.

5-16. Operation

When the Mayday relays are energized, the abort sequence (See Figures 5-5

and 5-6) will occur as follows: The ABORT light on the left hand console will

illuminate, the Capsule Separation Bolts Power relay is energized, the Capsule

Separation Warning Light Time Delay relay is energized, and the Tower Jettison

20 Second Time Delay Relay is energized. After 20 seconds have elapsed the Abort

Relay in the Maxim,-- Altitude Sensor is energized. The M_ Altitude Sensor

computes the time delay required for the capsule to reach a safe dynsmic pressure

hefore Jettisoning the escape tower. The capsule separation bolts squibs will

be fired, releasing the capsule-adapter clamp ring and allowlng the three limit

switches to return to their normal positions energizing the Emergency Escape

Rocket Fire relay, the Escape Rocket Fire relay and the Capsule Adapter Dis-

connect Squib Fire relay, firing the escape rocket and the four capsule adapter

explosive disconnect squibs. The e_cape rocket's 56,000 pounds of thrust rill

separate the capsule from the missile and carry it away from the sustainer and

at a small angle. The capsule separation sensor limit switches also energize

the Capsule Separation Sensor relays, which turns on the Green capsule Separation

PAGE

REPORT

MODEL

5-!14

SEDR 104

133

Mc'DONNE

_VI11 I_IJlIJIil I Ig'_ iI-

DATE

REVISED

REVISED

1 NOVEMBER 1961

P_E-SETBY qRo_%

PP.,E-SET _'f FAS"T P,ON/_T

AUTOMAR_C

PEE-SET

BEFORE

' SATELL_.TE CLOCK I

_£T RO C_RA,DE

S_G_KL S\N _TCH

,,,,, T

CAP%OLK

SE.P _,RATIO_

R£LA'Y

tMh_N j7..4-V D.C. _U S

_ RETRO SEqUEnCEREL!k'Y

(3osEc T.b.)REL _,'Y

IASCS CALIBRATORI

"--"P1R,ETP-,OI_TERLOCKl-'--

l _W'Tr"H I

LcIR R _ RETROI ATTITUDE

P E.P,M t_S_ON l IR,T__L ,l_'x'

RE'fRO R.OCKETe,, LI

TVELOCITY

SENSOR,

NOTES

[D AFTER _o SEC.T.D ¢_CORR_-CT•_,TTI'TL_D_ IS A_X_I_D

AFT_._. SO g_C..T.D.

ATTKR _,0 _EC.T.D,

[_D AFTEIK ZO SEC..T,_).

[_ PWR RKt,AOVED AFT_.R2q_ Sr..C.

ATTEIK ?_ SEC.,T.D.

RETRO F_RE

W_ L_HT_EL _,Y

R.ETRO ROCKET

FIRE R.EL&'YS

IR ET_,O g iQ_,IA,L

L A,TC_, _.EL k'f

R.ET IKO ROCKET

ASSE_BL'X"

SE_APRATiON

RF.LA,y

1,P-,ETRO ROCK_.T I

L_I_ILICAL

_EPA,R_T Io_

IK_-LAy

R_.T RO IKOCKET

LIMBIL_C&L

b I_CO_',II_ECT

_ P-,ETRO ROCKET

SEP,_RAT_OI_

SENSOP., I RETRO ROtKET

_SSEMBLY

,TE.TT_SOl,i P,ELK'(

RETRO FIEE IS_C_N_L b_SE_C_AC_EL..__.

(.5o SECT.b) I_

R ELik_l" ]

RETP, O ROCKET __

S E PAP-,A,Tiot,i

BOLT

_ R,ETRO ROCKET l

ASS EMILY I_--

3"ETTI _o_,i I -

_'_.TT_SON _TROWARN _NC_ L IC_HT

(z sEcT.b)RELLY

,IETTI SOR,ETR.O

FIgUrE 5-4- NORMAL P-,E-EI'4TRYS£QL_ENCE PM_5-Z3BA

!: " i

i" C_ _, _", ,", _" '_' "" "_ ._..... . I I I _ I I

/

!

/

/

®

_ (_

'_Y \ .-//

®

_®

UPON RECEIPT OF ABORT SIGNAL...

_ SHUT OFF BOOSTER, SUSTAINERENGINES.FIRECAPSULE ADAPTER BOLTS

_2_ FIREESCAPE ROCKET

(_ SENSE CAPSULEADAPTER SEPARATION,JETTISONRZTRO-PACKABEAND JETTISON RETRO-ROCKET UMBILJCAL_

_._ MAXIMUM ALTITUDE 3ENSO_ RUN3 OOT FiRE TOWER 3EPAI_AT/ON BOLT3I

SENSE TOWER RING SEPARATION, FIRETOWER JETTISON ROCK_.T

_ SENSE TOWER SEPARATIONTHROUGR ELECTRICALDISCONNECT COMMAND _'ATE DAMPING, 3' 5E.C.TIME DELAY EJECT ANTENNA FAIRINr_ANI) DEPLOY MAIN CHUTE-

RATE PAMI_IN6 .STOP3 AT CHUTE PEPLOYMENT

_ mm 111o o

z0<m

m

,w

m >

II

PN

REPORT _I_ 10_ REVISEDST. LOUIS, MISSOURI

MODEL-] 33 _ - _ REVISED_f .....

telelight, and also energizes the Tower Separation Abort Interlock Latching

relay. The abort interlock relay energizes the Retro Rocket Assembly Jettison

relay through the"ARM" position of the Astronaut's Auto Retro switch and fires

the two squibs of the retro rocket assembly jettison bolt. The bolt will

fracture and the package will drop free of the capsule, being assisted by a coil

spring installed between the heat shield and retro package assembly for this

purpose. When the capsule reaches a maximum altitude, contacts in the MAX ALT

SENSOR will close and energize the Tower Separation Bolts Power relay firing

the bolts. As the three tower bolts are fractured, the se_nented tower clamp

ring: separates allowing the three tower ring limit switches to return to their

normal position energizing the Emergency Jettison and Jettison Rocket Fire re-

lays. Through these relays and their parallel contacts Main and Isolated bus

power will fire the two squibs of the Jettison rocket. The tower will be

_ettisoned clear of the capsule resulting in separating the two tower to capsule

electrical disconnects. The separation of either disconnect will de-energize

the Tower Separation Sensor relays energizing the Abort Rate Duping relay.

This relay will send a signal to the A_CS cosmmuding rate damping until time of

main chute deployment. De-energizing the Tower Separation relays will also

start the two 2 second timers in the recovery sequence which will arm the 21,000

foot and i0,000 foot baroswltches after 2 seconds.

5-17. ESCAPE A_ TO_ER SEPARATION

The methods of initiating an abort after staging are identical to the

methods named for the escape after liftoff and are: (I) Ground command receiver

abort signal; (2) Astronaut Abort handle; (3) Booster Catastrophic Failure De-

tection system. Any of the three methods will energize the Mayday relays. The

sequence which occurs by the energizing of these relays is described in the

d-I f'l, "_T 1"_ T T_ T_ "ILl' rr, T "1

DATE

REVISED

REVISED

1 NOVEMBER 1961 Mc'DONNE ST.LOUIS. MISSOURI

PAGE ,,,

REPORT

MODEL

5-17

SED, R 10,4

133

.s-f- ,,,

: ,. \

MAXIMUM

ALT%TUDE

5ENSO_

BLOCK

HOu 5E

CAPSULE. 5EPAP_TtON TgLELIGHT

' HJ---. CAPSULE

.__J " ,.SEPARATIGN_ I SENSOR

/ I RELAYS

L

TOWER

_EPARATION

ABORT

_NT_LOCK

RELAY._

JE'ITt._3N

RETRO

WARNING

LIGHT

2,0 SEE.

TIME. bELAY _@_LAM

CAPSULEUMBILICAL

H GROUND H

COMM,

A_ORT

SIGNAL

• RELAy,(ENERG.)

ABORT LIGHT

CAPSULE

SEPARATION

SENSOR

LIMIT

SWITCHES

TO'WE _

JETTI SON

?-0 .SEE. TIME

DELAY

TOWER,

JE[TISON

WN. LIOBT

TIME DELAY

RELAY

ESCARE

ROCKET

4 CAPSULE.

ADAPTER

EXPLOSIVE

DISCONNECT

V ill

TowH H5EFARATION TOWER

BOLTS RINC9POWER BOLTSRELAY

H HREIRO ROCKET ROCKET

JETTISON ASSEMBLY ASGEMP_YSWITCH JETTISON JETTtSON

(ARM POSITION) RELAY E::)LT

LANDINO

SYSTEM

Z SE.C.

TIME 0ELAYRELAY

RATE SEPARATION

PAMPItJG AB3K["tNTE.R- LOCK

RELAY RELAY

i

L J RATEASCS

_ DAMPING/ RELAYAISW,TCH

),

GROUND

TEST

UMBILICAL

RELAY

DE-ENERG.)

,i

CAPSULE

SEPARATION

WARNINOLIGHT

TIME DELAY

RELAY

ANTENNA

FAIRING

EJECTOR

ESCAPE

ROCKETFIRE

RELAYS

CAPSULE

ADAPTER

DISCONNECT

SQUIBFIRE RELAY

F ,TOIVER

R II,,IG

uMIT

5_)ITCHES

MAY'DAY

RELAY5

CAPSULE

SEPARATIONBOLTS

POWERIRELAY

CAPSULE

SEPARATIONBOLTS

CAPSULE

ADAPTERCLAMP RING

LIMIT

SWITCH

JETTISON

ROCKET

FIP.E

RELAYS

)

H RETKO H RETR0

PACKAC_ ROCKET

ASSEMBLY ASSEMgLY

l LIMIT SEPARATION

5Wi TCHES , RELAYS

RETRO JETTISON TELELICq-IT

I R I G I-R i- I _T_o II I _ J l J I I _ C K E T I

_ I ASSEMBLY, IIf' " " _ "l [ I UMBILICAL " I

I / / I SYSTEM II RETRO / / I RELAY II ROCKET I_, g I i

I PACK_I uM_,_A_ I

J LEJgg,_L

/ SEPARATION I. ; I /

/ RELAYS I "

-- - I _ MUST _E ENEREdZE0 _Y UMSIU-

CAL RELEASE FOR C.I_CUIT TOGET THRU,

//_ SWITCH CLO_ED _LOW E)_OOOFt

FIGUI2E5:-G. ESC.-A.PE BEFOI_E STA61N(5 BLOCK DIA, roI2AAA P_,;s-_;B

18

REPORT _]_ 104

MODEL 133

following paragraph.

5-18. O_eration

MCDONNE REVISED

ST. LOUIS, MISSOURIREVISED

The signal which energizes the Mayd_7 relays also is transmitted to the

missile to shut down the sustainer engine (See Figure 5-7 and 5-8). Through

contacts of the energized Mayday relays, a power circuit is completed to the

ABORT light on the main instrument panel and the .20g contacts of the thrust

cutoff sensor are armed. As thrust decays to .206 the contacts close and

energize the Capsule Separation Bolts Power relay firing five capsule separation

bolts squibs and separating the capsule adapter clamp ring. The sequence follow-

in6 clamp ring separation is the same as the normal sequence (Refer to Paragraph

5-7)- Re-entry may be acccmplished by any of the emergency procedures (i.e.,

Astronaut or ground initiated). Refer also to Paragraph 5-9. If the abort is

initiated before the capsule has obtained the correct velocity for orbital

flight and it is not desired to fire the retro rockets, the retro package must

be Jettisoned manually. It should be noted that even if the capsule does not

attain orbital velocity the quickest way for re-entry is by emergency firing

of retro rockets.

5-19. TEST CORFIGURATION CAPSULES

5-20. TEST CORFIGURATION CAPSULE NO. 8

5-21. General

Capsule No. 8 is the same as Specification Compliance Capsule in the se-

quence of events that takes place; however, the circuitry of the Launch Orbit

and Escape and the Retrograde Relay panels differ in the following manner.

5-22. Launch Throughsecond

Same as Specification Compliance Capsule, except that immediately upon

firing the Tower bolts_ the Tower Ring limit switches spring to their actuated

P,G'f, YIr_, ;'..N =:

"11

c

111

--4I

•., f 0

Z

UPON RECEIPT OF AISoR'r SIGNAL...

Q SHUT OFF 5USTAINER ENGINE

Q SF-NSE T_RUST DECAY TO .?.DO AND FiRE CAPSULE ADAPTER I_OLT5

O SENSE CLAMP RiNG RELEASE, i:iRE CAI_SULE TO ADAPTER EXPLOSIVE.DISCONNECT5 AND File I:IO_IGIRADE I:I.OCKET_.

(_ SENSE CAPSULE-ADAPTE._ SEPARATION. START 5 5EC RATE DAMPINQ,AND JETTISON RETRO-PACKA_E,

Q ]_PTER S .SEC. GATE DAMPlN6 CAPSULE TURN,_ AROUND.

Q ABTRONAUT C_ROUNO COMMAND _NiTIAT'..5 EMEP,6E_CY PROCEED-ORURE5 TO PERFORM RE-ENTRY AT 34" ATTITUDE,

?",4

i-OE

(I)0

!

D m

rtlr" zl

"4

¢/1fln

4_

O>-IIll

'1>QIii

2'0

REPORT SEDR 104

MODEL 133

Mc'DONNEL LST.LOUIS, MISSOURI

DATE

REVISED

REVISED

1 NOVEMBER 1961

GROUND

P,EC EIV_.

ABORT

NANDLE

MISf:JLF_

CATASTROPHIC

DETECTOR

AROI_T LIGHT I

4 CAPSULE

ADAPTEREXPLOS_VE

DIBCONNEC/5

L_ CAPSULE SEPARATION

DAMP(NG

51C-NALSSEE.

T.D._LAY Z_

CAPSULE

SEPARATION

SENr-_R,

P,ELAYS

,(.___

CAPSULESEPARA_]0N

BOLTS

POWER.

R.ELAY

CAPSULESEPARATION

WARNIN&

UONT

I .SEC. T,D.RELAY

CAPSULE

ADAPTER

DISCONNECT

SQUIB

FIRE RELAY

CAPSULE

SEPARATION

SENSOR '

LIMIT

5WITCHES

CAPSULE

S£PARATI_

_OLTS

CAPSULE

ADAPTER

5I_PARATION

P, IN(a

LIMIT 5WITCMES

iPOSIG_R/C)E

ROCKETS

FiRE

RELAYS

POSIGRADEROCKETS

//_ REMOVED AFTER 5 SE.C.

//_ APPLIED AFTER 5 5£C.

FIGURE 5-8 ESCAPE SYSTE.N,1 AFTER TOWER SF..PAP,ATION(BLOCIX,DIA_P.AM) PM4s-c,os,I

/

< _'_

DATE ! November I_i _ __A_ PAGE _-21

R_'iSEID, ST. LOUIS 3. MISSOURI REPORT _ 10_

.............. ., MOD_ 133L ,

REVISED,

position and complete a circuit to the Emergency Jettison and Jettison Rocket

Fire relays and to the Emergency Escape and Escape Rocket Fire relays. _ough

these four relays which are connected in parallel for each rocket circuit, the

rockets are fired and the tower separates from the capsule.

_-23. Re-_atz 7

The stone as Specification Capsule except that the velocity sensor is re-

placed by three pressure switches, one on each Retro Rocket. Closing of these

pressure switches energize three Retro Rocket Gone Relays which extinguish the

Red Retro Telelight and illuminate the green Retro Telelight.

5-24. TEST CONF_ION CAPSULE NO. 9

uener

Capsule No. 9 is the same as the Specification Con_liance Capsule in the

sequence of events that take place; however, the circuitry in the Retrograde

Relay panels differ in the following manner:

5-26. Re-Entry

The Retro Rocket Fired Relay which extinguishes the Red Retro Fire telelight

and illuminates the Green light is energized by a pressure switch located on the

Right (No. 3) Retro Rocket in place of the Velocity Sensor. All the Retro

telelights are extinguished through a series of relays except the Retro Jettison

light which remains on.

5-27. TEST CCMFIGURATION CAPSOLE NO. 13

e,e r.Z

Capsule No. 13 is the _ as the Specification Compllance Capsule in the

sequence of events that take place; however, the circuitry in the Retrograde

relay panels differ in the following manner:

Mc,DONNE REPORT .¢_1_ 1(_ REVISED

MODEL 3.33 .o_TJ.OUI$_MIS$OURI REVISED.


5-_. _-Entr,/

The Retro telelights are extinguished through a series of relays except that

the .05g Retro Telellght Power Drop relay is not in the circuit and the Retro

Jettlson light remains on.

5-30. TEST COBF_RATION CAPSULES NO. iO AND 16

Capsules No. IO and 16 are the same as Specification Capsules.

Q

6-I-

/'4_- _,

S£CTION V_

ESCAPE AND JETTISON ROCKET

::::::'_--_.._

'::_ii_iiiiiiiiiiiiiiiiiiiiiHiiii_'":

SYSTEMS

TABLE OF CONTENTS

TITLE PAGE

SYSTEM DESCRIPTION ......................... 6-3

SYSTEM OPERATION 6 3eeee.ee.eoeoeoeeee.eeeeeee.

ABORT HANDLE .0. ............................... 6-3

ESCAPE ROCKET ....... , ......... , .............. 6-S

JETTISON ROCKET. .............................. 6-7

TEST CONFIGURATION ....................... 6-11

_ALIIPlRPILIqI_N ,il, I

• n_ ¥ m li 8 IkllP n I I I I/_1_ b

PAGE

REPORT

MODEL.

6-2

SEDR 104

133

MCDONNEL_L_ __ST.LOUIS, MISSOURI

DATE ... 1 NOVEMBER 1961

REVISED ...

REVISED .

zS uJ

v'3

.,%

',O

,.oh" ,._ 0 --

x

FIGUPE ¢o'1 ESCAPE SYSTE_ (SI-IEE_I'I OF;?..)

QLY

Z

o_,i-.. c_

'-_ IJJ

.P_¢O

,J3

i

• .,,,_-_ il"i,L

• • i_/'

l o ember Mc,DONNE 6-3REVISED ST. LOUIS 3. MISSOURI RI_ORT _ 10_1 •

VI. ESCAPE AND JETTISON ROCKET SYSTEM


The escape system consists of the capsule pylon, escape rocket and pylon

Jettison rocket. The system also utilizes items illustrated on Figure 6-1.

These items are not part of the escape system, but assist in the sequence of

events to complete the escape function. During normal flight conditions where

an abort is never initiated, all of the associated items perform their same

function but in different sequences. For a written description of" the escape

system and diagrams of the items under discussion, refer to Section V.


The capsule electrical system provides for an abort any time after the

gantry is removed. When an abort is initiated, the capsule adapter clamp ring

is released, the escape rocket ignited, and the capsule is carried to an

altitude of approximately 2500 feet. At this time, by means of the altitude

sensor, the capsule tower clamp ring is released, the tower Jettison rocket

ignited, and the escape tower Jettisoned. Two seconds after tower jettisoning,

the drogue chute is deployed. Two seconds after drogue chute deployment, the

antenna fairing is released. Twelve seconds after antenna fairing release, the

heat shield is released, extending the landing impact skirt. During a normal

mission where the escape system is not utilized, the escape rocket is used to

separate the escape tower from the capsule.

6-3. ABORT HANDLE

The abort handle's primary function is to initiate the abort sequence.

The handle is also used as a restraint handle during launch. Location of the

abort handle is forward of the Astronaut's support couch left arm rest. For

-CAP3ULE TO ADAPTERSEPARATION RIN_

SENSIN6 SWITCH

--CAPSULESEPARATIONSENSIN6 SWITCH

"----STRIKER (LOCATEDIN ADAPTER)

ADAPTER RING SEPARATION

3ENSOR AND CAPSULE-ADAPTERSEPARATION SENSOR

ESCAPE AND _-JETTISON [Z.

ROCKET -,_

u)

rn

H

0-rlr_

v

CAPSU LEITO ADAPTER.

SE PARATIOIq RIN6

"D

J>.

i

RECOVERY--_COMPARTMENTCAPSDLE

CLAMP RING

SEHSING SWITCH _

CAPSULE RECOVERY_COMPARTMENT

TOWER SEPARATION

RING SENSING SWITCH-

0 m >

Plr" •

-t

!

m Z

o _C

0

;o _o oI11 Ill ),<: < ,-.I

rrl I11El 0

Z

rl

DATE 1 November 1961 pA_,, 6-5

RUrVlSED ST. LOUIS 3, MISSOURI REPORT SRDR l0 b,

._,sEo _omm. 133, , J,

an Astronaut initiated abort, the release button located in the top of the

handle must be depressed, allowing the handle to be rotated outboard. When

moved to the abort (outboard) position, an electrical switch is actuated,

which acts to detonate the capsule-to-adapter clamp ring bolts. The escape

sequence is then initiated, providing that the main umbilical has been dis-

connected. Before umbilical release, the abort handle is inoperative. (See

6-2.)

6-b,. ESCAPE ROCKET

The escape rocket consists of an electrically actuated igniter assembly, a

I inch b,130 steel case, rocket nozzle assembly, plenum chamber and a solid fuel

propellant (See Figure 6-b,). The length of the escape rocket is approximately

70 inches. The diameter of the rocket case is approximately 15 inches. The

weight of the motor prior to firing is approximately 350 pounds. For aero-

dynamical stability, ballast is added to the top of the rocket (See Figure 6-1

Sheet i of 2). The nozzle assembly incorporates three equally spaced exit

cones. The exit cones are canted at 19 degrees from centerline of rocket case

to centerline of exit cones so as to direct the rocket blast outward and away

frQm the tower and capsule. The plenum chamber incorporates a Jettison motor

boss which facilitates for the installation of the Jettison rocket motor. The

Jettison motor boss also provides for the attachment of the thrust alignment

mirror. The optical sighting of the resultant thrust vector is accomplished

by the thrust alignment mirror. For off the pad escapes the rocket will obtain

a maximum capsule altitude of approximately 2500 feet.

The escape rocket propellant is a polysulfide ammonium perchlorate formula-

tion which is widely used in the rocket industry. The United States Bureau of

Explosives classifies the propellant as a "Class B Explosive". The propellant

is sensitive to pressure and a spark or flame may easily ignite it. The

• _ left1 A •

6 r

REPORT SEDR 104

MODEL. 133

Me'DONNELL__ __ST.LOUIS, MISSOURI

l -b

DATE

REVISED

REVISED

I NOVEMBER 1961

\\

J

DAVE I November 1961

REVISED.

REVISED.


pA_z 6-7

Rm,ORV SEDR i0_

.om,_ 1_3

'< ••

propellant grain is an internal burning nine point star which is cast directly

into and bonded to the case. With the nlne-polnted port design, the possibility

of thrust mlsalignment is reduced. This is due to the improved alignment between

the star ports and the exhaust nozzles. The nominal resultant axial thrust at

70 degrees F is 52,000 pounds for 0.78 of a second; it then drops off uniformly

to 5000 pounds in the next 0.6 of a second. The thrust will then diminish at a

reduced rate to zero. The total impulse of the motor, at sea level, is

approximately 56,500 pounds - second.

The escape rocket igniter is a head mounted dual unit with two completely

independent initiation systems to each unit. The dual initiation •system to

each unit has independent circuitry from different batteries. This igniter

is cylindrical in shape, and is a central dynaflow type of long duration. This

igniter is essentially a miniature rocket motor. It incorporates a small pro-

pellant grain which can be ignited by either of two squibs surrounded by

boronpotasslum nitrate pellets. Surrounding this is an annular plastic tube

filled with a metal-oxidant mixture in which are located two sets of four-

squibs. Either set is capable of initiating the igniter. Each igniter has

two initiation systems, either of which can start the igniter in the event some

of the squibs are inoperatlve. The igniter is a Class A Explosive.

6-5. JETTISON ROCKET

The Jettison rocket is a qualified Thor retro unit and is manufactured by

the Atlantic Research Corporation. The rocket consists of an electrically

actuated igniter, a motor case and a tri-nozzle assembly (See Figure 6-5). The

nozzle's cones are canted at a 30 degree angle (from canterline of motor case

to centerline of exit nozzle). It weights 19.5 pounds, has a length of 18 inches,

a diameter of 5.5 inches, and produces 785 pounds of thrust for 1.4 seconds at

70° F. in vacuum. The rocket has been successfully fired from -7_ O F. to 175 ° F.,

PAGE

REPORT

MODEL ,

6-!8

SEDR 104

133

ST.LOUIS, MISSOURI

DATE

REVISED

REVISED

1 NOVEMBER 1961

ESCAPE

• I_OC KET

"METAL CONDUIT

_TI.L,; _

DATE

REVISED

REVISED

1 NOVEMBER 1961

' Mc'DONNE_ _,,_ST.LOUIS , MISSOURI

PAGE , 6,;9

REPORT SEDR 104

MODEL 133

SGNITER FLIGI4 T

I-4 E_, D

PROPELLANT

!-1 O:

SEDR 10:4REPORT

133MODEL

Mc'DONNEL_L_ C__ST.LOUIS, MISSOURI


REVISED

REVISED

/i

L,_ C E DEbFJ

l << c_ ,'61'Ai ,A,I_I

P OT T IN C-i

SQUIB _

I_N\TION PKLLE-TS _

Nl IGNITER F_E Iv__LW, /J

__ \I W/- _ov_,.,•

j-L, NEa

'b"mN6_...

NOT..ZLE TNSE_IT J (_"_,_J _/_ "-_" N0 ZT. L _: A, f) EM,_LY

ELECTRICAL DIAG, RAM

FIGUI:2E 6-5 JETTISON _OCI¢,F_TI" pM4s-_7-¢

j___7"

DATE l _°vemb_r l_ 1 _ _ PAGE 6roll

REVISED , ST. LOUIS 3. MISSOURI REPORT ._,nR IO).l.

REV'SED " " MOC_. 133J

and from sea level to vacuum.

The Jettison rocket igniter is a head mounted unit with dual ignition

capabilities. This unit is cylindrical in shape with a hexagonal head and

threads into the top of the jettison rocket. The igniter contains approximately

7 grams of USF-2D ignition pellets which are ignited by either of four squibs.

Each pair has independent circuitry from a different power source aud either

palr is capable of igniting the pellets.


6-7. TEST CONFIGURATION CAPSULES NO. 8, i0 AND 16

The above capsules differ from the specification capsule in the following

manner. For a normal launch, the escape tower will be Jettisoned from the

capsule by the simultaneous firing of the escape and jettison rockets.

64. •EST CONFIGURATION CAPSULES NO. 9 AND 13

Same as specification capsule.

7-1

l -"........"_.....................................$£CTJON

mPOSIGRADE ROCKET SYSTEM

VB_

TITLE

TABLE OF CONTENTS

PAGE

SYSTEM DESCRIPTION. ....................... 7-3

SYSTEM OPERATION ............................ 7-.3

POSIGRADE ROCKET ............................ 7-3

TEST CONFIGURATION ...................... 7-5

.-::::. .::::::"

-A AIIIPllll_lPLl_lel A |

_V|l| |flJimll • Io"_b_

PAGE

REPORT

MODEL

7-2

SEDR 104

133

MCDONNEL_L__"__ST.LOUIS, MISSOURI

DATE

REVISED

REVISED

t NOVEMBER 1961

.FIGURE -7-I

\\

\

POSIG_ADE I_OCKET SYSTEM

DATZ I November 1961

REVISED

REVISED

ST. LOUIS 3, MISSOURI ._oR'r ._.I_ 104

MOO_ .... 1_

VII. POSIGRADE ROC_ SYSTEM

7-i. SYSTEM _ESCRIPTION

The poslgrade rocket system consists primarily of the three poslgrade

rockets and igniters mounted in the retrograde package and the associated wiring

necessary to ignite the rockets at the proper time. (See Figures 7-1 and 7-2. )


The purpose of the poslgrade rockets is to accomplish separation between

the capsule and booster at a rate of 15 feet per second when orbital velocity

has been achieved. They also perform the same separation function during an

abort after tower separation. The three rockets are fired simultaneously;

however, should two of them fail, the remaining unit would successfully affect

separatlon.

7-3. POSIGRADE ROCKET

The poslgrade rocket primarily consists of a nozzle assembly and •case, a

solid propellant and an electrically actuated igniter. It is a cylindrical

device measuring approximately 14.7 inches in length, 2.8 inches in diameter

and weighing approximately 5.24 pounds. This rocket is basically an Atlas

retro-rocket with minor changes for increased reliability. Reliability has

been gained by two methods; (a) Dual ignition of the igniter squibs from two

different buses, (b) only one of the three rockets is necessary to accomplish

successful separation. Due to the wide temperature range of these rockets,

a temperature control system is not required. The propellant utilized in the

posigrade rocket is Arcite 377 which provides an average thrust of 370 pounds

for one second in a vacuum.

..... ° "_ n"_ l"Jl" I AI_,_1 11 I WIm,*l • , .....

PAGE

REPORT

MODEL

7-4

SEDR 104

133 _

Mc'DONNEL__ __ST.LOUIS, MISSOURI

DATE

REVISED

REVISED

1 NOVEMBER 1961

(0 A

PO,StGR_,DE

ROCKE"r ¢_ BUS

EM ERGEMP..Y

PQSIGRAOE

ROCK ET5 BUS

III

i I

I •

I

A:I

I

r

F-

• ,IPOCJ, JGRADE ; ROCKET

FIRE _I_ LAY

ii

I

A,1

I

I,&jI

4

EM ERGI_t_.YPOSIC_RADE _OCKE'r

FIRE RELAY "

w

,,lie

)--.-

,&

F'IGURE 7-_ POSlGRAOE ROCKET IGNITION 5Y'STEM _CHEMA'I'IC

"1"0

POSIGI_,DE ROCKET¢_

2 AND "_

-} +°CAI_uI.P- AD_P'I'ER Rt_I_

t..Ik,t J"r 5wr'I'CH ES

_,."TO G=ROuMI_ TEST UM_,iLIC,e,.L

RELay AND _lAy DAY

ALARM RELAYed.

PM4S'G6A

.+

....... _='m • |4f-t. L--,

r •

L_

• r•:,•

OAT_ i November I_i

REVISE:D

RE[VISED

i

7-4.. Rocket Igniter

VONNE ST. LOUIS 3. MISSOURI

i

PAGE T-5

REPOnT SEDR 104

.o_ 133

The posigrade rocket igniter is a head mounted unit with dual ignition

capabilities. The igniter is cylindrical in shape with a hexagonal head for

threading it into the top of the posigrade rocket (see Figure 7-1). This unit

contains approximately 3 grams of ignition pellets which are ignited by either

of two pairs of squibs. Each pair has independent circuitry from a different

power source and either pair is capable of igniting the pellets.


7-6. TEST CONFIGURATION CAPSULES NO. 8, 9, i0, 13 AND 16

Ssme as specification capsule.

8"1

RETROGRADE ROCKET SYSTEM

S[CTION VJl_

TABLE OF CONTENTS

TITLE

SYSTEM DESCRIPTION .......................... 8-3

ROCKET MOUNTING • 8-3oeeeeeleeoeleeleeeee eeeee.

RETRO PACKAGE ELECTRICAL WIRING. 8-3

SYSTEM OPERATION ................... ......... 8-6

RETROGRADE ROCKET ........................ 8-8

TEST CONFIGURATION ....................... 8-9

PAGE

_..I A i I i. i l.k I.. L i .i_'i A i _'_ ............. _ ....

_Vlll l_ll I ini--

2

REPORT SEDR 104

MODEl, 133

Mc'DONNE_ __ST.LOUIS, MISSOURI

DATE

REVISED

REVISED

1 NOVEMBER 1961

ADAPTEP.

@

BLANPCETP, EC F-PTA C LE5

FIGUI_E 8-1 P, ETI_,OGI_ADE ROCKET SYSTEM _M4.5-65A

DATE,, 1 No'ulCer 1_ 1 , _ __#_, PAGE 8-?

REVISED. -,.,_- --_--_----7----'-ST,LOUIS 3, MISSOURI REPORT _]_ 10_"

REv,sEo ........... Moron. 133

VIII. REZRCORAIZ ROCKET SYSTEM

8-1. SYSTEM IESCRIPTIONQ

The retie rocket system consists primarily of the three retro-rockets,

their pyrogen i_£tere, and the associated wiring necessary for rocket _tlon.

The retro-rockets are housed in the Je_tlsonable retrograde packa_ along with

the ro ts. 8-i.)

8-2. ROCKET MDURTIm

The retro-rockets are mounted in the retro-package which, in turn, Is

mounted to the capsule by means of three straps _oined at the bottom center of

the package by an explosive bolt. Sixty seconds follovi_ retrograde firing

signal 2 the bolt detonates, the straps are released, and a toll spring e_ects

the package away fr_ the capsule. To protect the rockets, particularS7 from

micro-meteorites, each rocket has a metal cover over its exposed nozzle end.

The cower is blown off by rocket blast at time of light-off. Mount_n6 of the

rockets Is so designed as to direct the resultant thrust vector towards the

capsule's predetermined center of grawlty st time of firiug.

8-3. REPRO PACKAGE _CAL WlRI_

The retro l_ckage Is supplied electrical power through the three electrical

explosive disconnects that are equally positioned around the base of the capsule

Electrical wire bun_les from the dtsccanecte follov the three retrograde package

retenslon straps down to the retro package, where they enter this unlt through

rubber grc_mts. Within the packase all wiring for the retro rockets, sensors

and heaters are routed to the outside of the package face end then into each

retro rocket through the slotted metal shield. Postgrade rocket wiring and

explosive bolt virin8 remain within the package. (See Figure 8-_.)

PAGE

REPORT

MODEL.

8-4

SEDR 104

133

Me'DONNELL_L.L.L.L.L.L.L.L____._ST.LOUIS, MISSOURI


REVISED

REVISED

Pg, E- 5£T

BY GROUND

COMMAND

AUTOMATIC

P RE - %ET

t_E_QRE

LA.UN C_

%A-I'ELL\TE CLOP.3<I _ P.ET_O %EQL_E./',_E

RETROG,R_DE I

I

_I_CAPSULE

_,EPAR AT_ON

_.ELK'f

tKAAIN

_ _'I"'T E_.'Y

(_o _Ec T.o.')RE L/kY

IA_cs CAUBR_GOR l

---l_j P-.E'_RO _TU2LOCY_ r

I _'T_ /

J j RE-i ROR G 9, SEQUENCE

T

AT'TITOOE

P,£ L,k.'_ 5

F_RE

NOTESE_ AFTEr. _Q &EC.'T.O._ CQ_I_,ECT

_.TTITuDE _ A-CCA_EQ

[_ A_'TER 30 %EC.,T._. "

A_'fE_ 6o SEC.q.D.

[E> AFI"_._ _0 5EC.T.b.

PWI_ REMO'VEO AE'I'EI_, %0. %EC.

[:E> AFTE._, 2 _EC.'T.D.

WA_,_ _l'tC_ LI C_NT

(20 sEc.T.b._

RE-fRO _.OCKET

[ P.ETgO £\G.NALLATC_ R EL K'Y

A%S_.MBLY

_,£L _,_'

UM_)ILICAL

I RE-T_D ROCKET

UMBiLiCAL

D ISCDNI'_EGT

._I_2ETRO £OCY-,f.."T I5E t_SGR

RETRO ROCKET

%EPA_ATION,

I_OLT

I RL_RO TI_E I

SIG,NAL O_5_N_AC_E L.,

C_ostc-_.bh [_RE L/_"Y J

3"ETTI SON RF_L¢_'YI I I

T 3ETT/_ONRE'TRO

_E-T_,O _.OCKET I

A%% £ Mf_L'Y

5ET-flSON I -

:; E-TT_SON _L'T _,O

_NK_NINC_ L_.C_HT

(.Z.sEc"T.OJRE L &"¢

FIGURE 6-2 RETROGRADE ROCKET AUTOMATIC FIRING 5YST£'_ PM45-_4-

J," r'l N ',=!m E ._:T. _-=-

DATE

REVISED

REVISED

1 NOVEMBER 1961 Mc'DONNELL H ST.LOUIS, MISSOURI

PAGE.

REPORT

MODEL

8-5

SEDR 104

133

(

¢g r-" -"ISOLkT_D

_ATT.

AN_ r_ECOVE_..Y ¢, _,A_I

IKIO. rZELAY

TO _i'_o POCKET F:J_E 2[LAY(30SEC.T._.)_'_----'_ I __";;..o _6L,_,Y

T

SELECTIOM

_.. ;=AIUJ_. r- OF SATELLITE

CLOCK T"ro I:::U_C.,TI_,K._

C..LOCl¢. _..U _-_ OUT.

ASSK_.VLEFT NAIAD

CONSOL_

i ¸ iFi '

,so_,T_o FIGUIKE8-3_TT£_Y

-n3_-- ROOr._.T

SE P_,_.ATIO_

I501._TI;D

e_,TT_I_y

i_c)_TO Q_TRO ASSEMBLY

QETT]S_4 _OLT

RE.TROR,OCKF.TOVERRIDE FIRING SYSTEM SCHEMATIC

_.THE'_._.T{'J.0 _TTITUOE' LIGl.IT

OOE_ _(_T ILLUMtkL_Tt 0t_

ILLtJN_INATF-_ _E0_ _JTVIBU_-L AIDS Ik.iOlC/kT_.

CAPSULE IS IM {2ETIZO

h "JET'ClSOt4 I_T_O * LIGHT

_0TES

EE> _I_EEN i.t@l-IT OMI.,.V.

tP" TWF..'_F..T12.0 A'_ LI_NT

Pil2_ t.lGl-I'T ILLUI,_II4/_'IT.tt

pM45qlB

........ |ITI i •

6

REPORT SEDR 104

MODEL_ 1_

McDONNEL LST. LOUIS, MISSOURI

DATE _. 1 November I_i

REVISED

REVISED

8-4. SYST_4 OPERATION

The purpose of the retrograde rocket system Is to slow the capsule prior to

re-entry. Actual firing of the rockets is preceded by a 30-second period during

which the capsule is positioned to the "retro" attitude. "Retro" attitude Is

defined as follows: 34 ° + 12.5 ° Pitch, 00 + 30 ° Roll or Yaw. The firing

sequence will not begin, nor_Llly, until the "retro" attitude limits have been

attained, and will be temporarily interrupted should the capsule exceed the

attitude 1/mits after the sequence has begun. Should the need arise 3 however,

the above ltmits may be manually overridden. Firing of the rockets, which occurs

at five-second intervals can be initiated by any of the following: (i) Satellite

clock runout; (2) Astronaut selection; (3) Ground command. Any one of the

rockets wall effect a satisfactory re-entry in the e#ent the other two fail to

fire. Sixty seconds after slgnal for retro fire, the entire retrograde p_ckage

is Jettisoned.

8-5. ROCK_ FIRING

All three rocket flre relays receive 2_ V d-c siemltaneous_7; however, the

No. 2 and No. 3 rocket fire relays have a five- and ten-second time delay, respec-

tlve_y. Therefore, the following table shows _hen each rocket receives its flre

signal and the length of burning time thereafter. Note that the asterisk lndi-

cares time of firing.

Left No. 1 R_ e

Bottom No. 2 RK_

Right _o. 3 R_

+

+

÷

123k 5 6 7 8 910 ll1213141516171819 20.

SECOImS

The retro rockets are fired sequentis_ to avoid the Inei_ectlve results

DATI_

REV,S_O -- "_" "_'a""'_rr.Loum s, MiSSOUm R_'OnT. _ 10_

133

\ /

from a failure of either of the first two rockets. Consequently, if No. 1 roc_t

failed to a degree which would disrupt the retro attitude position, the ASCS

attitude interlock would remove power from the attitude permission relay and

also the No. 2 rocket fire relay. The capsule could then be reposltloned auto-

matically or manually by the RCS, end upon regaining the 34° position s the No. 2

rocket fire relay would receive po_er and fire. The same sequence would occur

if the No. 2 rocket were to fail. (See Figure 8-2. )

8-6. RETRO ROCKET EMERGERCY OVERRIIE

There are four telellghts on the Astronaut's left console which concern

the retrograde system. The first one is RETRO SEQ. and is a green function

light. This light will illmninate when the retro sequence is started, either

by the satellite clock or by the button adjacent to the light. The purpose of

the button is to initiate re-entry prior to satellite clock runout or failure

of (seen re 8-3.)

The next two telelights in the retrograde sequence are REdO ATE. and

FIRE RETRO. For a normal flight, the RETRO ATTITUDE switch adjacent to the

RETRO ATT. light should always be in AUTO. The RETRO ATT. light will illum_te

green as soon as the capsule reaches the 34 ° retro attitude position. Approxi-

mately forty seconds later the FIRE REdO telelight should illmninate green. If

the _ ATT. telelf_ht 411,--tn-tes red, the Astronaut must check the capsule

attitude in order to determine if the capsule is in correct retro fire Position.

If the capsule is found to be in the correct attitude, then the Astrcnaut should

position the RETRO ATT. switch in the BY PASS Position, and also push the FIRE

REdO button. Ten seconds later the FIRE REdO light should illuminate green.

However, if the Astronaut determined that the capsule was not in the correct

Position s the fly-by-wlre system should be employed in order to correctly posi-

tion the capsule in the 34 ° attitude. (See Section IV. ) When this is accem-

..... ''"_"_I _ I

8 MCl DONI_.h_._ ___T_TT A I"9 DATE 1 November 1961

REPORT _ 104 _ _'_--_" "_ REVISEDST. LOUIS, MISSOURI

MODEL. 133 _I* ....... REVISED,,

pllshed the RETRO ATT. telellght should illuminate green.

If the EETR0 ATT. telelight illuminates green, but the FIRE EETRO telelight

illuminates red, the button adjacent to the FIRE RETRO telelight should be pushe_

leaving the RETRO A_T. switch in the AUTO position.

The fourth telelight is the JETT. RETRO. This telellght will illuminate

green 60 seconds after the illumination of the FIRE RETRO telelight. In the

event this light illuminates red, the adjacent button should be selected to

supply an alternate source of power to the Jettison bolt. If the retro package

cannot be Jettisoned by the automatic or override method, it will be ejected

sometime during re-entry when the extreme heat encountered will detonate the

explosive bolt or burn the retention straps to allow the coil spring to eject

the package.

8-7. RETBO ROCEET HEA2ERS

The retrograde rockets are equipped vlth blanket type heaters operated by

means of ground power only. A resistor type thermostat maintains heater tempera-

ture between 75° + 5°F and 95 ° + 5°F preventlmg moisture from collecting on the

retro-rocket nozzle closures.

8-8. RETROGRAnE ROCKET

The retrograde rocket, manufactured by Thiokol Chemical Corporation, is a

variation of the Model TE-236. Leading particulars are : Total weight approxi-

mately 69.55 pounds, length 15.4 inches, diameter ]2 inches. These rockets

have a total impulse of approximately 13,000 pound seconds, providing an average

thrust of 992 pounds each for 13.2 seconds action time. Due to the importance

of the retrograde system to the overall mission, a redundant rocket firing system

has been employed. Dual ignition to all igniters has been provided from separate

electrical sources. Heaters are bonded to motor case and nozzle closure and are

MAC 23TCL (27 APR 59)

DAT_ I November 1961

R£VISED

IR£%rIS£D


P^G_ 8-9

MOm_ 133

.4--'-,

thermostatically controlled.

8-9. TEST CO_FIELTATION CAPSUI_S

8-10. T_ST COIFIGURATION C_ NO. 8, i0, 13 AND 16

The above listed capsules are basically the same as the speclficatlon

capsule.

_A_E '-,0 MC,DONNELL__.__¢_'_j,'ez._ t, _ DATE

REPORT, SEDR 104 ST.LOUIS, MISSOURI REVISED

MODEL.. 133__F:_ S".'T :_ L REVISED

I NOVEMBER 1961

\

: /

/

/

/

F_URE 8-,4--RE-FRO PACKAQE EL.EC-rRICALINS,TALLATION; _ ,,_,

.t_kll=..ll_lm.li.,-r- - : :

pH45-'13

• /

_lm_. a_.:.,p. ,._,,.,m,_ _ - •

S£CTJON JX

SEQUENCE SYSTEM LANDINGTHROUG RECOVERY

\

TITLE

TABLE OF CONTENTS

PAGE

AUTOMATIC SEQUENCE DESCRIPTION .. 9-3

AUTOMATIC SEQUENCE OPERATION .... 9-3

EMERGENCY SEQUENCE DESCRIPTION... 9-6

EMERGENCY SEQUENCE OPERATION ... 9-6

SYSTEM COMPONENTS., ....................... 9-11


_^ilPII'_IP|I'TI A I .

tv i 11 i IBw bl 1 I Idr_ll

I_1315A5 ,K_I'_AOD3_I (3blW _bllq_IW70IIW_OIOW I-b SB_I3

.; ii:

03SLASH IHROSSIIN 'SlOOl'/s _ol llOlq /HOd'ai:l

lg6l _I_RW:IAON l

DATE i November i_i

REVISED

REVISED

Mc'DONNE ST. LOUIS 3, MISSOURI

p^_E 9-3

REPORT SEDR 104

MODEL I_

IX. SEQUENCE SYSTEM LANDING THROUGH RECOVERY

9-I. AUTOMATIC SEQUENCE DESCRIPTION

The landing and recovery sequence system provides automatic electrical

sequencing to land the capsule safely after an abort or a/_er re-entry, and to

initiate locating aids for assistance in the subsequent recovery. The primary

(completely automatic) system incorporates a drogue parachute, used initially

to decelerate and stabilize the capsule in the initial phase of recovery and a

main parachute which further decelerates the capsule. Capsule landing is

accomplished by a 63 foot diameter parachute which is deployed at I0,000 feet.

In the event of a main chute failure, a 63 foot diameter reserve chute may be

deployed by the Astronaut's manual selection. Both main and reserve chutes

are reefed to limit shock loads at initial opening. Automatically, the reefing

line is severed after a predetermined time delay an_ the chute will open fully,

lowering the capsule at the prescribed landing speed. After main chute deploy-

merit, the landing impact bag is extended, providing a cushioning effect for the

landing impact. Immediately'after impact, the main chute is autcma_ically dis-

connected and the reserve chute ejected. The Astronaut will then egress normally

taking with him the survival kit which contains a life raft and other survival

aids.

9-2. AUTOMATIC SEQUENCE OPERATION

On tower separation, power is removed from the Tower Separation Relays

allowing the Main Chute System Arm 2 Second Time Delay relays to be energized

(See Figure 9-I). After the 2 second time delay has run out power flows through

the closed contacts energizing the Main C_ute Delay 2 Second Time Delay relays

which in turn after a 2 second delay arms the 10_000 ft. Baroswitch. The 21,000

ft. Baroswitch is armed through the closed contacts of the Main Chute System Arm

_

REPORT _I_R 1OZ_

MODEL_ l_


I REVISED

2 Second Time Delay relays. Upon descent to 9_I,0OO ft. the _1,000 ft. ]_o-

switch is actuated, energizing the Drogue Deploy relay, firing the Drogue Chute

Mortar, deploying the Drogue Parachute, and ejecting the chaff package. The

Drogue Chute stabilizes and decelerates the capsule; the chaff package disperses

finely cut _etal foil that provides an enlarged radar reflection area that can

be picked up by search planes hundred of miles distant. At approximately I0,000

ft. the I0,000 ft. Baroswitch actuates the Main Deploy relay resulting in the

removal of ground circuits and firing of all four squibs of the Antenna Fairing

Ejector. Also, the Main Deploy Warning Light 2 Second Time Delay relay is

actuated, and at the end of 2 seconds delay the Red Main Deploy Telelight is

illuminated. The Antenna Fairing Separation Sensor Arm relays are energized

through the closed contacts of the Main Deploy relays arming the two Antenna

Fairing Separation Sensor Switches.

The firing of the four Antenna Fairing Ejector Squibs causes the Antenna

Fairing to separate from the capsule. A lanyard, connected from the Antenna

Fairing to the Main Chute, extracts the Main Chute frca the chute compartment.

The Main chute opens initially in the reefed condition to limit shock loads.

Four seconds after the chute is deployed the reefing line is severed by a

pyrotechnic charge in the reefing line cutters allowing the parachute to open

fully.

The separation of the fairing from the capsule allows the Antenna Fairing

Separator Sensor Switches to function. Through the switches, power is routed

to energize the Main Ejector Relay firing the Main Ejector Bag Squibs. When

the squibs fire, they generate a gas, filling the Ejector B_ at the bottom of

the _ Chute cc_r_ent aiding the ejection of the chute. At the same time

the Antenna Fairing Separation Signal'relay is energized, illuminating the Green

Main Deploy Telelight and removin6 power from the Red Telelight. Power is also

CC_!FIDENTIA,.

directed through the Antenna Fairing Separation Sensors to energize the Main

Inertia Switch Arm 12 Second Time Delay relays. After the 12 second time delay

the energized contacts allow power to be supplied to energize the Landing Be_

Extend and Landi_ Bag Warning Light 2 Second Time Delay relays as well as power

to the Landing Bag Unlock Signal Limit Switch and Tnertia switch. The closed

contacts of Landing Bag Extend relay fire the squibs of the La_iing Ba_ Valve

releasing the heat shield, and extending the impact landing ba_. As the 2 second

time delay runs out the Landing Bag Warning Light relay illuminates the Red

Landing Bag telelAght. Upon heat shield separation the T_na4nZ Bag Unlock Signal

Limit switch is actuated and through its closed contacts power is directed to

energize the Landing _k_ Extend Si_ relay illuminating the Green Landing _ag

Telelight and extinguishi_ the Red light. The force of impact on landing

operates the Inertia Switch and in turn energizes the Electric Switch which pro-

wades a ground for power flo_ to the Impact relay coil. Through the closed

contacts of the Impact relay, power is supplied to energize the Post Landing

System Relay. Through the activated contacts of the Post T_na_nZ System Relay,

power is transmitted to energize the Impact Signal, and the Capsule Stabilization

1 Second Time Delay relays. Through the closed contacts of the PoSt Landing

System relay the self-powered Flashing Recovery Light circuit is con_leted

setting the light in operation. When the _pact Signal relay is energized the

Green Main Deploy and Landing Bag Telelights are extinguished and the Red Rescue

Aids Telelight is illuminated. At the end of the 1 Second time delay the Capsule

Stabilization relay is activated allowing the Main Disconnect and Reserve Dis-

connect relays to be energized. Through the energized contacts of Main Dis-

connect relay, the Main Chute Disconnect squibs are fired, releasi_ the main

chute f_ the capsule. The Reserve Disconnect Relays fire the Reserve Chute

Disconnect Squibs releasin_ the Reserve Chute and energizes the Reserve Deploy

REPORT ,SEDR lOLl• ST. LOUIS, MISSOURI REVISED

MODEL_ 133 ' ' "* REVISED

relay. The Reserve Deploy relay fires the Reserve Chute Deploy Gum Squibs de-

ploying the Pilot Chute and the Reserve Chute Ejector Bag squibs. The Reserve

Chute Ejector Bag squibs activates the gas generator which has a one second delay

in ignition time before inflating the ejector bag expelling the Reserve Chute

and the dye marker. When the Rescue Aids switch is placed in the "MAN" position,

the Rescue Aids Switch Signal, and the Post Landing System Power Drop Hold relays

are energized. The energized Rescue Aids Switch Signal relay removes power from

the Red Rescue Aids Telelight and illuminates the Green light. The Post-Landlng

System Power Drop Hold relay energizes the Post-Landing System Power Drop 30

Second Time Delay relay. At the end of the 30 second time delay the Whip Antenna

Extend relay is energized firing the Whip Antenna Extend Squibs activating the

gas cartridge extending the active element of antenna to its full length. When

the Post Landing System Relay is energized on impac% power is removed from a

number of components in the circuit. After a 30 second delay the Post Landing

System Power Drop relay is energized removing power from the remainder of the

components, except the Whip Antenna Extend relay and the Rescue Aids Switch

Signal relay which leaves the Green Rescue Aids Telelight illuminated.

9-3- EMERGENCY SEQUENCE DESCRIPTION

The Emergency provisions of the landing system basically consists of

manually operated back-up systems initiated by the Astronaut. The appropriate

button, pull-ring, and switches are located on the Left Hand Console. The

emergency system controls manually initiate deployment of the Drogue, Main and

Reserve Chutes, extend the Landing Bag, and initiate rescue aids.

9-4. F._R_ENCT SEQUENCE OPERATION (See Figure 9-3)

On descending to 21,000 ft. and Drogue Chute failure is detected by lack

of opening shock and by a visual check through the window, depress the Drogue

/

DATE

REVISED

REVISED

1 NOVEMBER 1961 Mc'DONNELL____ST.LOUIS, MISSOURI

PAGE 9-7

REPORT SEDR 104

MODEL 133

i,i '

\\

F WHIP ANTENNA

PILOT CHUTE LANYARD

TO TOPOF PILOT CHUTE

\

EtGU!_E 9-2, _MAIN AND 12ESEI_VE PAI2ACI4UTE SYSTEM(SHEET I OF

i

_8

REPORT SEDR 104

MODEL 133

MCDONNELL ST.LOUIS, MISSOURI

DATE

REVISED

REVISED

I NOVEMBER 1961

\\ . ',P . , \

\

'\

I)I_.o _'J E -._

_/SO_k__o_,_

"_--__ __--__ __-__RK_ _ __

FIGUP.E g-2 MAIN AND 12ESEI2VE PAP..ACHU'ITESYSTEM(_SN, EET Z OF Z) PM,_s--7_,_

}

l .......MCDONNELL 9-9DAT£

REVISED ST._" _'_'LOUIS 3, MISSOURI REPORT _D_:_ i(_

REVISED .... x MODEL 1BB

button. Depressing the button allows the Emergency Drogue Deploy relay to be

energized and the Drogue Chute Mortar squibs to be fired deploying the Drogue

Chute and dispersing the chaff. If the Green Main Deploy telelight fails to

illuminate, failure of the Main Chute deployment may be detected by a lack of

opening shock, a visual check and no decrease in rate of descent. Upon determin-

\

ing that the Main Chute has not deployed, operating the Main Deploy Pull Ring

energizes the Emergency Main Deploy relay, firing the Antenna Fairing Ejector

Squibs, ejecting the Antenna Fairing and deploying the Main Chute through the

normal automatic sequence. When the Green Main Deploy telelight is illuminated

and the rate of descent is above 32 feet per second, check the chute visually for

damage. If the chute is damaged or did not deploy, actuate the Reserve Deploy

Pull Ring which energizes the Reserve Deploy relay. Through the energized con-

tacts, power is applied to the _ Chute Disconnect firing the squibs disconnect-

ing the chute from the capsule. At the same time, the Reserve Chute Deploy Gun

Squibs are fired deploying the Pilot Chute, and the Reserve Chute Ejector Bag

squibs are fired generating a gas after a i second delay inflating the ejector

bag which aids in deploying the Reserve Chute.

Twelve seconds after the Main Chute is deployed the Green Landing Ba 6 tele-

light should be illuminated. If the light does not come on, place the _-d_ng Bag

switch in the "MAN" position, energizing the Emergency Landing Bag Extend relay,

firing the Emergency Landing Bag Valve Squibs, releasing the heat shield and

extending the impact landing bag. Ten minutes after impact the Rescue Aids Switch

By-Pass relay is energized. When activated, the relay by-passes the Rescue Aids

switch and energizes the relays that supply power to fire the Main Chute Dis-

connect squibs as well as the squibs for the Reserve, Disconnect, Deploy Gun, and

the Ejector Bag in the same manner as would be done if the switch was placed in

the "MAN" position.

C_::y:___:'T' AL

PAGE , ' 9-10,

REPORT SEDR 104

MODEL 133

Mc'DONNELLj ST.LOUIS, MISSOURI

_ ,,p_ m- I]P" II_" L I "_l" .


REVISED ,, ,

REVISED

EMERGENCY

DROGUE DEPLOY

RELAY

£_ER_ENCX MM_

DEPLOY

RELAY

MAIN

CNUT _- FAIL5

"TO DF.PLOY C,R 15

DAN1/kG&O

.FAIL ¢' TO r=."_TEt,4D

RF..SCUr=A_05 sw.Nor _N "MA_"PO'_TION

FIGURE 9-5

R_VE F

_EPLOY

RELAYS

DP.OGU E CHUTE

MORTAP.

_CtUI B-_

CH_.FF __

q ncE

._J MAIN C_UTE,

E)I5CONNE.CT

SQ_I B._

__ _E._E_NE CHUTe.

0 _:I_LOY GU l,,t

5QLIIB5

____ _E._E I:l.Nt E CHUTE

EJ ECTOR

J

PILOT CHUTE

J --"-_ ELECTRICAL SI6klAL j

, MOVEMENT II

l _.MER_ENCy EM E R _ENC"('

._._.J_LAND_NG BAG L._N_INC_ _,,_C_

I "IEXTENO RELAY VALVE %q_IBS LANI_ING BAG,

/ _',,_ c_,u_-_ Ir--IN _sco_c'r I

_---_ - _¢ONN_.CT I

J I s_,_ I

IT _ DEPLOY Gu_ k\\\\\_ .>, . , °

EaECTOR _AG

LANDING AND P, ECOVERY EMERGENCY SYSTEM iSLOCK PM45-z6o_

• !

DATE 1 _ove_er l_61

REVISED

REVISED,


PAG _"

REPORT

MODEL

9-11

/ ",

"LI.J

9-5. SYSTEM COMPOHE_TS, , ,

9-6. PARACHUTE

The drogue parachute assembly (See Figure 9-5) consists of a conical ribbon-

type drogue canopy with integral r_ser, drogue deployment bag, drogue mortar,

sabot, chaff packet, and drogue mortar cover. The drogue parachute canopy t s a

conical ribbon parachute having 8 gores of 2-inch wide, 460-lb. tensile strength

ribbons and 8 tubular nylon suspension lines of 1,O00-lb. tensile strength each.

The parachute is constructed to a diameter of 6.85 feet end permanently reefed

(restricted) to an effective diameter of 6.0 feet by means of pocket bands. The

constructed total porosity is 27._ and the effective porosity (through reefing)

is 36.3%. The SO-ft. long integral riser is made from three layers of 3,000-Ib.

tensile strength low-elongation hot-stretched Dacron webbin 6. The drogue para-

chute stabilizes and decelerates the capsule. The canopy weighs 2.9 lbs. without

riser and 5.9 lbs, includi_ the 30-ft. Dacron riser. The drogue parachute de-

ployment bag serves a dual function of (i) protecting the drogue parachute during

ejection and (2) providing means for orderly deployment of the drogue parachute.

The bag is manufactured of cotton sateen fabric reinforced with nylon webbing and

covered at the upper end with a heat insulator of glass cloth. The bag is

weighted at the upper end with a 0.5 lb. lead disc which assists in stripping

the bag from the canopy at the completion of line and riser stretchout. Inside

of the bag are _ cotton tapes to which the riser is secured during packing in

order to provide orderly riser deployment. The mouth of the bag is closed with

a light cotton cord.

9-7. m0uuE CN_E M_a A_D _

The drogue parachute ejection mortar is a device for positively deploying

the drogue parachute with sufficient energy to overcome local pressure gradients

and gravitational forces. The drogue parachute is packed in a protective bag

-C__":".":DZ;_T; A:.

PAGE

REPORT

MODEL

9-12

SEDR 104

133

McDONNELLST.LOUIS, MISSOURI REVISED

_ I_ I_r'__ ! _ I1_'_._..r_!"_P Lz.__.., REVISED

1 NOVEMBER 1961

I, ANTENNA FAIRING EJE'CTOR CBUN

2. PILOTCHUTE D_PLOYMP-N'T FdJN

5. PILO-r CHUTE

4. _OFAR E_4_ ( 2 )

5. SEA MARKER

6. SHARK REPELLANT

7.RF_ERVE CHUTE ANO BA_

8. EJECTION BAG_ (2) ,

9. GAB G_NERATO_S L2)

I0. INERTIA %WITCH

• fl. 5EQuENCE CONTROLLER BO×ES(,Z) /

12. c'_JRVIVAL KIT I

f3. MAIN CHUTE ANO _AG I

14. EIAROSWITCHE3 (4) I

t5. ANTENNA LANYARD I16. CHAFF PACKET I

t7. RECOVERY LIGHT I

I& WHIP ANTENNA I

19. PARACHUTE. OlSCONNEC'r_(2) !

20. DROGUE I MORTAR I II I_

NOTEt CAPSULE 8 ONLY

FIGURE 9-4 LANDING AND RECOVERY SYSTEM INSTALLATIONPM45-74C

pj_l_llpIlitpIl--- - ---vi I In il_ll_I1 i I_ L

DATE,, ,1NOVEMBER1961

REVISED

REVISED

Mc'DONNELL_'J_.___ST.LOUIS, MISSOURI

PAGE

REPORT .....

MODEL

9-1'3

SEDR 104

133

FIGURE 9- 5 DROGUE PARACHUTE

"_ L ' e"s r'_P"_'i"PI A |

I_

REPORT S_I_ i04

MODEL_ 133


._,,_,T.T_ _._Tr_Z_JL,=-- _ REVISED

and stowed in the mortar tube on top of a lightweight sabot (See Figure 9-6).

The sabot functions as a piston to eject the parachute pack 2 when pressured from

below by ga se s generated from a pyrotechnic charge. The propellant charge is

initially fired into a breach chamber of small volume, to produce high pressure

which is subsequently vented through a small orifice and into the main chamber

at relatively lower pressures. In this manner_ reaction loads are kept to a

minimum, since the pressure energy is _ot expended instantaneously. The pressure

sealing quality of the sabot is derived from an "0" ring t installed in a groove

near the base. Two small holes are located in the "0" ring groove to vent air

trapped in the mortar tube underneath the sabot on installation. For proper

operation, the "0" ring and the inner wall of the mortar tube_ which is always

in contact with the "0" ring, are lubricated before installation. The drogue

parachute pack is retained in its stowed position within the mortar tube by

a thin metal (Rene "_1) cover which is attached to the upper surface of the

antenna housing. Three cut-out sections, provided in the sides of the cover,

permit routing of the steel cable risers into the drogue chute can. The cover

is designed to constrain the chute in its compartment against negative decelera-

tions end also to require minimal forces to break loose from its attachments at

the time of deployment. Pressure of the chute pack causes the cover to deflect

such that attachment tabs pull out from under attaching screw heads through a

slotted hole designed for this purpose. The energy required to expel the drogue!

chute from its compartment is provided frcm high pressure gasest generated by

ignition of a pyrotechnic charge. The cartridge is loaded with 66 grains of

powder_ contained in a propellant can attached to a steel body which houses the

ignition wiring, and teminates in an electrical connector. The ignition cir-

cuitry consists of two separate and individual bridges, either of which is

capable of igniting the Lxr_der charge upon application of the proper current.

DATE

REVISED

REVISED

1 NOVEMBER 1961

ST.LOUIS, MISSOURI

PAGE

REPORT

MODEL

9-i5

SEDR 104

133

\

1. ['O" RING

2. ',SABOT

3. ICHAFF PACKAGE

4. INSULATION

5. ICOVER

6. ',C_TRIDGE

7. [CHAMBER

FIGURE 9-6 DROGUE CHUTE MORTAR ASSEMBLY

PAGE,, 9-16

REPORT _ I0_.

MODEL. I_B

9-8.

MCDONNELLREVISED

ST. LOUIS, MISSOURI

_'_ Ik.Jck,_l 41, ,ILU.IL,4J._I A

i November 1961

REVISED .....

CHAFF PACKET

The chaff packet is a locating aid which performs its function by distribut.

ing fine divided metal foil having radar reflecting capability. The foil strips

act as miniature antennae and are capable of providing an average echo area of

600 square feet, covering the S-_ L- and C-band radar frequencies. The package

is ejected on deployment of the drogue parachute. The chaff is packed in a

cardboard package of rectangular shape with dimensions approximately i x 3 x 5

inches. When Jettisoned into the airstreem, the package spills open and dis-

perses its contents.

9-9. _._ P_,_Jl_l_.

The main parachute assembly consists of: Main parachute canopy, riser,

deployment bag, and parachute disconnect. The main parachute canopy is a 63

foot nc_inal diameter ringsail type. The ringsail parachute is a slotted canopy

similar in design to the ringslot parachute. The parachute is fabricated from

2.25- and 1.1-ounce per square yard nylon parachute cloth into _ gores with

suspension lines of _50-pound tensile strength. The main parachute is

packed in a deployment bag which provides a low snatch force and orderly deploy-

merit (See Figure 9-7)- The bag is manufactured from cotton sateen fabric, re-

inforced with nylon webbing and covered at the upper end with Thermoflex and

glass cloth insulation. Inside the bag, midway along its length, is a pair of

transverse locking flaps. Their function is to separate the canopy fabric from

possible entanglement with the lines and to cause full time stretch-out before

canopy deployment.

9-10. PARACHUTE DISCORRECT

Both main and reserve parachutes are attached tO the capsule by a device

designed to sustain the parachute loads during descent and to disconnect the

J

_L'VtSEO ST. LOUTSa, M,SSOUm nZPORV _ 10_

Ev,s=o Moo . 133

parachute on ground impact (See Figure 9-8). The disconnect function is neces-

sary to prevent capsule upset or damage by dragging in surface winds after

touchdown. The assembly consists of 5 separate details installed in a mounting

structure which is an integral part of the capsule. The parachute riser is

looped around the arm which transmits the load to the structure through the

piston. The shear pin restrains the piston from any motion tending to displace

it. On ground impact, an electrical impulse from the inertia switch reaches the

squib cartridge causing it to fire. The gas pressure, thus generated, forces

the piston forward into the arm recess, cutting the shear pin in the process.

Full displacement of the piston removes parachute load transmission to structure,

allowing the arm to rotate around the pivot pin. The loop of the parachute riser

slips off the arm and the disconnect function is complete. The lead buffer

serves to absorb energy of moving piston and prevents rebound of the piston

back into the locked position.

9-ii. RESERVE PARACHUTE

The reserve parachute assembly consists of: The pilot chute deployment gun

and lanyard, pilot parachute, reserve parachute canopy, reserve parachute deploy-

ment bag, and reserve parachute disconnect. The reserve parachute deployment

bag is similar to the main parachute deployment bag with the addition of flaps

at the upper end of the bag to contain the packed pilot chute. The reserve

parachute disconnect is identical to that used to disconnect the main parachute.

The reserve parachute canopy is identical to the main Parachute canopy.

9-12. PILOT PARACI_

The pilot parachute is a flat, circular type, 72 inches in diameter with a

30 ft. bridle. It is manufactured of 3.5-ounce per square yard fabric in the

canopy and 2.25-ounce fabric in the vanes.

PAGE

REPORT,

MODEL

9-1S

SEDR 104

133

Mc,DONNF,LLLL DATE 1 NOVEMBER 1961

REVISED,,

REVISED ,

.FIGURE 9-'7 MAIN PARACHUTE AND PACKINGBOX

. s_UCTUR_ s.s._R PIN

SHORTING WIRE 6. PISTON

',31 SQUIB CARTRIDGE 7. LEAD BUFFER

• BUSHING S. ARM .

FIGURE 9-8 MAIN AND RESERVE CHUTE DISCONNECT

J

\, J

DAT _" i November 1961

REVISED.

REVISED

ST. LOUIS 3, MISSOURI REPORT _ lO_

MODEL 133

9-13. PILOT CHUTE _PLOYMEBT GUN

The pilot chute deployment gun (See Figure 9-9) initiates the first step

in the sequence of reserve parachute deployment. Either gas pressure or an

electrical impulse will cause the gun to fire, thus expelling a 12-ounce pro-

Jectile to which is attached the reserve parachute pilot chute. The pilot chute

inflates and in turn pulls out the reserve landing chute, ccmpleti_ the sequence

Whether fired electrically or pneumatically, a one-second time delay is provided

between receipt of the Impulse and detonation of the main charge. This delay

permits the main parachute (if deployed and damaged) to separate from the capsule

to avoid entanglement with the reserve parachute to be deployed. The gun is

basically a tubular body which contains the main firing cartridge and the pro-

Jectile assembly. The projectile assembly is held in place by a pin which is

sheared when the projectile is expelled. The main cartridge, which generates

the gas pressure to eject the projectile, is fired as follows: (i) Gas pressure,

through the gas flrln 6 mechanism (supplied when RESERVE-PULL-RIX} is operated),

drives a firing pin into the primer cap at the base of the main cartridge,

initiating a time delay train, causing a subsequent detonation of the charge.

A minimum of 750 psi gas pressure is required for pneumatic operation. (2) An

electric impulse is received at the time delay igniter installed through the

side of the gun. After a one-second delay, the igniter fires through the wall

of the main cartridge and detonates it instantaneously. Firing characteristics

of the igniter cartridge are as follows : All Fire Current 2.5 emps per bridge,

All Fail Current 0.5 amps per bridge. The ignition circuit consists of two

individual bridges terminating in a _-pin receptacle. _tzzle velocity of the

projectile is 2r)o-_X) ft/sec.

9-i_. PARACHUTE EMPTOR

The ejector bags are inflatable air cells made of lightweight rubberized

vva_a I_a_a Jd'TKJhne

PAGE

REPORT

MODEL

9-201

SEDR 104

133

M 'DONNE ST.LOUIS, MISSOURI


REVISED

REVISED, ,

II

FIGURE 9-9 PILOT CHUTE DEPLOYMENT GUN

FIGURE 9-10 PARACHUTE EJECTOR BAG

J

DAVE I November 19_i

REVISED

REVISED.

nylon fabric (See Figure 9-10). The design inflated shape is that of a cylinder 3

ii inches in diameter and approximately 35 inches in height. The upper end of

the bag is slanted at full inflation to promote Jettison of the parachute pack

overboard on landing impact.

9-15. PARACH_ EJECTOR GAS GEaR

This is a device to provide a rapid and sufficient volume of gas to inflate

the main and reserve parachute ejector bags (See Figure 9-11). The reserve

parachute gas generator is similar to that used for the main parachute except

the additional feature of one second delay in ignition time. The generator

functions to produce gas by the relatively slow burning of a solid powder pro-

pellant in the main chamber. The gas is directed from the main chamber into

the ejector bags through a 3/8 in. diameter stainless steel tube. The tube

serves also as a heat exchanger to reduce temperatures to within tolerable

values prior to entry into the ejector bag. The generator body is equipped with

lugs for mounting to the parachute container with four bolts. Ignition circuit

characteristics are as follows: All Fire Current 2.5 amps, All Fail Current

0.5 ups.

9-16. SOFAS

A post-landin_ recovery aid. SOFAR is an abbreviated form for "sound fixing

and ranging" (See Figure 9-12). This component performs its function when it

detonates by hydrostatic pressure at a predetermined water depth. Shock waves

from the explosion are received by sound detection devices sboanl picket ships

or shore bases and a position fix on the capsule is thus made. The

range of the Mercury SOFAR bombs is 3000 miles. Two Bombs are carried aboard

the capsule; one set to detonate at _ feet depth and one set for 3500 feet.

The b_b weighs approximately 2 pounds. One 3500 foot bomb is tossed over-

_ v i Ii I !11 I i ....

1 November 1961

REPORT _ 10_ REVISED-.4;T_LOUI$ ,_,MISSOURI

MODEL 133 ,.,v,,.-.,.uL_,, .... REVISED.

board at main chute deployment. The second SOFAR bomb remains with the capsule

and only serves to notify the search party that the capsule is sufficiently

(See Figure 9-13below the water's surface to render it non-recoverable.

for Operation. )

CAUTION

The bombs are relatively safe to handle, but it should

be remembered that they are high explosive devices and

hence common sense precautions should be practiced.

9-17. DYE MARKER PACKET

The dye marker packet (See Figure 9-14) is a post landing recovery aid

which performs its function by dissolving in water, thus producing a highly

visible yellow green patch. Approximately 1 pound of fluorescein dye is packed

into a soluble plastic bag, which in turn is packed into an outer aluminum con-

tainer. The entire packet assembly is ejected overboard, at the time of reserve

chute ejection. The fluorescein dye forms a spot on the ocean surface which is

visible from an airplane i0,000 feet high at a distance of i0 miles on a clear

day.

CAUTION

The dye marker package should be stored in a dry

place and not be exposed to water in any way.

9-18. _ECO_ LIGHT

To aid in the visual location of the capsule al_er landing, a flashing

light is installed in the recovery compartment. The intensity of the light is

such that it will be visible in normal darkness for _O nautical miles and up to

an altitude of 12,000 feet. The flashim_ rate is approximately 15 flashes per

minute. Powered by self contained, dry cell batteries, the light's circuit will

f_ g'a w.v r,_,','_ _ ------- •_ v J. , A A A.F A_ J. , £ £ ._A. JL

DATE

REVISED

REVISED

1 NOVEMBER 1961 M*,DONNE ST.LOUIS, MISSOURI

PAGE

REPORT

MODEL

9-23

SEDR 104

133

I 1 . ELECTRICAI_ CONNECTOR

2. MAIN CHAMBER

3. PROI_ECTIVE CAP

4. TUBE FITTING

5. ATTACHMENT LUGS

6. SHORT!NG PLUG

FIGURE 9-11 MAIN AND RESERVE CHUTE GAS GENERATOR

FIGURE 9-112 SOFAR BOMB

(,..m._ ...... _"1 A !VVIll iJb/Vllllll • ia 'l.I

2_4

REPORT $EDR 104

MODEL 13 3

McDONNELL ST.LOUIS. MISSOURI

• •,- . ,_,eat#l

DATE

REVISED

REVISED

1 NOVEMBER 1961

/

OPERIqTIO_q

DETONRTION OFTHE UAIN CHARGE 15RCCOMPLISHEDIN TWO ST/::IGE,5:

WATER PRE.%_URE ON .SURFACE ",q'CREATES /_FORCE 3UFFICIENT TO BREAK SHEAR PIN',q"PERI_IITTING THE INTERRUPTER BLOCI_ TO.t_OVE UPW/_RD /_GRIk/_TTHE 3TOPPING

SHOULDER. WHEN IN THIS POSITION_ THEPRIMEg CHRRGE 13 IN LINE WITH THE FIR-ING PIN.

B. W/_TER PRE53URE ON SURFACE 'B' CREATES

FORCE TO BREAK SHEAR PIN 'B' ANDDRIVE THE FIRING PtN INTO THE PRIMERCHRRGE. THE PIPIMER CHRRGE BLASTS IN-TO THE BOOSTER CHFIRGE VIR THE LERDIN ORIFICE_ fiND THE I_OoSTER CHARGECRUSE3 THE MPdN CHRRGE TO DETON-ATE, STRENGTH OF SHEAR PIN "B' IS PRE-DETERMINED FOR DESIRED DETONFITIONDEPTH. STRENGTH OF 5HERR PIN "R' I_SUCH THRT IT _IILL SHEAR RT A DEPTHOF RPPROXIMATELY ONE H/:ILF THE DEPTHREQUIRED TO 5HERR Plkl "B'.

SHEFIR PIN

SURFACE

DETON _TO R

LERD IN

BOO3TER C

MAIN CHRRGE

(O.? LB. HBX

FIGURE. 9-1.5 SOFRR BOMB 5CHE_FITICPM45-16;

/n_/_ILIPiii_IpI, I'q_u- - -=

_J

_J

R_VIS_D s'r. -ou,s -_.MISSOUR, nm=ORV. _DR 10_

R_VlSED _ MODe. 133

, f::\,

be closed through an energized contact of the Post Landing System Relay which

is activated by the closing of the Inertia switch on impact and energizing

the Impact relay. The light will operate for approximately 28 hours.

9-19. WHIP A_rE_mA

To provide operation of the HF voice receiver-transmitter and HF recovery

beacon, a Whip Antenna is used. The active element is stowed in a collapsed

condition in the recovez-j compartment and when extended is approximately 16

feet long. The antenna is extended by a gas cartridge which is activated when

the Post-Landing System Power Drop 30 Second Time Delay relay energizes the

Whip Antenna Extend relay. When it is extending a galling action takes place

between the segments of the active element holding it rigid in the extended

position.

9-20. BAROSWITCHES

There are two pair of Baroswitches used in the recovery system (See Figure

9-16)' In these switches an over-center spring is included in the design to

minimize chatter during vibration and shock and to prevent contact oscillation.

One pair of switches is set to close at 21j000 feet and the other is set to close

at 10,600 + 750 feet. The switches are located in the recovery compartment where

they are connected to a plenum chamber. The plenum chamber collects ambient air

pressure through four static pressure ports equally located around the recovery

compartments outer surface.

9-21. INERTIA SWITCH

The inertia switch is essentially a spri_ device actuated by mass (See

Figure 9-17). A landing shock of 7.5 plus or zLtnus 1.13g's _ will produce

momentary closing of two electrical contacts, thus completing an electrical

circuit. This switch is used in conjunction with a latching relay which receives

• m ! P'_ Im'lk |_lp, | I!

_it_llwa Ii aml,Na 11 • ia ._r--=--.

PAGE.

REPORT

MODEl,.

9 -26

SEDR 104

133


--_ L. a. :--_, I it1, ir, k ! ,,I- !. ,i_jm_

DATE ,,

REVISED

REVISED

1 NOVEMBER 1961

FIGURE9-14 DYE MARKER PACKETP_ 4-5-i?O A

a,.._ a,._ _. p. ..... ---v,._-i"li aL/r---I_l I I/_L.,.

_AT_ 1 November 1961

REVISED

REVISED

PAG- 9-27

sT. Loum 3,MlSSOUm RZPORT _ IC_

__C__ _!V_ MOnm. 133

an electrical pulse and, by latching into a latched position, provides continuous

electrical continuity. The inertia switches used consist of four Selmrate snap-

action switches and two separate masses, all housed in a common case.



The normal mission _equence and escape sequence for Capsule No. 8 differs

from the Specification Compliance Capsule as described in the following para-

graphs.

The reserve parachute is replaced with a flotation pack. This flotation

pack will be attached to the main parachute in such a manner as to act as a buoy

after main chute disconnect to enable recovery of the main parachute. Three dye

marker packets are installed in the antenna, fairing, which remains attached to

the main chute. These markers will assist in locating the floating main chute

and sn_nna fairi_.

9-2_. Operation

The capsule's landing system is armed by 28 volt d-c power at time of escape

tower separation. Both isolated and main battery power circuits are applied

throu6h the de-energized impact relay No. 1 located in the No. 1 recovery relay

box, through the de-energized No. 2 and No. 3 orbit attitude relays and the de-

energized No. 2 and 3o. 3 tower separation sensor relays located in the No. 3

launch and orbit relay box, to the two 3 second time delay relays located in

sequence controllers, units A and B. After the 3 second time delay both relays

are energized and complete two separate circuits to the four baroswitches. The

Baroswitch contacts will be open due to altitude being in excess of 21,000 ft.,

and therefore the power circuit will stop at the open contacts of the switches.

Upon re-entry from orbit, at an altitude of 21,000 feet the two 21,000 ft. baro-

switches are actuated and the drogue parachute is deployed and a chaff package

PAGE

REPORT

MODEL

9-28

SEDR 104

,133

Mc'DONNEL_L_ __._....ST.LOUlS o MISSOUR,/

DATE

REVISED

REVISED

1 NOVEMBER 1961

FIGURE 9-15 BAROSWITCH

FIGURE 9-16_ INERTIA SWITCH

r

! • r

"_±j

DATE 1 November l_l MCDONNELL,,_' '...7_ PAG_ 9-29ST. LOUIS 3. MISSOURI REI=ORT. _ 10_

Moola. 133i ,,

is ejected. The drogue chute stabilizes and decelerates the capsule; the chaff

package disperses finely cut metal foil. As capsule descent passes throu_ the

I0,000 ft. level, the two remaining baroswltches will close causing dual circuits

through the small pressure bulkhead disconnects to the system A and B sequence

controllers. These two circuits energize a main squib short (auto) relay within

each controller unit, resulting in the removal of ground circuits for all four

squibs of the antenna fairing ejector. At the same time, and by the same l_wer

that energized the relays, power is applied to the pre-grounded circuits of the

four antenna fairing squibs through the de-energized main over-ride relay. As

the circuits are completed to the four squibs, two other branch circuits are

applied to the two antenna fairing separation sensor limit switches. The firing

of the four squibs causes the antenna housing to separate fr_a the capsule. A

lanyard, connected frcm the antenna housing to the main chute, extracts the

main chute from the main chute c_npartment. The separation of the housing from

the capsule allows two antenna fairing separation sensor limit switches to spring

to their actuated position. Through these two double pole, actuated limit

switches, three signals are returned, two entering the system A and B sequence

controllers where they start two 12 second time delay relays, and the third

signal entering the No. 1 recovery relay box where it energizes the four antenna

fairing separation relays. Through the energized No. 3 antenna fairing separa-

tion relay, in the No. 1 recovery relay box, a 28 V si_ml is completed to the

Main Deploy telelight, illu_tuating the light Green. Power is also applied

through the contacts of the No. 3 antenna fairing separation relay to fire the

two Main Chute E_ector Bag Squibs. The firing of the squibs allow the eject

bag to be gas inflated end therefore, simultaneously eject the main chute as

the chute is being extracted by the antenna fairing lanyard. At the run-out of

the two twelve second time delay relays, the relay coils are energized and sa-maing

, _= lli,==llT=_ .......wwa., alllvL--i_l ! I¢'_ill.-.

30

REPORT _E_R 104

MODEL 1"_:_

REVISED---t_r..muls,..Mlssg.uR_,[._,

REVISED

the contacts of the inertia switch. At the time of landing the inertia switch

will sense the impact and complete two 28 V signals to the two inertia switch

slave latching relays located in system A and B sequence controllers. These

two relays when energized will in turn energize the two reserve and main Jettison

relays In their respective sequence controller boxes. The energized reserve

and main Jettison relays will fire the two squibs of the main chute disconnect

thereby releasing the main chute from the capsule. The reserve chute disconnect

will not be fired at this time. The main battery power circuit that energized

the system A reserve and main Jettison relays through the inertia switch slave

relay is now continued out of the system A sequence controller to the No. I

recovery relay box. This is the first time in the overall sequence that a dual

redundant circuit is not provided. This 28 V circuit to the No. i recovery

relay box passes through this relay box to the No. 2 recovery relay box where

it again passes through the de-energized air shutoff relay and out of the No. 2

recovery relay box after branching into two circuits. One circuit is applied

directly to the Astronaut's rescue aids switch and the other is returned to

the No. I recovery relay box where it energizes the four impact relays. Through

the energized No. i impact relay the self-powered recovery flashing light circuit

is closed starting the flashing light to operate. Through this same relay, power

is removed frcB the two 3 second time delay relays and the Main Deploy telelight

will go out. With the rescue aids switch clo_ed, a 28 V circuit is completed

to the No. 1 recovery relay box where it energizes the rescue aid relay. Through

the energized relay the Torus Bag Deflate 5 second time delay relay is energized

and starts timing. Power circuits to the two squibs of the reserve chute dis-

connect, and also to the two squibs of the reserve chute deploy gun and the two

squibs of the reserve chute eject "bag are-cc_rpleted. Simultaneously_ the reserve

chute is discounected_ the reserve pilot chute is deployed and the eject bag be-

.... _ : , -.: _. _-_ _-2L_-

DATE

REVISED

REVISED

1 NOVEMBER 1961

ST.LOUIS, MISSOURI

PAGE

REPORT

MODEL,

9- 3_1

SEDR 104

133

FIGURE 9-117 SEQUENCE CONTROLLER SYSTEM A AND B

REPORT _:_ 1011" REVISEDEl'. LOUIS, MISSOURI

MODEL. 133 • _ REVISED

neath the reserve chute is inflated forcing the chute out. After the runout of

Torus Bag Deflate 5 Second Time Delay relay the Whip Antenna Extend relay is

energized allowing power to flow to the whip antenna squib. The energized Gas

Cartridge extends the active element its full length.

9-25. Emergency Sequence

9-26. Description

The landing and recovery manually operated emergency system is the same as

the Specification Compliance Capsule but Capsule No. 8 is unmanned.

9-27. Components

9-28. Sequence Controller Assembly

There are two landing and recovery system sequence controllers located

within the pressurized section of the capsule (See Figure 9-18). These sequence

controllers in conjunction with three relay boxes accomplish all the system

sequencing and provide other capsule systems with initial connnands. The sequenc_

controller assembly contains the relays_ fuses_ and timers needed to accomplish

deployment of the chutes in proper sequence.;

9-29. TEST CONFIGURATION CAPSULES NO. 9 AND 13

Basically the same as Specification Compliance Capsule.

9-30. TEST CONFIGURATION CAPSULES NO. i0 AND 16

Same as Specification Compliance Capsule.

iJ

- 10-I

H

SECTION X

ELECTRICAL POWER AND INTERIORLIGHTING SYSTEMS

TABLE OF CONTENTS

TITLE PAGE

ELECTRICAL POWER SYSTEM

SYSTEM DESCRIPTION .....................

SYSTEM OPERATION ......................

SYSTEM UNITS ...............................

TEST CONFIGURATION CAPSULES.

_° ..................

............... °....... ...........

iiiiii!iiii_iiiiiiiiiiii_jN

i_[i!_i_ii!_i!ii!iiii!gi_i[i[![g;_iiiffiffffffff!ffiffffffiffffL--'_ff,

._iiiiiiiii!i!!iiiiiiiiiiiiiiii!ii_iiiiiii_iii_

==============================================================

iiiii!iiiiiiiiiii!i!iiiiii!iiiiiiiiiiii!ii!iiiiiii!iiiiiiiiiiiii_==============================================================================

.iiii_ii!iiiii!iiiiiiiiiiii_iii_!iiiii!iiiiiii_i!iiii_iii!!iiiiiiii_iii_iiii_.

10-3

10-5

10-11

10-12

INTERIOR LIGHTING ............................ 10-27

SYSTEM DESCRIPTION ..................... 10- 27

TEST CONFIGURATION CAPSULES. 10-30

_ A i Illll_ll'lZlllWll_l • I

_li_ V I I ! I liz_ lira I 1 i IN_l lira

7I

A

DIODE POW|

5WITCH FOSE PANEL

/ t/

i

\

[1_ C,t_PSULE16 NASI_00 WATt- HOUP_15_,TTE P..IE5 INTHESE LDCATIOI4 S

--- 1500 WAT THOUR BATTERY

BATTERYON*OFF

5',N ITCH

X REMOTE

7\

I

DETAIL'A"BATTEP._' ON'O.CF 5WITCH

ZSO YA _N_/ERTER5

PAklEL

OETAIL'C =

I_ELAY5

\\5NUNT

"" DE.TAIL'B'

__ ELF_CTRICAL POWEI_ CONTROL 'SECTION

(MAIN IN_'t'RCJMF-.NT _AI4EL)

/ Ii

/

"_ DE.Th, I I. _'C"

i:U 5E HO"H"_DEI:_'(TOP TO BOTTOM) /

_I P,E.'I'ROGRADE _P.ECO_ERY CSA) 1 ' / /

COMMUk_CATION5 (SA) _ \- l /

LAUNCH, 0_T _' ESCAPE (SA) --

MISCELLANEOLI5 (_0 _ ZS/_I 05_, ACCELEg, OMETEli:Itv_L5 C E LL A NEOLI'5 (_A)

I_ 0

m m

REVISED ST. LOUIS 3, MISSOURI REPORT _ 104

RSVISED _ MOO,=. 133

X. ELECTRICAL POWER AND INTERIOR LIGHTING SYSTEMS

I0-I. ELECTRICAL POWER SYSTEM

10-2. SYSTEM _ESCRIPTION

The capsule power supply consists of three main batteries, two standby

batteries and one isolated battery which supply 6, 12, 18 and 24 volts d-c

through control circuitry to the d-c power distribution busses. Distribution

is accomplished through high priority and low priority busses. Low priority

busses may be switched off to conserve battery power. External d-c power is

supplied through a diode panel prior to launch. (See Figures I0-i and 10-2. )

The capsule ammeter is used to indicate bus current when capsule power is

applied. Capsule bus voltage may be read on the capsule d-c voltmeter when

external power or battery power is supplying the busses.

The d-c electrical loads are supplied through fuses, except the "Abort"

Control which incorporates a solid conductor in place of a fuse. Some of the

d-c circuits utilize two fuses in parallel for redundancy, with a two position

switch which permits operation in the normal (No. i) Position or the emergency

(No. 2) Position. In addition s to prevent possible loss of power during an

emergency, a solid conductor is installed in place of a fuse in the emergency

(No. 2) position of the following circuits.

(a) Emerg. Capsule Separation Control

(b) Tower Separation Control

(c) Emerg. Main Chute Deploy

(d) Retro. Jett. Control

(e) Retd. Manual control

(f) Reserve Chute Deploy

(g) Emerg. Reserve Chute Deploy

.... _ .... ---_a 1row A |

PAGE

REPORT

MODEL

10-4

SEDR 104

, 133

, ,0

M 'DONNELL: , l" _'_ST_LOUIS. MISS_UR| _"

F " =""lmm_V a I u Jb,r _

DATE

REVISED

REVISED

1 NOVEMBER 1961

i RECOVERY IRELAY PANELNO. 2

I I_ELAY PANEL NO. 1III

,-T'_E ._s I_;IiS'_E " ', I_"__ I

I AF "_ it OI sQutts_ I

ARM _ JI RELAY --I1=.L

_40"T EE> t5oo w. _, _

C.APS. _G

r.._u _ _ _ ................

981

24V MAIN lPRE-IMPAET + I0 M.

9814.1 i

S4, i

94-1qq _

imo_

UI_glLIChLDISCONNECT

IS01

_us "IISOL

II,,

24- I_ *b -

;ISOLATED _ATT EEYIcjO0 W-H

FIOURE I0-2 D-C POWER CONTROL SCHEM_IE (CAPSULES IG,I_ 19)PM45-_ F

i_,,i p ili.i IE. 1 i,,,,,I p i _ _ - =...... .,_=,..= _= I IJ"=ll, IL-

The a-c loads are not fused because of Luherent overload protection in the

imverters.

The a-c power is obtained by using two main imverters and one standby

inverter to transform battery voltage to I15 volt, 400 cycle, single phase

a-c. The a-c voltage is fed through control circuitry to the a-c distribu-

tion busses.


10-4. D-C POWER CONTROL

The main 24 volt d-c power supply consists of three 3000 watt-hour

batteries. (See Figure 10-2). Each battery is connected in parallel to the

circuit by an ON-OFF switch on the battery. Individual reverse current diode

protection prevents discharge through a faulty or low battery. The 24 volt

d-c power from the three main batteries, or from the external power source

prior to launch, is supplied to the main d-c bus. The main 24 volt d-c bus

is connected directly to the 250 and 150 volt inverter filter inputs.

Two 1500 watt hour standby batteries are installed in the capsule to

supply communications bus voltage and to act as standby power for the main

system. The standby batteries incorporate diode reverse current protection

and are connected to the circuit through ON-OFF switches located on the

batteries.

Standby-battery taps, through diodes, supply 6, 12 and 18 volts d-c to the

various system busses. Prior to launch these circuits are energized by external

power through the umbilical disconnect and external power diode package. Stand-

by battery 24 volt d-c power application is controlled by the STDBY BATT.

switch on the main instrument panel. This switch may be placed in the OFF or

ON position. In the OFF position, the main batteries supply 24 V d-c power

to the capsule electrical systems through the main bus. In the "ON" position,

T__ ._:.": D -";.T :A L

REPORT _R1_ 104 "'t'IP._'tOUt$_'MI$$QURL._ REVISED

_"" _T_TL-" E _T_I_dIL_I_ REVISEDMODEL 1_3 _...

the standby 24 V d-c bus is connected directly to the main bus and both battery

groups supply power to the capsule systems in parallel. (See Figure 10-2).

An emergency hold circuit is utilized in event a HOLD command is initiated after

umbilical separation. To reduce cabin heating and provide external observation

through the periscope the emergency hold circuit removes power from the non-

essential circuits and also applies power to the cabin vent squibs and to the

extend motor of the periscope. Circuit switching is accomplished as follows:

The hold signal from the booster is applied through normally closed contacts

of the ground test umbilical relay to the solenoid of the No. 1 emergency hold

relay. Power from the main d-c bus is then applied through the normally open

contacts of No. 1 emergency hold relay to the solenoid of No. 2 and No. 3

emergency hold relays. Actuation of these relays_ removes power from some of

the nan-essential circuits, and energizes the impact sensor relay. At the

same time, power is applied through the normally open contacts of the emergency

hold relays to extend the periscope, and fire the cabin vent squibs.

A 1500 watt-hour Isolated battery is installed to provide emergency audio

bus and squib firing voltages and to supply emergency voltages to other circuits

in event the main and standby batteries are depleted. The isolated battery also

incorporates reverse current protection and is connected to the isolated bus

through an ON-OFF switch. Isolated battery taps supply 6 and 18 volts d-c

through self-contained diodes, to selected system busses. The 24 volt isolated

battery output is available through the ARM position of the squib arming switch

and through the EMERG position of the AUDIO BUS switch to the associated busses.

The Isolated 2_ volt d-c output may also be connected in parallel with the 24

volt output of the standby batteries through the STDBY position of the ISOL-BTRY

switch.

External d-c power is supplied through the umbilical cable to capsule

"k

:L ¸ i

_./

DATE 1 November 1961,I

REVISED

REVISED,

ST. LOUIS 3. MISSOURI REPORT ,_..T'_ i0_

Moo,,,, 133

circuitry. This power is used for pre-launch operations in order to conserve

the capsule battery supply. Normally 6, 12, 18 and 24 volts d-c are supplied

through seven inputs to the external power diode panel, however, only four

external power supplies are used to supply the 6, 12, 18 and 2A volt require-

ments. A d-c voltmeter and selector switch permit the Astronaut to read

individual battery and main bus voltages as desired. The d-c ammeter is used,

with the as_eter switch in the NORM position to indicate d-c load current from

the batteries in the circuit. A zener diode panel is incorporated connecting

zener diodes between ground and each of the Main and Isolated 24 d-c Busses

which provides protection for the transistorized equipment from transient spike

voltages (See Figure i0-2).

10-5. A-C POWER AND CONTROL

10-6. Main Inverter

Main 115 volt 400 cycle a-c power is supplied by two inverters of 150 volt-

amperes and 250 volt-amperes. The a-c load is divided into two groups namely

the ASCS bus and the FANS bus. The 250 VA inverter supplies the ASCS bus and

the 150 VA inverter supplies the FANS bus. The main d-c bus Powers the 150 VA

(fans bus) inverter through a filter circuit and a 25 ampere fuse. The 250 VA

inverter (ASCS bus) is also powered from the main d-c bus through a lime filter

and 25 ampere fuse. The d-c power is controlled through the NCRM. position of

the ASCS, AC B_s, and Fans AC Bus switches on the Main Instrument Panel. The

outputs of the FANS and ASCS inverters feed the solenoids of the Fans Bus Relay

and the ASCS Bus Relay. These energized relays feed the inverter output through

the closed contacts of the relays to Power the fans and ASCS busses. (See

lO-3.)

10-7. Standby Inverter

Standby IISV _ cycle a-c power is supplied by one 250 volt ampere standby

.... --;'-"''" a lv sis _aml _ a .l_m

PAGE

REPORT

MODEL

10-8

SEDR 104

133

M_,DONNELL___,_,_ (_,_,_......... ST.LOUIS, MISSOURI

DATE , ,

REVISED

REVISED

1 NOVEMBER 1961 ,,

[ MAIN INSTRUMENT PANEL!

FAt4S •

T_ SCS

SELECT CWITCH

_ 1Z/26VDC

• LT (AUTO) |prL

------otl

o

STBYOFF

r--o* 1

A_CS AC BUS

SW ITCH

STaY _

OFF'

No_,_o' ', Il

t-o'FANS AC BUSSW ITCH

STAN0BY

!NVEP.TEP,

Z50 VA

j,_ll(iMAIN IINV ERTEP. I

150vA IF_NS)__J

MAIN I

I zsovA IL_'"'_PLJ

i SI A_CS

5E ,_. D.C

III

_J

Ii

It

I

II

j ,

....,, _: _ _I T ,-J MAIM STBY _ MAIN J

I zsovA Iso v_ IL i.._,v..._|,'rER =.v _L.1,_E¢._j

, j

riIII

l' I

I

II

I

'iIII

POWEP-, SYSTE.M CONTROL

P,ELAY PARCEL NO. I

L.

m

! --

JhSCS BUSRELAY

P---O_ A

IrD

I"

FA-JN BUS_ RELAY

O'_D

IA

_--'_STAN DBY

T INV. POWER,

F.,ELAY

TIMER.C_TcHDIsCONI4ECT)

FIGURE 10-3 A-C POWER '.CONiROL .SCHEMATIC (,CAPSULES. I/o,I_.F))PM4-5- ZI5 IB

'_'_ I _11,_ I_11 I I

/_ -4

OATE i November 196_

REVlSE;D

REVISED,

ST. LOUIS 3, MISSOURi

inverter.

R_PORT SEDR 104

MODm. 133

The standby inverter will supply a-c power to either, or both, ASCS

and Fans A-c busses by selecting the STANDBY position on the respective ASCS

or Fans Bus switch located on the mai_ instrument panel.

In event of failure of either the 250 VA or 150 VA Main inverters the

respective Fan Bus relay or ASCS Bus relay will be de-energized. This action

will automatically energize the Standby Inverter Relay which in turn will apply

d-c power from the filter to the standby inverter. The a-c output from the

standby inverter is then directed through contacts in the de-energized ASCS or

Fans Bus Relays to their respective busses. A warning light on the Main Instru-

ment Panel indicates when the Standby Inverter is switched into operation by

reason of failure of either of the main inverters. (See Figure 10-3. )

10-8. POWER DISTRIBUTION

i0-9. D-C POWER DIS_I_JTION

D-C power is taken from three separate battery groups, namely the main

battery, standby battery and isolated battery. Various sub busses which operate

from these sources and the bus separation method are as follows:

(a) Main d-c bus directly to the main batteries.

(b) Main 2_ V d-c antenna separation bus from main bus through

separation relay.

(c) Pre-impact plus i0 minute from main bus through impact relay.

(d) Main 2_ V squib bus through SQUIB ARM SW from main bus.

(e) Pre-impact main bus through impact relay from main bus.

(f) Audio bus from main bus or isolated bus through AUDIO BUS SW

(3 position, center OFF).

(g) Isolated d-c bus directly to isolated battery.

(h) Standby d-c bus directly to standby battery.

(i) Isolated 6 and 18 volt Busses directly to taps on isolated battery.

......... ii-r_| - •--_ _m#" Jl _11 Jl J[ &mr &m| 11i i | J--_ J&m

PAGE

REPORT

MODEL,

10-10

Mc'DONNE :SEDR 104 ST. LOUIS , MISSOURI REVISED

133 ' _"_._,m_-- P4P_kll_-ir%L'_'_ _ REVISED


NOTE,S

_>:!/-Y _E fN3TALLEDIN CAPSULE FOR r3,ROUND q EST_ OR FLIG, FIT_h,lAY _:,E !NST?,LLE_ IN CAPSULE,FOR GRQUN.b TESTS3L___bONOT INSTALL Ikl CAPSULE, MAY _P_. ACTIVATE.) AND USED FOR #OWER.

._Y,._T=----...'N_TESTS/G;'-_OUND CA_T FOR."I'HFa,U THE HATCH POWE.I_"AND B4TTEeY CHARGERTE:ST,_

i

1-24 v,

OI::F

ON

A A

C, _4 D E._ev I_e

C

!

I •i i

I

I 24V Z4V

[_EAGLE PICHER MAR 4.02B-I, MAC 45-79707-15 (ISO0 W FI)

EAGLE PICHER 1,4AR4027-5, MAC 45-79707-21 ('..5000 WH)AGLE PlCHER _AIA 4028-A, MAC 4.5-79707-19 (I.500 WN)A&LE PICHER MAR4028-8, MAC 4S-7_707-19 (.ISO0 WFI)A&LE PIe.HER _AR4028-1_,,I'4DE4567020-5 (.1_00 WFt)

OFF

I "{EAGLE PICHER MP_R 4027C, MAC 45-79707-/7EAGLE pICHER MAR 4027-1/ MAC 45-79707-13_AG.LE PlCHER MAR 4027A/ MAC 45-797o7-17EAGLE. PIqHF_.P,_AR, 4027C/ 1"4DE 4587020-._

(SOO0 W/O(_ooo WH)(3o0o W_)C3(_o t4//4)

FIG 10-4- BATTERY' INTERklAL WIRING, DIAGRAMPM 45-93A

: \

i _ _i• i_J'

CO II, ! llll - . . - __•., ,P._.-'-;'.;T,r,.L

MC,DONNE REPORT _xE]_ 104 REVISED

.....St. ,_Outs, MISSOU_IMODEL. 1_ ....... _, " - " '_ REVISED


put in an ambient atmosphere of 160°F or at 80°F at 5 psia 100% oxygen. The

output is ll5 volts a-c + 5%, single phase to ground, with a frequency of 400

cycles + 1.0% and essentially sinusoidal in wave-form. A short circuit across

the output of an inverter will not damage the inverter or the wiring involved

in short circuit.

10-14. D-C AMMETER 0-50 AMPERE

The d-c ammeter is located on the main instrument panel and provides the

Astronaut with an indication of total current drain from all batteries. The

basic ammeter movement has a 50 millivolt sensitivity. A shunt of suitable

resistance is connected across the input of the meter providing a low resistance

path to ground with proper voltage drop for the meter movement.

10-15. D-C VOLTMETER 0-30 VOLTS

A d-c voltmeter, and its selector switch, are located on the main instrument

panel. Approximate battery condition can be determined by placing the D-C VOLTS

switch to the appropriate positions and reading the individual battery voltages.

lO-16. TEST CONFIGURATION CAPSULES

Deviations from data applicable to the Test Configuration Capsules are

explained in the following paragraphs and if no data is presented for a particula]

item, this item is the same as that used on the Specification Compliance Capsule.

lO-17. TEST CONFIGURATION CAPSULE NO. 8

The Electrical Power System on Capsule No. 8 is the same as the Specifica-

tion Compliance Capsule except for dlfferencea as noted in the following

paragraphs. (See Figure 10-6 for major components installed.)

lO-18. System Description

The Capsule Power Supply in Capsule No. 8 consists of three 3000 watt-hour

_-_v_.- _ .=..JJ.It,.4_.l JI. J_"L llj-

DATE

REVISED

REVISED

1 NOVEMBER 1961

McDOtNNEL LST.LOUIS, MISSOURI

PAG E 10-13

REPORT SEDR 104

MODEL | 33

L. /

PRE-LAUN.CNZ. HRS.

LAUNCH

.IHK

oRBIT_5 HRS.

RE-ENTR_(.5 HRS

POST

PERIOD

I?..H RS.

1oo ZOOI I

WATT&

300 400 500 _oOO 700 800 _E)O IC_)O {I00 (ZOO

I I | I I I I I I f

SZ4.q.- WATER %EF. 30 SEC/Bo ML_q.+.

I _51._- PROt%_AFAM£._ "A" 5OMIL-SEC/17.5 SIP_.I

To-30 MIN.---- _ -- T__LE.METV<'.(-ONi

I_ |QHF T'P,ARC_EI_VER, _8OOST ST_'I'.

Im /_¢. BAND BEACON-ON,To-IZ MIN. i "_ TAPE REC.ORb-O_

J &,S'S.q L PHOTO LIqHT,%- Og

To-(. M,I,,i.- h_--- s _ c _,_o ,E_,co_ ,NXERROC_ATiONl&:

$ "_UixA_ DI C.._:::_ "754-.o PERISLOPE RETKACT

• --_'7oo,8 '73Z.-/ It,lhT. CAM. _o PIJL/,SEC..

;:::_ "/_Z.7 PILOT CAM. _PUL/SF..C..

TWW. %EP. -- J TOWER SEP. B, OU"r_.

EBCApIE _KT'.

+

0N C_PB. ADAPT. BOLT5

CAP. $EP, -- . l POS_._TS._ UMS. O_C.

j[4 _O1._ PEP..IS:,COPE E'/,T.O_lr ATT_

-- _ 711.7 PILOT _ INST. CAM. _ PUL/SEC. _ %r._t_/5OMlkL

_9q.8 PILOT CAM, 5 PUL,/MIN.

6_].q 5C-ANgER HEATERS

67q.8 INSTR. r-AJv%. 3DPL_L/MIN.

_.8 $_-ANhIF.R5 SLAVE 8.5 MINI./30 MIN.

FI%#'7 9 _oG4-.5 I/HF TRANSMIT

" &,-_.5 HF TRANSMIT

I "Tq_.q P_O_AMME_ "h_"

50.Z PRO£_RAMMER "5" (C_D COMD. ONLY)

_OS.q REACT. CONTROL

"_S.9 WATEIW SEP.

.'7 _ _ C BAI_D 5EACOR II_"tEIW.O%A,,TIOP4,

(_OZ._ _LOOO PRE.SSL_RE 140 BEC./30 MI_,L

T.,-IO MIN L_:8._. 5

Tl_ "/5_.4- PILOT( IN.ST. CAM. (a PUL/$£C. %O %EC/3OMIN

im+ _O..%F.£.._..... F {-Sq.B I_ETRO RK'T'%. (B PEAK_)

-- , ..... 1-725-% _&TI_O AS.%Y. SEp.

II_. "IU _.._.-.-- I______ET_'.O UW%I_. DI&C.I

_0 8Zq.'5 PER|SCOPE _.F-To.0s_ --?.iK ,__ I,(o'LI.O DR_O%U£ MORTAR

IOK'--- _-_o?.Z.'_ ANT. FAIR- SNORKEL % MAIN CHUTE

_. '_"_ _'---- t_SZ. I PE.RtSCOPE, EAT (5 SEC_

_--- {_3Z.7 P,E_,CT, CONT'L (&,O ,%EC)IMPA.CT

RE,%. _ MI'4. DISC. (IMPACT + I SEC)

RE.S, _,JECT _ DER

_'75-dr" 9JH|i m AI,4T ENIqA.

(na/

'X:

A

,,90-:

I"-

¢%

.<o..J

>-IV

J

#-OI-

I_ESCUE AID,% _" 30 SEC. t ;"

IMP. ÷ IOMIN. IIO_°_

351.9 PROC_RAMMKR "A"

IZZ_-.9 WATER SEP.

FI&URF-. IO-5 D-C WATT _OUR LOADINr_ (CAPSULES , /0;l(o,lg _ (q) PI'4_S-Z74

v..,_.='ii ll./r-;-l'l I 1/96 _

PAGE

REPORT

MODEL

I0-I 4

SEDR 104

133


-:.t'_:d_,, Ig ! P ! I'% I_",1_ I "riP'1, , ALl_lPV I li i ;imw, a ¢ ! i IN ILB _liL_

DATE

REVISED

REVISED

1 NOVEMBER 1961

\

/

_[O o

,,40:: 0

_// _

\\

\

j

DAT__ i November 1961-

REVISED_

REVISED--

main batteries, one 1500 watt-hour Main battery, one 1500 watt-hour standby

battery, and one 1500 watt-hour isolated battery. (See Figure 10-7.)

D-c electrical loads are supplied through fuses except to the (1) Retro-

grade Seq. control, (2) Emerg. Capsule Separation, (3) Abort Control, end

(4) Auto Landing System A circuits - these circuits incorporate solid conductors

in place of fuses. S_ne of the d-c circuits utilize two fuses in parallel for

redundancy, with a two position switch which permits operation in the normal

(No. l) position, or the emergency (No. 2) position. In addition, to prevent

possible loss of power during an emergency, a solid conductor is installed in

place of a fuse in the emergency (No. 2) positions of the following circuits:

Retro Manual Control (No. 1 and No. 2)(a)

(b)

(c)

Reserve chute deploy - Systems A and B

Tower separation control.

A-c loads are not fused because of inherent overload protection in the inverters.

i0-19. D-C Power Control

Capsule special instrumentation uses two of the four main batteries. The

normal connector plugs on the No. 3 and No. 4 main batteries are tied back at

bundles 800A and 8013. Special instrumentation bundles 867 SI and 836 SI,

respectively, are connected to the No. 3 and No. 4 batteries.

The main 24 volt d-c Power supply consists of only two main batteries.

(See Figure 10-7.) Each battery is connected in parallel to the circuit by an

ON-OFF switch on the battery. Individual reverse current diode protection

prevents discharge through a faulty or low battery. The 24 volt d-c power from

the two main batteries, or from the external power source prior to launch, iis

applied to the main d-c bus. The main d-c bus is connected through the secondary

bus relay to the secondary bus.

The 1500 watt-hour standby battery is installed in the capsule to supply

196l _I3_W:IAON t

oss,^s_ ................. %"; ..L;,I "-'--"-' ..2'-="_ S

O.;l SIA.;II: I I_INOSSIIN ' SINo-rJ.S

_IVO&,,

££l "1300H

t_Ot II0_$ J-_lOd=l I:t

91-01.


REVISED

REVISED

ST. LOUIS 3, MISSOURI REPORT R_T)R i0_

_oom.., 133a_LL , ......... ,,

communications bus voltage and to act as standby gower for the main system.

The standby battery also incorporates diode reverse current protection and is

connected to the circuit through an ON-OFF switch located on the battery.

Standby battery taps through diodes, supply 6, 12 and 18 volts d-c to the

various system busses. Prior to launch these circuits are energized by exteraal

power through the umbilical disconnect and external power diode package. Stand-

by battery 24 volt d-c power application is controlled by the STDBY BATT switch

on the main instrument panel. This switch may be placed in the AUTO or MANUAL

position. In the AUTO position, a decrease in main battery voltage to a level

somewhat below standby battery voltage causes the No. i secondary bus control

relay to energize. Power is applied through normally open contacts of this

relay to energize the No. 2 and No. 3 secondary bus control relays. These

relays have holding contacts which lock their solenoids to the main d-c bus.

With the No. 2 and No. B control relays energized 3 power is applied to the

solenoids of the secondary bus relays. Energizing the secondary bus relays

removes voltage from the secondary bus and connects the standby battery 24

volt output to the main bus in parallel with the reduced main battery output.

The secondary bus relay also energizes the STANDBY D-C AUTO indicator light

indicating automatic use of the standby battery. Signal voltage indicative of

STANDBY D-C AUTO lamp operation is supplied to the instrumentation system.

The _N position of this STDBY BATT switch connects the standby battery

24 volt output directly to the main 24 volt d-c bus and through the secondary

bus relay to the secondary 24 volt d-c bus. No visual indication is made of

this use of the standby battery other than Astronaut checks of current and

voltage. An emergency hold circuit is utilized in the event of a "hold"

command after umbilical separation. To reduce cabin heating the emergency hold

circuit removes power from the secondary and the main ASCS busses and applies

/t_n

<i','.

f_

/,

"'_' ""'-_; :_G.,__ _ - a ,._ l _ll --_

O_

I"I

_0_r

• FI__

r_,

.,_r# .._

(

3, .o

I

70

IIIIIII

E_o m

/4 " re_ o I-_"-I m_l _"_-T"_

_gr'.4

I

, i

I

ii..... _j_Ic_z

_'Z

L96t }I]SW+AON I

O_ISIA=IId

03SIA3_I

_IVO

o ' T[_O(I_hT

££L

t_OL _lO]S

81_OL

..LUOd=lU


REVISED.

REVISED,

s-,-.Lou,s 3. M,sSOURI ,,_ORV _n 1O4

_' DV;_T;AL ,.,oom. 133

power to the cabin vent squibs end to the extend motor of the periscope. Cir-

cuit switching is accomplished as follows. The '_old" signal from the booster

is applied through normally closed contacts of the No. 3 ground test umbilical

relay to the solenoid of the No. 1 emergency hold relay. Power from the main

d-c bus is applied through normally open contacts of the No. 1 emergency hold

relay to the solenoids of the No. 2 and No. 3 emergency hold relays. Normally

open contacts of the No. 2 emergency hold relay apply power to the solenoids

of the secondary bus relays, impact sensor relay and to the extend motor of the

periscope. Other normally open contacts of the No. 3 emergency hold relay

apply power to the cabin vent squibs and remove power from the main 2A volt

Ascs bus. (see Figure lO-?.)

10-20. A-C Power sad Control

10-21. Main Inverters

Main, 115 volt, 400 cycle a-c power is supplied by one 250 volt ampere

inverter and one 150 volt ampere inverter. (See Figure 10-8.) The a-c load

is divided between the ASCS bus sad the fan bus. During flight when the ASCS

is the primary a-c load, the 250 Volt ampere inverter powers that bus while the

150 volt ampere inverter powers the fan bus. During re-entry, at approximately

300,000 feet, the fan system becomes the primary a-c load. Therefore, the In-

verters are switched such that the higher capacity inverter powers the fan bus.

The main d-c bus supplies input power to the inverter feeding the fan bus while

the secondary d-c bus supplies input power to the inverter feeding the ASCS bus.

The output from one inverter energizes the ASCS BUS RELAY while the output of

the other inverter energizes the FAN BUS RELAY. Inverter output is then

supplied through the energized bus relays to the appropriate bus. An A-C VOLT-

METER is provided with a spring loaded A-C VOLTMETER SWITCH which normally

closes the voltmeter circuit to the fan bus sad must be manually operated to

read ASCS bus voltage.

REPORT SEDR 10/4 . REVISED....sT. LOUlS, MJssou!_! _

MODEL l_ ........ ,,-,_nn,, • = , REVISED_ IL.4%.I.L, JL' .IL./I_4L_.I., 4L 4L.C'JkJL./-

10-22. S..t_sadby Inverter

Standby, 115 volt, 400 cycle a-c power is supplied by one 250 volt ampere

inverter. The STANDBY INVERTER switch determines which d-c bus shall supply

the standby inverter input voltage and whether the a-c output voltage shall

power the ASCS bus or the fan bus or shall automatically power either bus in

the event of main inverter failure. With the STANDBY INVERTER SWITCH in the

ASCS ONLY position, the standby inverter is energized by 24 volts d-c from

the secondary d-c bus. The standby inverter output energizes the STANDBY ASCS

BUS RELAY. The energized STANDBY ASCS _JS RELAY removes the main inverter out-

put from the llne nnd applies the standby inverter output.

When the STANDBY INVERTER switch is in the FANS position the standby in-

verter is energized by 24 volts d-c from the main d-c bus. The standby inverter

output energizes the STANDBY FAN _JS RELAY. The energized STANDBY FAN BUS RELAY

removes the main inverter output from the llne and applies the standby inverter

output.

The AUTO position of the STANDBY INVERTER CONTROL SWITCH allows the in-

verter to power either a-e bus should the main inverter feeding one of them

fail. Failure of a main inverter causes the associated bus relay to de-energize,

This connects the standby inverter input to the d-c bus used by the failed main

inverter and feeds the output to the proper a-c bus. The STANDBY A-C AUTO

light illuminates during standby inverter operation while in the automatic mode.

Should both main inverters fall while in automatic mode, the standby inverter,

operating from the main d-c bus, will power the fan a-c bus. Signal voltage

indicative of STANDBY A-C AUTO light operation is supplied to the instrumenta-

tion system.

No Emergency A-C Power switch is provided for use in Capsule No. 8. In-

stead, 24 volts d-c is connected directly through the No. 10.05g relay into the

/

J

MAC 231C (Rev 14 Oct. 65)

1, owber Mc,DONNEg. ..o. lo-2 nev,sED ST.LOU,S s, u,ssoum _e_oRv SEDR 104

REV,SeO . MOOre. 133

150 VA Main Inverter.

10-23. D-C Power Distribution

On Capsule No. 8, d-c power is taken from three separate battery groups,

namely the main battery, standby battery and isolated battery. Various sub

busses which operate frcm these sources and the bus separation method are as

follows. See Figure 10-7 for special instrumentation battery usage.

(a) Secondary d-c bus supplied by main d-c bus through secondary

bus relay.

(b) Secondary ASCS bus supplied by secondary bus through ELEC PWR RELAY.

(c) Pre-impact secondary bus through impact relay.

(d) Main 24 V squib bus through SQUIB ARM SW from main bus.

(e) Pre-impact main bus through impact relay from main bus.

(f) Audio bus from main bus or isolated bus through AUDIO _JS SW

(3 position, center OFF).

(g) Isolated d-c bus directly to isolated battery.

(h) Standby d-c bus directly to standby battery.

(i) Isolated 6 and 18 volt busses directly to taps on isolated

battery.

(J) Standby 6, 12 and 18 volt busses directly to taps on standby

battery.

10-24. D-C Power Loading

See Figure 10-13 for graphical summary of the Primary d-c Power Loading

on Capsule No. 8.


The Electrical Power System on Capsule No. 9 is the same as the Specifica-

tion ,ompliance Capsule except for differences as noted in the following

paragraphs. (See Figure 10-6 for major components installed. )

A A - -- ---

PAGE

REPORT

MODEL

10"22

SEDR 104

133

M 'DONNELjL_---_T_.OUlS,,.MISS_I..,,,

DATE

REVISED

REVISED

1 NOVEMBER 1961

-13

CbT

0

0

P_

o 8

F"

0

010

CO

01

.FIGL_E I0- q:

(WATT._)

700.8 PROGRAMMER 50 MIL-SEC/30 5EC

01

8,

T0-50_558.8 WATER _ER 30 5EC/3OMIN

TO-I2 L

v -- _:::l?2:_.BINSTRU. CAM. & PUL/SEC

_740.6 EARTH & _KY CAM I0PUL/MIN

UMB. DIS.---_ 774-.9 " 'UMB.DI5.---_ 774.9 PERISCOPE RETRACT

_::::_740.?_.PERISCOPE CAM. :3PULJSEC

-r,,,,,__.=-,::,_:::_'-Lt'_:--?4?-.lUNF TRANSMIT TWR SEe BQbT_

TWR. 5ER I PYLON JETT. & EECApF: RK'T.

rAo _=_ !_-&97'?- C/_R ADAPTI_R BOLT&........ I POS, RKT,& UNI_

_773.5 PERI5COPE EXT.

"rR--p7oo.8 RETRO RKTS ('3 PEAKS)

T +50 5EC-- "..... 1-,--726.4 R_TRQ ASS'Y SER

_R÷'_u _=u--[ RETRO UM8. DISC.

= 785.5 PERISCOPE RET._._.

1_'_-_"----787-.0 REACTION CONT.

.05(_ i..._59h 9

_6_9.2 HF&UNF TRANSMIT DROG E M

I0" ' !'_--594"5 SNORKEL.ANT.. FAIR. & MN. CHUTEow E----J"--_(,85.1 PERISCOPE EXT. ( 5 ,_EC)

-_J'--P_(,2_.I REACTION CONT. ((_0 SEC)

I_FOROF.SEN., MN. DI.9,C.,BES. E,,I'ECT, DER & DISC.

TORU.._ BAG YI_NT., M_N- HEUUM _ ANTENNACOVER

WHIP ANTENNa.-. (IMR-505SEC')

I 478.5 PROGRAHIER

_516.3 WATER SER

D-C WATT- HOUR LOADING(CAPSULE NO. 8)PM_5"- g-09 E

r'O""-'D-"t;, ;A_-1 i I i •


REVISED.

REVISED.

ST. LOUIS 3, MISSOURI REPORT _E_R 104,,

• " - MOOW. 133 ,

10-26. S_stem Description

The capsule power supply for Capsule No. 9 is similar to that used on the


i0-27. D-C Power Control

The d-c power control on Capsule No. 9 is similar to that used on the

Specification Compliance Capsule (Refer to Paragraph IO-A), except for the

following differences. (See Figure i0-7).

On Capsule No. 9 the Secondary bus control relays No's. I, 2 and 3, and

the Secondary bus relays No's. 1 and 2 are not used. The standby battery power

is connected directly to the Main d-c bus, in parallel with the main batteries,

with the standby battery switch placed in the "OR" position. The standby d-c

light (AUTO), or automatic switching of the standby bus to the Main bus is not

used. Operation in the "ON" position of the standby battery switch as well as

all other controls is the same as the Specification Compliance Capsule. The

hold relay operation is the same as used on the Specification Compliance Capsule

except additional contacts are used in the No. 2 hold relay to control the

Power to the electrical power relay from the umbilical discomnect.

10-28. A-C Power and Control

10-29. Main Inverters

Main 115 volt _00 cycle a-c power is supplied by two inverters of 150 volt-

amperes and 250 volt-amperes. The a-c load is divided into two portions namely

the ASCS bus and the FANS bus. The 250 VA inverter supplies the ASCS bus and

the 150 VA inverter supplies the FANS bus. The main d-c bus powers the 150 VA

(fans bus) inverter through a filter circuit and a 25 ampere fuse. The 250 VA

inverter (ASCS bus) is also powered from the Main d-c bus through a line filter,

a 25 ampere fuse and the antenna separation relay. The Main ASCS bus is

energized through the EL_ 1_ relay.

............ |!"'_¥1_ili i ll./_ll_ll • it-ilil--

REPORT SEDR 10_ REVISED..... ST, LOUIS, MISSOURi ......

MODEL_ 133 C,_ _'_ _i_) [1 _ TI._._ REVISED,

(Other ASCS d-c loads are fed from the ASCS bus.) The outputs of the Main

150 VA and Main 250 VA inverters feed the solenoids of the Fans Bus Relay and

the ASCS Bus Relay. These energized relays feed the inverter output through the

closed contacts of the relays and through the normally closed contacts of the

Standby ASCS Bus Relay to Power the fans and ASCS busses. (See Figure i0-ii).

The 250 VAC invez_ers are deactivated by the antez_,za fairing separation relay

during descent.

10-30. S_t_and_byInverter

Standby 115V _00 cycle a-c power is supplied by one 250 volt ampere standby

inverter. The STDBY INVERT switch determines the mode of operation and/or which

a-c bus shall be supplied by the standby inverter.

The EMER A-C position of the switch manually energizes the standby inverter

from the ASCS bus. Standby inverter a-c power then energizes the solenoid of

the Standby ASCS Bus Relay. A-c power then flows through the energized Standby

ASCS Bus Relay's contacts to Power the ASCS a-c bus.

The FANS ONLY position of the STDBY INV switch manually energizes the

standby inverter from the main d-c bus. Standby inverter a-c power then energlm_i

the solenoid of the Standby Fan Bus Relay. A-c power then flows through the

energized standby fan bus relay's cOntacts to Power the FANS bus. (See Figure

lO-n.)

The AUTO Position of the STDBY INVERT switch allows the inverter to Power

either a-c bus should the main inverter feeding one of them fail. Failure of

a main inverter causes the associated bus relay to de-energize. This connects

the standby inverter input to the d-c bus used by the failed main inverter and

feeds the output to the proper a-c bus. The STDBY A-C AUTO light illuminates

during standby inverter operation while in the automatic mode. Should both

main inverters fail while in automatic mode, the standby inverter operating from

//

\

dT_ _ _LT T_ T T-_ T_ .....

! •'!

-q

Frl

O|

C)

"X3O

F,1

C7313

Cn-tFrl

if--.

.'X3

C

(..n

io

,/i

I /

\s/

TO66LE

DIODE

5WITCH FUSE PANEL

/

1.500 WAT T

HOIJR BATTERY

0N-OFF

WtTC_

_EQ)

DETAIL'A"BATTERY ON-OF-F SWITCH

_N'4 E RTE_.5

PANEL.

OETAIL"C =

RELAY5

@@

• OFF

PWR O_F

I .___ .... I _ I aUTO |

s/

_ (MAIN IN_TRL}_F.NT PA_L)

• i

/ /

/ "_..

"_'1 P.EI_OGRADE _ P.EC.OVERY CSA) _'_ _, . /

/? RETROGR_,DE ( RECOVER'( C5 _ IOA) _, -- _ /

LAUNCH, ORBIT ItE_CAPE CSA) _ -- ._ /MISCELLA_EOtJ.T;, (_0 _' _SA,) "x-'05o. ACCELE'P.O_AETER - "

WIISCE LL ANEOU5 (SA) '_

g g m

13 0

0 m >

m pl

I

lOOK

lOOK

il

P,.ELAY

"1

.I

<<i __AC WA_N, LT.

;_ _ ----FANSAE. BUS

G_,_. "TESTUM_, EELA'Y

___ I?./Z.4. V O CWASH,. LTS. E_U._

;_ "um >

II.-I

1';

m m >< < --I

_ m

,/


REVISED.

REVISED


p._ 10-27

the main d-c bus, will power the fan a-c bus. Signal voltage indicative of

STDBY A-C AUTO light operation is supplied to the instrumentation system.

10-31. D-C Power Distribution

The d-c power distribution on Capsule No. 9 is the s_ne as used on the

Specification Compliance Capsule (Refer to Paragraph 10-8), except for differ-

ences as shown on Figure 10-7.

10-32. D-C Power Loading

See Figure i0-i0 for graphical summary of the primary d-c power loading

on Capsule No. 9.

10-33. TEST COHF]DORATION CAPSUI3S NO. i0, 13 AND 16

The electrical power system on Capsules No. i0, 13 and 16 are the same

as the Specification Compliance Capsule. (See Figure 10-5 for graphical

summary of the primary d-c power loading on Capsules No. I0 and 16, and Figure

No. 10-13 for Capsule No. 13. )

iO-3_. INTERIOR LIDHTING

10-35. SYST_q _gSCRIPTIONi

Interior lighting for the Specification Compliance Capsule consists of

four fluorescent flood lights and a series of warning telelights. See Figure

i0-I_ for iocatic.1 and arrangement of cabin and system telelights.

10-36. Cabin Flood Li_ts

Two flourescent flood lights are mounted on bracgets to the right and

left and above the Astronaut. Power for the cabin lights is supplied from the

115 V a-c Capsule invezCer Fans _ts and controlled by a three position switch

located on the lef_ console, the switch positions are marged "_>I_" "L.H. 0nly"

and "OFF". The cabin flood lights are of high actinic value_ especially suit-

able for camera usage. The lights produce little heat and have a low wattage

.-b_= ---- .... _w • |

PAGE

REPORT

MODEL

I0-:2,8_

SEDR 104

133,

McDONNELLjH__o_ST.LOUIS, MISSOURI

_Vlli I'llJ_lll i 18--_ l'-T'-

DATE

REVISED

REVISED

1 NOVEMBER 1961

0 /00

2 2j

ORBIT

1

2OO*

300t

�OK'

_31.0

I "7"/1. 3 PROGRAMER

3 9._ l-IF ,,?E r O VE R Y

28<A 3 WA TER 5ER

F/GURE I0:1_ D-Cw,_T_-HOU_LO._/NGCAPSULE NO.,9)

PM45 - _55

VVI _l aal_mlll _l • If'_ L-

£L_.-Stl_d

I

oo_l

1

I I I I I I

OOtl 000_ 00b 009 OOL 009 00"3

gllVM

0% - o.L

I i I iOOt 00£ DO?. OOI

£t;t

t,0t aa3s

6_'Ot

-I'_(]OW

.LblOd_t:T

_DYd

l_nOSSll_l ' S11"103"1S

L96L _I:ISW_AON L

G=ISIA_I_I

03$1A'_1_i

_.LVCl

70 ' McIDONNE_ %_r_ DATE 1 November 1961

REPORT SEDR lO_ ST. LOUIS, MISSOURI REVISED

13_ _a_l _.T _ _.__ REVISEDMODEL_

mtlng of four watts each.

10-37. Photo Flood Lights

nm='e 1o-15).

Two flourescent flood lights are mounted on brackets to the left and right

of the cabin flood lights described in Paragraph 10-35. The photo flood lights

are identical to the cabin flood lights and are controlled by a PHOTO LIGHTS

switch, which has an ON and OFF position. The PHOTO LIGHTS switch is mounted

on the left console.

1o-38. TeZeli hts

Warning telelights are proviaed for various capsule systems and are mounted

on the main instrument and left console panels as shown on Figure 10-14. The

telelights are connected to the various systems to notify the Astronaut of mal-

function of a particular system or verific•tion of an individual function.

Power for the telellghts is supplied by the Capsule 12V d-c or 24V d-c bus

through • five ampere IbASe as shown on Figure 10-15. A Dim-Brlght Switch is

provided for daylight or dark operations.

10-39. TEST CORF_ION CAPSULES

The data contained in Paragraphs 10-34 through 10-38 applies to the

Specification Capsule. Deviations fr_n the data applicable to the Test Con-

Figuration Capsules are explained in the following paragraphs. If data is not

presented for • particular item, then the item is the same as that used on the


i0-_0. TZST CONFIGURATION CAPSULE NO. 8,, ,,,

1o- 1. hood m ts

The, cabin flood lights on Capsule No. 8 is the same as the Specification

CoEpliance Capsule, except the control switch on Capsule No. 8 has "ON-OFF"

positions only. (Refer to Paragraph 10-43. ) No photo flood lights are used on

DATE

REVISED

REVISED

1 NOVEMBER 1961 Mc'DONNE #ST.LOUIS , MISSOURI

• __ . " ,,

PAGE 10-31

REPORT SEDR 104

MODEL 133

NOTE_

EE> _AME PL_E.

[_ _IOT II_-T'_t.t.F._ OI4 CAPeJ,_LE ¢)

......... I • •

_vilr Iur-iN I In_--'

PAGE ,, 10-32

REPORT S_ 104

MODEL. l_

Capsule No. 8.

i0-_2. Warning Telelights


REVISED

The warnin6 telelight installation on Capsule No. 8 is the same as the

Specification Compliance Capsule (Refer to Paragraph 10-38 and Figure 10-16),

except for the following differences.

(a)

(b)

(o)

(d)

(e)

(f)

The Periscope retract telelight is not used on Capsule No. 8.

The Lending Bag telelight is not used on Capsule No. 8.

A Drogue Chute telelight is used on Capsule No, 8.

The Cabin Pressure telelight is not used on Capsule No. 8.

The Fuel _antity telelight is not used on Capsule No. 8.

Mayday and Ready telelights are used On Capsule No. 8 in place

of the abort lights.

(g) A recording telelight is used on Capsule No. 8 to indicate

operation of the tape recorder.

(h) A Standby d-c Auto telelight is used on Capsule No. 8.

lO-_3. _ST co__o_ c_ _o. 9t lOt 13 A_ 16

The interior lighting system on these Capsules is the same as the Specifica-

tion Compliance Capsule (Refer to Paragraphs 10-35 through i0-_) (See Figure

lO-I_ _ lO-15).

_mw • AJ'q _'_ ILT IF'_ T _r_L _


REVISED

REVISED

Mc,DONNELL__ __ .PA_E ,ST.LOUIS. MISSOURI REPORT

_ l . MODEL

10_33,

SEDR 104

133

L:: • :,;

P IC_.,UIEEIO-.IBI_IEIEIOP.,LkC_HTS AND WARNIi',I_LIGHTS. scHE_ATIC(,cA_._I_I_i_._;)._v_._n=

li'l = "i:i-- _l Ill-I I ....

tvilr Ilrl/_lrl=ll ! ii iJ

I\

[_ Nh_ME PLATE

\

\

m >

11-t

i --¢'_

g g m

°°10 o

m

_ F 19,E_CUE MAIN DROGUE .OSG JET_. RETRO INR.ETRO. 5 TAR]I_. C'-A P_5--ULE TOWER GNt) _O_t.q _,ET_,0 R_,T5 t4"fR_ C_

_

!__ , 2 E

_1'15 ,o _E._,._ I I

EXCE55 EXCE55 OXYMAYDAY READY RECORDING STDBY, AC $'FDB"( Ex3 OXYGEN SUIT CABIN EMER.

AU TO. AU TO. WAR N, W AT E R WAT E R F LOW

WARNING LIGHTS

MAIN INSTRUMENT PANEL,.

Z ;0 OF! m >< < -!

0 0 :

/11 .

11-I

rji_,_+_._ •._:<_,_, _,

SECTION XI

COMMUNICATION SYSTEM

+

+++iiiiii+ii_iiiiii.:.'-ii'i_ii.-:.-_!_iii_::::::::::::::::::::::::::

iiiiiiMiiitMilttii_-_%

===================================

;:__iiiiiii_+:'_::!iiiiiiii_:

TITLE

TABLE OF CONTENTS

PAGE

SYSTEM DESCRIPTION ......................... 11-5

SYSTEM OPERATION 11-9eee.eeeo oeeeoeoeo el oeeeeeeee

SYSTEM UNITS .................................... 11-28

TEST CONFIGURATION CAPSULES ...... 11-36

el e'_'_._. _r ," _ +,'_V,_ "+

I _111 I1_1_i_!1 I_MI, L

• S

oo OW hl

I--

Q -' I1:

[

IZW

a.

ONION___VdWl

IN_/AOld30"

_,LnH_Nt_A_t

E:

NOSlll_r

9N1_1¥_

VNN31NY

NOSlll_r

_V_DVd

I

\

\

illlZlO

_ _

gI, IIglNV1 1!;0,1 g

l_VdWI I,

A_J.NZ-|II [

.1.111_lO

llS_lO Ol H:_Nnv'i [

(ONIWWVZlgOZld _!0:1 [-II 311_V1 33S)

'3_N3nO3s NOI/DNN:I NOIIY31NnWWO_

J, • /

/

NOIIV_'d_S _l[1SdV_

I

/ _ NOSll,l._r_,_0.1.

/I \ _vosn

u

r

A'STEONAUT'5 I_E.LMF.T(HEABSETS

t s

//

iI

]Jit

"--UHF Soo_'r,_MPUR_

ANTENNA ML_TI PLEXER

MAIN UHF RECEIVE:R-TRANSMITTER

IJHF- DE:,

SWITCH _T_ANSMIT SWITCH

VOLUM LCONTROLS/_ L X

I I_ llfmllll_llli_ltl_<_,I I _ I ll_WJII IIIL--III IILILL-IIII '_ _ u. _H_ .sEuEcrI 1 uc_--Ju._u._u " ,.o _'\ ._

PANEL (ANT SWITCH) DETAIL ASELECTOR

HANDLE " _WIT_H:(,M ICROPHDNE

5WITCH)

. r-.)-IFRECOVERY ANTENNA

, _ / (STOWED)

.--_ I /--- UHFIIESCENT.AND

/_ _ / RECOVERY ANTENNA

"_'Z "'",_.___/-_ ' (BICONE ANTF-UI'_A'_

/

-. (,.. _o"_X_,_I '°"_'"

:UMBILICAL DISCONN,F..CT_"

AUDIO CONTROL PANELSEE DETAIL k

XI _ 0

g g m

CO14_IffICATIONI_'NCTIONS

CALL CAPSULES).

FJRCTION

m_' (_,, _,_,_:,) R/_

m,' (_) R/_

_ (_) RI_

HF (Recovery) R/T

C_and Receivers

Telemetry Transmitter

C and S Band Beacons

C and S Band Beacons

UHY Recovery Beacon

H.F. Recovery Beacon

Aux. UHF Rescue Beacon

Ultr. Sarah Rescue Beacon

Unmanued Capsules - No. 's 8, 9Manned Capsules - No. 's 10, 13,

LAUNCH ORBIT RE-ERTRY POST LANDINGIMPACT

Astronaut Selection on All Manned CapsulesI I !Pre-Launch Selection on All Unnmnned Capsules

i IAstronaut Selection on Manned

Capsules

iPre-Launch Selection _--

on Unmanned Capsules

-_ -- All CapsulesI

._ --All Capsules

I-_Manned Capsules - On Continuous

or Controlled by Astronaut and/orGround. CcmnaudI I

_-U_d Capsules - On Continuousor Controlled by Ground Command

I

Bicone Ant. Separation

Bicone Ant. Separation

I16, 18 & 19

-_---Al.lC_sules

v

=-i0 Minutes After Impact

, All Capsules

All Capsules

ii0 Minutes After--_-Capsules I0_13,16,18 and 19

Impact I

Capsule 8 & 9 only

MCDONNE ll-5R_-VtSEO. ST. LOUlSa. M,SSOUm _ORT SE_ 104

.... \

--f,

XI. COMMUNICATIONS SYSTEM

ii-i. SYSTEM DESCRIPTION

ii-2. VOICE COMMUNICATION

The Astronaut Is provlded with volc_ communlcatlons throughout the entire

mission (See Table ii-i). A dual headset and microphone contained within the

Astronaut's helmet, operate through the audio control circuits to the selected

voice communications set (See Figure 12-2). A capsule-pad Luterphone system is

available prior to umbilical cable disconnect.

HF reception is available through the main KF voice communication set during

launch and orbit. HF voice transmission may be used only after capsule separa-

tion by Astronaut selection of the HF position of the Tranmnit Switch. The main

set is disabled during re-entry as the antenna fairing is Jettisoned. It will

be de-energized and replaced by the recovery HF set upon landing. The recovery

HF voice communications set provides reception and transmission, during the post

landing phase of the mission.

UHF reception is available throughout the entire mission by the Cc_m. UHF

voice communications set and its UHF Booster Amplifier. Transmissions over this

setmay be made when the "UHF" position of the TRANSMIT switch is selected by

the Astronaut. A backup (low power) UHF voice cce_unication set identical to the

main set, but without the UKF Booster Amplifier, may be placed in operation by

the Astronaut at any point during the mission.

The selected transmitter may be energized by operation of a push-to-talk

switch_ or by a voice operated relay when the VOX switch is in the "ON" position.

By speaking into the microphone, the selected transmitter is automatically

energized. Normally the selected UHF transmitter will automatically be energized

upon landing to provide a direction finder signal. This automatic feature may be

_J,J,;_D; D-,_.i4T;AI.

l.....

REVISED ST. LOUIS 3, MISSOURI RI[PORT _ 10_

REV,S¢. ................. MODm. , 133

overridden by the Astronaut.

The Cc_mmnd Receivers provide an emergency ground station-to-capsule voice

communications channel throughout the mission until capsule impact. Power for

the voice communications systems is supplied through fuses located in the

CQmmunications and Ccmnunications ASCS fuse holders (See Figure ii-2).

11-3. COMMAND RECEIVERS

Two separate sets of receiver-decoder and auxiliary decoder units are used

for reception and decoding of ground ccmnand signals. These signals are for th_

purpose of activating various capsule control circuits.

Power for the command receivers is supplied through the fuses located in

the Cc_unications and the Communications ASCS Fuse Holders (See Figure 11-10).

ii-4.

Telemetry transmitters are provided for ccm_mieating capsule information

to ground stations. Information is picked up throughout the capsule in the form

of voltages from vol_a6e divider circuits. These voltages are modified by coding

circuits to sul_ly suitable inputs to the telemetry transmitters. (Refer to the

Instrumentation Section XIII of this manual). Two transmitters are used for

transmission of the telemetry information, each having a power output of 3.3

watts. Their frequencies are slightl_ separated. Transmitters are operated

continumasly frum launch, until i0 minutes after impact. The power outputs of

the telemetry transmitters are fed to either the main or the UKF Recovery

Antenna. Power for the system is obtained fr_n fuses located in the Instrumenta-

tion Fuse Holders (See Figure 11-_ and Figure 11-11).

_-5. z_co_s

The beacons provided in the capsule to aid tracking by ground stations are

a C-Band end an S-Band beacon, a UHF recovery beacon, energized during re-entry,

_, .... -- w _"lr"% !'1" ! AItWINIi" i lll*llli . . ...__

,....

U'_.C:

m

i;o

ANTENNA

SWITCH

El

-TELEMETRY

ANTENNAL POWER SUPPLY

MULTIPLEXERTELEMETRY

TRANSMITTERS

\INSTRUMENTATION

PACKACE"C"

MAIN INSTRUMENT PANELDETAIL A

RL'VmED. rr. Louts 3. M,ssoum Rm:,owr ,Sg_, lOk,

.SVmED. --- ..... ,,,or,,- 133

an aux. UEF beacon energized 10 rain. after impact, and an HF recovery beacon,

energized upon land_. These beacons provlde signals compatible with direction

finding equil_nent used by the recovery crews. The U_ voice communications

transmitter may be keyed upon landing to provide an additional signal for

direction finders. A flashing light is installed for visual location of the

capsule after landing. (See Section IX of this manual. )

Capsule power for the beacons system is supplied through fuses located

in the communications and ASCS fuse holders. (See Figures II-_ and 11-12).

The voice communications, telemetry and beacon receivers and transmitters,

with their various frequencies and types of outputs require an antenna system

with wide capabilities. Therefore, four types of antennas are used to fulfill

the entire mission requirements. A main HF-UEF antenna is used for the major

portion of the mission. During re-entry this antenna must be Jettisoned to

allow main parachute deployment. To replace the UEF function, a compact UHF

antenna is automatically placed in operation. Upon landing, an HF Recovery

Antenna is extended to permit HF operation. Throughout the entire mission, C

and S band antennas are provided for operation of the radar beacons. Antenna

switching and multiplexing are Performed autcmatlcally by the RF circuitry.

(See Figures 11-6 and 11-13). Power requirements for antenna switching are

supplied through a switch-fuse located on the left console switch-fuse panel.

(see 11-13).

11-7.

11-8.

11-9.

OPERATION

VOICE COMMUNICATIONS

Audio Control and Ground Inter_hone ST_em

HF and UEF receiver outputs are routed to the control panel. This panel

1_*Vil_lla la,..__. _ Jl _ ___

11-10 DATE 1 NOVEMBER 1961PAGE

REPORT

MODEL

SEDR 104

133

ST.LOUIS , MISSOURI REVISED

REVISED ,

/

/

/, //

\\.,

\\

==

g

/

CC, ;,i F; C_,_- ;,iTiAL

REVISED. ST. LOUIS 3, MISSOURI REPORT... _ ]-0_

Revis_ __,'_ _ I _, ,-_,- L ..... 133_ Rm_R_Y_'_._ _ __,_, __-_ ,_.-- MODEL

' i

_-_:_

provides one volume control for HF audio and one volume control for UHF audio.

Outputs from the two c_and receivers are connected to the Co-_unication Control

Panel for mixing. Separation of command and voice audio signals by a low pass

filter, and amplification of resulting voice audio is done in the control panel_

(See

Communication audio signals from the volume controls, the interphone audio

from the pad-to-the-pilot and alarm tones from the satellite clock are supplied

to the tape recorder relay and the two headset amplifiers in the audio center.

The headset amplifiers serve to amplify the audio signals and feed them to the

individual earphones in the Astronaut's helmet. The de-energized position of

the tape recorder relay supplies a path for receiver audio to the main tape

re corder.

Audio from the microphones is fed to two separate microphone amplifiers

in the audio center. These two amplifiers serve to amplify microphone output

' to a level sufficient to supply modulation circuits of the voice transmitters.

The microphone smplifer output is also fed to the input of the VOX (voice

operated relay circuitry). The voice circuits are energized by use of the Push

to Talk switch on the abort handle, or by the VOX circuit when the VOX switch

on the instrument panel is in the "ON" position.

ii-iO. KF Voice Communications

11-11. Main HF Ccmnunications

The main HF voice cc_mnications set is an AM receiver-transmitter unit

designed to operate on a frequency of approximately 15 MC.

Power from the main pre-impact 24 volt d-c bus is fed directly to the

receiver section of the set. The transmitter is fed 2It volts through the EF

Position of the Transmit Switch and the closed contacts of the tower separation

relay, after tower separation. Audio input to the transmitter Portion of the

....... .,_,..a i_ ! _, ,..

P'_E. ,,.'1_ MCDONNE_ __ D_TEREPORT SEDR 104 ST.LOUIS. MISSOURI REVISED

_' ".-_ m •

MODEL 133 ___-__ REVISED

1 NOVEMBER 1961

PM4S-IO'7,D

e,1 o

I-,

ld 0 I_

< Id 0a. It

0

P_.

3-I

..=.

o

w __ m

W &d

i i

73NVd .[N3_Nn_ISNI NIV_

Id

n

Id

ONOHdO_31_ 0N¥ J.3cJOV:IH)I_33H. SolI_VNO_JIS¥

' I

• /

/f

}

• IMPACT BICONE

pRE-i_Cr iillJ u:7¢1 _4V _:: BL)S.JlI_ I A iMPACT J TO I_I_CEIVE . T

i1.1 t i lie, ......... / HF VOLUN_F_ / SWtTCHE_

I ._J _ IA|CROPHONE AUDIO IC AS DESIRED . .. t'_lNO'i,TOt-lo-2

/ I I I I_ '°_iT

A_TRON_UT_'_ tAF.LIV_ENT I I | / SWITCH OR USE SWiTC_4 |('_E _. D6EI" AN{:)

lY'dC RO PI40 NIE) 1 I / .a Iv VOICE OPE_J_TED -'_

i SER /

IL_CEIVE2

. V'OX OFI:

, iiI IV_A_N |NSTRUh_ENT _:::_Ak_F..L

--'_ANSMtT_ER CONTROL-- H

-- MICROPHONE. AL)O_O C

RIEL/_y I_

AUDtO _ I

NOTE[_VOICF.- O_R_,TEO BELAY CONTROLLED

SY VOX BWiTCH

_,VA_ L A,E_ L _ AFTE_

LAN £)iNC__

TO _.ECE _VF..

NF VOI..U bAR

AS DESIR_D

T(3 TRANSIenT

OPE2_TE I_AIC _PHO_ E

Sw_'_C_ O_ USE

VOtC_. _::_ _ATEO

_ELAY"

J

H F RECOVERY

ANTEN N,_

AVAIL A 5LE ,c_FI'E{_

LANDIN_

H F RECOVERY VOICE

R:ECE _VEI_ -'Te..A_5_TTE 2

[ ;o 11) m ).

-,t

m Z

;_ 7o o

g g mm mo o

I .] z0

m

R_VISED ST. "OUm s. MiSSOURi ma:ORT. SE_ 10_

REV:sEo. . ........... _oom. 133

unit is from the microphone amplifier in the audio center. The transmitter is

energized either automatically through the VOX circuit or manually by thei

Astronaut's use of the push to talk switch. (See Figure ll-8).

The antenna connection from the set is through the antenna multiplexer and

the antenna switch to either the bicone or the UHF Rescue antenna. HF raddatiau

from the descent autenna is negligible. Audio output from the receiver, includ-

Lug sidetone during transmission is routed to the HF volume control in the

control panel.

ll-12. Recovery HF Ccemm_uications

The recovery HF voice comnmicatioms set is basically the same as the main

HF unit but with the transmitter having a lower output.

The power input to the recovery HF unit is supplied upon laudimg, through

the impact relay, from the audio 24 volt d-c bus. Audio is supplied and keying

of the transmitter is in the same manner as the maim set.

The antenna connection is through the recovery dIplexer to the extended

HF Rescue antenna. Audio output from the receiver, including sidetome, is

routed through the HF volume control in the control panel through the audio

center and to the headsets.

11-13. UHF Voice C_icatlons

ll-14. Maim UHF

The main UHF voice camumicatious set is am AM receiver-tramsmitter unit

designed to operate on a frequency of approximately 299 MC. The transmitter

output is increased by a separate _THF booster amplifier.

Power fram the audio 2_ volt d-c bus is fed through the HI-PWR position

of the UHF Selector Switch directly to the receiver section of the set. (See

Figure 11-9). This power is also fed to the Transmit Switch. Power for the

tramsmitter section of the set is then taken from the UHF position of the

!1-16 ..... _ f3__ DATE 1 November 1_961

ST. LOUIS, MISSOURIMODEL,, 1B3 ............_,.,_,_"..............,.,_, _._-_.._ REVISED,

Transmit Switch. At bicone antenna separation the bicone separation relay con-

tacts assume the same function as the UHF contacts of the Transmit Switch thus

providing a continuous UHF signal for DF purposes. Audio input to the trans-

mitter portion of the unit is from the microphone amplifers in the audio center.

The transmitter is energized either automatically or manually by the Astronaut.

When the HI-POWER set is selected with the UHF Selector Switch, it will be

energized automatically at bicone separation to provide a UHF signal for direc-

tion finding equipment. This feature may be overriden by operation of the UHF

DF Switch on the control panel to the OFF or the UHF position.

Antenna connection from the set is through the UHF booster amplifer coax

switch, antenna multiplexer, and the antenna switch to either the main bicone

or UHF rescue antenna. Operation of the microphone switch or energizing the

voice operated relay while in the UHF mode causes the booster amplifier to be

inserted in series with the coax line. Transmitter output is then boosted by

this amplifier to 2 watts. The booster is also available after landing. The

multiplexer output is connected through the antenna switch to either the main

bicone or the UHF rescue antenna. Audio output from the receiver, including

sidetone during transmission, is routed to the UHF volume control in the control

panel.

11-15. Backup UHF

The Lo power USF voice communications set is identical to the main set but

without the booster amplifier. It may be energized by Astronaut operation of the

UHF Selector Switch to the "LO Ir_R" position. Power input, audio input, receiver

output, and the control of the transmitter is in the same manner as used for the

main UHF set.

Antenna connection is routed through the UHF coax switch, which has been

energized by selecting the "LO PO_R" position of the UHF Selector Switch, throu_

1

MAIN• POWER :UH_ VOICE

_EC EIVER.- TR_kN$_ iTTER

,]l_. I_ICROPi-IOt4E AUDIO _ 30 REC'EIVE (_E]

"_ TRA / UNF SELECT _,WITCI4 -

NSMITTER CONTROL 1" .oR_

UNF VOLUk_E-A$ DEStRE£

RECEIVER AUDIO-- 1" TO TP.ANSMIT

/ u.r _.-_ 3G NORI_.

/ TR_N ", MIT 5WtTCI4 - UHF

r -'_ _ _E OPERATE MICROPHONE

| .-_ _ BICOh_E. SEP J 5WITrN OR USE VOICE _ I

1 _ /...,,I. la.I_LAy , _ I I

_. 'I_--'_'_K OPERA'TED RELA+ _E] /AUDIO Z4VDG - ,.L.u= .] - .L+ ++,,.. I o_-_o.,-i.uo_,=I

_ TRAm+mlTTER POWER-- F --

/ ,J I I " Hi Pw_ tb _) I I Ut4FDFSVVITCI-J-t,.tO,I_ /

I l I I VOLUME _ _ _ |

t t tf

" " :-I _&-- '

, - -, .11 '1I - W + I I ; _ _,,_m ImstitumeNt +_._L r ----'------d I ' , q

LI ,,,.,,,,,,,_ _..o.,.,,_i i i,._ _ / "-I ,

-- ! ....... I-I- t ,.,,'rE.,,,,,,,L/" I0 I Q : 0 I O t "d 3 _

_ / laF OFF uHt=.J F- .'--'"7 _ _ SWITCHE_ TO flO 7.

BtCOl_E _PT::_F.t. A'V'

}1=

TRANSMIT'TER POWER

'_ RECEIVE_ AUDIO

,IK>_

_l_ T R_,NSEAITTER CONTROL-

NOTE

Mt CROPHO_E AUDIO

EE_ VOICE OPERATED RELA"( CONTROLLED BY VOW' SWITCH

[_ "To REC'EIVE AFTER IMPACT, AL_.O PLACE UNF DE 5WITC_ TO R/T, POS=TION

TO DECEIVE (_E],,,.--,I

'E UHF 5ELECT 5WITCH-

RESERVE

UI-iF VOLUME-AS DESIRED

KI TO T P,ANSMIT

UNF ,SELECT 5WITCR-

F I RESERVE

• T_AN,SMIT SWITC_-IJ¼F

eI OPERA'_E MICROPHONE_WiTcHo_USE'.'O,C_

DF- _o N TINUOLI S

I314F SELECT 5WITCI4-

LO PWK

--t UHF Or= SwITcl4 -NORM,.

II

I]

BACKUP UHF VOICE

_ECE IVEE -TRAI, I$_ITTER

Iit+

ItI

D m >

-11 m m-t

18

REPORT SEDR-104

MODEL. 133

McDONNE DATE 1 November 1961

REVISED-,,_ST. LOUIS.,. MISSOURI

"/'_'_T ...... n.,.,- • _."_ REVISED_,_,_._ 4,_I.IL .iL,LJ41.JJ. ll JL JL,Z-LJ.._

the UHF booster's coax switch, the antenna multiplexer and the antenna switch

to either the main bicone or UHF rescue antenna.

11-16. Command Receivers

The receiver-decoder unit consists of an FM receiver operating in the

frequency range of 406 to 450 MC. The received signal may be modulated with a

maximum of six of a possible twenty audio frequencies. The receiver reduces

the input signal to the modulation frequencies which operate individual control

relays. (See Figure 11-10).

Each control relay provides contacts for a normally open or a normally

closed control channel. Ten channels are provided in the "A" recelver-decoder

with an additional ten available in the "A" auxiliary decoder. These channels

are paralleled by the output of the "B" receiver-decoder, and auxiliary decoder

units. Command channel assignments are not disclosed for security reasons.

Emergency voice communications may be had from the ground station to the capsule

through the command receivers. Receiver outputs are supplied through a filter

and amplifier in the audio center circuits to the Astronaut's headset. Power

for the Hi frequency command set is supplied from the isolated 18 volt d-c bus

while power for the Lo frequency command set is supplied from the standby 18 volt

d-c bus. Both power circuits are routed through sections of the impact relays

in order to de-energize the set upon landing.

Antenna input is from the bicone or UHF rescue antenna through the antenna

switch and antenna multiplexer to an impedance match which supplies both re-

ceivers.

-17. Telemetr v

11-18. Low Frequency Telemetry

The low frequency telemetry set is an FM transmitter operating on a fre-

quency of approximately 228 MC.

"_D_4T_ Lr_ _LT T_ T w-_ 5T_

s_A'*,.,,L.'_*L .LLA'.LL_J._I ,JL JLJ'IL IlL

/

X.2;,/

-_++.,r,..,_i+q+,2.,:'" r_

r:- i

££L

t_Ol _la+l$ J.hlOci'=l>.i I_II"IOSSIIN ' SlnO'I'.LS Q=ISIA':I_I

"°""___%_om_ ,.°,.,.w,^o.,--,,°6;L'LL

o

I-- > >

O n, n,

0',_ U_

_ J

i

!

I

II

W bl

< _ o

,,a,,_ 9V,_3¥,6NOI.L¥.LN3Wn_NI

F-_ H311MS

S "ON

_tV

yI

oN

,,,v1_ _1/,:pwwoo _,OWd.3_

IV_

--7

AV"/3gA_L_VS.L 3Vdlql

I)

• AV13_ 3'_N2-115 3-M3q0H _ N3P_$NI '_J,,ql3 ..LS._/ _lNflO_19

._. "1 r_.L::lO

I

U JUN!UNUo_ 41.1n _H )

• %-

73NVd ±N31,'Nfi_IISNI NIV_ ,;_,,'ll_.Lg 0

:L_0 NO

O

eJ_O_.U_;Od 3sn_-N3_s / I / _ 13Vd_l-3_d

, ON=L _N_ N_l_l$Od ddO / IL "_41/ • _

' " -_ {N "_-,_ e""° '" °

AlddnS I ;! : / L .I __ .._J I-

I NO1± I I J_3X]ld IJ_fi_1 [_)_] C_..._ --I-VzN]_n_sNI _ I I r_ _ T_

I(a_.sn,"_a_ . I T

I / _I3,_od _ I = I ]9Vll0A +_ -- _ . •

• N OI ,,I._/'_ :JdO $O0_NIINO)

-- _n_ _-'O

REVISED _lr, LoUIs 3, MISSOURI REPORT ,_, 10_ ,

_v,sED ,'___!F! ___._'._._._L_ MOD,_ IS3

Before umbilical drop, the low frequency telemetry transmitter and its power

supply receive 24 volts d-c from the M_in Pre-impact bus through the energized

Ground Test Umbilical Relay, normally open contacts. This relay's solenoid

is energized through the umbilical until the umbilical is dropped. (See Figure

ll-ll).

To silence the TM transmitter, the solenoid of the Instrument M,c_leand

R-F Silence relay may be energized through the following three methods. First

by poSitioning the GROUND TEST switch in the block house to the "TEST" position,

the Instrument Mode and R-F Silence Relay will be energized. By a second

method the solenoid may be energized through the de-energized Orbit Attitude

Relay, thus causing the silencing of the TM transmitters. The third method of

energizing the Instrument Mode and R-F Silence Relay is through the normally

open contacts of the energized Retro Command Relay #2. After the umbilical is

dropped, the ground test umbilical relay is de-energized and power is directed

through the closed contacts to the telemetry Power supply. (See Figure 11-11).

A LO FREQ. TLM, 0N-OFF switch located on the left console, when in the "OFF"

Position, will break the Power source to the LO FREQ. TM.

Coded instrumentation information is supplied from the instrumentation

package "D", and used tO frequency modulate the transmitter. (See the

Instrumentati_ Section XIII of this manual).

RF power output is fed to the antenna multiplexer where it is routed througk

the antenna switch to the main bicone or UHF recovery antenna.

11-19. High Frequency Telemetry

The hi frequency telemetry set operates on a frequency of approximately

260 MC. The 2_ volts d-c to the hi frequency telemetry is supplied by the same

method as described under the low frequency telemetry description, with the

exception that the ON-OFF switch provided in the capsule is in the form of a

REPORT ,S_DR 10_ ST. LOUIS, MISSOURI REVISED

i'_ --'_ ...... "_ _"' .... REVISEDMODEL. ,._.... -_.- .......

switch-fuse (HI FREQ. ), located on the left hand switch-fuse panel. Input power

for the set is from a separate telemetry power supply operating from the second

pre-impact 24 volt d-c bus and supplying filament and B+ voltage. The B+ volt-

age supply is routed through the key on the control panel. This allows the

Astronaut to interrupt the circuit transmitting code, in the event the voice

communications fail. (See Figure ll-ll).

Coded instrumentation information is supplied from the instrumentation

package "D" to frequency modulate the transmitter. (See the Instrumentation

Section XIII of this manual).

RF power output is fed to the antenna multiplexer where it is routed through

the antenna switch to the main bicone or UHF recovery antenna.

ll-20. Beacons

ll-21. C-Band Beacon

The C-Band beacon is a transponder unit consisting of a receiver and trans-

mitter operating on a frequency of approximately 5_O0 to 5900 MC. The beacon is

double pulsed and is compatible with the FPS-16 radar when the ground units are

modified for this type of operation. Upon ground command, through the command

receivers, or by Astronaut selection of the "CORTIN." position of the Beacon

Switch, the beacon receiver is energized. Interrogation by ground radar will

then result in a coded reply from the beacon transmitter. Input power is from

the main pre-impact 24 volt d-c bus through the beacon relay controlled by the

command receivers, or, for continuous operation, through the Beacon Switch.

(See Figure ll-12. )

Beacon antenna connection is through a phase shifter and the C-Band power

divider to the three C and S baud beacon antennas.

11-22. S-Band Beacon

The "S" Band Beacon is a transponder unit consisting of a receiver and trams.

C_JA'q J. A_-I_A_ A £A_MLR _"

..r:. r • "

PRE-IMPACT

Aux UHF IRESCUEBEACON

ANTENNA ANTENNASSW ITCH

No_T%_,TION . ¢R_co,,E.y________UPON ANTENNA

F_ RINC_ JE.TTV_ON

(_ PR:E - tW_PAC1"_-_ ?..4 V. D-C.BUS

_-4_ RECOVERY

ANTENNA EXTENDED

_F_ONLANOINr._

DtV| DER 4

¢

PHASESHIFTER

g g _

0 0

-I

C

U)

;0 "0ill >

-!

II

PAGE ! 1-2_

REPORT _]_ 10_

MODEL_ 133

Mc,DONNE DATE 1 November 1_1REVISED

ST. LOUIS, MISSOURI

_, _. _'__1;.____. _ 'i' _. ,_.._r_ REVISED

_Ltter. (Bee Figure Ll-12). The unit operates on a frequency of approximately

2700 to 2900 MC and is double pulsed to reduce possibilities of unauthorized

interrogation. This unit is compatible with ground based Verlort Radars and

operates at a positive acceptance tolerance of -+ 0.5 micro-seconds and a positive

rejection tolerance of +- 1.8 micro-seconds.

Power circuits, interrogation and reply are the same as the C-Baud Beacon.

(Refer to paragraph 11-21).

Beacon antenna connection is through the S-Band Power Divider to three "C"

and "S" Band Beacon antennas.

11-23. HF/UHF Recovery Beacon

Two recovery beacons are combined into one unit. One beacon operates on

high frequency, while the other operates on ultra high frequency. Both are

energized to provide radio signals for recovery direction finder equipment.

(See FJ.g_e Ii-12).

The HF recovery beacon operates on a frequency of 8.364 MC with a tone

modulated output. It is powered by the 12 volt standby bus through the impact

relay and is energized upon landing. The RF power output is fed through the

rescue diplexer to the elevated HF recovery antenna.

The UHF recovery beacon operates on a frequency of 211.3 _ with pulse

modulation. It is powered by the 6 volt isolated bus through the antenna fair-

img separation relay. This circuit is energized during re-entry when the

antenna fairing is Jettisoned. The RF power output is fed through the antenna

multiplexer and the antenna switch to the UHF recovery antenna.

ii-2_. Auxiliary Rescue Beacon

The Aux. Rescue Beacon operates on a frequency of 243 MC with pulse modula-

tion. It is powered by the 6 volt standby bus through the emergency hold relay

#2 and the 10 minute delay impact relay. These circuits are energized 10 minutes

r

r

Cirri_:_!:_i_%:,y;

I_ECOVERY P4 C0VERY *A" H I,- FREQ 'E_" LO- F_EQ MAI_ H,E " COMIViAND 1CO_tMAND I UHF tAAIN i UHFBACI_UPu_F_.TVOICEH.E BEACON TELENIETRY TELEMETRY VOICE RECEWER RECEIVER I UNF VOICE

l TI T I t I I ;E

"3"

/ Y' iiANTENNA MULTIPLEXER ..L

,

/ / I......... I _ / I UHFSEtECTOR

& I ' I I I I IAux u..H_FI I Li{ ,yCOAXIAL5_llTr._lANTF..NI_AFAI_IN61 {q('--_ f"t_=,,-,,_,_-*_

I I I t 1 I I I [ I _}'" 4tl _A_NInSTrUMENT

BAND AI'ITEI_I_S AUX. UHF HF UHF DESCENT BICONE

RESCUE RECOVERY # RECOVERY ANTEN_ _WITCH FUSE. PROVIDE5 PRE-IMPAET

' OFF PO$1TION AIID TWO _4V. D-C BUSANTENNA ANTENN& ANTENNAINDIVIDUALLY FUSEDROSITION_

REPORT SEDR 104 REVISEDST. LOUIS, MISSOURI

MODEL. 1_ _r,,rt.l_ T_ lr n _ __L_... REVISED

after impact. The RF power is radiated from the Aux. Rescue Beacon Antenna.

(see Figure n-12).

11-25. Antennas

11-26. Main Bicone (HF and UHF)

A biconical antenna is used for pre-launch, launch, orbit and initial re-

entry phases of the mission. This antenna is an integral part of the antenna

fairing and is located over the open end of the recovery system compartment of

the cylindrical capsule a_erbody. The blconlcal antenna serves the main HF

and UHF voice receiver-transmitters, the command receivers, and the telemetry

transmitters. The active element of the biconical antenna forms the upper

portion of the antenna fairing while the lower portion of the fairing and the

capsule body forms the ground plane for the antenna. (See Figure If-IS).

II-L_'/. _ Recovery Antenna

A UEF antenna is used for the final phase of re-entry, landing and rescue.

It is a compact antenna located on the open surface of the recovery systems

compartment. The antenna is folded when the antenna fairing is installed. Six-

teen seconds after the fairing is jettisoned the UHF recovery antenna is erected

and serves the UHF voice receiver-transmitters, the UHF portion of the recovery

beacon, the command receivers, and the telemetry transmitter. The main EF voice

receiver-transmltter is connected and operating but radiation from this antenna

is negligible. (see Figure 11-6).

11-28. Main Blcone and UHF Recovery Antenna Feed

The various radio systems are connected to the bicone antenna or the UH_

recovery antenna in the following manner: (see Figure 11-13).

(1) The main HF voice receiver-transmltter antenna lead is connected to the

antenna multiplexer.

(2) The IUHF Selector Switch determines whether the hi-power or the lo-power

,:i ¸'

- C,CNF:DENYiX-,.-

OAVE i November 1961

ST. LOUIS 3. MISSOURI REPORT

UEF receiver-traasmitter is used. It also energizes the EEF coax switch to

connect the operating UHF set to the antenna multiplexer.

(3) The two ccmmmnd receiver antenna leads are connected to an impedance match-

ing network. This enables both receivers to share a single antenna lead from

the impedance match to the antenna multiplexer.

(4) The Hi and Lo frequency telemetry tranm_Itters each feed directly to the

antenna multiplexer.

11-29. Antenna Multiplexer

The antenna multiplexer enables simultaneous or individual operation of the

radio systems using one antenna. Effectively this is a radio frequency Junction

box. Final connection to the antenna is through the antenna switch to either

the biconical antenna, or the UHF recovery antenna. The antenna switch is

operated by the antenna fairing separation relay to cause the automatic shift

from the maim antenna to the UEF recovery antenna upon antenna fairing Jetti-

son. (See Figure II-13).

ll-30. Recovery Antenna

An antenna is provided to permit HF radio transmission and reception after

landing. The antenna is a telescoping whip antenna which is automatically

extended by gas pressure after impact. Once extended, the antenna is used for

the HF rescue voice receiver-transmitter and the HI _ portion of the recovery

beacon.

Antenna leads from the HF recovery voice receiver-transmitter and the HF

recovery beacon are connected to the HF recovery diplexer. This diplexer allows

simultaneous or individual operation over the single lead to the antenna. (See

nm, -e ll-Z3).

ll-31. C and S Band Antennas

Three C and S band antenna units are installed in the capsule structure

lz-2?

._.nR, Io4

.....,..,.,, ..r" LL',E_MTI A h.

PAGE, ii- 28

REPORT ._.T_R 104

MODEL l_

•,MC'DONNE oA, REVISED

.... ST. LOUIS, MISSOURI _,-- _"_ _lIT1_ _r-r_ _r_,, ,._ -7_3 B REVISED

_J.l._l.l, ,l..IL_l.4.l. ll .IL

for the C and S-baud beacons. These units are equally spaced about the circum-

ference of the conical section. Each antenna unit consists of one helix as a

C-band antenna and one helix as an S-band antenna.

Antenna leads from the C-band and S-band beacons are routed through indi-

vidual power dividers to the three associated helix antennas. (See Figure ll-13)

Ii-32. SYSTEM UNITS

11-33. AUDIO CENTER

The audio center provides trausistorized audio amplifiers, a "voice operated

relay" (VOX), an audio filter, tape recorder control circuitry and transmitter

control circuitry. (See Figure ll-1). All comments are contained in a light

weight, foam encapsulated unit.

Two fixed gain headset amplifiers are used to bring audio signals up to

headset level and feed the headsets separately. Two fixed gain amplifiers are

provided to increase the dynamic microphone output to a level suitable to be

used with the various transmitters.

A low pass filter, with a cutoff for frequencies above 300 cps, filters the

audio supplied from the command receivers. Outputs from the filter is fed to a

variable gain, ccmmaud audio amplifier.

The "voice operated relay" is a transistorized amplifier with separate

adjustable threshold level and release time controls. The amplifier operates a

relay to provide a grounding circuit for transmitter control. This unit parallelJ

the external microphone switch.

The audio center furnishes a circuit to apply the transmitter control ground

I_tential to the various transmitters. Each circuit is protected from the rest

by a crystal diode.

A relay is installed in the audio center for supplying Imwer and audio

; 7 r_\

//

REVmEO ST. LOUIS S, MmSOUm n_ORT _R lO_

REVISED, __#"*_ _I I_'I r_eli-r I A 1__

signals to the tape recorder. In the de-energized condition, the relay closes

a circuit to the tape recorder input, thus audio received by the capsule is

recorded whenever instrumentation programs tape recorder operation.

When the microphone switch or V0X is operated, the tape recorder relay

is energized. One set of closed relay contacts now completes the recorder

power circuit independent of instrumentation programming, while a second set

of contacts routes signal from the microphone amplifiers to the recorder input.

The circuits in the audio center operate directly from the capsule 2_

volt d-c inputs with no further regulation or voltage increase.

ii-34. CORTROL PANEL

The audio control panel provides controls and _ircults for the audio

signals of the various capsule receivers. (See Figure 11-7).

The two HF and two UHF circuits are routed through individual T-pads to

volume controls. The two EF circuits share a single volume control, the same

is true of the two UEF circults_ while separate volume control is provided

for the command audio circuit. Fixed inputs are used for the alarm tone and

ground interphone circuits.

The panel also contains a switch override for the impact Eeying feature

used with the UHF transmitters, and heylng button on the panel to interrupt

the Hi-Frequency telemetry B+ supply during emergency keying. (Refer to

Figure n-lO).

11-35. MAIN HF VOICE RECEIVER-TRANSMITTER

The main HF voice set is an AM receiver-transmitter designed as a small,

light weight unit operating near 15 MC. (See Figure 11-8).

The receiver section of the unit is a transistorized circuit using a

crystal filter, crystal diode detector and class B audio amplifier. The final

%e_q_ l "l I i li_lmai it i aE =i

PAGE II-_Q

REPORT S_DR 104 ....

MODEL. J._

m

audio amplifier is used for sidetone during transmissions.

The transmitter section of the unit utilizes vacuum tube stages for the

crystal controlled oscillator, driver and power amplifier. The power amplifier

may be modulated up to 90% by a transistorized speech amplifier and modulator.

These audio stages are also used for sidetone. Transmitter output is 5 watts.

Capsule power, 2_ volts d-c, is supplied to the unit, with voltage regulator

provided by a Zener diode, trausistor circuit. Power is routed through an

external switch and contacts of the capsule separation relay which controls

transmitter filament power, relay operation and a transistorized power converter.

High voltage from this converter is used for the transmitter power amplifier.

Antenna switching is accomplished by a solid state circuit which blocks the

receiver during transmission. D-c voltage is also removed from the receiver

RF stages.

11-36. RECOVERY HF VOICE RECEIFER-TRANSMI_I_R

The HF Recovery voice set is similar to the main set. (See Figure 11-8).

The main difference liem in the transmitter section. This section consists of

a crystal controlled oscillator and power amplifier delivering i watt output.

11-37. HIGH POWER(MAIB) Am) LOW PO_ (BACKUP) b'EF VOICE E_CEIVJ_-TZ_NS_

The main and backup sets are identical. (See Figure 11-9). They consist

of an AM receiver-transmitter designed as a mall 3 lightweight unit operating

near 297 MC. Transmitter output is .5 watt. The main receiver-transmitter is

boosted in output by a final booster amplifier.

The receiver section of the unit is a transistorlzed superheterodyne circuit

using a crystal controlled local oscillator, crystal filter and crystal diode

detector. The audio section of the receiver also serves as the speech amplifier,

modulator and provides sidetone for the transmitter. The transmitter section of

(._ ir._ _T T.q= .=..,.-,,.., --..'t._ _.aV _k I A" & 41=F 4K4 g I A A_J4d

OATE i November 1961

REVISED

REVISED,

st. LOUmS S.M'SSOUm nEPOnV SEDR 104

_oo_ 133

the unit utilizes a crystal controlled oscillator, tri_ler and power amplifier.

The RF section uses vacuum tubes while the modulation circuits are transistor-

ized.

Capsule power, 24 volts d-c, is supplied to the set. This voltage is

applied to the receiver, audio circuits and back through an external transmit

switch to an internal power converter. This transistorized converter supplies

B+ voltage to the transmitter RF sections. Transmitter filament voltage is

also applied by the external transmit switch or the bicone separation relay

after bicone separation.

Switching from receiver to tlansmltter operation is accomplished when

ground potential is applied to a switching relay and a blocking circuit. The

relay provides antenna and power converter switching. The blocking circuit

removes receiver voltage.

11-38. UHF 200STER AMPLIFIER

A booster amplifier is used prior to landing to increase the .5 watt out-

put of the Main UHF transmitter to 2.0 watts. The higher power is also avail-

able after landing.

Signal input to the booster is routed through a double pole, double throw

relay. When the relay is de-energized, the signal is routed through the con-

tacts to the output Jack. Energizing the relay feeds the signal through the

amplifier and takes the amplifier output to the output Jack.

11-39. RECEr - CO ERS

The cc_aand receiver-decoder is a transistorized unit consisting of an

FM receiver designed to operate in the frequency range of _O6 to 450 MC, and a

decoder unit to operate control circuits. (See Figure 11-10).

The receiver section of the unit is a dual conversion superheterodyne

32

REPORT ,_EDR 1011•

MODEL_ 1"_

Mc'DONNEL L..... ST. LOUIS, MISSOURI


REVISED

REVISED

e

circuit. The first local oscillator is crystal controlled and uses two stages

of frequency multiplication. Two sta_es of amplification are used for the first

IF, 78 ME signal. The second local oscillator is also crystal controlled, mix-

ing with the first IF and giving a resultant second IF of 10.75 ME. Output from

the IF strip is through a limiter to the discriminator. Audio amplifiers boost

the discriminator output for the co_nand voice channel and the decoder driver.

The driver in turn supplies the ten decoder channels in the set.

The individual decoder channels each provide filters for their specific

ccmmand frequency and amplifiers to operate a double pole, double throw relay

for each channel. The ten relays thus make available normally open and normally

closed contacts for external control circuit operation.

Capsule power, 18 volts d-c, is used to power the set. A Zener diode

circuit, within the unit, is used for voltage regulation.

11-40. AUXILIARY E_CODERS

An auxiliary decoder operates with each of the two receiver-decoder units,

allowing an additional ten channel capability.

The decoder channels in the auxiliary decoder are identical to the decoder

channels of the receiver-decoder, with the exception of the command frequencies

at which they operate.

The auxiliary decoder operates from capsule 18 volt d-c power. No further

voltage regulation or increase is required.

11-_i. _=EMETRY PO_ER SUPPLIES (See Figure ll-ll)

The telemetry power supplies generate voltage used in the telemetry trans-

slitters. The unit is transistorized and uses crystal diodes. Capsule Power,

2_ volts d-c a is applied to a transistor switching circuit operating into the

primary of a power transformer.

• !

'k

/

OATE 1 November 1961 PAOE ii-33

.EVmED ST.LOUm 3,MISSOUm R_o_r S_nR i0_

RL_mED, _ Moo,- 133

A full wave, crystal diode rectifier is used on one secondary, with volt-

age regulation, to provide 200 volts d-c.

11-42. TELEMETRY TRANSMITTERS

The two telemetry transmitters are essentially identical (See Figure ll-ll).

They must be ground adjusted for an output of 3-3 watts. One set is operated

at approximately 228 MC while the other is tuned to approximately 260 MC.

The transmitter is an FM unit using modulation inputs from instrumentation

circuits. Modulation signals are applied to the oscillator which through four

stages of doubling feeds a power amplifier stage. All stages, with the excep-

tion of the final doubler and the power amplifier, are transistorized. Fila-

ment voltage, 6.3 volts and B+ voltage, 200 volts d-c, are obtained from the

separate power supply. Capsule power, 24 volts d-c, is applied to the trans-

mitter which provides voltage regulation.

Ii-43. C-BAND BEACON

The C-Band transponder is a pressurized superheterodyne receiver and pulse

modulated, 400 watt peak output transmitter, operating in the frequency range

of 5400 to 5900 MC (See Figure ll-12). With the exception of the magnetron, the

unit is transistorized. The receiver consists of a pre-selector, local oscil-

lator, 40 MC IF amplifier strip, pulse detector, pulse amplifier and decoder.

Resonant cavities are used for the pre-selector and local oscillator.o

The transmitter section accepts decoder outputs and pulse modulates the

transmitter output.

The unit contains a power supply for converting capsule 24 volt d-c input

to filtered 24 volt d-c and regulated, 115 and 150 volts d-c outputs. Antenna

switching is through an internal dIplexer.

PAGE II-_ZI.

REPORT SEDR IO_

MODEL 133

McDONNE REVISED

ST. I.OUI$, MISSOURI

REVISED_k_l_A1JL JLJt_w41.4J. 1 _L A_LJI_

1 November l_l

iI-_. S-BAND _F_ACON

The S-Band transponder is a pressurized superheterodyne receiver and pulse

modulated, lO00 watt peak output tranmnitter operating in the frequency range of

2700 to 2900 MC. (See Figure ll-12). Like the C-Band beacon, the unit is

transistorized except for the output tube.

Receiver and transmitter circuits are the same as those used in the C-Band

beacon with the exception of the pre-selector, local oscillator and transmitter

which are designed for S-Band frequencies.

xx- 5. /U RECOV YZ ACON (SeeFigu -X2)

The recovery beacon combines an HF, tone modulated, 8.364 MC transmitter and

a UHF, pulse modulated, 243 MC transmitter into one small, foam encapsulated unit.

The UHF section of the beacon is a one tube circuit with a pulse coding network.

The KF section of the beacon is a transistorized crystal oscillator and two stage

power amplifier with tone modulation supplied from a power converter. The beacon

utilizes 6 and 12 volts d-c from the capsule power system. The UNF section is

energized by applying the 6 volt d-c to a transistorized power converter. A

full wave, crystal diode circuit is used to rectify the power converter output

which is applied to theUHF stage. Applying 12 volts d-c energizes the HF sec-

tion of the beacon. No power converter is required for the L_ volt input.

M_dulation for the _ section is provided by routing the 12 volt supply to

the power amplifier stages through a secondary winding of the power con_rter.

11-_6. AUXILIARY UHF RESCUE _ACON

The Aux. UHF Rescue Beacon, consists of a pulse modulated transmitter and

power supply which is enclosed in a foam-encapsulated case. (See Figure 11-12).

The unit is connected to the 6 volt standby bus and has an output of 91 watts.

• /

_vA*_ A _e.f ae._ A

i_!:_¸

oA_ ,! _ovember 1961

REVISED

R L:/3/lSlED

ST. LOUIS S, M,SSOUm R_"ORT _]:_ 104

__f-t-_._____5_v_i "----._T:;,: Moom.__ 133

_U.J__. J I .............. . ......

11-_7. AWI'lm_A MJLTIPLEX_

The antenna multiplexer allows reception and transmission of the many

capsule frequencies over one line to the bicone or UHF recovery antenna. The

unit consists of a number of filters arranged so that all capsule frequencies

between 15 and 450 MC can be multiplexed on the single feed line. Each input

channel is provided 60 db of isolation.

iI-_. RECOVERY DIPLEXER

The recovery diplexer unit is used for the HF recovery voice receiver-

transmitter and HF section of the recovery beacon. One low pass and one high

pass filter is used to diplex 8.364 and 15 MC on one feed line to the HF

recovery antenna.

ll-49. COAXIAL s_n_s (_ s_)

RF switching is accomplished with motor driven SPDT switches. Application

of capsule 24 volts d-c through external circuits drives the switch to the

appropriate RF position and opens the power circuit for that position.

11-50. BICOHE ARTENNA

The capsule is electrically divided in two sections. (See Figure ll-6).

The antenna fairing structure at the Junction of these sections resembles a

discone antenna. This Junction is center fed by a coaxial cable from the

communications sets. At frequencies between 225 and 450 MC the antenna fairing

acts like discone antenna. A lower frequency of 15 MC causes the unit to re-

semble an "off center fed" dipole. Between the upper and lower limits, at 108

MC, the unit behaves as a composite dipole-discone antenna.

Thus the bicone antenna serves all capsule frequencies, with the exception

of C and S-bands, allowing reception and transmission within limits of the cap-

sule system.

_"_ = lll"l II'% I_"I_.I"I" | X I_,n_Vl ,mi . .........

36

REPORT SEDR 104

MODEL_ 133

Mc'DONNE REVISED

.....St, LOUIS, 1MISSOURL_

ll-51. BICOHE ISOLATOR

Au isolator is provided to shield electrical wires that pass through the

bicone antenna fairing s_ructure. The isolator is formed into a tube which is

curved to allow mounting beneath the periphery of the antenna fairing.

11-52. UHF _ESCENT AND RECOVERY ANTERNA

The UHF descent and recovery antenna takes over the UHF functions of the

bicone antenna when the antenna fairing is Jettisoned. (See Figure ll-6). The

UHF descent and recovery antenna is a fan shaped3 vertically polarized monopole

located on the top of the recovery compartment.

Ii-53. HF RECOVERY ANTENNA

Upon landing, impact circuits initiate a sequence for the HF recovery

antenna. (See Figure 11-6). The elevated antenna acts as a vertically polarized

monopole for HF frequencies.

Three antenna units serve the C and S band beacons. (See Figure 11-6). Each

unit consists of a C and a S band radiator. Each radiator is a cavity mounted

helix antenna.

ii-55. TEST CONFIGURATION CAPSULES

The data contained in Paragraphs ll-i through 11-54 applies to the specifi-

cation compliance capsule. Deviations from this data as applicable to test

configuration capsules are covered in the following paragraphs. Differences

mainly involve such things as UHF Transmitter power output, pre-recorded tape

method of voice modulating transmitters, sequencing differences in transmitter

operation, umbilical control of C and S band beacons. Certain items common to

the manned capsule will not be utilized in some other capsule, such as the

. j/

dp ir_ _v lr:_ lr TI _ !-'--" v '

_/_%••

REVISED. _ro LOUIS 3. MI_|OUIR| REPORT ..... _ ZO_

.w,s_ .oom. 13_

telemetering key, push to talk switch, umbilical interphone, headset amplifier

output and beacon switch modes of operation. (For operation of systems see

Communications Table ll-1). If no reference is made to a particular item, it

is the same as the specification compliance capsule.


Cc_mnication systems on Capsule No. 8 are the same as the Specification

Compliance Capsule except that Capsule No. 8 is intended for an unmanned mission

therefore data pertaining to Astronaut control is either progrmmned within the

capsule or remotely controlled by ground command through the Command Receivers

and De-coders. Differences are explained in paragraphs 11-57 thru 11-67.

(see Fi_res ll-15 t_ru 11-25).

L£-57. Voice Communications

Voice ccemm_nication for Capsule No. 8 is similar to the Specification

Compliance Capsule, except Capsule No. 8 is un-manned and is equipped with a

playback tape recorder containing a pro-recorded tape to simulate the Astronaut 'E

voice which will modulate the NF and UHF transmitters in the capsule. (see

Figures 11-15, i1-19 and 11-22). This playback tape recorder is provided with

a dual track recording. The output is staggered as shown on Figure I_I-14.

Starting of the tape recorder is controlled at the beginning of the mission by

the CAMERA AND TAPE RECORDER Switch in the blockhouse or the additional tape

record relay (see Instrumentation section XIII). The playback tape recorder

operation begins prior to launch and continues throughout the_mission until

tape depletion. Duration of tape recorder running time is approximately 45

minutes. Single ended output from the playback tape recorder is fed to the

two separate microphone amplifiers in the audio center which energizes the

voice operated relay circuit in the Audio Center. The voice operated relay in

turn completes a ground circuit to the tape recorder relay thus causing the

PAGE iI-_8 M_DONN__ __ DATE, 1 November 1961REPORT _ 104, REVISED

._,.tguns, MISSOUmMODEL_ 133 _,u,-_v.,_ .,,.u _ _._,._ .=_-_r.,J REVISED

modulation signal to be routed to the main tape recorder as well as modulating

the HF and UKF transmitters. A push to talk switch is not utilized.

20 Sec. i00 Sec. 20 Sec. i00 Sec.

Audio Silence Audio F"--- Silence

Silence "_' Audio '_-'7 I_-"I00 Sec. 20 Sec.

Silence -----_ Audioi00 Sec. 20 Sec.

FIGURE 11-14 PRE-RECORDED TAPE SEQUENCE

11-58. HF Voice Communications

The H_ C_unication Tape Recorder will transmit the playback recorder

signal alternately 20 seconds "on" and i00 seconds "off" until blcone separation

or until the pre-recorded tape is exhausted, whichever occurs first. Audio out-

put from the HF Receiver is directed into the main tape recorder only, since the

headsets and amplifiers are not utilized. After impact HF Communications is

conducted through the HF Recovery Tape Recorder. (See Figures 11-15 and 11-20).

11-59. UHF Voice Communications

Operation of the UHF _in Tape Recorder (T/R) is similar to the Specifica-

tion Capsule (refer to Paragraph 11-I_) except the UHF Booster Amplifier is not

installed. The transmitter is modulated by the playback recorder and the

receiver output is fed into the main tape recorder similar to the HF Comm. T/R

except that an extra channel inthe main tape recorder is utilized to record the

UHF receiver audio. The UHF Voice Communications set is not utilized unless the

UHF Selector Switch should be placed in the "UHF" position prior to launch. UHF

,i;j

f --

y--JINSTRUMENTATIONpAC K.AGE --_

- j- /

H__IPLEXER --,

1 ,2 iH_'RE'--_VERY I IRECEIVER" I I

Tl_NS.,T " I ..li

_, I /J

TP_NSMITTER-

BACKUP UHF.

1'RAN _MITTE.R,

.

'UHF BOOST

i_IIYIPLIF i_

\

ii

IS

././

PlO CENTER

ANTENNA MULTIPLEXER

'iTENNA SWITCH

MAIN UHF RECEIVER-

TRANSMITTER

TAPE RECORDER.K][]

TAPE

RECORDE_

,\

DF DEFEAT-

SWITCH

L__........ co_.,o0,oTCH -FUSE"

PANEL (ANT SWITCH)

RECORDER

_AIN INSTRU_A[NT PANELDETAIL A

NOTES

_x_xI?ANSM iT SWITCH

RANSMIT

H.E

OFF

II

LLFLE._

J HORIA RESERVE

SELECTOF

-SWIT_:H

[I_ LOC_."Tf.D _ORIZOI4TF,,t._.'Y OKt %_Et¥ (CA_. q).

[_ INSTALLED BUT NOT NORMALLY OPERABLE UNLESS

THE UHF SELECTOR ,'SWITCH IS IN THE RESERVE

POSITION.

[_. CAPSULE 8 HAS AN EXTRA TAPE RECORDER INSTALLED.

"" .-"_--_'. / /'-"-UHF DES-'---'--C,ENT--_-

/ C''-- /_ /_/,, / RECOVERY ANTENNA

;o ;0 orq rn ),

< <: -I

ill !11

o O

C

m )'

PAGE

REPORT

MODE[

11-40

SEDR 104

133

Mc'DONNELL__ __ST.LOUIS. MISSOURI

liiee _ I 1 I i liJ lille i _i • la ilk


REVISED

REVISED

¢o_11

_-2 _

°N:d_L_

\

P-___

Z

/

FIGURE li-16 COMMAND RECEIVERS SYSTEM IN3TALLATION (:CAP3ULES 8 _ 9)PM415-t_/_

DATE ,

REVISED

REVISED

I NOVEMBER 1961

ST.LOUIS, MISSOURI

PAGE = 11- 411

REPORT, SEDR 104

MODEL 133

/,

t '

/7.[7; _

FIGURE tl'17 TELEMETRY- SYSTEM (CAPSULE% 8 _ 9)I:_14.5. 189£

l/ _ II I p i I,_lll_, kl_l,, Iii i..lllil alil I • i_ii

PAGE ,, 11-42.

REPORT SEDR 104

MODEL 133

McDONNE_ __ST.LOUIS, MISSOURI

/'_,_ki.lE", _, _Ira"p_ T' A_L__V I I I • I _ t IMIil

DATE

REVISED ,,

REVISED

1 NOVEMBER 1961

\

/

/

..... /

REVISED ST. LOUIS 3, MISSOURI REPORT _'_T_R 104

REVISED MODEL 1_

transmission and reception is available throughout the mission, after impact

the receiver will continue to feed its output to the main tape recorder, end

the transmitter will emlt voice signals until the pre-recorded tape is depleted

after which a CW signal will be transmitted. The CW signal also serves as a

direction finder signal. (See Figure ll-15 and ll-21).

ll-60. HF Recoverer Taps Recorder

HF Recovery Tape Recorder (T/R) operation is similar to the Specification

Compliance Capsule (Refer to Paragraph ll-12), except that after impact the

transmitter will emit the pre-recorded tape voice signal until the tape is

depleted, after which a CW signal will be emitted. The HF Recovery T/R is

connected to an automatically raised whip type antenna. (See Figures ll-15

and ll-20).

ll-61. Command Receivers

The Ground Command Receiver operation is the same as the Specification

Compliance Capsule (Refer to Paragraph ll-16), except the audio is routed into

the main tape recorder instead of into the Astronaut's headset which is not

used. The C and S Band Beacon operation is controlled through the command

receivers. (See Figures ll-16 and 11-22).

11-62. Telemetr_

The two telemetry transmitters perform their functions in the same manner

as in the Specification Compliance Capsules (Refer to Paragraphs 11-18 and Ii-19)

except that operation is continuous from launch to impact. (See Figures 11-17

and 11-23) •

11-63. C and S Band Beacons

Operation of the C and S Band Beacons is the same as the Specification

Compliance Capsule (refer to Paragraphs 11-21 and ii-_2), except that both

beacons operate continuously throughout the mission. The beacon switch must

a a

_- > _,< ul0 E I1:

w

,<Q,.

o

D

£

73NV_ INBV_RalSNINIV_

:lHn I]NV :IX olOlOrr_

Id

Id

eo

uJ_..i

4:

l.u

_J0O_

F""70

0

I

la..

-11

Frl

I

IX)

O

-q

<

rrl

'C),C)

+EE

-n

B

r,l

-o(.p

oo

4',.

MAIN _

PI_E :ItC_PACT il _ U

'_4 V DC BOS .el

IPLAYB_,C K

TAPE RECORDER

RELA'Y

TAlC I

AUDIO _j__4V D-C

BU_

IMPART __ _

RELAY

I,A_C_OPI._ONE AUDIO _ C

--PTT TI_ANSMITTE_ CONTI_OL-- H

--_ECEIVE_ AUDIO--

i

l I IV_PACT

RELIkY

AI 3.II_PACT

AUDIO

C.EN"FEG_

CON

PA

-i--

+1r IL --RECEIVER AUI_O---

/ I4E_,D _l_T SIGNAL

Li'TRP, NSt_ ITTE R CONT t_OL--

MICROPHONE _'_L)D _ O

TO _ECEIVI_

HF VOLUN_E

AS DES_ED

UHF SELECTORSWITCH.IN I_ORI_KEYED AND

I<. MODULkTED BYPLL'(I_ACKTM_-RECORDER

II.-

BtCONE

ANT_

INO.I

i_o,z_OSITIONANTENNA _ IO_N AN_N_

" _ 1 U"I I F'AIRING

+ [_11_ I JEFTISON,IDISABLEN_

AN'r_KI'NAy NO.Z" _ F

SW ITC_ I

I------ E

'_ t N1AIN I-IF• -- 1 F VOICE

F------ _ECEIVER

TITAN S Iv_ITTE R

FIL'PWR'K_t + _/ - ('_5 I

_, __/o +I /

T I;2ANSI_ |T J

I_AIN INSTI2UI_ENT F3WNEL

AVA_ L AE_LE AFTE;Z

LAN bINC_

TO _:ECE _VE

_F VOLU W_E

AS DESIRED

TO T_ANSN_IT

MODULATED

RECORDER. CW

E_I,_S_ON &¥'IE'R

TKPE bEPLE.TIOI,.t

RECOVERY L

NOTE5

[_ CAPSULE q

RECOVERY _t: V01CE

I_ECE _VE_ - "I_ANS_TTE_.

_DCAP_ULE

RECOVERY ANTENNA

AVAt LA_>LE A.FTE R

LAIJDIN_

;0 ::0 0

g g mm ffl

I+Z

I;

: ;o "o) I;I ).

1II

;I

o _ Ko

o

P

zO.4rnU_

r_r)

CCrr"

mm

(6) '8. s33nSdv::)) _O"t.-! V.LVQ £NOI.LV,_:INN1NNO_ 3::)-Joh3Hl'I', IL_-If, i3_lN_l_-I

1go

:7<

_,-13

:_o

d

qp,

_-I _ _

-I

-I

2,

O n_O _ :_ n_ -r :,_ m ,.',.,-

(_I_ N r_ en

..4 r_ ;_o HI>r- HI n

In -r

•-I m

_

' I °l 'I r-X_ _; r" .r U_E:

' ;;o °- ',

'oi _ '' L-o', I : °°

i'-111_................. .J

o_

==< _-_

;___ T _ m_ _ F_

Z_ "-O Z 0

c_O_ -- 0_

c_)_

_c' z<i

7-- 0

_ ( )-'--- ,

m

6I

_.<... m .-.._ _ <= _;

r_r-- r"

l_ _ ---- .:.j P_ _. ,._ ' _ --_ _ _1_ -_I_r-r

_<_0

i:N

-4

t961 _I:_gW]AON t

_!_ 11 J_ ! • [ I mill _!111 i III. I AA03 SI A3 El 7"_ r I -_ i_l _ _ h.,,a ,msa.'_,,_.,.,_

O-=ISIA=IEI IEIrlOSSIi_l "slno-r.l.$

6,

C£L

_OL _iO3S

9_"LL

naao_

&MOdeM,

_Vd

DATE

REVISED

REVISED

1 NOVEMBER 1961 Mc'DONNEL LST.LOUIS. MISSOURI

PAGE

REPORT.

MODEL

11-A_7

SEDR 104

133

k • :i"

,.u O <_ 0 --_ -

_o- 0. 4 _-_-__,4L__u

1% i

Ill

og

i 8

x

r _

I _'__'B

1 _<[I-- .q

I oO _s._O

J___<

,, _ 8._U UD ._- U iij

Is,_ L

°' 0[>

i I_b_ _,

._L_L <_ -- O I_ (_._: O

,_ I U._l_u _z o

0 'Z .'/ _.J

0> Iu_l

U ]

_1

.YI

JouJrv.i

ui

I11

.io ,i

No

V_g

gu_o

_J - opo

<_

_o__o_

u/

.,1 Ill

_D

_0__._,OO;"ZZ_

^._-_

_'.

_Jlu

'%P" Z

I.L_ ', .... I:.Z]_ ,3,',I .:_._ I/_

_,_,_ I__

z_'_l_"_01z_l_t_Ol

_1-- u

F'IGUI_E I(-_ COMMAIqD I_EC_E'!VEI_$ DATA FLOW (CAP 8 (,9_

_Vill I I1,,_' r--.2- l _11;" i IP._"I_I,J_

b

tu(] ''

0O

D -_

__ I_--_

[--" ,

13

d__ J I

P_Ew I

,,i

PH4S-188;I_

).TII'-

_I_- ID,A_A.¢.T _ ["6.-_"_ / IZ4.V. t::)-C ESU_

cP-l_

'*" t l-O- FI:ZE_

+_-_V.co._V.D-C.A_C J _:_OVYF='I:2 TF-'c_'T

"I

_ +_'d""& £_)-C ] l::X_'w_'l:;2"T_--_T_:_.5V, _,-C. >

TEST 2F-C F-I::_'A.?.LE

C)PEI2.h_'TE_5 C..O h,IT INL_:)U%LYl::tZOl_ _Ut',4C.t-i ut,,4-rlL.tOM, II4. ,&I:TF.._. |IxAPkCT

[Z_>CAR 8.

;t :;o "o3 m >

-t

C

UImo

:;13_0 0111 111 >< < -4

o.li

li7_

\L_ /

/C: "¸ . / ,!i ¸_ i

/

,inNOT 5E_a,R_"t'E D

_L)S _ _ AN'I'ENN_k FA=IRII_I

5T/::,,_ BY "llC.. . I_

,zv. D-C BX..p ,- IMPACTL

BUS ,Ill. IMPACT

_ EL/_Y

I:_I_E" I Iv"PACT 111_ ._

'_4V. D-C U _Bus <i] ""

"b

2

, c/----.J-.'C_o %_D co,so!

CONTINUOUS J

i C' lJ

W".c',,_N [NSTP.UI"AE_T PANEL

ULTRAI BATTERY SARAHRE5CUE

[_EAGON

H UI_F F A

I I___F/_____.I.4----Ia I RECOVERYI

ANTENNA

MUTt PLEXE_

ULTRA I"ISARA"IRESCUE _1

ANTENNA

] REC-0VE_Y'

ANTENNA

5W ITCH

-SWITCHES TO INO. "2 I:::;_OSITION

UPON ANTENNA

F_a l_IN_i ,,JEC'FIBON

ANTENNAS

_,1C ON E_]

DESCENT _ _'1

RE COVER Y_.....J

HF RECOVERY

ANTENNA E%TENDED

UPON LANDINB

III

C t.S BEACON ?4V D-C FEOM

l GDOUND COMM_AND "RECEIVERSiL.. . TI_A|LER O1_ PAD

"91"-- CONTI2OL 24V D-C

UMB, ILICP, L

__ ,.5- BAND

C- I_,AN£)BIEAC_O N

UI::_N _ECEtVIN_ CODED

INTE RRO(_AT |ON PULSES

'THE _EA.CON WiLL I_EP't..y

WiTH A. TRAN_JIVitTTED)

C013E13 I:_LSE,

I;_WER' 3

DIVI D E r'_.. 4

A I

F:OWE I_

C01V_Iv'_ON C AND S _A.NO ANTENN},,S

NOTES

CAP B MAIN PRE-_I_IPALT

CA_ 8 SEEQkI_P_P._ PRE-tMPI_C.'[

m Ill >< < ,-.t

--[_(,111 01

O O

Ill

) Ill >,

I' II

I'I RECOVERY

r'A"_H I:-FREQ IT ELEk_ETRYTRANSMITTER

ANTENNA MULTIPLEXER.

IN

¢ ;0 "0

q

m

m _

o

;0 ;0 0Ill FI 3,< < -I

_ m!11 I!10 0

Z0<

o,

IL /

DATE i Novem___D____

REVISED•

REVISED,

Mc'DONNE _A_ _--_1 r

ST. LOUIS _, MISSOURI R_ORT _DR 104

MODEL 133

be placed in the "Continuous" position prior to launch. The S-Band Beacon is

double pulsed as on the Specification Compliance Capsule but the C-Band Beacon

is single pulsed which requires different ground coding for interrogation.

(seeFi e ii-24).

ii-6_. Auxiliar_ UEF Rescue Beacon and Antenna

Capsule No. 8 does not have the Aux. UHF Rescue Beacon installed, however

it is equipped with an ultra Sarah Rescue Beacon which is a self-contained unit,

energized by bicone antenna separation and operation is automatic. (See Figure

ii-65. Antennas

The antennas used on Capsule No. 8 are the same as the Specification

Compliance Capsule (Refer to Paragraphs 11-25 thru 11-31).

11-66. Main Instrument Panel

Capsule No. 8 does not use a tone generator.

11-67. Special Instrumentation

Capsule No. 8 is equipped with special instrumentation and incorporates

an extra capsule tape recorder. This tape recorder is located in the special

instrumentation pallet and consists of a power supply and seven channels for

recording. The extra tape recorder is controlled through the communicati@ns

control panel (Refer to Section XIII Instrumentation. ).

11-68. _ST CONFIGURATION CAPSULE NO. 9

Capsule No. 9 is the same as the Specification Compliance Capsule except

for differences as noted in Paragraphs 11-69 through 11-71. (see Figures 11-15

t rough11-25).

11-69. Voice Ccurunications

Voice communications for Capsule No. 9 is similar to the Specification

Compliance Capsule except a playback tape recorder is installed to simulate the

_J_::V:D=;;Y_AL

PAGE l ] -5?

REPORT ,?_EDR 1OL_

MODEL. 13B

REVISED_**_T,, LOUIS, MISSOURI

Astronaut's voice, as in Capsule No. 8. A Special Instrumentation Relay is

installed to provide playback tape recorder control. (Refer to Paragraph 11-57).

11-70. C and S Beacons

Operation of the C and S Band Beacons is the same as the Specification

Compliance Capsule (Refer to Paragraphs 11-21 and ii-22), except that both

beacons are on continuous. The beacons switch must be placed in the "Continuous"

•position prior to launch.

11,71. Auxiliary UHF Rescue Beacon and Antenna

Capsule No. 9 does not have the Aux. UHF Rescue Beacon installed, however,

it is equipped with an Ultra Sarah Rescue Beacon, which is a self contained unit_

energized by bicone antenna separation and operation is automatic. (See Figure

11-25).

ii-72. TEST CONFIGURATION CAPSULES NO. i0, 13 AND 16

Communications on Capsules No. I0, 13 and 15 are the same as the

Specification Compliance Capsule (Refer to Paragraphs 11-1 thru 11-54).

12-1

S_CTJON Xl_

NAVIGATIONA.L AIDS

TABLE OF CONTENTS

\4

i i :

:::::::::::::::

..................;!iiiiiiiii!i!_!_iii!

::'::,

':i:.

TITLE PAGE

GENERAL ............................................. 12-4

PERISCOPE .......................................... 12-4

SATELLITE CLOCK ................................ 12-14

EARTH PATH INDICATOR .................... 12-17

ALTIMETER ........................................... 12-18

LONGITUDINAL ACCELEROMETER ....... 12-18

HAND COMPUTER ............................... 12-18

ATTITUDE RATE INDICATOR ................ 12-26

NAVIGATIONAL AID KIT ................... 12-27

TEST CONFIGURATION ...... ._................ 12-27

2

REPORT $EDR 104

MODEL, 13 3

ST.LOUIS, MISSOURI

CC_ .".' F ' _ "- "''_-'_"


REVISED

REVISED

CAUTIONI.ALLOW 5 M_NUTE_ COOL-

IN_ TIk_E FOR MOTOR AFTEt

E/kC_ ETEND-RETRACT CYCLE

Z, IN_URE MOTOR _% '_TOPPED

BEFORE RE_ERS_ I_

EXTE_D-RE_RACT CYCLE

WARNINGINSURE ENGAGE LEVER

UP BEFORE PERISCOPE

POWER APPLIED.I I "

UMBILICAL (REF.)

FIGUR£ I?.-IPER_SCOPL ASSEmbLY (SHEET I:OF2)

_ ,_llr I RI I

PM4,5-110C-I

, -.- )

DATE

REVISED

REVISED

1 NOVEMBER 1961 " MCDONNELL,>_ __ST.LOUIS, MISSOURI

___"

PAGE

REPORT

MODEL

12-3

SEDR 104

133

r

_.TURAL

FIGURE 12-'iPERISCOPF..ASSEMBLY (_)HEE'T2 OF 2)Dk445- __O-;:'

_

REPORT SEDR 101_

MODEl 133

MCDONNE REVISED

ST. LOUIS, MISSOURI

__ ,_,_ _T _..-, _ .... REVISEDirl

XII. NAVIGATIONAL AIDS AND INSTR_S

12-1. GENERAL,,, ,

Normally the Astronaut will not find it necessary to compute any of the

factors relative to his flight or landing. In the event the need should arise,

however, the Astronaut is provided with all the equipment required to compute

altitude, course, velocity and landing data, and to attain and maintain the

proper attitude for each phase of the flight.

12-2. PERISCOPE DESCRIPTION

The periscope is a compact navigational instrument designed to withstand

loads up to 100 G's. The periscope consists of three major assemblies: The

display assembly, the upper housing assembly, and the lower housing assembly.

(See Figure 12-1.) The periscope is mounted in the capsule so that the objective

cartridge may be extended and retracted through a periscope door opening in the

bottom of the capsule. The opening and closing of the periscope door is

synchronized with the extension and retraction of the objective cartridge by

means of a mechanical link. Periscope progra_ning, during a normal mission,

begins with the periscope extended while the capsule and booster are still on

the pad. Upon capsule umbilical disconnect, the periscope retracts and remains

retracted until capsule separation. At this time the periscope extends and

remains extended during orbit. Thirty seconds after retro-package separation,

the periscope is again retracted. At approximately 10,000 feet altitude, the

periscope is extended for the last time and remains extended thronghout impact.

Following umbilical disconnect and Just prior to launch, if the "HOLD" sequence

is initiated, the periscope will automatically extend. Located on the left

hand console is the RETRACT SCOPE telelight and a switch which has AUTO and MAN

!/ !

-i'Ir .... m m_v_, _ _AD_, _ l_ _


REVISED

REVISED

Mc'DONNEL_L-_ __ST.LOUIS , MISSOURI

PAGE

REPORT

MODEL

12-5

SEDR 104

'133

;ROLL

®

®

-T,

KNOB

FIGU_'E:]Z'Z T_.I_cSC--OPEDISPLAY (,SHEET iIOF"7--SHEETS)i

PM4$-II ZA'I

PAGE.

REPORTMODEl

12_!6

SEDR104i ,

i 133i

Mc,DONNE_ST.LOUIS. MISSOURI


REVISED

REVISED

©

7 °4

P-t ,--._

I LP-i

oX

5* LEFT ROLL

EXAMPLE NO.1.

©

' i-i

Nw

CAPSULE 5MALLENDPITCHED 5 Q BELOW ORI_IT ATTITUDE

E_AMPLE NO.,_.

FIGUI:2E IZ-?_

o/ \o

J_i X ) / ,-,

O

CAPSULE LEVEL

EXAMPLE NO.2.

r---'-i

©O/ ,_

i-t

i-t

-q-4

0\< '0

CAPSULE_ IN _ETROGIRADEATTITUDE

EXAM F:::)LE NO. 4-.

PEQISCOPE DISPLh,_( (SNEF_.T. 2 OF 2)

- _-p ,L. I ..... --

pH4.5- tlZ- 7-

:'4

p_. I

RL'VlS_O ..... ST. :.OUlS 3, MISSOUm RmPORV SEDR 104

positions. If the periscope does not retract _0 seconds after retro-package

separation, the RETRACT SCOPE telelight will go on. The switch is then placed

in the MAN position and the periscope is retracted manually. The following

navigational information can be obtained concerning the capsule's position

relative to the earth: Drift, altitude, pitch, roll, true vertical, retro

angle, field of view of the earth-sky camera and relative bearings of the sun

and moon.

12-3. DISPLAY ASSEMBLY

The display assembly (See Figure 12-1 and 12-2) includes the following:

Scales, indicators, altitude reticles, attitude reticles and the controls for

their manipulation, earth image, horizon image and the retract pilot light. It

is mounted at the top of the upper housing assembly. The display assembly pro-

vides the Astronaut with a visual indication of the capsule's altitude and

attitude relative to the earth. It also provides him with the necessary indi-

cators and scales for obtaining bearings relative to the sun and moon. When

the earth is centered in the display, the portion of the image bordering the

altitude reticles will depict the earth's horizon. The center of the view

(crossline reticle) represents a vertical line to the center of the spherical

earth (see Figure 12-3). Image erection is such that the horizon and straight

down views are true.

12-_. True Vertical and Optlcal Vertical

In the true vertical attitude (see Figure 12-3), as compared to the

optically vertical attitude, the longitudinal axis of the capsule is perpendicular

to a line through the center of the spherical earth. The capsule is optically

vertical with respect to the earth when the capsule is pitched nose down at l_

degree amgle. _-

L w W,m g mR. _ ..... ._ . .. i_.JL--|_l Jl. |f'_im

PAGE,

REPORT

MODEL

12-8

SEDR 104

133

MCDONNE ST.LOUIS. MISSOURI

DATE

REVISED

REVISED

I NOVEMBER 1961

..J

cJ

_zLd;>

bJ

F-

bJD_f

0_dk-

:v

0

O-

oY",¢co

d

J,f

Z

ooO-

J

0_ Ig_dO>

FI_L_R,r- Z-3 VEHICLE ATTITUDES

_,,,,,,¢,,,_,,.,.,,-• --,,..--vvila al.,IL---i_ I g#'_ L

C)_C

_uJ.<

"iV)

Q_

PM4-5-Z_3

REVISED ST.LOUIS3,MISSOURI REPORT,SEDR 10_

REVISED MODEL 10_

12-5. Altitude

When the capsule is in the optically vertical attitude, the altitude of the

capsule may be determined by means of the altitude mechanism. This mechanism

includes four pairs of altitude reticles, which form a square within the circular

display area, the altitude knob and the altitude indicator (see Figure 12-2).

Turning the altitude knob moves the reticles to change the size of the square

and also rotates the scale of the altitude indicator. To determine altitude,

the knob Is turned to change the size of the square until the earth's image is

inscribed within the inner square formed by the reticles. The altitude is then

read from the altitude indicator. The point on the earth's surface vertically

below the capsule is indicated by the crossline reticle which appears at the

center of the display area. The crossline reticle is illuminated by a lamp,

the brightness of which is controlled by the reticle knob. The altitude indica-

tion range extends from 50 to 250 nautical miles. The altitude mechanism is

calibrated to indicate altitude within +5 nautical miles within the range of lO0

to 140 nautical miles, within +lO nautical miles at altitudes below lOO nautical

miles and within +50 nautical miles at altitudes above l_O nautical miles.

12-6. Pitch and Roll

The pitch and roll degree of the capsule with respect to its optical vertical

attitude may be approximated by use of the altitude mechanism (see Paragraph 12-5)

The distauce between the parallel curves which form each side of the altitude

reticle square is equivalent to a 5-degree angle at an altitude of ll5 nautical

miles. If the vehicle is off pitch, it will be impossible to adjust the reticle

square so that both the fore and the aft reticle curves (reticle curves relative

to the 180 ° and 0° positions on the drift scale) are tangent to the earth image.

If the vehicle is off in roll, it will similarly be impossible to make the left

and right reticle curves tangent to the earth image. To determine the approximate

--_AL ,,-, ,-_z-_l-_ i A !

REPORT SEDR 10_ REVISED"$T:"_UI$,, ,_MlUQU_I_. _,,,

MODEL I_ . -- C/___._.__T_W_.TTT._.T. REVISEDF

pitch angle, the reticle square is adjusted so that the horizon image lles across

either the fore or aft (depending upon the direction of pitch) inner reticle curve

by approximately the same amount that the opposite horizon edge lles inside the

opposite inner reticle curve (see Figure 12-2, Sheets 1 and 2). The degree of

pitch is estimated by comparing the distance that the one side of the horizon

image extends across the inner curve with the distance between the inner and

outer curve. The approximate roll angle is determined Im the same manner as

pitch angle.

12-7. Drift

Vehicle drift is determined by reference to five parallel drift reticles

etched on the face of the drift plate covering the circular display area (see

Figure 12-2 3 Sheet i). The drift plate is rotated by means of the drift knob.

A clear plastic drift scale is mounted under the drift plate. The drift scale

covers plus and minus 5 degrees of drift in increments of one degree. To

determine drift, the periscope is set for high power magnification. The Astro-

naut then rotates the drif_ knob until the ground track of the capsule in the

central high power view appears to parallel the drift lines. The drift of the

capsule is then indicated by the position of the center drift line with respect

to the drift scale.

12-8. RetroGrade An_le

The retrograde reticles provide an indication of whether or not the capsule

is in the proper retrograde attitude prior to re-entry. To achieve proper retro-

grade angle starting from the optically verticle attitude at an altitude of 115

nautical miles aud with zero drift angle, the nose of the capsule must be pitched

down until the horizon image at the bottom of the display is taugent to the three

retrograde reticles which form an arc across the lower half of the display area

(see Figure 12-2_ Sheet 2).

i[

: 7::_

LT_ LT-_ 1LT 5r_ T _ _ ..... _

-... vJ._ A" A_A_i, A A_L

DAT_

REVm_D. Srr.'--_ "'-'0""_LOUlS3, MmSOUm R_POnV _g 104

REV,SED .... MODm.. 133

.+

12-9. Sum-Moon Index

A ring shaped sun-moon index scale, used to indicate relative bearings of

sighted objects, is mounted so as to frame the circular display area (see Figure

12-23 Sheet l). The index ring is mauually rotated by means of a finger-grlp

control. The index scale is calibrated from zero to 360 degrees. A sum index

indicator, which enables sighting on the sun to obtain bearings, is mounted at

the zero degree position of the sun-moon index scale. A moon index indicator,

which enables sighting on the moon for bearings 3 is mounted at the 180 degree

position of the sun-moon index scale. Bearings are read off the sun-moon index

scale at the sun-moon bearing index mark located on the display assembly directly

in front of the Astronaut.

12-10. Earth-Sky Camera View

Four camera reticles located at the right center of the display area give

the approximate outline of the field-of-view of the earth-sky camera which is

included in the capsule equipment (see Figure 12-2, Sheet 1).

12-11. Orbit Velocity

The crossllne reticle is used to aid in the computing of orbital velocity

(see Figure 12-2, Sheet 1). A stopwatch is started as the first check-point

passes under the crossline reticle. When the second checkpoint passes under

the crosslime reticle, the watch is stopped. With this elapsed time, the orbit

velocity is computed by employing the satellite hand computer.

12-12. UPPER HOUSI_D ASSEMBLY

The upper housing assembly will incorporate the following functional com-

ponents: Two periscope mirrors, a filter installation, a magnification change

control mechanism, a manual extension-retraction control, a housing exhaust

valve, a desiccator assembly which includes the housing intake valve and the

housing purging valve.

_-"_""'"_"'*''! A I,_ll ma • i,=_'llll 'ql • il .__

PAGE, _,2-_2

REPORT SEDR 104

MODEL_ l°,_

_ DATE I November 19(31

St. LOUIS, MISSOURI

12-i3. Periscope Mirrors

The mirrors are so situated in the upper housing assembly as to present the

earth's image at a convenient angle to the observer (see Figure 12-_).

12-14. Filters

The upper housing assembly contains a clear, a red, a yellow and a medium

neutral density filter. The filters are mounted in a rack which can be rotated

to position the desired filter in the optical path. The filter rack is manually

driven through a system of pulleys and cables by means of the filter selector

which is located on the left side of the upper housing assembly (see Figure 12-1,

Sheet I of 2). Detents accurately position the filters with respect to the

optical path.

12-15. Ma_ification Chan6e Control

The periscope optic system is capable of high and low magnification. The

change in magnification is brought about by manipulation of the magnification

changer (see Figure 12-1, Sheet I of 2).

12-16. Manual Extension-Retraction Control

The manual extension-retraction mechanism enables the objective cartridge to

be extended and retracted manually (see Figure 12-1, Sheet i of 2). The mechanism

consists of a manually driven gear system which couples to the gear box and motor

drive assembly of the lower housing assembly through a manually operated clutch.

The gear system is driven by the ratchet handle on the right side of the upper

housing assembly. The ratchet handle is pulled up to place it in operating

position and pushed down to place it in the stowed position. For manual manipu-

latic_, the manual engage lever will be in the down position. The ratchet pawl

arm will determine the direction of motion (see instructions affixed to naviga-

tional aid kit).

12-17. Intake and Exhaust Valve

The intake and exhaust valve (see Figure 12-1, Sheet 2 of 2) allows the

upper housing to "breathe" without the passage of dirt to the inside of the

upper housing. The intake valve is mounted in an intake valve body to which the

intake end of a desiccant tube is attached. When the ambient cabin pressure

exceeds that inside the upper housing' the intake valve admits air to the upper

housing through a desiccant (silica gel). Moisture and dirt is thus removed

from the entering air to minimize condensation and dust deposits on optical

components. A purging valve (see Figure l, Sheet 2 of 2) provides an inlet and

an attachment point when purging the upper housing assembly with dry nitrogen

gas.

12-18. LOWER HOUSING ASSEMBLY

The lower housing assembly consists of a structural shell housing the

objective cartridge. The following items are mounted on the structural shell:

Extension-retraction motor, gear box, lower limit switch assembly and a reticle

illumination assembly (see Figure 12-1, Sheet 2 of 2).

12-19. Objective Cartridge

The objective cartridge houses the objective lens, power change lens and

the collective lens (see Figure 12-4). It is mounted inside the structural shell.

A connecting link between the objective cartridge and the periscope door allows

the door to move in unison with the telescopic motion of the objective cartridge

(see Figure 12-1).

12-20. Objective and Collective Lens

Wide-angle objective lens provides a wide field of view (approximately 180°).

Light gathered by the objective lens passes through the collective lens, where

the first image is formed (see figure 12-_).

MCDONNE REPORT SF.,DR'lOb.. REVISED

ST. LOUIS, MISSOURIMODEL 1,_,_ '_-_Jr%_,T117T T_T:_...... REVISED

12-21. Power Chaz_e Lens

The power change lens (see Figure 12-4) can be moved in and out of the

optical path by means of a mechanical linkage.. The mechanical linkage is actuated

by the magnification changer (see Figure 12-1). For low power periscope operation

the power change lens is moved out of the optical path; while for high power

operation, the lens is moved into the optical path.

12-22. SATELLITE CLOCK

The specification satellite clock is an electro-mechanical timing device

located above and to the right of the periscope display assembly. The satellite

clock will indicate time of day, TIME FROM LAUNCH, TIME TO RETROGRADE and RETRO-

GRADE TIME (see Figure 12-5). The time of day will be reflected by a manually

wound spring-driven movement watch. The manually wound watch is located in the

upper left-hand corner of the satellite clock. Time From Launch, Time To Retro-

grade, and Retrograde Time will be displayed on drum counters (digidial). The

drum counters will indicate time in hours, minutes and seconds. The time

elements will move in one step increments. The Time To Retrograde digidial will

be supplemented by a telelight, located in the upper right-hand corner of the

satellite clock, which will illuminate 5 minutes prior to retrograde time; in

addition to the telelight, an aural signal to the Astronaut's headset is

initiated i0 seconds prior to retrograde time. The satellite clock is auto-

matically started by 28V d-c power at liftoff. Should this not occur, a push

button switch is provided above and adjacent to the clock to allow the Astronaut

to energize the clock (aud maximum altitude sensor) manually. The retrograde

time is normally computed and set prior to flight, but the retrograde time can

be manually changed by the Astronaut (retrograde time reset handle) or remotely

set through the cce_nand receivers. Ten minutes prior to retrograde time, the

)_J

DATE

REVISED

REVISED

1 NOVEMBER 1961

ST.LOUIS. MISSOURI

PAGE.

REPORT

MODEl

12'15

SEDR 104

133

DISPLAY ASSEMBLY

UPPER HOUSING ASSEMBLY

MIRROR

LOWER HOUSING ASSEMBLY

OBJECTIVE CARTRIDGE

POWER CHANGE LENS

FIGURE 12-4 OPTICAL SYSTEM SATELLITE PERISCOPE

DRIFT LINE PLATE

FIELD LENSES

MIRROR

FILTERS

ERECTOR LENS

COLLECTIVE LENS

OBJECTIVE LENS

PM45-262

PAGE

REPORTMODEL

12-16

SEDR 104

133

ST.LOUIS, MISSOURI


REVISED

REVISED

' POSITION RELATIVE TO EARTH

TIME OF DAY

IEARTH PATH INDICATOR

ELELIGHT

,'TYP .)

SATELLITE CLOCK

TIME P_SET HANDLE

I FIGURE 12-_5 i EARTH PATH INDICATOR AND SATELLITE CLOCK PM4._-II3E

VVl 11 ni.tl---,I I i l/'_i,IL-

DAT_, ,iNovember 1961

R£V|SI[D,

R£VIS£D


PAG_ 12-17

mm=ORV, SEDR 10b,

MOmta. 133

satellite clock transmits a signal to the ASCS to start horizon scanners operating

continuously and assures rate gyro operation in preparation for retro sequence.

Upon reaching retrograde time, a set of contact points within the clock close,

initiating the retrograde sequence. Time From Launch and Retrograde Time

digidials provide outputs for telemetering.

12-23. EARTH PATH INDICATOR

The earth path indicator (see Figure 12-5) consists of a spherical map

(globe) of the earth gimballed and rotating in a manner to indicate ground

position under the capsule. The indicator is spring motor powered and is

capable of running 20 hours without re-windlng. The globe, which is approxi-

mately 3.85 inches in diameter, will display the following geographical features:

(i) All continents

(2) All bodies of water having major dimensions of 300 statute miles

(3) The sixteen largest rivers of the world

(4) All islands having major dimensions of 500 statute miles

(5) All known islands or island clusters separated from continents

by 300 statute miles and having major dimensions less than 500

statute miles shall be identified by an .020 diameter circle.

(6) The fifty largest cities of the world are identified by .020 dots.

(7) 15° latitude and longitude lines are presented and numbered.

Controls are provided on the face of the indicator to wind the spring motor

and to adjust the orbit time, adjust orbit inclination and to slew the globe

about the earth and the orbital axis. The touchdown area is displayed as a

rectangle and the luminous dot inside of the rectangle being the point of impact.

The landing area is 3040 nautical miles ahead of instantaneous orbital position

above the earth as indicated by the four ring bullseye. The instrument is

externally lighted by cabin floodlights.

T.L;4Fi_V.i,iT;AL

18

REPORT S_nR Ina

MODEL_ i_

Mc'DONNE ,REVISED

ST. LOUIS, MISSOURI_,-_r%]%TW_Tw-_W_T.n. • T REVISED

12-24. ALTIMETER

The altimeter visually indicates external pressure above sea level. (See

Section I for location.) It is a single revolution type, calibrated from 0 to

i00,000 feet, with a marker at I0,000 (MAIN) and 20,000 (SNORKEL). Static

pressure is obtained from a centrally located plenum chamber which connects to

four static ports spaced equally around the small end of the capsule conical

section. The instrument is lighted externally by cabin floodlights.

12-25. LONGITUDINAL ACCELEROMETER

The accelerometer is a self-contained unit which is housed in a hermetically

sealed inclosure. (See Section I for location.) The accelerometer is designed

to indicate acceleration in the range 0 to -9 and 0 to +21 g units (acceleration

of 32.2 feet per second per second). Attached to the face of the accelerometer

are three pointers. One pointer will indicate instantaneous acceleration. The

remaining two pointers are memory pointers. One memory pointer will record

positive acceleration and the other will record negative acceleration. The

memory pointers will incorporate a ratchet device which will maintain a deflec-

tion until they are reset by means of a reset knob which is located in the lower

left hand corner of the accelerometer.

12-26. HAND COMPUTER

The satellite hand computer (see Figure 12-6), physically resembling a

circular slide rule, is provided to aid the Astronaut in solving navigation

problems. The computer consists of three discs; a basic fixed disc, a small

top fixed disc and a rotating intermediate disc. The computer is stowed in the

Astronaut's map case. The computer may be used to find orbital tangential

velocity, orbital angle, drift, true ground speed, indicated ground speed, and

for multiplication, division and proportions. Operation of the computer is as

d_ ink ?LT _ T lr'k lr_ _v r_r_ v *


REVISED

REVISED

M 'DONNELL ' ST.LOUIS, MISSOURI

PAGE,

REPORT

MODEL

12-19

' /

SATELLITE (_

'_ HAND COMPUTER

USI_ NUM_RStN (")

FIGURE 12.-8 Z_,NE) CO_P_TF-.Q.Pk445 - 115

20

REPORTSED: lo4

MODEL_ 1,3_


-_ _',-,,"_"_'r_ **'_ ...._ REVISED

follows :

12-27. Orbital Tangential Velocity

A. To compute orbital tangential velocity when ground distance, altitude

(nautical miles) and time (minutes) are known, proceed as follows:

(a) Set the time on scale B opposite the ground distance on scale A.

(b) Read orbital tangential velocity in nautical miles per minute on

scale C opposite the altitude.

(c) Read orbital tangential velocity in knots (nautical miles per hour)

on scale A opposite the altitude (at 6.0 on scale B).

I.

Be

Sample Problem

Given:

ground distance

time

alt it ude

Re quired :

= 2880 nautical miles (N.M.)

= 12 minutes

= 120 N.M.

Orbital tangential velocity in N.M. per minute and

orbital tangential velocity in N.M. per hour.

Operation:

(I) Set the time 12 (1.2) minutes on scale B opposite the ground

distance 2880 (2.88) N.M. on scale A.

(2) Read orbital tangential velocity 248.39 N.M./min. on scale C

at 120 on the altitude scale.

(3) Read orbital taagential velocity 14,903.4 N.M./hr. on scale A

opposite 12Oon altitude scale (at 6.0 on scale B).

To compute orbital tangential velocity when angular position in degrees,

time in minutes sad altitude in nautical miles are known, proceed as

follows:.

(a) Set the time on scale B opposite angular position on scale A.

v// ¸

......rr-,---.... TIA '-

REVISED. ST, LOUIS 3, MISSOURI RKPORT, SEDR 10_

REVISED ......... MODEL. 133

i

Ci

(b) Read orbital tangential velocity in nautical miles per minute

(N.M./rain.) on scale D.

(c) Read orbital tangential velocity in N.M./hr. on scale A opposite

altitude on altitude scale (at 3.6 on B scale).

II. Sample Problem

Given :

angular position

time

altitude

Required :

= 48 degrees

= 12 minutes

= 120 N.M.

Orbital tangential velocity in N.H./min. and orbital

tangential velocity in N.M./hr.

Operation :

(1) Set the time 12 (1.2) rain. on scale B opposite angular position

48 degrees (4.8) on scale A.

(2) Read orbital tangential velocity 248.39 N.H./min. on scale D.

(3) Read orbital taugentlal velocity 14,903.4 N.M./hr. on scale A

opposite 120 on the altitude scale (at 3.6 on scale B).

To compute orbital tangential velocity when ground speed in nautical miles

per minute (N.H./min.) and altitude in nautical miles are kno_ra, proceed

as follows :t

(a) Set the altitude zero (0) on the E scale opposite the ground speed

on the scale A.

(b) Read orbital tangential velocity on scale A opposite altitude on

scale E.

IIl. Sample Problem

Given:

ground speed = 239.6 N.M./rain.i

22

REPORT _..oI_ 104

MODEL. 133

REVISED .....ST. LOUIS, MISSOURI

_'_ .',,,..._ REVISED ....

altitude

Required :

Operation:

= 120 N.M.

Orbital tangential velocity in N.M./min.

(i) Set altitude zero (0) on scale E opposite the ground speed

239.6 (2.396) N.M./min. on scale A.

(2) Read the orbital tangential velocity 248.00 N.M./min. on scale A

opposite altitude 120 N.M. on scale E.

NOTE

Conversion of orbital tangential velocity to

ground speed is the same as the above procedure

but in reverse. Set altitude on scale E opposite

orbit tangential velocity on scale A then read

ground speed on scale A opposite zero (0) altitude

on scale E.

Orbital _le

To compute orbital angle when grotmd distance in nautical miles (N.M.)

is known, proceed as follows:

(a) Set 1.O of scale B opposite the degree index mark (located at 1.67)

of the A scale.

(b) Read orbital angle on the A scale opposite the distance on the B scale.

I. Sample Problem

Given :

ground distance = 2880 N.M.

Required: Corresponding orbital angle

Operation:

(1) Set 1.O of B scale opposite degree index mark (located at 1.67)

of the A scale.

,L/',


R_VlSED

RF-.'VIS£D

MCDONNELL.ST. LOUIS 3, MISSOURI

PAGE 12-23

Rm_o,_T _oR 104

MOOre. 133

,k,

_j

B.

(2) Read equivalent orbital angle of 48 degrees on scale A

opposite the distance 2880 (2.88) N.M. on the B scale.

NOTE

The procedure is the same for finding

ground distance when the orbital angle is

known. Set 1.O on B scale opposite degree

index mark on A scale then opposite to any

degree on the A scale the equivalent ground

distance is read on the B scale.

To Calculate orbital angle when latitude and orbital inclination are known,

proceed as follows:

NOTE

The G scale has two sets of numbers. The

plain numbers, increasing clockwise_ are

used for computimg drift while the numbers

in parenthesis, increasing counterclockwise,

are used for cc_puting orbital angle.

(a) Set zero (0) of G scale opposite latitude on F scale.

(b) Read orbital augle on G scale opposite orbital inclination on F scale.

If. Sample _roblem

Given:

ground latitude = 14 degrees 29 minutes

orbital inclination = 30 degrees

Required: Orbital angle

Operation:

(1)

(2)

Set zero (0) of G scale opposite latitude 14° 29' om F scale.

Read orbital amgle (30°) on G scale opposite orbital inclina-

24

REPORT SFZ)R lO4

MODEL_ IBB


"-_v _ _ _,.._._,_, REVISED

C.

De

(a)

(b)

12-29.

A.

tion 30° on F scale.

To compute latitude when orbital angle and orbital inclination are known,

proceed as follows :

(a) Set orbital angle on G scale opposite orbital inclination on F scale.

(b) Read latitude on F scale opposite zero (0) on G scale.

To compute angle of inclination when latitude and orbital angle are known,

proceed as follows:

Set zero (O) of G scale opposite latitude on F scale.

Read orbital inclination on F scale opposite orbital angle on G scale.

Drift

To compute drift when orbital inclination, orbital angle in degrees and

orbital velocity in degrees per minute are known 3 proceed as follows:

(a) Set the orbital angle on the G scale opposite the angle of inclina-

tion on the F scale.

(b) Read the drift in the lower window opposite the orbital angular

velocity on the I scale.

I. Sample Problem

Given:

orbital inclination = 32°

orbital angle - 0O

orbital angular velocity = _°/min.

Required: Drift

Operation:

(I) Set orbital angle 0° on the G scale opposite 32° angle of

inclination on the F scale.

(2) Read drift 1.897° in lower window opposite 4° orbital angular

velocity on the I scale.

4

J

_J_'A JLJLJJL_I" A JL_IL]L_

"4

REVISED ST. L.OUIS 3, MISSOURI RI[PORT SEDR 101r

REVISED ._ _ MO0_. 133

12-30. Orbital Ground Speed

A. To compute orbital ground speed, we must first find the effective component

of the earth's tangential velocity and then add it to the indicated ground

speed. To find the earth's tangential velocity component, the following

must be known: Orbital inclination, orbital angle and the earth's tangential

When the above information is available, proceedvelocity at the equator.

as follows :

NOTE

In the following presentations, the F and

G scale is not used according to their desig_

nation. They are to be used as directed.

(a) Set the orbital Imclinatlon on the G scale opposite 90 degrees (zero)

degrees) on the F scale.

(b) Read effective component of earth's tangential velocity on the A scale

opposite the earth's tangential velocity at the equator on the B scale.

(c) Orbital ground speed will be indicated ground speed plus effective

component of earth' s tangential velocity.

I. Sample Problem

Given:

earth's tangential velocity at the equator =

orbital inclination

orbital angle

indicated ground speed

Required : Orbital ground speed.

Operation :

(1)

15 ..../rain.

= 30 degrees

= 0 degree

= ..M./min.

Set the orbital inclination 30 degrees on the G scale opposite

orbital angle zero degrees (90 degrees) on the F scale.

t#1_/i_iF i1.11_il • l* le,r_-

26

REPORT S_ 104

MODEL_ I,,_

,MCDONNE ST. LOUIS, MISSOURI

DATE 1 November l C_l

REVISED.

REVISED

(2)

(3)

Read effective component of earth's effective tangential velocity

12.99 (1.299) N.M./mln. on the A scale opposite the earth's

tangential velocity at the equator 15 (1.5) N.M./min. on the B

scale.

Orbital ground speed-- indicated ground speed (240 N,M./min.)

plus effective component of earth's tangential velocity (12.99)

or 252.99 N.M./min.

NOTE

Effective earth velocity is constant;

orbital ground speed for all practical

purposes can also be considered constant

for any given orbit.

12-31. ATTITUDE-RATE INDICATOR

The Attitude-Rate indicator is a three axis angular rate and attitude indi-

cating system located approximately at the top center of the main instrument

panel. It is designed to indicate attitude and the rate of change of attitude.

The unit is a composite arrangement consisting of a rate indicator around which

are positioned a roll attitude indicator, a yaw attitude indicator and a pitch

attitude indicator (see Section I, Figure 1-15). The rate indicator will display

three pointers. The rate of roll pointer is the pointer which is parallel to the

pointer of the roll attitude indicator. The rate of yaw and rate of pitch

pointers are pointed towards the yaw and pitch attitude indicators respectively.

All components are completely interchangeable. The failure of one component will

not necessitate recalibration or replacement of allied components. The attitude-

rate indicator is activated by pitch rate, roll rate and yaw rate transducers.

Each transducer consists of a gyroscope, an amplifier and a demodulator. These

J._ A A_ILJIm

___ImmJeiOMbm_

REVISED ST. LOUIS 3, MISSOURI REPORT. SERE lO_

REVIs_o - L _ Moo_ 133

/,r ,

components function together to produce a d-c output signal proportional to the

input rate of change of attitude.

12-32. NAVIGATIONAL AID KIT

The navigational aid kit consists of a neoprene coated nylon case, a binder

assembly and a computer board. It is mounted to the periscope directly below

the circular display area (see Figure 12-1, Sheet 1 of 2). The binder assembly

consists of a number of index cards. The index cards will be used to file check

lists, rate cards and navigational charts that shall be provided as required by

the particular capsule mission. The following Items are attached to the binder

assembly: Pencil holder, mechanical pencil and nylon retention springs. The

pencil holder is fabricated from neoprene coated nylon and is sewn to the case.

The mechanical pencil is secured to the binder assembly by means of a nylon

retention spring. A nylon retention spring also secures the binder assembly to

the neoprene coated nylon case. A computer board, which is constructed from the

hand computer (see Figure 12-4), forms a part of the navigational aid kit.


12-34. TEST CONFIGURATION CAPSULES 8, 9, i0, 13 AND 16

12-35. General

Capsules 8, 9, I0_ 13 and 16 are fundamentally the same as the specification

capsule. Some differences will exist in the location of the various instruments.

(See Section I for instrument panel illustration. ) Other differences are

enumerated in the following paragraphs.

12-36. Periscope

Capsule 8 periscope system will not incorporate a RETRACT SCOPE telellght

and the associated MAN-AUTO periscope retract switch. Capsules 9_ 13 and 16 will

have provisions for telemetering periscope door closure. Before ground operation

vvx_. m_awa ,mm zm mkm

REPORT _DR 104 ST. LOUIS, MISSOURI REVISED

MODEL. 133 ---L'_ .NF'_ E N,_. REVISED

of periscope, observe operational instructions attached to the navigational aid

kit (see Figure 12-1). Equipment in the periscope upper housing assembly in

Capsule 9 has been removed to faciliate installation of an internal camera

(see Figure 12-7).

12-37. Altimeter

The altimeter used in Capsule 8, 9, i0, 13 and 16 have markings at the 20,00C

and I0,000 foot levels to indicate when the snorkel valves and main parachute,

respectively will actuate. Along the outer edge of the instrument dial starting

at 0 feet and advancing to 28,000 feet are psia indications which are as follows:

0 feet 15 psia, i0,000 feet i0 psia and 28,000 feet 5 psia.

12-38. Longitudinal Accelerometer

Capsules 8 and 9 will not have memory pointer or a reset mechanism. The

location may vary with each capsule depending on planned mission. (See Section I

for instrument panel illustration. )

i2-39. Hand Compute.r

Only manned capsules will be equipped with the hand computer.

12-40. Attitude-Rate Indicator

NOTE

External appearance of attitude-rate indicator display is the same for all

capsules except for color of pointers and as follows:

On Capsule 9, the pitch dial of the display mates with the zero pitch rate

index at -43 degrees.

On Capsules 8, i0, 13 and 16, the pitch dial of the display mates with the zero

pitch rate index at -34 degrees.

12_41. Navigational Aid Kit

Capsules 8, 9 and 13 will not contain a navigational aid kit.

.....i,i mil i i _wJk _

DATE ,

REVISED

REVISED

I NOVEMBER 1961 M_'DONNE__ __ST.LOUIS, MISSOURI

PAGE 12_29

REPORT SEDR 104

MODEL 133

\4 __

(_ ,_"_"%_ UPPER PERISCOPE

f ""d) _ f HOUSING ASSEMBLY

V %..

CLOCK---...._ / - t+_7_-,__

, ............ _,__+_-_: + ,_,,_+,

MIRROR LENS j

WINDOW ASSEMBLY _ " " " _/ ll_'_""_r+..._mr+....+. LO_/E R PE pjSC O p_

HOUSlNG ASSEMBLY

FIGURE 12-7 INTERNAL PERISCOPE CAMERA (CAPSULE 9 ONLY)

CC.;-;;_..JT:AL

PM45-272

13-1

SECTION XII

INSTR UMENTATION SYSTEM

_..j1

:::::::::::::::::::::::::::

iiiiii!!ii_'i_@

================================

, ili!ii!iiiiiiiiii!i!!iiiiiiiiiiiiN ,iiiii!!iiiiiiiiiiiiiiiiiiii!iiii!,_

:_iii_!iiiiiiiiiiiiiiiiiiiiii!iiiii!iiiiiiiiii _;::''• t -:. .. ================================================

:i!: iliiii!!!ilililiili!========================================

TITLE

TABLE OF CONTENTS

PAGE

SYSTEM DESCRIPTION ...........................

SYSTEM OPERATION ....... •......................

SYSTEM MONITORING ...........................

SYSTEM INSTRUMENTATION CONTROL ...

INSTRUMENTATION RECORDING ............

13-4

13-4

13-4

13-24

13-25

SYSTEM UNITS ........................................ 13-29

TEST CONFIGURATION ......................... 13-55

- 8_AIl. llpIIIl_.lmi tool I. I

_il]l ll_i--i I I i/_l I-

i.i.i

I.Ii,I

0Z

n nI.I,I Id

w _ -

=)

m

o

I-

ILl I_

,_ w CIf. If: _i

H_IIM9 11B17

NOZIaOH /--_±nma NI_V_

/ "--_"/_ /--(Hglld) _I3"NU)5 / --HDI'/_C

/ V _ NOZIaOH/ / 11"I]

/ /,_ ----_:-_ / ,_old3_

N051113C /

I',ll_'lN

//

(S3)V-W) 7V)Id_I)SOION370S, 70_1N0)

NO(13V3B ISnBH1-MO'I

fSlJVTd 9 IV3M_±)S_ION3IO_ 70_JIN03

1Sfl_IHI-IH

"3"_ 7'# (_N _Vt

(°dM3± _11:/i37NI J.tn S')

Sg3_d7'_ _l_d_0

7 CrdlNO_) NOII_V_

_:m_C_N_LL. "_:_r_--_l_ "

70_I140") V_3J.%_.%

_OSti3C BY13J_ _3J,._3h_il

J._o C]N_ _43MF_7

$ 'ore xo@ ,_VTa_j._o C]N'_ Hor_nv7

(_anSSB_d _l_f

_70N_H 1_09V

_£3_NOIJ.N310d

NOIIOV_HOkld

/

, \

• I

DATE , ,, , I NOVEMBER 1961

REVISED

.REVISED

_'11 .....

Mc'DONNELL_L_ __ST.LOUIS, MISSOURI

PAGE ,,

REPORT

MODEL.

,13-3

SEDR 104

133

':<}}.

/

//

/

--,_-_,,;.;, ;T-,_-;4T ;A.L

PAGE, 1B-_

REPORT _EDR lOl_

MODEL. 133

ST. LOUIS, MISSOURI


REVISED

REVISED

XIII. INSTRUMENTATION SYSTEM


The instrumentation system consists of the major components as shown on

Figure 13-1. These components coupled with various transducers and other pickup

devices provide a means of monitoring the physical condition and reactions of

the Astronaut as well as capsule conditions and systems performance. The data

so obtained is coded and applied to the telemetry transmitters and radiated to

ground stations for immediate analysis and evaluation; it is also recorded on a

tape recorder in the capsule for subsequent study and interpretation. Cameras

are installed and so positioned to record the Astronaut's facial expressions

and to provide a chronological record of the instrument readings on the main

instrument panel. Provisions are also provided for automatic programmed control

over some components not intended for continuous operation.


The instrumentation system is completely automatic in operation from the

time power is applied to the capsule until lO minutes after landing impact,

however, certain components may be controlled or interrogated during flight by

either the Astronaut or ground command. The instrumentation system is divided

into three groups, namely_ monitoring, control and recording. These three groups

are treated individually in paragraphs 13-3, 13-59 and 13-63.

13-3. MONITORING

Instrumentation monitoring consists of sampling values of pressures, tempera-

tures, conditions and operations of various units and functions throughout the

capsulej these samples are converted into signals composed of voltages propor-

tional to the temperature, pressure and conditions being measured. The proper-

MAC 231C (Eev 14 Oc +. GG)

DAT£ I November i_I ___- _'_' IB-5

R_VlSED ..... s'r. Lou,s s, MJssoum ms,owr SEDR 104

RWmEO. ..................... Hoom. 133

/

, \

tlonal voltages are calibrated within common maximum and minimum ranges to pro-

vide zero to full scale readings. These signals are then channeled into either

or both of the two commutators (electronic switches) designated High Frequency

and Low Frequency, which are located in Instrumentation Package "A". The

majority of the signals are fed to both "HF" and "LF" Commutators for redundancy.

Each commutator continuously samples its input Channels, combining the signal

voltage pulses into a pulse train for each commutator. The pulse train from the

HF Com_Atator and the LF Commutator is applied to separate but identical 10.5 Kc

voltage controlled subcarrier oscillators, where the changing voltage of the

pulse train vary the frequency of the oscillators. The output of this and other

voltage controlled oscillators driven by aero-medical information are mixed and

used to modulate the telemetry tram_mltters. The HF Commutator signals are

telemetered through the high frequency transmitter while the LF Commutator

signals use the low frequency set. Both the HF and LF Commutator signals are

also converted to pulse duration signals and recorded on a tape recorder in the

capsule.

Figure 13-2 is a block diagram showing the parameters of the instrumentation

that is monitored as well as the Commutator Point assignments with a brief

explanation of each parameter given in paragraphs 13-_ through 13-58.

1S-4. Capsule Electrical Power

Capsule electrical power system instrumentation consists of monitoring the

circuit illustrated on Figure 1S-2.

13-5. 400 cps Monitor

ASCS and fan bus ll5 volt a-c is applied thru two 115/6.3 volt transformers

in Instrumentation Package "A" and '_". The secondary outputs are rectified,

filtered and attenuated prior to being applied to the commutators as a zero to

three volt d-c signal. A three volt signal (full scale) represents 120 volts

PAGE, 13,_6

REPORT SEDR 104

MODEL 133

Mc'DONNELj__ __ST.LOUIS, MISSOURI

v v i ! n 8 IltW mines| 1 • | _J_lk Ikm

DATE

REVISED

REVISED

1 NOVEMBER 1961

I hiIVELOC,T'_s_._o__i1_H

l;'r=C-TI _'l E_,_.N D I i_'r'T _.. t-a U O:r 0 _.

I _-_'_-'_ I

_ECE_T_CL5

_ICONE

_ _t_'TENNA_w LT¢

_)E$C6NT

_NTE_N _,

T _J:_, N% K^. IT'T E 0

VOICE _ G%',4_,LS ]

LANDIN_

FIGURE. 15- Z. bI_NI_OI_Ik_GIlN,ST_UMEt/TATION BLOCK DI/_GP, AM-(C,_PSULE5 ie_£)

• a,lJml..n _l • I1"_= 2

J

MAC 231C (Roy 14 Oct. 55)

ovemberl l Mc,DONNELL 1 -7

for each bus.

13-6. D-C Current

D-c current amplitude is sensed by the shunt for the instrument panel

ammeter. This shunt is in the negative lead of all capsule batteries and senses

total battery current. The voltage across the shunt is 50 millivolts when 50

amperes are flowing. This voltage is applied to two d-c amplifiers in package

"C" which amplifies it to a zero to three volt level. A three volt level (full

scale) represents 50 amperes battery current. The output of one amplifier is

applied to the HF Commutator, and the other amplifier output is applied to the

LF Comnutator.

13-7. D-C Voltage

The 24 volt d-c monitor circuit is made up of a voltage divider network

in package "A". Voltage from the main pre-lmpact 24 volt d-c bus is applied to

this divider. A three volt signal (full scale) represents 30 volts bus voltage.

The 18 volt d-c isolated bus and the 18 volt d-c standby busses are similarly

monitored through voltage divider networks located in the '_" package.

13-8. Standby Inverter

The standby inverter on signal is obtained through normally open contacts

of the standby inverter relay. This relay energizes when either of the main

inverters fails. With the relay energized, 2_ volts d-c is applied to an

attenuator in the power and control relay box. Attenuator output (2.2 volts

d-c, nominal) is applied to the commutators.

13-9. Instrumentation Power Supplies

Instrumentation power supplies instrumentation consists of the monitor

circuits for the 3 volt d-c reference, zero reference, and 7 V 400 cps power

supplies. (See Figure 13-2. )

YVlll |ia/l_mll • illl_q

PAGE,,, 17-8 MCIDONNE_ __ DATE 1 November-1961

REPORT SEDR 10_ .......... ST:'_OUIS-, _MtSSQURL. REVISED

13-10. Three Volt Reference

The 3 volt d-¢ reference power supp17 furnishes excitation for all potenti-

ometer type instrumentation pick-ups. The power suppl7 is located in package "A"

It is a zener diode regulated supply fr_n the 24 volt bus. The output from the

power supply is applied directly to the cumautators and serves as a reference

full scale si_l..

13-11. Zero Volt Reference

The zero reference si6nal is slsnal ground and is also the return for the 3

volts d-c reference power supply output. This signal is also applied to the

c_utat ors.

13-12. Seven Volt 400 cps

The 7 volt 400 cps Power supply fur_Lshes excitation for the input bridge

circuits utilized with the resistance element amplifiers. Power supply output

is rectified, filtered and attenuated to a zero to three volt level. This zero

to three volt signal is applied to the cazmutators. A three volt si_l (full

scale) represents a 7 volt output level. The power supply is a transistorized

Power inverter which operates on 2_ volts d-c to provide the 7 volt 400 eps out-

put. It is located in package "A".

13-13. Calibration On

Calibration ON instrmnentation consists of a circuit which monitors presence

of the full scale and zero scale calibration cunm_d s_ls. 1_ds_ is present

when the CALIBRATION switch in the telemetry trailer is placed to "FULL SCALE" or

"ZERO" position. When the f_l scale calibrate cc_nand is present, 24 volts d-c

is applied to an attenuator in Package "C". The output of the attenuator (2.8

volts d-e, naeLinal) is applied to the ca_utators. When the zero scale calibrate

command is present, 24 volts d-c is applied to a different input point on the

same attenuator network. The output of the attenuator (1.5 volts d-c, nce_mal)

f_ lr't _T lr_ lr "ri T_ ",_',"-" - •

MAC 231C (l_v 14 Oct. §S)

1Novem r Mc,DONNEg 13-9REVISED ST. LOUIS 3, MISSOURI REpoRT, SF_R 10)-t -

RWISE= -_- MO.m. 133

L !

is applied to the commutators.. Thus, an upper scale signal indicates presence

of the full scale calibrate command and a half-scale signal indicates presence

of the zero scale calibrate command. These command signals energize relays

which apply calibrate signals to numerous other instrumentation channels. The

'_" and "Z" calibrate function may be initiated from a ground station through

the command receivers while in orbit.

13-i_. Static Pressure

Static pressure instrumentation consists of a potentiometer type transducer

which is operated by static pressure. The potentiometer is excited with 3 volts

d-c from the instrumentation power supply and wiper voltage output is inversely

proportional to static pressure. A three volt signal (fUll scale) is representa-

tive of 0 psia.

13-15. Environmental Control System

Environmental control system instrumentation consists of circuitry which

monitors primary and secondary oxygen supply pressures, suit inlet air pressure

and temperature, cabin pressure and temperature and coolant quantity.

13-16. Suit 02 Partial Pressure

02 partial pressure is sensed by a transducer in the Astronaut's suit# the

signals are amplified and transmitted to a pressure gage on the instrument panel.

The signals are also applied to the "HF" and "LF" commutators in Instrument

Package "A" where they are converted to PAM and PDM signals. The PAM signals

are telemetered to ground and the PDH signals are recorded on the capsule tape

recorder.

13-17. Oxygen Supplies

Primary and secondary oxygen supply pressures are sensed by pressure

actuated dual potentiometers in the environmental area. One potentiometer

operates a panel indicator while the other wiper picks off a value for instru-

..... •_-L,-P! A !

PAGE .... 13-10

REPORT _nR lo_

MODEL. l_

Mc,DONNE DATE 1 November l_l


--- C___. ___T__T_____.T___T_ REVISED ,

mentatlon. Wiper voltage output is linearly proRortional to pressure. Excitation

is applied from the 3 volt d-c instrumentation power supply. The zero to 3.00

volt wiper output represents a pressure range of zero to 7,500 psi with 0 to 100%

meter indications. Outputs from the primary and secondary oxygen supply pressure

transducers are applied to both commutators.

13-18. Suit Inlet Temperature

Suit inlet air temperature is sensed by two resistance element transducers

in the suit inlet air line. Transducer resistance varies proportionally with

temperature. Each transducer is part of a bridge input circuit to an amplifier

in package "A". The zero to three volt (full scale) output from the amplifier

is representative of a temperature range of 35 ° to lOO°F. One amplifier output

is applied to the HF Commutator; the other amplifier output is applied to the LF

Commut at or.

13-19. Suit Inlet Pressure

Suit inlet air pressure instrumentation consists of a potentiometer type

transducer which is pressure actuated. The potentiometer is excited with 3

volts d-c from the instrumentation power supply and wiper voltage output varies

linearly with pressure. The zero to three volt (full scale) output represents

a pressure range of zero to 15 psia and is applied to both commutators.

13-20. Cabin Pressure

Cabin pressure instrumentation consists of a potentiometer type pressure

transducer installed in package "C". The potentiometer is excited with 3 volts

d-c from the instrumentation power supply and wiper voltage output is linearly

proportional to cabin pressure. The zero to three volt (full scale) output

from the wiper represents a pressure range of zero to 15 psia.

13-21. Cabin Air Temperature

Cabin air temperature is sensed by two platinum resistance wire transducers

i •

MAC 231C (Eev 14 Oct 55)

l ovember Mc,DONNELL l -llREVISED ST. LOUIS 3, MISSOURI REPORT _EDR lO_

REVISED _____ Hoo" ,133

mounted in package "A". Transducer resistance varies proportionally with

temperature. Each of the transducers is part of a bridge input circuit to an

amplifier in package "A". The zero to three volt (full scale) output from the

amplifier is representative of a temperature range of zero to 200°F. Amplifier

outputs are applied to the HF and LF Commutators.

13-22. Coolant Quantity

Coolant quantity is measured by sensing the pressure of the oxygen bottle

used to force water fr_n the coolant tank. This bottle supplies five hundred

pounds pressure. As coolant quantity decreases, the confined volume of the oxygez

increases with a resulting decrease in oxygen pressure. A pressure potentiometer

excited by three volts d-c from the instrumentation power supply monitors oxygen

pressure. Wi_r output is applied to the HF and LF Commutators and through an

attenuator in package "A" to the coolant quantity indicator. Zero to three

volt (full scale) covers a range of zero to 100% coolant quantity. Oxygen

pressure at 100% coolant quantity is 480 psi, oxygen pressure at 0% coolant

quantity is 230 psi.

13-23. Reaction Control STstem

Reaction control system instrumentation consists of monitors for automatic

and manual reaction control supply pressure and Astronaut hand control position.

13-2_. Horizon Scanner

Horizon scanner instrumentation monitors for the pitch and roll horizon

scanner outputs and ignore signals for each of these outputs.

The horizon scanner system utilized two identical infra-red scanning units

to provide pitch and roll reference signals. The Horizon Scanners are on con-

tinuously, from launch until re-entry at which time the Scanners are de-actlvated

by the O.05g relay but during the orbital phase the reference signals are applied

to the ASCS attitude gyros only upon command from the programmer. (Refer to

"--'_"_i A !Ill !- ! !_1 ! i ii ii

12

REPORT SEDR 104

MODEL. 133

l%4c,DONNE REVISED

ST. LOUIS, MISSOURI•-I"L _,T_ T*_ • REVISED

Table 13-i. ) The signals that are applied to the gyros are monitored by instru-

mentation. The pitch and roll signals range between + lO volts d-c. These

signals are applied to a biased attenuator card to provide a zero to 2.68 volt

output which is coupled to separate channels of the HF Commutator. The signals

represent an output range of + 35°.

Occasionally a scanner sweeps across the sun. Since the scanners are infra-

red devices, sweeping of the sun introduces error voltage. To prevent utiliza-

tion of this voltage, the scanner supplies an "ignore" signal to the ASCS. This

"ignore" signal is monitored as an on-off type of signal by instrumentation.

Pitch ignore and roll ignore signals are applied to the HF Commutator only. A

half scale signal represents presence of the pitch ignore signal and full scale

level indicates presence of the roll ignore signal.

13-25. Attitude

Attitude instrumentation consists of telemetry channels which monitor capsule

pitch, roll and yaw attitudes. Each attitude is read out of a syachro actuated

potentlometer. The synchros are driven by the automatic stabilization control

system. Excitation for the potentlometers is furnished by the three volt d-c

instrumentation power supply. Signal voltage varies along a multiple slope

function with capsule attitude. Pitch and roll signals cover a range of +130 °

to -190 °. Yaw signals cover a range of +70 to -250 ° . Each of the attitude

signals is applied to separate channels of HF and LF Commutators. After retro-

grade assembly Jettison and energizing of a O.05g relay, the potentiometer-

positioning synchros become inoperative. At this time, attitude signals are

removed from the commutators and attitude rate signals are applied to the re-

linquished commutator channels.

13-26. Attitude Rate

Attitude rate instrumentation utilized signals from rate gyros. The gyros

•LAG 231C (Eev 14 Oct. 55)

oA_ i November 1961

REVISED

REVISED


paG= 13-13

R=Pom'. SEDR 10_

are part of the attitude rate indicating system. A zero to three volt signal

level represents a rate level of decreasing 40 ° per second to increasing 40 °

per second. Attitude rate signals are applied to the LF Commutator. Roll,

pitch and yaw rates are assigned to separate channels. In addition, attitude

rates are applied to the channels normally occupied by attitude data when

attitude data is no longer generated. (Refer to Paragraph 13-25. )

13-27. Reaction Control System Solenoids

The reaction control system solenoids control the thrust Jets used for

capsule stabilization in flight. These solenoids can be energized manually or

automatically. When a solenoid is energized, 24 volts d-c is applied through

an attenuator in package "C" to the HI_ and LF Commutators. Each of the twelve

solenoids is represented by a separate commutator channel. This on-off signal

is presented to instrumentation circuitry from the amplifier-calibrator in the

ASCS system.

13-28. Supply Pressures - H202

The monitor circuits for reaction control supply pressures are identical

in operation. A helium source of 2050 psi is utilized to expel hydrogen per-

oxide frum a bladder. As hydrogen peroxide is expelled, the confined volume

of the helium increases and helium pressure decreases. A pressure po_entiometer

senses this change in pressure. The potentiometer is excited with three volts

from the instrmaentation power supply. Wiper output voltage is applied to both

commutators and through an attenuator to an indicator. Transducer range is

600 to 2200 psi. A pressure of 2050 psi provides a reading of 100% on the

indicator. Hydrogen peroxide is exhausted at approximately 600 psi. helium

pressure. Indicator reading at this pressure is approximately 0%.

13-29. Hand Control

Astronaut hand control position is monitored by three potenticmeters. The

C:::7:::;.T:--L

PAGE ' 13-1_

REPORT ,q_.T_ 1 Oh

MODEL. l_

,MCDONNE ST. LOUIS, MISSOURI

DATE I November i_61

REVISED

REVISED

wipers of these potentiometers are driven by linkage to the hand control. Three

volts from the instrumentation power supply is utilized to excite the potenti-

ometers. Zero to three volt signal level represents + 13° hand control movement

in the roll and pitch planes and + lO ° movement in the yaw plane. Wiper outputs

are applied to both commutators.

13-30. Capsule Acceleration

Capsule acceleration instrumentation consists of circuitry which monitors

acceleration along the mutually perpendicular axes. Three accelerometers in-

stalled in package "D" provide zero to three volt d-c outputs proportional to

acceleration along the longitudinal (Nz) lateral (Nx) and normal (Ny) axes of

the capsule. The accelerometer outputs are linear with a zero acceleration

providing a 1.5 volt d-c signal. The longitudinal axis accelerometer covers

a range of + 30g to provide zero to three volt output signals. The normal and

lateral axes accelerometers operate in two ranges. During launch and re-entry

a zero to three volt signal represents accelerations between -+ _g. During orbit,

a zero to three volt signal represents accelerations between + 0.Sg. These zero

to three volt signals are applied to the commutators.

13-31. Velocity Sensor

The velocity sensor is designed to measure separation velecity increase

during posigrade rocket firing and velocity decrease during retrograde rocket

firing. During posigrade firing the integrating accelerometer will, with appli-

cation of 24 volt d-c signal, integrate for 1.5 + _ seconds after a velocity of

lO ft/sec. + 1.5 ft/sec, has been reached. At this time the msximum velocity

signal will be held for approximately six (6) minutes. This signal is applied

to the HF and LF Commutators as a zero to three volt value and is used to

determine the separation velocity of the capsule from the preceding stage. Dur-

Lug retrograde firing, integration will be started by application of a 24 volt d-c

MAC 231C (Rev 14 Oct. _5)

,,o,REVlSEO. ST._" --_'--0"_7"'_'°aOUmS, MnSSOUm _ORT $_DR 104

signal and will integrate maximum velocity for 22 + 2 seconds after a velocity

of 2_0 + 40 ft/sec, has been reached. The signal will be held for 30 minutes

or until impact. The integrating accelerometer will also actuate the 240 ft/seco

relay which wlll direct 24 volts d-c power to the Telemetry velocity sensor relay

through a four and eight minute timer; the timer in turn directs the 24 volt

power through various slze resistors to produce a signal composed of three

different values Of four minutes duration each. These timed signals together

with the velocity signals are applied to the HF and LF Commutators to be used to

determine the approximate impact area of the capsule.

13-32. Structural Temperatures

Structural temperature instrumentation consists of monitor circuits for

ablation shield, outer skin and inner skin temperatures as well as inverters,

telemetry transmitters and retro-rockets.

13-33. Ablation Shield Temperatures

The ablation shield temperatures are monltored through the telemetry system.

Four transducers are embedded in the inner face of the shield. The transducers

have a temperature range from zero to 2000 degrees F. wlth a nominal resistance

of lO0 ohms at 70°F. Input power of 7 V d-c 400 cps applied to the transducers

Is attenuated to a value dependent upon the transducer resistance. The output

from the transducers is directed Into two identical smpllflers (two transducers

to each emplifler) in package "A" where the voltage Is converted and amplified

to a zero to 3 V d-c signal and applied to the telemetry commentators. The

amplifiers are "R" and "Z" calibrated at intervals from ground command.

13-34. Outer Skin Temperature

Outer skin temperature is sensed by two resistance element transducers

welded to the inside surface of the outer skln shingles In forward and aft loca-

tions. Transducer resistance varies proportionally wlth temperature. Each of

PAGE i_-16

REPORT n1_nn io_

MODEL_ i_


these transducers is part of a bridge input circuit to an amplifier in package

"C". The zero to three volt (full scale) outpu_ from the amplifier is representa-

tive of a temperature range of -65 to 2200°F. The out1_at from the amplifier

associated with the aft transducer is applied to the HF Commutator. The forward

transducer amplifier output is applied to the LF Commutator.

13-35. Inner Skin Temperature

Inner skin temperature is sensed by two resistance element transducers

adhering to the inner skin in forward end aft positions. Transducer resistance

varies proportionally with temperature. Each of these transducers is pert of

a bridge input circuit to an amplifier in package "A". The zero to three volt

(full scale) output from the amplifier is representative of a temperature range/

of 0 to 300°F. The output of the amplifier associated with the aft transducer

/

is applied to the LF Commutator. The forward transducer amplifier output is

applied to the HF Commutator.

13-36. Inverter Temperatures

The 150 VA and the main 250 VA inverter temperatures are monitored through

the telemetry system. A zero to 300 degrees F. transducer is attached externally

on each inverter. The transducer resistance change of 133 ohms to 2_0 ohms is

representative of a temperature change from zero to 300 degrees. Input power

of 7 volts 400 cycles applied to the transducers is attenuated to a value de-

pendent upon the transducer resistance, which in turn is controlled by the

temperature,of the inverter. The output from the transducer is directed into

an amplifier in package "A", where the voltage is converted and amplified to a

zero to 3 volt d-c signal and applied to the telemetry commutators. The ampllflez

is "R" and "Z" calibrated at intervals from ground command.

13-37. Telemetry Tran_nltter Temperatures

Both HF and LF telemetry transmitter temperatures are monitored through the

.

MAC 331C (P,_v 14 0_... 66)

DATE 1 NOVember 1_1 ____i_j_ _p,_4_ PAGE I_'17

R_|SE:D

telemetry system. The transducers are the some as used on the inverters (refer

to paragraph 13-36) and ere attached externally on each telemetry transmitter.

The processing of the temperature signal is the same as for the Inverters except

that the amplifier is located in "E" package.

13-38. Retro-Rocket Temperature

The retro-rocket temperature is monitored through the telemetry system.

The transducer is the same as used on the inverters (refer to paragraph 13-36)

and is cemented to the surface of the lower retro-rocket case. The processing

of the temperature signal is the some as for the invaders except that the

amplifier is located in "E" package.

13-39. Aercmedlcal

Aercmedlcal instrumentation consists of monitor circuits for electro-

cardiograph, respiration signals_ and body temperature.

13-_O. Astronaut Blood Pressure

The blood pressure system consists of (1) an occludin 6 cuff, (2) a pulse

sensor_ (3) differential transducer, (_) pressure source_ and (5) a control

system. The occluding cuff is attached externally to the Astronaut's pressure

suit and contains a transducer which measures the differential pressure between

the cuff and the capsule cabin pressure. The pulse sensor is a small transducer

attached to the Astronaut's skin. The pressure source is a separate oxy6en

bottle containing sufficient oxygen to provide 150 cycles of operation during

the mission. The system measures the Astronaut's blood pressure_ converts the

pressure to a corresponding electrical signal which is then applied to the 2.3

Kc voltage controlled oscillators and transmitted by the Hi and Lo telemetry

transmitters.

The blood pressure system may be put into operation either by an "R"

calibrate signal initiated from ground c_maand or by the Astronaut actuating a

REPORT _xEDR 104 REVISEDST. LOUIS, MISSOURI

MODEL_ 133 ........... REVISED.

"start" switch on the instrument panel. In either case, a 24 vdc pulse of five

seconds duration, causes the system to pressurize to 4.4 psi differential pressure

from the pressure source. After pressurizing the system bleeds off at a linear

rate to 0.75 psi in approximately 22 seconds. The output signal from the pulse

sensor is routed through the pressure suit disconnect and mixed with the differ-

ential pressure signal in a superimposing manner. This combined signal is routed

through a relay and relay contacts to the two 2.3 Kc VCO's located in "D" package,

and then to the Hi and Lo telemetry transmitters. Directing the signal through

the relay is necessary in order to share the 2.3 Kc VCO's with the EE_ signals.

The first appearance of the signal indicates systolic pressure with a

minimum peak amplitude of 150 mv while the last occurrence of the pulse signal

indicates diastolic pressure with a minimum peak amplitude of 150 my. The maximum

pulse pressure is 1 volt peak.

Upon completion of the cycle the system will remain at rest (below 3/4 psi

pressure) for lO seconds, after which time the cycle will repeat. If the system

is manually (Astronaut) initiated, operation will continue for 6+1 minutes or

approximately lO cycles unless manually interrupted by the "stop" switch on the

instrument panel. A light on the panel indicates when the system is operating.

13-_l. Astronaut EEG

Electrocardiograph signals are obtained _from four transducers attached to

the Astronaut's right and left side, and on the upper and lower chest. The out-

puts from the transducers are applied to two amplifiers in "D" package (left and

right side paired to one amplifier and upper and lower chest paired to the other).

Signals from the amplifiers are then directed to the 2.3 Kc and 1.7 Kc voltage

controlled oscilators, which in turn apply their outputs to the Hi and Lo

telemetry transmitters. The 2.3 Kc VCO's input signals are divided between the

Astronaut's EI_S and blood pressure outputs.

CCrJY.'DX;_Ti_,.

_c zslc (_v 14o__ ss)


REVISED

REVISlED_

srr.-oum s. Mmsoum ._om" __.._R ;L04

.,......................... .oo ,

13-42. Respiration Rate

The Astronaut's breathing rate and depth is monitored through the telemetry

system. A thermistor is mounted inside the Astronaut's helmet, adjacent to the

microphone. Input power of 3 vdc applied to the thermistor is attenuated pro-

portionally to the changing resistance of the thermistor, which in turn is

proportional to the magnitude of the Astronaut's respiration. The respiration

rate is determined by the frequency of the Astronaut's breathing. The changing

output voltage of the thez_istor varies the bias of a transistor; the transistor

output signal is then applied through a calibrate card in "E" package, to two

1.3 Kc voltage controlled oscillators in "D" package. The output of the VCO's

is then applied to the Hi and Lo frequency _mlemetry transmitters. The calibrate

card provides a means of interrupting the signal for "R" and "Z" calibrate. A

potentiemeter in the electronic assembly provides an adjustment for sensitivity.

13-43. Astronaut Body Temperature

Body temperature is sensed by a rectal temperature probe. The probe is

a 1490 + _ ohm thermistor element which is utilized as one leg of a bridge

circuit, which forms the inputs to two d-c amplifiers. The output of each

amplifier is applied to the telemetry commutators. The zero to 3 vdc output

represents a temperature range of 95° to 108 ° C. Both amplifiers are "R" and

"Z" calibrated by ground command.

13-44. Sequence System Normal Launch

Normal launch sequence instrumentation consists of monitor circuits for

tower release, capsule separation, retrograde attitude command, and retrograde

rocket assembly Jettison. These signals are -all on-off type functions and each

is applied to the HF and LF Commutators.

13-45. Satellite Clock

The satellite clock utilizes potentio-_ters to provide electrical signals

representative of elapsed time from launch and retrograde time. These potenti-

REPORT _DR 104 ST. LOUIS, MISSOURI REVISED

MODEL. 933 ..... __ " REVISED

ometers are excited with three volts from the instrumentation power supply. The

outputs for each type of time are divided in signals representative of O to 10

seconds, 0 to 1 minute, O to lO minutes, 0 to 1 hour, 0 to lO hours and 0 to 30

hours. Wiper output is linearly proportional from zero to three volts for each

time span. Wiper outputs are applied to the HF and LF Commutators. Instrumenta-

tion monitors ELAPSED TIME from LAUNCH and also EVENT TIME of retrograde. Elapsed

time from launch is the length of time capsule has been in motion. Prior to lift-

off, elapsed time will be zero. Instrumentation recording devices also will

indicate zero time. Output signals for elapsed time therefore are directly pro-

portional to time. As time increases so will output voltage, for example,

elapsed time recorded by clock is lO hours, 5 minutes and 10 seconds. Output

signals will then be as shown below:

SATELLITE CLOCK OUITUTS FOR i0 HOURS,

5 MINUTES, iO SECONDS, AFTER LAUNCH

TIME POTERTIOMETERS SIGNAL

POTENTIOMETERS WIPER TRAVEL IN _ VOLTAGE

0 - i0 Hours 100% 3 Volts

0 - 1 Hour 100% 3 Volts

O - i0 Minutes 50% 1.5 Volts

0 - 1 Minute i00_ 3 Volts

0 - i0 Seconds 100% 3 Volts

Event time of retrograde is pre-set prior to lift-off. After retrograde

time has been set, instrumentation will receive this time signal continuously

throughout the mission. Event time of retrograde can be changed at any time

during the mission by either the Astronaut or by ground command. When retro-

grade time is changed during the mission, Instrtmentation will receive this

change also. Signal output voltage is proportional to retrograde time. For

example, if retrograde is set to commence at 20 hours, 5 minutes and 5 seconds,

MAO _31C (l_v 14 Oct.. 5_)

DA'r_

remora" s_R lO4

MOO,-- 133

ST'. LOUIS 3. MlSSOUR|

instrumentation will be receiving the signal voltage outputs as shown below:

SATELLITE CLOCK OUTRYI_ FOR RETR0-FIRE AT 20 HOURS,5 _3V_ES A_D 5 SECONDS

TI_ POTENTIOMETERS SIGNAL

POTERTIOMETERS WIPER TRAVEL IN _ VOLTJ_E

O - iO Hours 100% 3 Volts

0 - 1 Hour 1OO% 3 Volts

0 - i0 Minutes 50% 1.5 Volts

0 - 1 Minute l_ 3 Volts

O - i0 Seconds 50% 1.5 Volts

13-46. Tower Separation

When the tower separates from the capsule, the No. 3 tower separate sensor

relay de-energlzes and applies three volts d-c to the commutators. This signal

is present for the remainder of the mission.

13-47. Capsule Separation

When the capsule separates from the booster, a limit switch closes and

causes the No. 1 capsule separation sensor relay to energize. While this relay

is energized a three volt d-c signal is applied to both commutators. This relay

remains energized for the remainder of the mission.

13-48. Retrograde Attitude

The retrograde attitude co_nand signal normally occurs when the retrograde

clock runs out. It may also be caused by ground command or by operation of a

bypass switch on the instrument panel. This signal remains present until the

retrograde rocket assembly is Jettisoned (approximately 90 seconds). Signal

level is approximately three volts. Normally open contacts of the retrograde

attitude ccmnnand relay in retrograde relay box No. 2 closes to route the signal

to the HF and LF Commutator.

_-22

REPORT S_DR lO_

MODEL_, 133


-- _'_._.T_*L-_ _':"_'_'_,._..._, REVISED, ,

13-49. Retrograde Rocket Assembly Jettison

The retrograde rocket fire occurs at five second intervals. The first fire

occurs thirty seconds after reception of retrograde clock rumout if the retro-

grade interlock is closed in the ASCS.

The retrograde rocket assembly Jettison signal occurs 60 seconds after the

initiation of the retrograde fire signal. The signal is routed through normally

open contacts of the retrograde rocket assembly separation sensor relay in retro-

grade relay box No. 1. This relay is energized by limit switches which close

when the retrograde assembly is blasted away from the capsule. The relay remains

energized until the O.05g relay drops out. (The O.05g relay de-energizes at

lO,O00 feet. ) A d-c signal of approximately 3 volts is applied through normally

open contacts of this relay to the HF and LF Commutators.

13-50. Emergenc Y Escape Sequence

Emergency escape sequence instrumentation consists of Mayday abort and tower

escape rocket fire signal monitors.

13-51. Mayday

The Mayday signal is produced by the Mayday alarm relay. This relay is

energized by any abort signal. With the relay energized, three volts d-c

(nominal) is applied to the KF and LF Commutators. Once initiated, this signal

is present for the remainder of the mission. The Mayday alarm relay is in launch

and orbit relay box No. 4.

13-52. Astronaut 's Abort Switch

Instrumentation is provided to monitor an abort signal originating from the

Astronaut's Abort Handle; this signal is applied to both commutators.

13-53. Tower Escape Rocket

The tower escape rocket signal is obtained from the emergency escape rocket

fire relay in launch sad orbit relay box No. 2. This relay remains energized

_.,_v _,,.m _..a..J4/_4.'_l JI. Jl.,Z'lkJL,I

\\

_XAC 2310 (P_v 14 Oct 55)


REVISED

REVISED

ST. LOUIS 3, MISSOURI REPORT _R_R 104

,._ Moore. 133 ,,

for less than one second but a capacitor is connected across the input to the

HF and LF Commutators to maintain a signal level of more than O. 3 volt for

approximately 30 seconds.

13-54. Landing System Sequence

Landing system instrumentation consists of monitor circuits for chute

deploy and Jettison and release of the antenna fairing. These signals are

approximately three volts and are applied to the HF and LF Commutators. Main

and reserve chute deploy signals are obtained from toggle switches in the chute

compartment. Lanyards from the chutes operate these switches when the chutes

deploy. The main chute Jettison signal is obtained through a limit switch in

the chute compartment. The antenna fairing release signal comes from the

antenna fairing separation relay in the communications relay box. This relay

is energized through a limit switch. All landing system signals remain on until

impact.

13-55. O.05G Relay

Instrumentation of 0.056 relay operation consists of an on-off type signal

which indicates whether the relay is energized or de-energlzed. The relay may

be energized by operation of the 0.05g sensor or by the command receiver.

When the relay is energized a d-c signal is applied to the HF and LF Commutators.

13-56. Drogue Chute

Drogue chute deployment is monitored by a three volt signal controlled by

the drogue chute sensorj through a set of contacts on the antenna separation

relay and is applied to both commutators.

13-57. Landing Bag

The landing bag operation is monitored by a voltage signal applied to the

HF and LF Commutators through two sets of unlock signal limit switches.

13-58. Periscope Retract and Door Closure

The periscope retract si_monltors the voltage applied to the retract

J_,;.;'; D_.;.T:AL

24

REPORT SEDR 104

MODEL

McIDONNE_ __ DATE 1 November 1961REVISED

ST. LOUIS, MISSOURI

_ REVISED

relay. While the periscope is retracting, 24 volts d-c is applied through an

attenuator in package "C" to both commutators. Input level to the commutators

is approximately three volts.

INSTRUMENTATION CONTROL SYSTEM

13-60. C_ing

The signals applied to the HF and LF Commutators are sampled once every 0.80

seconds. Commutator outputs are square wave pulses with amplitude between -i and

+3 volts. These pulses are applied to voltage controlled oscillators and pulse

duration modulation converters.

a. The frequencies of the voltage controlled oscillators are varied

between 10.5 Kc + 6-3/4_ by the commutated pulse an_litude signals. This fre-

quency band corresponds to IRIG Channel 12. The frequency modulated outputs of

the 10.5 Kc voltage controlled oscillators are applied to two mixers.

b. Commutator pulse amplitude modulation signals are also applied to pulse

duration modulation converters. The converters reshape the pulse amplitude

wave-shapes to obtain pulse duration wave trains. These wave trains are then

applied to the tape recorder.

c. Amplified aeromedlcal signals are coupled to pairs of 1.3 Kc, 1.7 Kc

and 2.3 Kc voltage controlled oscillators. A zero to full scale signal causes a

deviation in center frequency of + 6-3/4%. The frequency bands of the oscillator=

correspond to IRIG Channels 5, 6 and 7- The oscillator outputs are applied to

mixers.

d.

combined.

In the mixers, the commutated outputs and the aercmedlcal signals are

Mixer A also accepts a signal from the compensating oscillator. (This

signal serves as a reference during data evaluation to indicate fluctuations in

tape speed. ) The composite signal from each mixer is applied to the tape

MAC _IC {l_v 14 Oct. _)

DATE:]- November 1961 _ _ PAGer 1_-'_

R_VlSE_ ST.LOUlS S,MISSOUm RIPO_r SEDR 10_

Moo.. i33

k

i

recorder, the ground test umbilical and a telemetry transmitter.

13-61. Transmission

Ground testing and control of the instrumentation system is provided through

the umbilical receptacle. Non-radiating checks can be performed to evaluate

system operation. Radiating checks are performed through the telemetry llnk.

Refer to Section XI for further information regarding telemetry.

13-62. Instrumentation Control

The instrumentation system controls and programs (see Table 13-1) power

to its own and other systems equipment by means of mode relays and programmer.

(See Figure 13-3. )

a. The ASCS horizon scanners are powered at regular intervals during the

mission to provide reference signals for the capsule gyros.

b. The water extractor in the environmental control system is also

programmed at regular intervals during the mission.

c. The pilot and instrument panel observer camera operates at a high and

low rate of speed during various phases of the mission.

d. Calibration voltages, R-calibrate for maximum readings and Z-callbrate

for minimum readings, are supplied periodically to the monitoring instrumentation

circuits. This is done prior to launch and by ground commaud at intervals dur-

ing orbit.

e. The X and Y axes accelerometer ranges are + 4 g from launch until orbit

and from retro command until landing. These ranges are changed to +_0.Sg while

the capsule is in orbit. The Z axis acceler_neter range is + 30g throughout

the mission.

13-63. INS_U_EATION RECORDING (see Figure 13-3).

Recording instrumentation consists of a tape recorder and two cameras.

:= ;:.-: :'__L:TIAL

CAMERA

ASTRONAUT-PRIMATE

9-13-16-18-19

INSTRUMENT PANEL

OBSERVER CAMERA

9, 13, 16,18,19

PERISCOPE

CAMERA 8, 9

EARTH AND SKY

OBSERVER CA_/_A

CAPSULE 8, 9

HORIZON SCANNER

ECS WATER

EXTRACTOR 8,9,13,16,18,19

PLAYBACK TAPE

RECORDER 8-9

INST. PANELOBSERVER CAMERA

TABLE 13-1. INSTRUMENTATION PROGRAMMING

Before Umb Umb.EJ.to Cap. Sep. Tr.to Retro Retro Jett.

Separation Cap Sep + Plus 60 Jettison to .OSG60 Sec. Sec.to Tr..

i frame/ 6 frames/ I frame/12 6 frames i frame

12 Sec. Sec. Sec.,Except per Sec. per 12

6 frames/ i Sec.Sec. every J30 Min.

.........................Slow Fast Slow,Except Fast SlowIF/2 Sec. 6 FPS fast 30 Sec.

every 30 Min

1800 frames*

per hour

i0 frames iI0 frames

per Min. _per Min.

!

operating O_erati_ i8.5 ran/30 Min.

1

On until tape depletion at

35.Sec./180 Sec. with 90 Min. stagger.

6 F?S 6 n_ 18oo _PH 6 FPS 6 FPS

•05G to Ht. Shld.Ht. Shld. onward

Deploy

per Sec. per 12Sec.

I

Mayl)ayonward

O

frame s

per Sec

Fast

i0 frames i0 frames

per Min. per Min.

OFF at

Re-entry

iO frame_ i0 frames

per Min. per Min.

............ f .................

30 Sec/

30 Min.

6 FPS 6FPS

F

m_m

!

g

m m

0 o

>m

t-i

:L" i


November _MC,DONNE ,.. 1 -2"rR_vlsEo s'r.-oms s. MiSSOUm _m-o_-r ._.nR :1o_

._IsED Moo_ 133

13-64. Ta_e Recorder

A low power, lightweight tape recorder provides seven channels for data

recording. Mixer A output, voice _m,_cations, LF Commutator, pulse duration

modulation and HF Commutator pulse duration modulation signals are applied to

channels i, 2, 3, 4, 5 and 7, respectively. The tape recorder operates continu-

ously during ascent and descent, and is on 1 mlmute and off 3 minutes during

orbit. In addition, the recorder is turned on during any voice transmission

from the capsule. Recorder speed is 1-7/8 inches per second.

13-65. Instrumen_ Panel Camera

A 16 millimeter camera is installed in the capsule to observe the main

instrument panel. This camera is mounted to the left of the Astronaut's head

and views the panel from over his shoulder. The camera is supplied 2_ volts

d-c from the capsule power system. Operation of the camera is controlled by

also applying 2_ volt d-c power pulses to the camera clutch. Each pulse trips

the shutter, exposing one frame, and advances the film for the next exposure.

The camera operates at a high speed of 6 frames per second and a low speed of

One frame every two seconds. The Instrument Panel Observer Camera contains

450 feet of 16 millimeter film. Power is applied through an Imstrumentatloa

Mode relay and programmer and internal camera programmers which produce the

necessary power pulses; these are supplied during ascent, descent and orbit at

speeds shown on Table 13-1.

13-66. Astronaut Camera

A 16 millimeter camera mounted behind the lower left corner of the main

instrument panel views the Astronaut. This camera is also supplied 24 volt

d-c power and trigger pulse voltage. The Astronaut camera operates at a high

speed of 6 frames per second and a low speed of 1 frame every 12 seconds. The

camera normally contains 250 feet of 16 millimeter film. Internal clock, time

28

REPORT SEDR 104

MODEL 133

ST.LOUIS, MISSOURI

_Vliln allm,_l---n I • B_e--lknm_

DATE

REVISED

REVISED

1 NOVEMBER 1961

_f,T_O _F.P. t:3.ELAY h

2P_,E- t_PACT8U3

I_A LANb_kI_ BAG

UNLOCK LthA_TSWITC_I

,L

F'I_URE 15-5 CAMERAS AND TAPE _ECORDE_ CONTROL CIP_UIS_CAP._ULE_:/_O,L_,I_/8,J_)

• +

vvnSi iikOkmlq I I/'_ l-

.,,_VL_ =,,.*..,,m.,*+_aa+mU__

51". LOUIS 3, MISSOURI

correlation is included within the camera. Operation is similar to that of the

instrument panel observer camera. Camera speeds are supplied at varying rates

as shown on Table 13-1. The cameras and tape recorder can be controlled through

the umbilical during 6round checkout. Return circuits from these components to

the umbilical provide indications of component operation.

13-67. SPECIAL INSTRUMENTATION

Not applicable to a manned capsule.

13-68. SYSTEMtmZTS

13-69. TRANSDUCERS

Potenti_neter type transducers are connected across instrumentation 3

Volt d-c power. The wiper is activated by the action to be measured. Wiper

voltage is then proportional to the action.

13-70. Control Stick Motion Potentlometers

Control stick motion is translated into rotary potenticmeter movement. One

potenticmeter is provided for each axis of motion.

13-71. Satellite Clock Potenticmeters

The satellite clock (refer to Section XII) utilized potenticmeters to

indicate elapsed time from launch and time to retrograde outputs for O-10

seconds, O-1 minute, O-lO minutes, 0-I hour, and O-lO hours.

13-72. Manual and Automatic Su_l_ Helium Pressure Potentlometers

Helium supply pressure, 2250 psig maximum, actuates the wiper of each

potentlometer transducer to a resistance position proportional to the pressure.

13-73. Attitude Potentlcmeters

The ASCS calibrator (refer to Section 17) provides synchro actuation of

potentlometers for pitch, roll and yaw. Each wiper output is then proportional

to the capsule attitude for that axis.

.... --e .... --...

qO

REPORT SRJ)R lO4

MOOa_Z33

MCDONNE REVISED

._Sty, LOUIS, MISSOURI

,_,.,,., .,..,..¢., -',-,I .= *.c_..=._ REVISED

13-74. Main and Reserve Oxygen Pressure Potentiometers

Each oxygen bottle pressure actuates a dual potentiometer transducer. A

low resistance linear element is used to operate a panel indicator while a higher

resistance linear element is used for instrumentation. Wiper voltage outputs

are proportional to applied oxygen pressure.

13-75. Static Pressure; Suit Pressure and Coolant Quantity PressurePotentiometers

Each pressure transducer is used to provide a linear output proportional to

the applied pressure. Pressure ranges are 0-15 psia for static pressure, 0-15

psia for suit pressure and 0-500 psia for coolant quantity pressure.

13-76. Respiration Rate and Depth Thermistor

Pilot breathing actuates a thermistor mounted in the helmet microphone area.

Respiration depth is determined by the extremes to which the thermistor is

actuated while breathing rate determines the frequency of actuation.

13-77. Resistance Element Transducers

Resistance elements are used to measure temperatures. The resistance of

the element varies proportionally to its temperature. Mounting of the element

depends on the application. Stick-on surface temperature elements are small,

lightweight units. Other elements are mounted as an integral part of the capsule

structure. The following llst indicates the purpose and approximate temperature

and resistance ranges for each transducer.

(a) Outer Skin Temperature: -65 ° to 2200°F

(b) Ablation Temperature: -55 ° to lO00°F

(c) Suit Inlet Temperature: 35 ° to lOO°F - 249 to 300 ohms

(d) Cabin Air Temperature: 0° to 200°F - 216 to 316 ohms.

1B-78. Body Temperature Transducer

The body temperature transducer is a rectal temperature pickup which con-

COy F,D -

MAC 231C (B.ev 14 Oct,. 55)


REVISED

REVISED.


PAGE 13-31

REPORT SEDR 104

.oow. 133

sists of a thermistor imbedded in sealing compound at the end of a flexible

pigtail.

13-79. D-C Current Shunt

The shunt resistance used for the instrument panel ammeter also supplies

voltage for instrumentation. This shunt is discussed in Section XI of this

manual.

13-80. Electrocardio_raph Pickups

Cardiac activity is sensed by four 3 one half inch square, stainless steel

wire screens. These electrodes are attached with silver metalized adhesive

to the Astronaut's body. Small connecting wires leading to the Astronaut's

suit disconnect, complete the circuit.

13-81. Oxygen Partial Pressure Transducer

The 02 Partial Pressure transducers are used to convert 02 partial pressures

to a signal compatible with high level telemetry. The voltage range of 0-3 V

d-c output is representative of 0-6 psi oxygen partial pressure.

13-82. TAPE RECORDER

A low power, lightweight tape recorder is used in the capsule to make avail-

able 7 channels of recorded data. At the present time channel assignments are

as follows: Channel i, HF VCO mixer output; Channel 3, voice c_ications;

Channel 5, LF Commutator PDM; Channel 7, HF Commutator PDM. Tape speed is

1-7/8 ips, convertible to 15 ips by a modification kit. Tape capacity is 4800

feet of ½ inch wide mylar base tape. The tape transport consists of a capstan

drive 3 supply reel and take-up reel mechanism. A d-c motor is used, through

reduction gearing, for capstan drive. A limit switch is provided to interrupt

recorder power should the tape break. Record amplifiers are incorporated in

the unit for Channels i and 3. Channels 5 and 7 utilize amplifiers incorporated

in the comratators located in instrumentation package "A".

Mc,DONNE REPORT ,-°_DR 104. REVISED

•_, STj LOUIS, MISSOURIMODEL- 133 _,tj,_._.t" xa.,, -',_', • ,.,-s.J_" REVISED

"1 Nnv_mher' ] <:k_]

13-83. INSTRUMENTATION PACKAGE "C"

The "C" package incorporates units of various functions into one compact

panel allowing convenience of mounting and of making electrical connections.

These various sub-units are discussed in the following paragraphs.

13-84. Cabin Pressure Transducer

Cabin pressure actuates the wiper of a lO,O00 ohm potentiometer located in

the "C" package. Three volt's d-c from the "A" package is applied across the

potentiometer. Wiper output voltage is then proportional to the cabin pressure.

13-85. Topic Cards

The instrumentation package utilizes a unique method of construction and

mounting of the transistorized amplifiers, power suppliers, attenuators and

monitors. Each unit consists of the necessary component parts mounted on a

printed circuit, dielectric card with printed connector contacts at the bottom

for plug-in insertion. The card is ghen covered 3 with the exception of base

connector contacts and side mounting edges, with a thin layer of epoxy resin.

This coating is used to provide moisture protection, to insure operation in a

100% oxygen atmosphere and to improve mechanical rigidity of components. These

"Topic Cards" are package mounted in boxes providing side rails, base contact

receptacles and printed circuit inter-connections.

13-86. D-C Current Amplifier Cards

Two amplifiers are used to bring the d-c current shunt voltage up to a

maximum of 3 volts d-c. One amplifier is used for the HF Commutator while the

other is used for the LF Commutator. The amplifiers are transistorized and

card mounted.

13-87. Respiration Rate and De_th Calibration and Attenuator Card

Relays mounted on this card allow "R" and "Z" calibration of the signal

supplied frcm the respiration rate and depth transducer. One relay is supplied

CONFILL':NT2 ..

MAC 2310 (Bey 14 O_ 55)

DAVE i November 1961

REVISED

REVISED

!DONNE , ! -BS ,ST. LOUIS 3, MISSOURI RII[PORT SEDR 104

MOm_ 133

for "R" calibration and one for "Z" calibration. Energizing the desired relay

breams the normal circuit and applies the calibration voltage to the commutators.

Resistors are also mounted on the card for attenuation of 24 volt d-c voltages

to proportloaal voltages compatible with the commutators.

13-88. Voltage Monitor Cards

Resistors, capacitors and circuit isolating crystal diodes are used to

attenuate reaction control solenoid valve energizing voltages, standby battery

voltage and periscope retract voltage prior to application to the cca_u_ators.

Each attenuator circuit output, a maximum of 3 volts d-c, is applied to both

commutators.

13-89. Horizon Scanner Card

The horizon scanner amplifier card provides circuitry for processing the

scanner roll and pitch signals, roll and pitch ignore signals and "Z" calibrate

prior to being applied to HF and LF Commutators. During launch and orbit the

scanners are operating continuously; however, during orbit the signals applied

to the ASCS and the c_mmutators are timed by the programmer located in "C"

package. In addition, the horizon scanner slaving signal is applied to the KF

commutator.

13-9o. PR_

The programmer contains switch contacts which operate control circuits for

specific intervals. The progra, ner is mounted on the forward side of the peri-

scope housing.

13-91. A - Section

The programmer used for orbital missions consists of two sections. When

power is applied to the progremmer, electronic controlled timers continuously

operate the following contacts:

.......... | • i_VI'qlF | JS,,_&&,dlRI It ,il4"_lS,M

'_4

REPORT SEDR 10_

MODEL 133


IL_v J, 1 I. JLJLP


REVISED

REVISED,

CONTACTS CLOSED

WAFER SECTION DURATION

i. Water Extraction 30 Seconds

2. Full Scale Calibrate 5 Seconds

3. Zero Calib. 5 Seconds

RATEu

1 per 30 minutes

See Table 13-2

See Table 13-2

13-92. B - Section

The B Section of the programmer is energized through the command receiver-

decoders and the electronic timers to provide full scale and zero calibrate

signal, as follows :

WAFER SECTION

Full Scale Calibrate

Zero Calibrate

CONTACTS CLOSED

DURATION RATE

3 Seconds On Command

3 Seconds On Command

le

2.

13-93. INSTRUMENTATION PACKAGE "A"

The "A" package also incorporates units of various functions into one panel.

These sub-units are discussed in the following paragraphs.

13-9_. Cabin Air Temperature Transducers

A platinum resistance wire is used to measure cabin air temperature. Tempera-

ture changes frcm 0° to 200°F cause the element to change resistance from 200 to

300 ohms. The resistance element forms a part of an amplifier circuit. Two

transducers are used in conjunction with two amplifiers to supply signal to both

commutators.

13-95. Filament Transformer

A filament transformer is used to step down ll5 volts 400 cps capsule power

to 6.3 volts for use In packages "A" and "C".

/'_ jr% I_T 1_ lr lr-i 117 _v n_Llr.-Jl-,I.d_ ....


DATe i November 1961 PAng I_-_ ,

REVISED. $1".LOUlS 3, .ISSOUR' R[PORT SEDR 10A

R_VlSED - * _OOU. 13_

13-96. Topic Cards

The instrumentation package "A" also utilizes the Topic Card principle for

amplifiers and power supplies.

13-97. Resistance Element Amplifier Cards

The same type amplifier is used for heat shield outer skin, suit inlet air

and cabin air temperature transducer signals. Each amplifier is of dual channel

design in order to accommodate the two transducers used to measure each type of

temperature. Seven volts, 400 cps is supplied from the resistance element power

supply. This voltage is applied across a bridge circuit in each amplifier. The

transducer associated with each bridge circuit causes the voltage in the circuit

to vary proportionally to the transducer temperature. This voltage change

appears across a transformer and is rectified, using crystal diodes, to a

maximum output of 3 volts d-c. The two outputs from each amplifier are supplied

to the commutators. Two relays on each card amplifier allow full scale and zero

calibration of each channel. Calibration potentiometers are also provided for

each channel.

13-98. Resistance Element A-C Power Supply Card

Resistance element amplifier circuits require 7 volts, 400 cps a-c. Capsule

power, 24 volts d-c, is applied to a transistorized power inverter. The In-

verter, using zener dlode-translstor voltage regulation and transistor switching,

supplies a 7 volt a-c output which is monitored by an attenuator, rectifier

circuit. The monitor output, a maximum 3 volts d-c, is applied to the

commutators.

1S-9R. Body Temperature Amplifier Cards

Two transistorized d-c amplifiers are used to increase the output of the

temperature transducer to a maximum 3 volt d-c level prior to application to

the commutators. These amplifiers are of the same type as those used in instru-

REPORT aEDR lOLl• REVISEDST. LOUIS, MISSOURI

MODEL 1_ -- C'_v_?;_==_E?_-'_I_:._i P REVISED,,

mentation package "C" for d-c current amplification.

13-100. Signal Condition and D-C Su_l_ Card

This Topic Card provides four functions in the instrumentation system.

Filament transformer output is applied to a monitor circuit. This circuit

attenuates and rectifies to provide a maximum 3 volt d-c signal indicating trans-

former operation. Capsule power, 24 volts d-c, is applied to an attenuator

circuit which provides a 3 volt d-c output for the monitoring circuit. This

3 volt output Is them applied to the commutators as a monitor of the main 24

volt d-c bus voltage. The signal condition and d-c power supply card also pro-

vides meter attenuator resistors which limit current flow in the panel indicator

circuits. These circuits involve the maln and reserve oxygen supply pressures,

the automatic and manual fuel supply pressures and the coolant quantity circuit.

13-101. HF and LF Cc_mutator-Ke_er-Record Amplifiers

Two units are provided in the "A" package for commutatlng transducer data

and supplying PDM and PAM outputs. The commutator portion of each unit is a

90 x l_, solid state device which samples sequentially, 88 channels of signal

input information. The output produced is a pulse amplitude modulated signal

wave train. Each 0 to 3 volts d-c input to the commutator is sampled l_ times

per second per IRIG standards. The PAM wave train output is fed through a

buffer stage to a PAM/PDM converter. The PDM output is then applied to a record

amplifier which produces a signal capable of directly driving the recorder head

in the capsule tape recorder. The PAM output is fed through a gating circuit

which introduces a master pulse and negative pedestal pulses to operate automatic

decom_utation equipment in the ground station. A power supply is incorporated

in the unit to provide the positive and negative voltages required in the circuits

CC, L :IDZ,. -

MAC 231C (Eev 14 Oc_ 55)

1 ovember Mc,DONNELL 13.37REVISED slr'. LOUlS 3, MISSOUm RE_OR7. SEDR 104

R_,SE_ .... _OOL 133

13-102. INSTRUMENTATION PACKAGE "D"

The primary function of the "D" package is to convert capsule informatlon

to signals capable of modulating the telemetry transmitters. Transducers and

amplifiers are also contained in the package to complete capsule information

circuits.

13-103. Accelerometers

Three accelerc_eters are mounted in the "D" packs_e and used to determine

"the static lon61tudinal, lateral and normal accelerations of the capsule. Each

unit gives a d-c output which is applied to 3 channels of each commutator.

13-104. Electrocardlo_ram Am_llfler Cards

Four amplifiers are used for the E_D transducer inputs. Each amplifier

increases the transducer output to a 3 volt peak to peak signal.

13-105. Oscillators

The "D" package supplies sub-carrler oscillators to allow two channels of

instrumentation data. The A channel is associated with the HF commutator, high

frequency telemetry transmitter and tape recorder. The B channel is associated

with the low frequency telemetry transmitter. The following paragraphs describe

the sub-carrler oscillators.

13-106. Cc_nsatlm_ Oscillator Card

During playback of a tape, the recorded signal from this oscillator is

monitored to detect changes in tape recorder speed. A frequency shift indicates

a change in speed. The oscillator is of Topic Card construction and operates

at 3125 cps. Output level is adjustable.

13-107. Voltage Controlled Oscillator (V. C. O. 1 Cards

Instrumentation data voltages are applied to the sub-carrler oscillators

causing oscillator frequency shift proportional to the input amplitude. The

transistorized oscillator consists of a free running multlvibrator and filter.

The oscillator functions and frequencies are given below:

i H

38

REPORT _DR 104

MODEL l_


........... REVISED

(i) C_mel A

Commutator - 10.5 kc

Right side (+) Ekg V.C.O. 2.3

Left side (Comm) Ekg V.C.O. 2.3 Kc

Lower Chest (+) Ekg. V.C.O. 1.7 Kc

Upper Chest (Co=m) Ekg. V.C.O. 1.7 Kc

Respiration rate and depth - V.C.O. 1.3 Kc

Compensating oscillator - 3.125 Kc

(2) c_el

Commutator - 10.5 Kc

Right Side (+) l_.kg V.C.O. 2.3 Kc

Left Side (Comm) Ekg V.C.O. 2.3 Ec

Lower Chest (+) Ekg V.C.O. 1.7 Kc

Upper Chest (Coma) Ekg V.C.O. 1.7 Kc

Respiration rate and depth - V.C.O. 1.3 Ec

13-108. Mixer Amplifier Card Power Supply

Capsule power, 24 volts d-c, is converted to 6 volt d-c for use by the sub-

carrier oscillators. A mixer circuit combines the sub-carrier oscillator outputs.

Solid state components for these circuits are combined on one Topic Card.

13 -109. CAMERAS

13-110. Instrument Panel Observer Camera

A standard camera is modified by the application of a special drive motor,

self contained slow and fast programmer and a special housing. Slow operating

of the motor shutter mechanism and film transport begins when the capsule camera

and tape record relay is de-energized by the block-house. Full capacity is 450

feet of 16 millimeter film.

• _ I¸

DATE I NOVEMBER 1961

REVISED

•REVISED

Mc'DONNE_ __ST.LOUIS. MISSOURI

:D _.;-, ,'7-I-A-L

PAGE "13-39

REPORT .SEDR 104

MODEL 133

" :;_

<7

_, _Q_:::.::;i_::i::::i_:_TE_/A`RSEM_LY:• _:•:::::::.:_.LEN_cmP_::_i::::M_::_7-iNE_SSEMaLY::::_iii::ii::iiiii::i::i::_:YEU.0W i : i ::i:ii_iiiiiiill_i C0V_.I:

!i ii !!iiiiiiiili!i?i i!i!,iiii!iiiiii!iiii!i i_:!!I ?iil!i i!i

FIGURE13-# EARTH AND:SKY :OBSERVER CAMERA PM45-1g&

._lil_lh. llllllllllklllLllllll | •

VVI_il lll_m,---ll I l,l"_ I,-,-

140

REPORT SRDR 1o4

MODEL 10;4

__Z DATE 1 November 1961

ST. LOUIS, MISSOURI

Table 13-2.. Instrumentation Commutator Point Assignment

(High Level 0-3 Volt. )

ELECTRICAL POWER SYSTEM

18V Isol Bus

18V Stby Bus

Fans A-C Bus

ASCS A-C Bus

D-C Current

Standby Inverter ON

Standby Batteries ON

ASCS Slovlng

24 Volts D-C

INSTRUMENTATION POWER

SUPPLIES

3V D-C Reference

0%' (Zero) Reference

7V, _0CPS

STATIC __

v_zol (co_ Ao_z)

EBVIRORME_TAL CONTROL

S_t I_%et Pre=sure

l_resm_z_

BY LF

12 12

12 12

9HF LF

_l' 41

42 42

62 62

63 63

83 83

41 41

42 42

62 62

63 63

83 83

1 1

2 2

3 3

22 22

5 2749 71-64 6_

8 8

9 9

1 1

2 2

3 3

22 22

6_ 6_

8 8

l0]IF LF

41 41

42 42

62 62

63 63

63 63

83 83

1 1

2 2

3 3

22 22

6_ 6_

8 8

9 9 9 9

t

33 33

77 77

42 42

62 62

63 63

63

26 26

1 1

2 2

3 3

22 22

6464

8 8

9 9

16BY LF

41 41

63 63

83 83

1

2

3

1

2

3

9 9

8 8

6_ 6_

22 22

MAC SIC (P_v I_ Oc_ 56)

OATE, ! November 1961

REVISED

REVISED


_IT: D__._ITIAL.,.

._s=, 13-41

._o_ SEDR 104

MOO= 133

Table 13-2. Instrumentation Commutator Point Assignment

(HighLevel 0-3 Volt.) (Cont'd.)

8HF LF

ENVIRONMEA_AL CONTROL

SYSTEM (Cont 'd.)

Cabin Temp. i0 I0

Suit Inlet Air Temp.

Reserve 02 SupplyPressure

Cabin Pressure 82 82

Coolant Quantity 84 84

sult 02 PartlalP_sm=_ 6 6

RERCTICm COWI_OL SYSTEM

Reaction Cont.

Pre,msre (Auto.) 39 39

Reac_i_ Cont. Supply

Control P_sltl_s

Pitch

Taw

X Axis

X Azle

is _s43 13

73 73

14 4_7_

9HF LF

i0 i0

11 11

12 12

82 82

84 84

6 6

39 39

4o

13 _s43 13

73 73

7_

i0EF LF

i0 i0

11 ii

12 12

82. 82

84 84

6 6

39 39

_o

23 23

24 24

25 25

13 43&3 1373 73

10 10

11 11

12 12

82 82

8_

39 39

_o

13 43

_3 13

73 73

16HF LF

i0 i0

11 ii

12 12

82 82

8_ 84

6 6

39 39

_o _o

23 23

7_ 74

15 1545 45

_-42

REPORT SEDR 104

MODEL i_

"" %6_'_ DATE 1n_ D ONNE__._ REVISED

ST. LOUIS, MISSOURI

November 1961


(ugh Level 0-3 Volt.) (Cont'a.)

ACCELERATION

z Axis(cont,_.)

STRUCTURAL _ERATURE

Heat Sink

Ablation Shield Temp.

Outer Skin Temp.

Inner Skin Temp.

25OVA Inverter Temp.

15OVA Inverter Temp.

AEROMEDICAL DATA

EKD

Respiration

Body Temperature

O.OSG RELAY

HORIZON SCANNER

Pitch, Output

Roll Output

Pitch Ignore

8HF LF

19 19

2O 2O

21 21

87 87

86 86

88 88

25 25

9

19 19

2O 2O

21 21

23.

l.T&2.3KcVCO's

1.3 KcVCO's

4 4

87 87

4o

88 88

S5

i0

HF LF

19 19

2O 2o

21 21

@

1.T&2.3 KcVCO's

1.3 KcVCO' s

4 4

87 87

86

88

85

13HF LF

19 19

2o 2O

21 21

Z.T&2.3KcYCO's

1.3 KcVCO's

4 4

87 87

16HF LF

2O 2O

21 21

1,7 &2.3_YCO's

1.3 KcVCO 's

4 4

87 87

88

86

85

MAC 231C (_v 14 0¢f. 5S)

oAr¢ i November i_61

REVISED

RL=V|SED,

ST. LOUIS 3. MI_._OURI

Moore. 133

k


(HighLevel 0-3 Volt. ) (Cont'a.)

HORRIZON SCANNER

(Cont 'd)

Roll Ignore

ATTITUDE

Pitch

Roll

Yaw

ALTI_N/DERATE

Pltch AB

Roll AB

Yaw AB

RCS CONTROL SOLENOIDS

Pitch High Up

Pitch High Down

Pitch Low Up

Pitch Low Down

Roll High CW

Roll High CCW

Roll Low CW

8KF 12

59 59

16 86

17 8888 17

18 18

2.3KcVCO 's

1.7KcVCO's

1.3KcVCO's

65 65

66 66

67 67

68 68

69 69

70 70

76 76

9HF LF

85

16 %16

17 17

18 % 18

S

16 16

S17 17

65 65

66 66

67 67

68 68

69 69

7o 70

76 76

lO

HF LF

85

16 16

17 17

18% 18

S16 85

s

17 86

s18 88

65 65

66 66

67 67

68 68

69 69

7o 70

76 76

13HF LF

16 86

18 18

65 65.

66 66

67 67

68 68

69 69

70 7o

76 76

:3;ir;D:;.7;A;

16

85

S16

16 85

1717 86

S18

18 88

65 65

66 66

67 67

68 68

69 69

7o 7o

76 76

I_4

REPORT _DR ZO4

MODEL 133



(High Level 0-3 Volt.) (Cont'd).

RCS CONTROL SOLENOIDS

(Cont'a.)

Roll Low CCW

Yaw High Left

Yaw High Right

Yaw Low Left

Yaw Low Right

SATELLITE CLOCK _lapsed

Time)

i0 Seconds

i Minute

i0 Minutes

i Hour

I0 Hours

0 - i0 Seconds

SATELLITE CLOCK (Retrograde

Time)

i0 Seconds

1 Minute

i0 Minutes

1 Hour

I0 Hours

0 - i0 Seconds

8HF LF

77 77

78 78

80 80

81 81

26 26

28 28

29 29

30 30

3l 3l

3e 32

33 33

34 34

35 35

36 36

37 37

38 38

77 77

78 78

80 80

81 81

26

28 28

29 29

30 30

3l 3l

32 32

33 33

34 34

35 35

36 36

37 37

38 38

10

HF LF

77 77

78 78

8o 8o

8l 8l

26 26

28 28

29 29

30 30

3l 3l

32 32

33 33

34 34

35 35

36 36

37 37

38

_gY.FIDEr:TIA_ c

?7 77

78 78

80 8o

81 81

16HF LF

77 77

78 78

8o 8o

81 81

26 26

28 28

29 29

30 30

31 31

32 32

33 33

34 34

35 35

36 36

37 37

38 38

MAC '_31C (Rev 14 Oct,, 55)

DATE. i _ovember 1961

REVISKD

REVISED


PAGt i_-_5

RmP,oi_-r. SEDR 104

MO.m. 133


(High Level 0-3 Volt. ) (Cont 'd.)

INTERIM CLOCK

0 - lO Seconds

O - lOO Seconds

0 - lO00 Seconds

0 - i0,0OO Seconds

TR TIMER

NORMAL LAUNCH SEQUENCE

Sync Pulse

Sync Pulse

Tower Release

Capsule Separation

Retro Attitude Cored.

Retro Rkt. Assy.Jett.

Retro Rkt. No. 1 Fire

Retro Rkt.No. 2 Fire

Retro Rkt.No.3 Fire

Ret ro Rk%. As sy.Jett.

EMERGENCY ESCAPE SEQUENCE

Pilot Abort

8HF LF

_6 46

47 47

48 48

53

50 50

52 52

53 53

9HF LF

46 46

47 47

48 48

53 53

5o 5o

51 51

52 52

53 53

lO

HF LF

_,7 47

53 53

53 53

59 59

13HF LF

26 3131 3333 26

28 3232 3434 28

29 3737 3535 29

30 3838 30

36 36

89 89

90 90

46 46

47 47

48 48

53 53

50 50

52 5e

53 53

_9 59

16HF LF

_6 46

47 47

48 48

53 53

59 59

46

REPORT SEDR 104

MODEL_ 1]_

Mc'DO1NNELL __ ST. LOUIS, MISSOURI

IL.,_.JJ.'q A AJILJJF,_.I.I .IL JLA'3L'_L4

DATE i November i_61

REVISED

REVISED,


(alghLevel0-3 Volt.) (Cont'd.)

EMERGENCY ESCAPE SEQUENCE

(Cont' d. )

May Day

Tower Escape Rocket

LANDING SYSTEM SEQUENCE

Drogue Chute Deploy.

Antenna Release

Main Chute Deploy

Main Chute Jettison

Reserve Chute Deploy

Landing Bag

PERISCOPE RETRACT

INTEGRATING ACCELEROMETER

;/_ _._re,_ a_SOR

PRINATE REACTION TOTAL

8 9 lO

_F LF EF LF HF LF

60 60

61 61

54 54

55 55

56 56

57 57

58 58

6o 6o

61 61

54 54

55 55

56 56

57 57

58 58

7_ 72

ANIMAL RESPONSE

R. H. Switch

Center Switch

L. H. Switch

3 -_-

6 _--

59 ---

Pos. Identification

COMMAND RECEIVER ALL

CHANNEL SIG.

PARACHUTE COMPT. PRESS

4 m__

--- 25

6o 6o

6]. 6l

54 54

55 55

56 56

57 57

58 58

72 72

52 52

50 50

13LF

60 60

61 61

54 54

55 55

56 56

57 57

58 58

72 72

5 5

16KF LF

60 60

61 61

54 54

55 55

56 56

57 57

58 58

5l 5l

72 72

CgNYIDZ;_TIA,_-

MAC 231C (_v 14 Oct,. 5s)

OATS, I November 1961 ]VIC'DONNEL L-ST. LOUIS 3, MISSOURI

m,A@,r 13-47

m_m1" SEDR IO_

,4oo-', 133

/ •

\

Table 13-2.

ROLL TO YAW COM' D

(m Gain)

ROLL TO YAW COM'D

(Lo Gain)

YAW TORQUER SIG.

HEAT SHIELD CAVITY PRESS

TELEMETRY INTERROGATIONMONITOR

Instrumentation Commutator Point Assignment(High Level 0-3 Volt. ) (Cont 'd.)

8HF LF

85 85

9KF I/

27 27

_9 49

71 71-

25

l0 13 16HY LF KF LF HF LF

_o

S.

Kr.

IF.

Not Ccmmutated

With O.05G Relay De-Energized

With O.05G Relay Energized and Retrograde Assembly Jettisoned

High Frequency T/M Transmitter Cosmratator

Low Frequency T/M Transmitter Commutator

=J. ;.7"; D _.;4T;A L

i 2

YAW CON'TI_. LMo'rioNPOTENTIOMETER

PITCH CONTROL

MOTIONPOTENTIOMETER

o, RESER_VE-ROLL ERROR ¢, PARTIALPRE_.Ua._ CHUTE'_W TORQUE DEPLOY

OEMOOULATOR LIMIT

TR,qNSDUCER

(_ul'r _ILET (.SUIT INLET M[IIN CHUTE

All_ PRESSL)RF.) RIR TF_.,MR) DEPLOYLIMIT 3WlTr.H

;0 "BF! >

m _

g

;0 ;0 0

g g m

°°10 0

L

rf• "L

X,Y,Z ACCELE P_OMET EIK%

INSTRUMENTATIONPACKAOE _B" --

"lAW PJkTE

DETECTOR ,_//

INSTRUMENTATION

"RA

_ RECORDERVOICE AND TELEMETERING

PDM-COIvlIvt A (HI FRE_.)PDM-COMM. B (LO FREQ.)

iI

i // j

I / /' /

I

, ', _ ,

HOLDER

(INSTRUMENTATION)

COOLANT QUANTITY

TR/kNSbI3CER

<iii_ mm 111o 13

o<m

i.

_ >m

m

_°o

5o

REPORT_ SEDR, 104

MODEL 13_


..:_-_l'_ _T_ x w'__. _T_ %_][_ ... REVISED

Table 13-3. Special Instrumentation Parameters Commutator Point Assignments

(Low Level - 3MV to 13MV Ref. )

CapsulePole

Nomenclature

Zero Scale (-3MY)

Full Scale (13MV)

Ref. Junction Temp60°F to lO0°F

Ref. Junction Temp70°F to 90°F

T/M "A" TransmitterZll2

UEF Power Amp.

ZLO6.5

Near Batt. Zl05

"S" Band Beacon

Zl07.5

Envlr. Area Zl17.5

H.F. Voice Trans-

mitter

Cabin Air Temp ZlO1.5

"C" Band Beacon

Cabin Air Tamp Z145.5

Heat Exchanger Outlet

Heat Exchanger Inlet

H_O_ Line, Conicalsec_. (Auto)

H209 Line, Conicalsec_. (man)

Solenoid Valve 24"

ZlTO.5

9

Chart. Chart.

i i

2 2

3 3

5 5

6 6

7 7

8 8

9 9

i0 i0

ll

12

13

#1 #2Chan. Chan.

5 5

6

7

8

9

lO

6

ii ii

12 12

13 13

7

8

9

lO

ll

12

13

4"

MAC $31C (l_v i40c_ _;

DArE 1 November 1961 I_I)0NN__........ _.-_ rAG,, .1.3-51 .n_VlSED ST.UOUm S.M,SSOU_, REPORT SEDR 104

Rsv,sm: _ _ Moo= 133

Table 13-3. Special Instrt..entation Parameters Commutator Point Assignments(Low Level - 3_ to 13MV Ref. ) (Cont 'd.)

Nomenclature

CapsulePole

(Outer

(Outer

9_1 •Chan. Chan.

14

15

16

17

18

19

20

21

22

23

24

25

26

27

28

14

15

16

17

18

19

20

21

22

23

24

25

26

27

28

29

H202 Line to 24"Chamber

_0 2 Tank(Man)

_o 2 T_ (Auto)

Heat Shield (Blkh'dcap)

L/O Auto System RollSolenoid Valve

L/O Auto System Roll

ti202 Line

Recovery Comp.

(_er _in)

Inner Skin Below

Reaction Control Jets

Recovery Comp (Int.Structure )

Recovery Comp (Inner

skin)

Ablation Shield (inbd)

Ablation Shield (inbd)

Parachute Comp. Z179

Parachute Ccmp. Z179

Parachute Camp.

Parachute Comp.

Emerg Egress Hatch

(Outer Edge)

Parachute Comp (outer

29

__ 30 30

Chin. Cm,_.

14 14

15 15

16 16

17 17

18 18

19 19

20 2O

21 21

22 22

23 23

24 24

25 25

26 26

27 27

28 28

29 29

30

::Y:____.':T'f.L

w

PAGE 13-52

REPORT SEDR lO4

MODEL_ 133



REVISED

REVISED

Special Instrumentation Parameters Commutator Point Assignments

(Low Level - 3MV to 13MV Ref. ) (Cont 'd.)

Nomenclature

CapsulePole

Parachute Comp (Outer

Skin) Lx

Emerg Egress Hatch

(Outer Edge)

Conical Section Sides

Outer Skin

z154.5 T7zA54.5z_54.5 LxZ_26.5 TFzi17.0 Ty

Emerg Egress (Per-

cussion Ignitor)


Outer Skin

Z126.5 ByZ126.5 By


Outer Skin

zao7. TyZI07 ByZI07 LxZa07 Lx

Tower to CapsuleRetaining Ring (Top)

Tower to Capsule Retain-

ing (Bottom)

Tower to Capsule Retain-

ing Ring (Bottom)

Window Outside of

Inner Pane

Chan.

69

31

32333435

36

3738

394o4142

43

45

Chan.

69

31

32

333435

36

3738

394o4142

43

45

13

Chart.

31

323334

35

36

3738

39404142

43

44

45

Chan.

31

Ablation Shield

Mid.25 Glass Fiber

Mid.25 Glass Fiber

46

4748

46

4748

46

4748

323334

35

36

3738

39404142

43

46

4748

MAC 231G (Rev 14 Oct. 55)


REVISED

REV|SED


PA_- 13-53

Rm_o_rr SEDR 104

MODL .....133

ii)

/! ;,

_.[T:."TJ

Table 13-3. Special Instrumentation Parameters Commutator Point Assignments(Low Level - 355/to 13}47 Ref. ) (Coat 'd.)

Nomenclature

Capsule 9 13Pole #1 ! #2 #l __ #_

Chan. Chan. Chem. Chan.

Inbd Surface of Glass

Inbd Surface of Glass

Hat Sect. (Bottom)

#12 str.

HatSect.(Bottom)#12_r.

R.H. Console Z126. 5

Hat Sect. (Side)

#12 _r.

T/MXmitterPwr

supply

Hat Sect. (Top)

#12 Str.

Between C&S Band

Beacons

Hat Sect. (Bottom)#24 Sir.

Hat Sect. (Bottom)#24 Sir.

Transmitter Equipment

Hat Sect. (Side)

#24 sir.

Hear Calibrator

H20 Tank

Hat Sect. (Top)

#24 Str.

Near Inverters

Left Side Window

(Bolt)

49 49 49 4950 50 50 50

51 51 51 51

52 52 52 52

53 53

53 53

54 54 54 54

55 55 55 55

56 56 56 56

57 57

57 57

58 58 58 58

59 59 59 59

...... "" _'-"T'| | I

PAGE, 1_-_4

REPORT SEDR 104

MODEL_ 133



REVISED ,

REVISED,

Table 13-3. Special Instrumentation Parameters Commutator Point Assignments

(Low Level - 3MV to 13MV Ref. ) (Cont 'd. )

Nc_enclature

Capsule

Pole #I

Chan.

6o

61

6263

64

65

66

6?

68

7o71

72

?3

75

Chart.

60

61

62

63

64

65

66

67

68

7o?_

13' #l _2

Chsa. Chart.

6o 6o

61 61

62 62

63 63

64 64

65 65

66 66

70 70

67 67

69 69

?l 71

72 72

73 73

74 74?5 75

76 76

77 77

Left Side Window

(Inner Pa_e)

React ion Control

Thrust Chamber

Auto 24#

Auto l#

Man 24#


Catalyst Bed L.H.


Catalyst Bed L.H.

Heat Shield

Attaching Bolts

Horizon Scanner (Pitch)

Horizon Scanner (Roll)

Ant. Comp. (Outer Skin)

Ant. Comp. (Inner Skin)

Ant. Camp. (Outer Skin)

Drogue Chute Can

Parachute Comp. (Outer Skin)Lx

Ant. Comp. (Inner Skin)

Ant. Camp. (Outer Surface)

Retro Rocket Package

z88 _ xoz88 _ XRZ88 _ X5

Retro Rocket (Right)

Retro Rocket (Bottom)

76

77

72

?37475

76

77

/

J

_MAC 231C (Rev 14 Oct,. 55)

OATE._._ November 1961

REVISED.

REVISED

MCDONNELL, ,, ST. LOUIS 3, MISSOURI

PAG-- 13-55

R,_PORT"aEDR ,_O_

MO0_. 133

Table 13-3. Special Instrumentation Parameters Commutator Point Assignments(Low Level - 3 MY to 13MY Ref.) (Cont'd.)

Nomenclature

Capsule

Pole

Retro Rocket (Exp.Bolt)

Adapter SidesOuter Skin

z79.5 LX

Z79.5 By

Z79.5 Ty

Cap. to Adapter

Retaining Ring

Adapter RetainingRing Cover

Cap. to AdapterExplosive Bolt

Escape Tower Z257

Escape Tower (Left Leg)

Pylon Explosive Bolt

Stability Wedge

Chart.

79 798o 8081 81

82 82

83 83

8_ 84

85 85

86 86

87 87

88 88

Chart.

13

798o

81

82

83

84

85

86

87

88

78

798081

82

83

8_

85

86

87

88

13-111. Astronaut Observer Camera

The mechanism of the Astronaut observer camera is the same as that of the

instrument panel observer camera.

13-I12. TEST CONFI_ION CAPSULES


13-i14_ S_stem Descriptiom

Instrumentation on Capsule No. 8 is similar to the Specification Compliance

Capsule (Refer to Paragraph 13-1) except that Capsule No. 8 is intended for an

unmanned (orbital) mission and therefore data pertaining to the Astronaut does

not apply. Major components installed are shown on Figure 13-5.

56

REPORT aEDR 10_ "

MODEL. 1_3

.MC'DONNEL LST. LOUIS, MISSOURI


REVISED

REVISED

13-115. S_stem OEe ration

Instrumentation on Capsule No. 8 is similar to the Specification Compliance

Capsule except is unmanned and operation is either automatic or ground controlled.

13-116. Monitoring Instrumentation

Monitoring instrumentation is the same as the Specification Compliance

Capsule (Refer to Paragraphs 13-3 through 13-58) except as noted in Paragraph

13-117 through 13-136. Figure 13-6 shows the various parameters monitored while

Table 13-2 lists the commutator point assignments for each parameter.

13-117. Standby Battery

The standby batteries, ON, signal comes from the secondary bus relay No. 2.

This relay energizes if the STANDBY BATTERY switch is in AUTO position and main

bus voltage is below 18 volts. Wlth the relay energized, 2_ volts d-c (nominal)

is applied to an attenuator in package C. Attenuator output (2.8 volts d-c

nominal) is applied to the commutators.

13-118. Environmental Control System

Environmental Control System instrumentation on Capsule No. 8 is the same as

the Specification Compliance Capsule (Refer to Paragraphs 13-16 through 13-22)

except that the emergency oxygen supply and 02 partial pressure is not monitored.


Reaction Control System instrumentation on Capsule No. 8 is the same as the

Specification Compliance Capsule (Refer to Paragraph 13-23) except that the hand

control positions are not monitored.

13-120. Acceleration

Capsule acceleration instrmmentation consists of circuitry which monitors

acceleration along three mutually perpendicular axes. The launch and re-entry

signal range is utilized throughout the flight. (Refer to Paragraph 13-30. )

DATE

REVISED

. REVISED

1 NOVEMBER 1961

M 'DONNE ST.LOUIS, MISSOURI

PAGE

REPORT

MODEL

13-57

SEDR 104

133

f- -

i 7

J CAPSULE _ AMPLIFIERS

ELECTRICAL

POWER SYSTEM RECTIFIER

AND

_ ATTENUATOR

INSTRUMENTATION:

POWER SUPPLIES

RECTIFIER

AND

SOUNDLEVEL j_ ATTENUATORPRESSURESTATIC

VIBRATION i

DATA

ANALYZER

CALIBRATIONON

ATTENUATOR

EN V_O:NT_N TA L

AMPLIFIERS i

ACCELERATION

--_ AMPLIFIERS

• r r REACTIONCONTROL

SYSTEM

AMPUFt_S L

AMPUFIERS,

!I •

J _:i ATTENUATORSR ATTENUATOR

I co _2_7_ i iAL

MF_GA ENC LAUNCH

I E Y SEQUENCE i

SEQUENCE / !' LANDINGSYSTEM

g_%_TON _ESSUREI

MONITOR j HEAT SHIEW

J CAVITYPRESSURE

\ IN_'Si _

"A" COMMUTATORO-3VINPUTSD--C J_

PDMCONVERTER

PULSE AMPLITUDE

r MODULATION

I 10.5KC VOLTAGE

CONTROLLED

OSCILLATOR J

II

COMPENSATING I

OSCILLATOR !

J MIXER "A"

2.3KC VOLTAGE

CONTROLLED

OSCILLATOR

1.7KC VOLTAGE J J

CONTROLLED

OSCILLATOR

1.3KC VOLTAGE J J

CONTROLLED VOSCI LLATOR

PULSE DURATION

MODUI.ATION q

J TAPE

RECORDER

1.3KC VOLTAGE

CONTROLLED

OSCILLATOR

2jKC VOLTAGE

CONTROLLED

OSCILLATOR

2.3KC VOLTAGE J_

CONTROLLED

OSCILLATOR

, f

MIXER "5"

J 10.5KC VOLTAGE

CONTROLLED

OSCILLATOR

LSE AMPLITUDE,

oo::,o CONVERTERJ t

..,,-co,._. I T0-3V D<

IN.ITS /_cooiNG ANDCO"TROL_'--'=_ \,,

Lv

HI FREQ

TELEMETRY

TRANSMITTER

81CONE

ANTENNA

TANTENNASWITCH

iDESCENT

ANTENNA

MULTIPLEXER _-- J)

TRANSMITTED

1. AND RECEIVED

VOICE SIGN_,LS

J LOW FREQ. J_

TELEMETRY

TRANSMITTER

TRANSMISSION

FIGURE!3.6 , MONITORING INSTRUMENTATION BLOCK DIAGRAM-CAPSULE 8 _

" |" _llm

VVlIIF lii..,BL.--ll l Ff=_T.i,

REPORT 8.EDR 104 ST. LOUIS, MISSOUR! REVISED

MODEL 133 _ C_.t_:_'_"_,_,.._. REVISED

13-121. Structural Temperature

Structural temperature instrumentation is similar to the Specification

Compliance Capsule. (Refer to Paragraph 13-32 through 13-38. )

13-122. Attitude Rate

Attitude rate signals are not commutated in Capsule No. 8. These signals

are applied to the voltage controlled subcarrier oscillators that are utilized

for electrocardiograph signals in the specification compliance capsule. A 0 volt

signal level represents a zero attitude rate. A -1.5 volt signal represents a

decreasing rate of 6 degrees per second and a plus 1.5 volt signal represents an

increasing rate of 6 degrees per second. Pitch rate is applied to the 2.3 Kc.

oscillators. Roll rate is applied to the 1.7 Kc. oscillators. Yaw rate is

applied to the 1.3 Kc. oscillators. Pitch and roll signals are routed through '

a biasing circuit to set up the proper center frequency signal level.

13-123. Parachute Compartment and Heat Shield Cavity

The parachute compartment pressure and the heat shield cavity pressure on

Capsule No. 8 is instrumented and monitored on the HF and LF Commutators.

13-124. Landing System Sequence

Landing system sequence instrumentation on Capsule No. 8 is the same as that

for the specification compliance capsule (refer to Paragraph 13-54) except clr-

cuitry is added to monitor the Betro Rocket Gone Relay #i, #2, and #3. This

signal is obtained from relays in Retrograde Relay Box #2. These signals are

monitored on the KF and LF Commutators. The Landing Bag and Astronaut's Abort

Systems are not monitored on Capsule No. 8.


The instrumentation system controls and programs (See Table 13-I) power to

its own and other system equipment.

a. The earth and sky camera viewing from capsule window Operates at I0

_ jr=,ir,.,ib,,L...-,,v,.,,,._.,v-,,_ _v .._ _,_1t, ,J.,L,F,,IL,_dlll ,I. ,A,_"IL IIj

DATE . . , n =:A.N_V.M.ER 1961

REVISED ,,

REVISED

Mc'DONNELjL_r_ __ST.LOUIS. MISSOURI

PAGE.

REPORT,

MODEL

13-59

SEDR 104

133

SEE TABLE. t3,-Z POR

PROGRAMMER TIMING

MAiN I

F_E-I M_'ACt"D-C. _.U5

-rAPF. R_C.ORO ON' LtO.M'I"

5_CONO_Ry 1

PR.E -IMPACT

34V D-C BUS

CAMERA _ID _h;_REC.oI_oER SWl-rCH

EARTH ANO 5V_y CAMERAFILM W 1"f14 DR.AW_.

;kISTRU_NT _NE.L. CAMEI_._Flt..M wFrHoR,_WL I.._,Gh"T

_'r_.O_UT OR. P_<_r_o_P¢.

_.IC_H_" •UMG_LIC.AL

COhl N P..c:*'lr0 I_,

IIJ

TAPI= RDERI_g.c¢

rC i

III

III

i

,

IPROVISI(_I5

FOR

AST _:ON/_,UT

-¢AMIERA

IN_-r_UI_ENT

I_ANEI.

GAM5R_

11r

i ''=

I

..£___ ._L

_-I' IANO _'Y (

CAMER._l

REPORT SEDR 104 ST. LOUIS, MISSOURI REVISED

..._'"_.'.,_"x"=__ _ --',"=_,'_LL=----_ REVISEDMODEL. 133 ...............

i November 1961

bo

C.

mission.

d.

frames per minute throughout the mission.

The periscope camera operates at 180 frames per minute throughout mission

The instrument panel camera operates at 360 frames per minute during the

Calibration voltages; R-calibrate for percent full scale readings and

Z-calibrate for zero readings, are supplied from the block house before the

umbilical is dropped, just prior to launch.

13-126. Recordin_ Instrumentation

Recording instrumentation consists of a tape recorder and three cameras. The

Astronaut observer camera is omitted from Capsule No. 8 and a periscope camera is

installed. (See Figure 13-7.)

13-127. Tape Recorder

The tape recorder used on Capsule No. 8 is the same as the recorder used ca

the Specification Compliance Capsule (Refer to Paragraph 13-64), except the tape

speed is 151 inches P/S. Also a Playback Tape Recorder to simulate the Astronaut'

voice (See Section XI and Table 13-1) is installed.

13-128. Cameras

Capsule No. 8, being an unmanned vehicle, does not use an Astronaut observer

camera. The usual Instrument Panel Camera is installed, as well as an Earth and

Sky Camera and a Periscope Camera. (See Figure 13-5). Programming is received

from the capsule programmer.

13-129. S_ecial Instrumentation

A special instrumentation package is used in Capsule No. 8. The package con-

sists of fuse blocks, special instrumentation relays, five track tape recorder and

a nine channel amplifier case with associated power supply. Vibration measure-

ments are taken from various points on the capsule, amplified and applied to

separate tracks on the package tape recorder or to the capsule tape recorder. A

--_......#_._ a. A4L2a/dl_ JL JL_kJL4--

MAC 231C (Rev 14, Oct. 55)

OAVE i l_ovember 1961

RI_/ISKD

RE:V|S£D


rA_tt, 13-61

R_o_r 8EDR 104

MO._ 133

i _ _

_L

total of nine tracks are recorded as follows:

P.a.llet Tape Recorder

Track 2 Z123 Ring Longitudinal

Track 3 Web at LXl2

Track 4 Instrument Panel

Track 6 Z123 Ring Tangential

Track 7 Parachute Compartment

13-130. System Units

Ca_st_le Ta_e Recorder

Track 2 Package "B" Noise Level

Track 4 Z123 Ring Radial

Track 6 Shingle Strain Gage

Track 7 Escape Tower

The system units used on Capsule No. 8 are the same as the Specification

Compliance Capsule except as noted in the following paragraphs. (Refer to

Paragraphs 13-68 and 13-69. )

a. Main and Reserve Oxygen Pressure Potentiometers are not instrumented

b. Respiration rate and Depth Potentiometers are not monitored

c. Control Stick Potentiometers are not monitored

d. Body Temperature Transducers are not used

e. Electrocardiogram Pickups are not used

f. Tape Recorder is the same as specification compliance capsule.

(Refer to Paragraph 13-82. )

13-131. Sound Level and Vibration Transducers

A microphone and amplifier are located in the B package for sound level

pickup. A piezo-electric/diap_ type microphome is used to pick up a pressure

level of lO0 to l_O db with a frequency range of 37 to 9600 cps. The variable

gain, transistorized amplifier consists of am impedance matching stage, filter

network, buffer Stage and final amplifier. Amplifier output, 3 volts R_, is

used with a data analyzer. A piezo-electric crystal is used as a vibration

pickup, measuring a frequency range of lO to 2000 cps. The tramsducer is used

in com_ctioa with vibration amplifier.

v_n Is mlimwm_a_ i aa_

Mc,DONNEL L REPORT SEDR i0_ ST. LOUIS, MISSOURI REVISED

MODEL. i_ _,z_ *" z.u_J._ * ,._L_:r" REVISED.


13-132. Vibration Amplifier and Data Analyzer

A transistorized amplifier is used to increase the output of the vibration

transducer to a level compatible with an accoustical and vibration analyzer.

13 -133. Programmer

The programmer contains switch contacts which operate control circuits for

specific intervals of time. The unit for Capsule No. 8 consists of one section

of wafer contacts. When power is applied to the programmer the electronic con-

trolled timers continuously operate the following wafer contacts.

Wafer Section Duration Rate

i 30 Seconds I Per 30 Min.

2 ii0 Milliseconds 6 Per Second

3 90 Milliseconds i0 Per Minute

llO Milliseconds 3 Per Second

13-13_. Instrumentation Package "C"

Function

Water Extractor

Instr. Panel Camera

Earth & Sky Camera

Periscope Camera

The horizon scanner output amplifier card in package "C" provides a bias

voltage to keep the horizon scanner pitch and roll signals within limits compatiblq

with other system components. Calibrate control relays are installed on the card.

Roll ignore and pitch ignore signals are Jumpered through the card. The Horizon

Scanners operate continuously from launch to re-entry.

13-135. Instrumentation Package "A"

The instrumentation package "A" is the same as the Specification Compliance

Capsule except for the removal of the body temperature amplifier card.

13-136. Instrumentation Package "B"

The components used in package "B" of Capsule No. 8 are the same as in the

package "D" in specification compliance capsule except for the following units.

(Refer to Paragraph 13-102. )

a. Attitude Change Rate Filter and Calibrate Cards

__/_/'_lLTT'?ITT'%lf_lLVlSqlT • -- --

._=4.,_r 4. I .A ._.._.r,.A.&, .._ 41.,_LJL.4

MAC 231C (Rev 14 Oct 55)

1No ber Mc,DONNEg, • ,... 13-63REVISED ST. LOUIS 3. MISSOURI REPORT. _DR 104

R_V,S_D t-*_'-__ ........ Homa. 133

/

'\ : _j!

Attitude change rate filter and calibrate cards replace the electrocardiograph

amplifier cards. Three attitude change rate cards are used. They are for

pitch, roll and yaw parameters. The cards associated with pitch and roll rate

provide for application of calibrate signals to these channels. The yaw rate

card provides this function and also contains a bias battery to set up center

frequency on the voltage controlled oscillator when yaw rate equals zero degrees

per second.

b. Voltage Controlled Oscillator Cards

The oscillator cards used in Capsule No. 8 are similar to those used in the

specification compliance capsule. (Refer to Paragraph 13-107. ) However, attitude

rate signals are applied to the oscillators instead of aeromedlcal signals.

Oscillator functions and frequencies are indicated in the following list.

HF Commutator

KF Commutator output is applied to the 10.5 Kc oscillator.

Yaw Rate Is applied to the 1.3 Kc oscillator.

Roll Rate is applied to the 1.7 gc oscillator.

Pitch Rate is applied to the 2.3 Kc oscillator.

Compensating Oscillator frequency is 3.125 Kc.

LF Ccv_nutator

LF Commutator output is applied to the 10.5 Kc oscillator.

Yaw Rate is applied to the 1.3 Kc oscillator.

Roll Rate is applied to the 1.7 Kc oscillator.

Pitch Rate is applied to the 2.3 Ec oscillator.


13-138. S_stem Description

The instrumentation system on Capsule No. 9 is similar to the Specification

Compliance Capsule (Refer to Paragraph 13-1) except that the capsule will be

ii

Ii

o ,,,

_ m_

INSTRUMENTATIOn"

PACKAGE'_"7

I_ADIAI'DETECTOR

6

ETER.

RECORDERVOICE AND TELEMETERINGPDM- COMM. A(ttI_,H FREQ)PDM- COMM. B (.LOWFREQ) '

XI 0

g g mm mo o

I -I Z' 0

<I m

I"m

I

I

r

3 m >

_ m

m

66

REPORT _EDI_ 104

MODEL 13_

_ DATE i November 1961

ST. LOUIS, MISSOURI

•_'_ _, *" z _ . . ,_ REVISED

unmanned and a special instrumentation pallet and primate couch replaces the

Astronaut's couch. Major components installed are shown on Figure 13-8.

13-139. Monitoring Instrumentation

Monitoring Instrumentation differs from the Specification Compliance Capsule

in that Capsule No. 9 is instrumented for primate occupancy. Figure 13-9 shows

the parameters in block diagram form while Table 13-2 lists the commutator point

assignments for all telemetered instrumentation. Deviations from the Specifica-

tion Compliance Capsule are explained in Paragraphs 1S-l_O through 13-157. )

13-140. Standby Battery

In Capsule No. 9 the standby battery power is connected directly to the

main d-c bus, in parallel with the main batteries. The standby d-c auto light

or automatic switching of the standby to the main bus is not used.

13-141. Special Instrumentation Pallet

The Special Instrumentation Pallet is installed in place of the Astronaut's

Couch. The pallet contains an array of circuits for instrumenting the various

parameters as listed on Table 13-3. Location of the sensors are indicated on

Figure 13-11 and the point assignments for each parameter are listed on Table

1B-3. The values measured by each sensor is encoded by the multicoder and

recorded on a tape recorder. Power for the pallet is obtained from the 150 volt-

ampere inverter and controlled by a multicoder "ON" - "OFF" switch.

13-142. Blood Pressure Oscillograph

The oscillograph-tape recorder, which records the venous and arterial blood

pressure of the chimpanzee is mounted beside the Special Instrumentation Pallet.

The oscillograph is powered by its own, self contained, wet-cell battery. The

power is controlled by an external ON-OFF switch. A transducer is attached to

the Solar-Plexis of the chimp, which converts blood pressure values to electrical

signals. These signals are routed through an amplifier in Instrument Package "A",

j:---\

DATE

REVISED

REVISED

1 NOVEMBER 1961

McDONNE__ __ST.LOUIS, MISSOURI

-LC .... ,.,,, , ,....,,,r-..,,'w

PAGE. 13-67

REPORT • SEDR 104

MODEL 133

.f'?-\

/ " .

;'68

REPORT SEDR 104,

MODEL 133


_ "_,,uJ i,,,/ L-

DATE .

REVISED

REVISED

1 NOVEMBER 1961

TAPE _ECOROE_ PP.E-

IMPACT MAiN D:C._,US

P.ETIRO - P.ECOV E RYZ4V D-C BUS

_-_l SCOPE CAMERA_.4V MAIN D- C _U5

CAMERA At_D TAPE_E.CG_E)E _ SW_TCH

"ON" L_GNT

EA_.TN A_D SKY CAMERA_LM XN _T_ b_ AWAL

L_GMT

PERt 5COPE CAMERA

_'_,M W|T_D_AYVAL

-/l{- .%E._. TABLE _,3-?-PROQ_AMER TI MIt_G

CAMEP, A AN(::) TAPE

I

CAMERA ANO TAPEI::::_,ECOI:_DE _, P,EL AY

I

T

TA_E

_.ECO_.bE _

COMBINEb, C_IVES THE

qOt4F!C_U_ATION.OF CAPSULE 9

PER|_COPP. CA_E_A E.A_:_,TH At4O _KY CAMERA

FIGURE _3-10CAMERA5 AND TAPE RECOP, DE_. CONTg, OL C_RCLI|T CCAPSULE.'9) .

p t_l IM =' I I"l =' I. _''JL-_l-"--_ --- --. _ • in II-T-

DATE

REVISED

REVISED

1 NOVEMBER 1961

M;DONNELLST.LOUIS, MISSOURI

"-_Vl _qll lug,,,, i'qF- I A I

PAGE, 13-_69

REPORT SEDR 104

MODEL 133 *

ITEM DESCRIPTION LOCATION

/ ' RETRO ROCKET PACKACE _ETEO ROCKET - RIG_) RX rY2 ADA_1ER SLOES - OUTER SKIN Z79.S

3 RETRO ROCKET PACKAGE Z88.0 RX BY4 RETRO ROCKEt EXPLOSIVE BOLl zsl 6 XO YO

5 ABt_.TION SHIELD - BETWEEN .06 AND .E FIBERGLASS RX33 TY36 RETRO ROCKET PACKAGE Z88.0 XO _Y

HEAl SHtELDATTACH POINT ZIC,4,5 XO TYCAPSULE IO ADAPTER EXPLOSIVE BOLT ZIO0,O XO TY

0 H202 lANK. AUTOMATIC Z104, 5 XOCONICAL SECTION SIDES - OUTER SKIN ZI07.0 TY

It ADAPTER SIDES - OUTER SKIN Z79.5 LX12 ABLA¥1ON SHIELD - BETWEEN .06 & .2 FIBERGLASS LXI TY2

13 CABIN AIR IEMPERATURE ZIDI.5 LXI8 _o14 ?]AT SECTION - 124 STRINGER, 9OTTO*_ z127.0 TY

IS CONICAL SECTION SIDES - OUIER S KIN ZI26.5 XO TY_6 HAT SECTION - #E4 STRINGER, TOP, Z127.0 XO TY

t 7 fIAT SECTION - 124 STRINGER, SIDE TYZI27.0IS I_T SECIIOH. e24 STE_NGER. BOTTOM {7 V2 o) zl27,0 IY

19 CONICAL SECTION SLOES - OUTER SKIN Z107.0 LX2O WINDOW - BOLTEl WINDOW - INSIDE OF OU?ER PANE22 WINDOW - ZNNEA PANE

23 L/O AUTO SYSTEM ROLL - F'_O2 LINE Z_Oe. 8 LX DYI24 IJO AUTO SYSPEM eOLL. SOLENOID VALVE ZIIO.2 LX BYI

25 I_#O AUIO SYSTEM ROLL.CATALYS T BED (L. H.I ZII4.0 LX 9YI

26 H202 LtNE CONICAL SECTION - AUTOMATIC Zl26,527 CONICAL SECTION SIDES - OUTER SKiN Z154. 5 1_f29 CONICAL SECTION SIDES - OUTER SKIN Zt54.S IX

SOLENOID VALVE TOF 24 IJ3. ZITO.5 XORFJ_CTION CONTROL THRUST CHAMBER - TOP (AUIO t24I Z178.0 XO

31 PARACHUte COMPARTMENT - OUTEe SKIN Zi78.0 XO T_32 REACTION CONTROL THRUST CHAMBEX - TOP (AUTO 01) Z179.O LX

33 TOWER TO CAPSULE RETAINING RING (TOP)

34 FARACHUTE COt,APARTMENT - OUTER SKIN

5 R_COVERY COt_PART_ENT INTERNAL SleUCIUKE6 ANTENNA COMPA_Tt_ENI INNER SKiN

37 HORIZON SCANNER (ROLE)

3e ANTENNA CO_AelMENI Lm

39 ANIENNA COMPARTMENT Oute_ SKIN (_OTTOM)

40 _ECOVERY COMPARTMENT iNNER SKIN

41 PYLON EXFLOSIVE BOLT

42 PYLON EXPLOSIVE _OLT COVER

_3 IOWE_ IO CAPSULE RETAINING RING (SOTIOM),W TC_R TO CAPSULE REIAINING RING - BOTTOM

45 PARACHUTE COMPARTMENT SIDE

46 INNER SKIN BENEAIH JET SUPPCeT

47 RECOVERy COMPAeTMeNI tNNEe SKIN

48 H202 LiNE - TOP 24 LB.

49 CONICAL SECTION SIDES - OUTEe SKIN

_0 CABIN AiR TEMP_RAIUXE

_I HAT SECTION BOITOM - 7 _/_" #)2 SInINGER

52 HAl SECTION BOTTOM = J12 STRINGE_

HAP SECTION SIDE - r_2 STR_NGERHAT SECTION IOP - _12 StrINGER

SS CONiC._L SECTION SIDES - OUTEe SKIN

5_ _EAI EXCHANGE (OUTLET)

57 HEAl _XCHANG_R 0NLEI)

se CONICAL TECIION SIDES - OUTER SKJN

_OAFtEe REIA_NING RINGAD_PIER REIA_N_NG X_NG COV_

61 ABLATION SHIELD - SHIELD INBOARD SURFACE

62 A_LATION SHIEL_ eETWEEN.2FtBEeGU_SS AND HONEYCO_

RETEO ROCKET PACKAGERETeO ROCKEt PACKAGE _REIRO ROCKET - 9OTT(_)

65 AOAPTER SIDES - OUTE_ SKIN¸

66 ABLATION S}IIELI)o SHIELD iNbOArD SURFACE

67 HEAl SHIELD - BULKREAO CAP

_ ESCAPE TOWERESCAPE TOWER

ZI84.6 XO TY

zlTa.O IX YOZI_.6 IX6 BY12

Z)91 XO _Y

Z_.l XO BYE.5Z191 xo BY

Z}79,0 RX5 BYI3Z184.6 RX85 BY

ZI84.6 XO BYZI85.7 LX.5 BY

Zl78.0 xo

Zl;7.0 _2 TY_3ZI 7"/.0 TY

Z168.5 xO TYz_.o BY

Z_45.5 xo YO

Zl2/,0 ByZI27.0 BY

ZI27.0 8YZl27,0 _Yz126 XO BY

Z107.0 BYZ)04.5 XO OY

ZI04.5 XOxo _2

z_.0 sY

xO eYZ/%5 BY

Z79.5 0Y

RX33 TY2

Z257.0 xO TY_

zt(_.s LX t_"

ABLATION SHIELD BEIWEEN,2 FIBERGLASS!AND'HONEYCOM RX33 TY3REACTiON CONTROE THRUST CHJU_ER -TOP (MANUAL e24 Zl 7S.O IX TY

Z104.5 XO7Z HE_ z TANK - _AI_UAL

_3 _O2 UNE CONICAL SECTION - MANUAL Z_2_.S

ZI23.O74 EMERGENCY EGeESS HATCH - OUTER EDGE

_5 E_ERGENCY EGRESS HATCH - OUTE_ Em3E Z_46,_

7_ EMEeG_NCY EGeESS HATCH - PERCUSSION IGNITEe. TOP ZIEB.5

S _ND BFACON ZI07.S

_0 EGRESS HATCH Z124,25EG_SS HATCH Z147.2581 TM TRANSMITTER

82 TM TRANSMITTER83 )N'_AERTER

B4 INVERTER

FIGURE 13- 11 THERMOCOUPLE LOCATIONS (CAPSULE 9)

P/A4_-2'JEA ,

PAGE, 1_-_0

REPORT _EDP, 104

_.MODEL, 1-_._.


• _ REVISED

where the signal strength is sufficiently increased to be recorded on the

oscillograph. These signals are not telemetered to the ground.

13-143. Parachute Compartment aud Heat Shield Cavity

The parachute compartment and heat shield cavity pressure is monitored on

the HF and LF Commutators. The pressures are measured by transducers, the out-

puts of which are liaear from 0 to 3 volts for a pressure range of 0-15 psia.

13-144. Inactive Parameters

The following circuits are not monitored on Capsule No. 9:

a. Control Stick Position

b. Abort Switch

c. Landing Bag

13-145. Yaw Data Converter

A Yaw Data Converter is installed on Capsule No. 9- The fumctlon of the

converter is to provide calibrated conversion of the ASCS slaving, output signals

to compatible input signals for the Telemetry Commutators. Two d-c signals are

produced which are proportional to the "Roll to Yaw-Low Gain" and "Roll to Yaw-Hi

Gain". Also a third d-c signal is produced waich is proportional to the 'Maw

Torquing" a-c signal of the ASCS calibrator, and is designated as the "Yaw

Torquer" signal. Zero yaw attitude is represented by 1.75 volts output for the

low-gain signal and 1.5 volts for the hi-galn signal. Meter ranges for all three

signals is 0-3 volts d-c and represents yaw commands of -45 to 45 degrees for

lo-gain, -lO to lO degrees for hl-gain and -6.5 to 6.5 degree/minute slaving

rate, for the yaw torquer signal. These signals are telemetered on both the HF

and LF Commutators. The Yaw Data Converter is powered by ll5V 400 cps a-c, 3.0

volts d-c and 23.5 volts d-c supplied from the capsule power circuits.

13-146. Horizon Scanners

The horizon scanners are instrumented on both HF and LF Commutators.

DATm 1 November 1961

REVISED

REVISED

W,DONNE , ST. LOUIS 3. MISSOURI

PAGE 13-71

REPORT _nR ] 02

MO._ l_

i

C_

13-147. Retro Rocket Firing - Velocity Sensor

The velocity sensor is not instrumented, instead, each of the three Retro-

Rocket firing signals are applied to the KF and LF Commutators.

13-148. Body Temperature

The chimp body temperature is monitored and applied to the EF and LF

Commutators.

13-149. Command Receiver

The cammand receivers all channel signal is instrumented on Capsule No. 9.

13-150. Aeromedical

Aeromedical instrumentation on Capsule No. 9 is the same as that for the

Specification Compliance Capsule (Refer to Paragraphs 13-39 through 13-43), except

that since a primate is being used the scale factors for EED and respiration data

are different and only three EED transducers are used on the primate.

13'151. Primate Instrumentation

The primate couch is mounted on the special instrumentation pallet and is

instrumented to monitor the prlmate's reactions and response. Since Capsule No.

9 is assigned to a specific mission, the primate instrumentation is programmed

differently than other primate test capsules. The primate Programmer consists

of an electronic panel assembly and a liquid feeder. The instrument panel con-

tains three display units, the left-hand unit consists of six symbols and a cyan

blue disc display, the center unit has six symbols, a yellow disc and a white disc

display and the rlght-hand unit has six symbols, a red disc and green disc display.

Three switch levers are provided for primate actuation, with each switch closure

recorded on a four digit counter mounted near the left switch lever. A pellet

dispenser is mounted on the panel and will dispense, on command of a 28 volt pulse,

reward pellets through a hole in the lower rlght-hand corner of the panel. A

liquid dispenser is mounted in the vicinity of the right-hand side of the animal's

I November 1961

head. It will dispense a drink of liquid when actuated by a 28 volt pulse and

triggered by the animal's lips. Power is supplie_ for the prlmate's couch from

the special instrumentation fuse block through the special instrumentation record-

er relay. The animal's response during the various program sequences is recorded

and telemetered as listed on Table 13-2. The programmed psychomotor presents the

sequence of test functions the animal must perform and are as follows:

TEST TIME

1. RS-CS - Regular and classified shock avoidance 15 min.

2. TO - Time Out 2 min.

3. DRL - Differential reinforcement of low rates 5 rain.

4. TO - Time Out 2 rain.

5. FR - Fixed ration reward 5 min.

6. TO - Time Out 5 rain.

7. I_PM/NRPM Position and Negative reinforcement

Perceptual monitoring

(a) 18 Combinations of symbols 5 rain.

(b) 18 Combinations of l, -3 X symbols

8. TO - Time Out (Note: If the last 36 combinations are

completed before the 5 minutes has

elapsed the remaining time is out

and the entire program starts over).

A description of the tests in the sequence they occur and required telemetered

data is as follows:

a. RS-CS (time 15 rain.). The telemetered outputs are as follows:

(1) Program identification through indication of shock.

(2) Cumulative response of left lever.

(3) Cyan blue light on and duration.

,,,,CCL'F.'DZT_TIAL


REVISED

REVISED

bl

Co

Mc'DONNE Er. LOUIS 3, MISSOURI

_--_r_=vlii ii_i--i_l i l/'lill

(4) C_ative response of right lever.

TO (Time 2 rain.) No displays.

Telemetered output s:

(i) Identification (zero input to TM)

(2) Cure. response of left lever

(3) Cure. response of center lever

(4) Cure. response of right lever

(mime 5

d8

e.

pAG_II 13-73

REPOR_ SEDR 104

MOO , 133

Green light in right display unit is activated. If animal waits 20 seconds

before pulling right hand lever, a green light appears beside the liquid

feeder and a drink may be obtained. If R/H lever is pulled before 20

seconds time span, the animal must wait an additional 20 seconds for

another opportunity for a drink.

Telemetered outputs :

(1) Program identification

(2) Cum. response left and center levers

(3) Liquid feeder actuation

(4) Cure. response right lever

TO (Time 2 min.) NO display.

(Time5

Yellow light in center display unit is activated. If animal presses

center lever 50 times, the pellet dispenser is actuated and he gets a

pellet as a reward.

Telemetered outputs :

(1) Program identification

(2) Ck_m. response of left lever

(3) Cure. response of center lever

..... "ill_ll I_PI /_l' "__i_li.ollr llli I . =. /I

REPORT SEDR 104 ST. LOUI,S ,.. MI$$OIJRI_,.. REVISED

MODEL_ 133 _ _: _: _ _ _: T :._ _ REVISED

f.

g.

(4)

(a:ime 2 sin. )

Cure. response of right lever

(t Line 5 rain. )

NRPM mode of operation - If correct lever is pulled, 15 seconds of time-out

results, ,lights are out. The lights then come on with new display and there

is 20 seconds allowed for another decision. Correct lever sets beneath

odd display. If no lever or wrong lever is pulled_ shocks occur every

five seconds after 20 second decision time, until correct answer is made.

PRPM mode of operation - The lever beneath the odd display provides a pellet

reward. Depression of either of the other two levers results in no reward

and provides 15 second time-out after which same display appears.

Telemetered output s :

(1) Program identifier

(2) Cure. response of left lever

(3) Ctnm. response of center lever

(4) Cure. response of right lever

h. Ten minutes after impact the nipple on the liquid feeder is armed and the

green light appears allowing the chimp to obtain a drink.


Instrumentation Control Circuitry for Capsule No. 9 is similar to the Speci-

fication Compliance Capsule except for the progra_ner which provides controlled

power (See Table 13-1) for the following circuits.

(a) The environmental control system water extractor is supplied a 30

second pulse every 30 minutes.

(b) The Instrument Camera is the same as ia the Specification Compliance

Capsule.

©

(c) The Earth and Sky Observer Camera is provided a 90 millisecond pulse,

ten times per minute, during the entire flight.

(d) The Primate Observer Camera is programmed the same as In the Specifica-

tion Compliance Capsule.

(e) The Periscope Camera is provided a llO millisecond pulse, 30 times per

second during re-entry aud 1800 times per hour while in orbit. The camera is

operable only when the periscope is extended.

(f) '_" & "Z" calibrate is the same as the Specification Compliance Capsule.

13-158. Recording Instrumentation

Capsule No. 9 Recording Instrumentation (See Figure 13-11) consists of a tape

recorder and four cameras, the tape recorder, Instrument Camera and Astronaut

Camera are the same as used in the Specification Compliance Capsule (See Para-

graphs 13-65 and 13-66), except that the Astronaut Camera is adjusted to view the

primate. A 70 millimeter Earth and Sky observer camera is mounted at the obser-

vation window. This camera is sighted to record a field of view through the

window. The image of a timer is superimposed on one corner of each frame. The

camera is supplied 24 volt power and pulsing voltage from the capsule power

system. Each pulse operates the shutter, exposing one frame and transporting the

film for the next exposure. Trigger pulses are applied to the camera at the rate

of lO per minute by the programmer. In addition, a periscope camera is used on

Capsule No. 9. The camera is mounted inside the periscope, to view the earth as

it would be seen through the periscope, by an observer inside the capsule. Power

is applied to the camera, only when the periscope is extemded. (See Figure 13-10. )

Pulses for the camera are supplied from the capsule programmer. (See Table 13-1. )

13-15_. System Units

System Units in Capsule No. 9 are the same as used om the Specification

Compliance Capsule, (Refer to Paragraphs 13-68 through 13-81), except the units

_l_i/ lJlm/L--'l _1 • I,'m .

_-76

REPORT _--D_ l N_.

MODEL. ]-33

MCDONNEL L C-__ DATE l November 1961REVISED

ST._:LOUIS, MISSOURI ....

REVISED

added in Paragraphs 13-155 thru 13-157.

13-155. Yaw Data Converter

The Yaw Data Converter is a small compact unit consisting of transformers,

demodulators, relays and summing circuitry.

section of the capsule near the periscope.

13-156. Periscope Camera

The unit is mounted in the lower

(See Figure 13-8.)

The Periscope Camera used on Capsule No. 9 is the same as the Instrument

Camera except that the periscope camera is mounted inside the periscope. (Refer

to Paragraph 13-110. )

13-157. Blood Pressure Oscillograph

The blood pressure oscillograph consists of a motor timer and tape recorder.

The oscillograph also has a self-contained battery mounted with the recorder.

The battery is vented in the same manner as the capsule's main batteries. The

oscillograph operates at a speed of 8 inches per minute and is on continuous

from the time the recorder's power switch is turned on, prior to launch, until

it is turned off, after landing.

13-158. TEST CONFIGURATION CAPSULES NO. I0, 13 AND 16.

13-159. General

The Instrumentation on Capsules No. lO, 13 and 16 is the same as the Speci-

fication Compliance Capsule (Refer to Paragraphs 13-1 thru 13-110. ) (See Table

13-2 for commutator point assignments. )

MAC 231CL (27 APR 59)

Mercury Capsule

Documents

Transcript of Mercury Capsule