Propellant Actuated Devices

UNCLASSIFIED

AD NUMBER

AD872430

NEW LIMITATION CHANGE

TOApproved for public release, distributionunlimited

FROMDistribution authorized to U.S. Gov't.agencies and their contractors;Administrative/Operational Use; 15 JUN1969. Other requests shall be referred toFrankford Arsenal, Philadelphia, PA.

AUTHORITY

FA ltr 3 Sep 1971

THIS PAGE IS UNCLASSIFIED

!* a

IEP 65-6370-8 REV A

0 7

PROPELLANT ACTUATED DEVICES

ENGINEERING MANUALNIOTICE

This manual includes items which were developed to

perform at an upper, temperature of 160-F. Certifi-

cation is hereby made that these items also meet the

200*F enironmental requirements of IIL-C-259.1.

Details on this and information relating to the use

of items in specific applications will be furnished

on requeat to:

- Commanding Officer

Frankford Arsenal

A - >Attn: Propellant Actuated Devices Labs.

SMUFA-J 5400

Phila., Pa. 1915

, This document is subject to special export controls and each

transmittal to foreign governments or foreign nationals may

Alp- be made only with prior approval of the Commanding Officer,

, oFrankford Arsenal, Philadelph-a, Pa., Attn: SMUFA-J5000.

15 JUNE 1969

&L Amm

DISCLAIMER NOTICE

THIS DOCUMENT IS BEST QUALITYPRACTICABLE., THE.COPY FURNISHEDTO DTIC CONTAINED A SIGNIFICANTNUMBER OF PAGES WHICH DO NOTREPRODUCE LEGIBLY.

ENGINEERING MANUAL

FOR

PROPELLANT ACT ATED DEVICESNOTICE

This manual includes itemc which were developed toperform at an upper temperature of 1600?. Certifi-cation is hereby made that these items also meet the2000F environmental requirements uf ,±1-C-25918.Details on this and information relating to the use

of items in specific applications will 'oe furnishedon request to:

Commanding OfficerFrankford ArsenalAttn: Propellant Actuated Dev~iceso abs.

SMUFA-J5400Pbila., Pa. 19137

This document is subject to special eixport controls and eachtransmittal to foreign governments or foreLgn nationals may

g be made only with prior approial of the Coizaanding Officer,Frankford Arsenal, Philadelphia, Pa., Attn:: SMWFA;J5000.

15 JUNE 1969

ReprO(4uction for nonmilitary use of the Information or illustrations contained in this publication is .ot per-mitted without specific approval of the Issuing service. The ,,1icy for use of Classified Publicetions Isemtablished for the Air Force in AFR 205-1.

INSERT LATEST CHANGED PAGES. DESTROY SUPERSED7" PAGES.

SOFEFFECTIVE PAfGE I

TOTAL NUMBER OF PAGES IN THIS PUBLICATION IS 271 CONSISTING OF THE FOLLOWING:

Page No. Issue Page No. Issue Page No. Issue

*Titie ........ .15 April 1969 2-32 and 2-33 ....... .Original 5-3 and 5-4 ....... .OriginalIP

A .......... 15 April 1969 2-34 Blank ........ .. Original *5-5 thru 5-20 ... 15 April 1969........... 15 April 1960 *2-35 .......... .15 April 1969 'Title (Section VI) 15 April 1069

ii .......... .. 15 April 1969 2-36 and 2-37 ....... .Original "6-1 thru 6-8 .. . . 15 April 1969

*iii .......... .15 April 1969 2-38 Blank ........ .Original

lttic (Section I) . .. . Original 02-39 .......... 15 April 1969

1-1 ............. .. Original 2-40 and 2-41 ....... .Original

1-2 Blank ......... Original 2-42 Blank ........ Original

1-3 thru 1-17 ...... Original *2-43 ........... 15 April 1969

1-18 Blank ....... Original 2-44 and 2-45 ....... Original

1-19 and 1-20 ...... Original 2-46 Blank ......... Original

*1-21 thru 1-24... 15 April 1969 *2-47 ........... 15 April 1969

1-25 -h-u 1-2P ..... Original 2-48 and 2-49 ....... Original

litle (Section II) . . . Original 2-50 Blank ........ Original

2-1 ............... Original *2-51 ........... 15 April 1969

2-2 B!ank. .. .. .. .. Original 2-52. .. .. .. .. .. ... Original

02-3 ......... .. 15 April 1969 *2-53 .......... .15 April 1969

2-4 aad 2-5 ....... .Original 2-54 and 2-55 ....... .Original

2-6 Blank ........ .Origival 2-56 Blank ........ .Original

02-7 ........... 15 April 1969 *2-j.7 .......... 15 April 1969

2-8 and 2-9 ....... Original 2-58 and 2-59 ....... Original

2-10 Blank ....... Original *2-60 thru 2-62 ... 15 April 1969

*2-11 ......... 15 April 1969 *2-63 Blank ..... 15 April 1969

2-12 and 2-13 ...... Original Title (Section i1) .... Original

2-14 Blank ....... Origina, 3-1 ................ Original

*2-15 thru 2-17... 15 April 1969 3-2 Blank .......... Original

"2-18 Blank ... 15 April 1969 3-3 thru 3-29 ....... Original

"2-19 ......... 15 April 1969 3-30 Blank ........ Original

2-20 and 2-21 ...... Original 3-31 thru 3-38 ...... Original

2-22 Blank ....... Original *3-39 and 3-40 ... 15 April 1969

*2-23 .......... 15 April 1969 Title (Section IV) .... Original

2-24 and 2-25...... .Original 4-1 ................ Original

2-26 Blank ....... Original 4-2 Blank .......... Original

02-27 ......... 15 April 1969 $4-3 thru 4-100 , . .15 /1 il 1969

2-28 and 2-29 ...... Original *Title (Section V1 .15 April 1969

2-30 Blank ....... Original *5-1 ............ 15 April 1969

*2-31 .......... 15 April 1969 *5-2 Blank ...... 15 April 1969

The asterisR Indicates pages changed, added, or deleted by the current change.

A ,'

TABLE OF CONTENTS

Section Page Section Page

I REMOVER, AIRCRAFT CANOPY M8 ................ ... 3-27Introduction ......... 1-1 M9. ............. 3-31M1A3 ..... ............ 1-3 M10 ..... ............. 3-35M2A1 .............. .... 1-7 XM38 ..... ............ 3-39M3A ............... .. 1-11M4 ............... .... 1-15 IV INITIATOR, CARTRIDGEM5 ............... .... 1-19 ACTUATEDM8A1. ............... ... 1-21 Introduction .... ......... 4-1M9 ............... .... 1-25 M3A1C ............. .... 4-3

M3A2 ................ 4-511 THRUSTER, CARTRIDGE M4A1 (Delay) ........... 4-7

Introduction .......... .... 2-1 M6A1 (Delay) .......... ... 4-11M1A2 .. ................ 2-3 M8 . . . . . ....... . 4-13M2A2 .............. .... 2-7 M9. ........... 4-15M3A3 .............. .. 2-11 M10 (Delay) .......... 4-17M5A2............. 215 M12AD (Del4y) 4-19M6 ............. 2-19 M14 (Delay) 4-21M7 ............... .... 2-23 M15 (Delay) ....... .. 4-23M9 .. ............. .... 2-27 M 16 (Delay) ......... 4-25M1.................2-31 XM17(Delay)............4-27M13 ................ ... 2-35 XM18 (Delay) ........... 4-29M15 ................ .. 2-39 XM19 (Dciiy) ............ 4-31M16 ................ .... 2-43 XM20 (Delay) ............ 4-33M17 ................ .... 2-47 XM21 (Delay) .......... 4-35MIS.. . . ........... . . 2-51 XM22 (Delay) ............ 4-37M19 ............... ... 2-53 XM23 (Delay) ............ 4-39M20AL .............. ... 2-57 XM24 (Delay) ............ .4-41M25 ................ .... 2-60 XM25 (Delay) ............ 4-43

M26 (Delay) ............ 4-45III CATAPULT, AIRCRAFT M27 ................. 4-47

EJECTION SEAT M28 ................ ... 4-49Introduction .......... .... 3-1 M29 ................ ... 4-51MIAl. ............... ... 3-3 M30A1 (Delay) ........... 4-53M2 (Training) ... ........ 3-7 M31 (Delay) ......... 4-55

M3A1 ............... .. 3-11 M32A1 (Delay) ........... 4-571IX A I1,1'rtl ............ 3-15 M33 (Delay) ............. 4-59M5A1 .............. .. 3-19 M42 (Delay) ........... 4-61M6A1 (Training) .......... 3-23 M43A1 (Delay) ........... 4-63

TABLE OF CONTENTS (Continued)

Section Page Section Page

M44 (Delay) .... ......... 4-65 V CUTTER, POWDERM45A1 (Delay) ........... 4-67 ACTUATED

M49A1 (Delay) ............ 4-69 Introductin .... ......... 5-1

M51(Delay). . . . . . . . . 4-71 M8 ... ............ .... 5-3

M52 (Delay) ......... 4-73 M9 ..... ............. 5-5

M53 ..... ............. 4-75 XMIO. ..... ............ 5-7M54 (Delay) ......... 4-77 XM11... ........... 5-9X4 (Delay) .. . . ..... 4-79XM12 ..... ............ 5-1I

XM64 (Delay) ........ 4-81 M13 ................. 5-13M72(Delay).............4-81 M21 .... .............. 5-15

M80 ................. 4-83 M22 ................. 5-17

M6 ...... ............. 4-85 XM23 ............... 5-19M87 ..... ............. 4-87M88 (Delay) .... ......... 4-89 VI MISCELLANEOUS PADM89 (Delay) .... ......... 4-91 DEVICES

M98 ..... ............. 4-93 Release, Firing Pin, MIA1 . 6-1M99 .................. 4-95 Gas Generator, M17 ...... ... 6-3XM107 ................ 4-97 Electric Ignition Element, M21 . 6-5

XMllO (De1ay) ........ 4-99 Electric Ignition Element, M55 . 6-7

(S

*.

C'"

INTRODUCTION

I

The major purpose of this Engineering Manual is to provide technical personnel of in-dustries involved in design and provisions for emergency escape from extra-terrestrial vehicles,a convenient reference of basic design and performance characteristics of Propellant ActuatedDevices. Since the advent of high-speed jet aircraft generated the need for an automated meansof escape from aircraft, Frankford Arsenal has pioneered the design and development of P'o-pellant Actuated Devices; such as Catapults, initiators, Thrusters, Removers and RocketCatapults.

The major consideration in the design, development and production of the dev'icesdescribed in this Manual was to attain an optimum Reliability Design Goal. Fundamental to thetheory of reliability is the relationship between total and component reliabilities. On thisbasis, total reliability can be no greater than the last reliable component. To attain this goal,the devices listed in this Manual undergo stringent quality control tests and analysis for thepropellant, pyrotechnic and hardware components, and finally the complete loaded and as-sembled device.

3i0

Proplaont Actuated Devices

Removers

A

SECTION I

A 9 a

Propellant Actuvted Devices

Removers

INTRODUCTION~Description:

The remover is a two or three tube telescoping device, containing an explosive compo.nent, designed to iettison the canopy from high-speed aircraft prior to the ejection of crevrmenfrom disabled aircraft.

The Removers are of two basic types, i.e., mechanical and gas actuated. A third typeis the electrlc-mochanical ba!liaic types which permits normal opening and closing of thecanopy as well as emergency jettisoning of the canopy.

ia

1-1/1-2

Propellant Actuated Devkces

Removers

REMOVER, AIRCRAFT CANOPY, M1A3

The MIA3 Remover is a three-tube, telescoping ejection device containing an explosivecarttidge, designed to forcibly jettison the canopy from high-speed aircraft to provide a safepath for the ejection of the crewman from disabled aircraft.

The remover is approximately 16 inches long and 1.93 inches in diameter. The removerhas the MlAl Firing Pin Release attat hed. The firing p.n release, which when functioned by the

* J M3Al Initiator, releases a spring loaded firing pin in the remover. The spring propels the firingpin which strikes and detonates the primer, thereby igniting the black powder and propellant inthe M29A2 Cartridge. The remover thrust which is developed from the expanding gases of theburning propellant, forces the inside and telescoping tubes to move simultaneously until theshoulder uf the telescoping tube comes in contact with the telescoping tube stop, thus restrict-ing its movement. The continuous moving head assembly and inside tube are jettisoned with theaircraft canopy. The base, outsid, and telescoping tubes, and telescoping tube stop remain withthe aircraft.

PRINCIPAL CHARACTERISTICS

troke 23.3 inchesWeight (total assy) 2.1 poundsPropefled Weight 300 1poundsTemperature Limits -65*F to +160'F

Velocity, min (at 70°F) 20.0 fpsThrust, min (at 70°F) 2800poundsStroke Time (at 70'F) 0.135 secondsFiring Method Gas Actuation of the MIA1

Firing Pin Release, whichreleases M1A3 P.emoverFiring Pin

1-3

Propellant Actuated Devices

Remover, Aircraft Canopy, M1A3

.Y,4

CROSS-SECTION DRAWING

Component Component

A Spring, Firing Pin G Base

B Pin, Safety H Tube, Outside and Pellet Assembly

C Wire, Locking, .062" x 8" I Tube, Telescoping

D Cartridge, Aircraft Canopy J Tube, Inside and Pellet AssemblyRemover, M29A2

F" SaK Stop, Telescoping TubeE~ Seal, Inside

L Head, FiringF Seal, Telescoping

MI Pin, Firing

A 16.00 MAX

.36,I --. 257 DIA 4 HOLES --- .21 I'oou {"

+1 1.932-.0 0IA

L 2.500 B C 2.20-.01DIA

ENVELOPE DRAWING

S 1.4

I


Remover, Aircraft Canopy, MIA3

-PREBSURE-TNAVEL RELATIONSHIP STANDARD PROPELLED WEPINT:UNtO LS

7 IF

0j 70 OF18202

1RA0L0N0E

TRAVEL-INCHES

VEOI -RVE EAINHPSANADPOELE E H 0 I

30---- 700

42


Remover, Aircraft Canopy, MIA3

Is

0 6C50 IF40 90 4 70 6 0 10 3 0 0 F I

0 Io 20 30 40 so0 s 'M 7 0 0 90 P00 110 20 130Tli- MIISECONDS

0~ I~

31.6 ---L-LU

4 _ _ _ _F

Propollant Actuated Devices

Removers

REMOVER, AIRCRAFT CANOPY M2A1

The M2A1 Remover is a two-tube, telescoping ejection device containing an explosivecartridge, designed to forcibly jettison the canopy from high-speed aircraft to provide a safepath for the ejection of the crewman from disabled aircraft.

The remover is approximately 31 inches long and 2.19 inches in diameter. The removeris actuated by removal of the safety locking pin first and the manual rotation of the searthrough a pulley system connected to a lever an the pilot's seat. Rotation of the sear releasesa spring loaded firing pin and unlocks the inside tube. 1 he firing pin is propelled forward anddetonates the primer, thereby igniting the black powder and propellant in the M31A1 Cartridge.The remover thrust which is developed from the expanding gases of the burning propellant,forces the inside tube outward. The Llock assembly and inside tube are jettisoned with aircraftcanopy. The cap and outside tube remain with the aircraft.


Stroke 26.0 inchesWeight 4.4 poundsPropelled Weight 300 poundsTemperature Limits -65' to + 160OFVelocity, min (at 70 0F) 20.5 fpsThrust, min (at 70'F) 2600 poundsStroke Time (at 70 0 F) 0.150 secondsFiring Method Mechanical Actuation

7

tv&


Removmr Aircraft Canopy, M2A1


Component Component

A Pin, Locking I Cartridge, Aircraft CanopyB Tube, Bearing Remover, M31AIC Spring, Firing Pin J Pin, FiringD Sleeve K SearE Tube, Inner L SpringF Tube, Outside M Safety Pin AssemblyG Cap N Block AssemblyH Ring, Retaining

0S

DIA

~ENVELOPE DRAWING

1 ... . . . ... . . . . .

9.2 .7 - Z


Remover, Aircraft Canopy, M2AJ

THRUST-TIME RELATIONSHIPSTANDARD PROPELLED WEIGHT 300 LB

0100

, , .o o o H -F I i l

-0)

0 20 I0 soI 100 120 140 ISO

TIME-MILLISECONDS '-

VELOCITY-TIME RELATIONSHIP

STANDARD PROPELLED WEIGHT*: 300 LB

II-- ----

5 i t -i

0 20 0 SO 0 t1O 120 140 160TIME-MILLIECONDS

1.9



THRUST-TRAVEL RELATIONSHIP

STANDARD PROPELLED WEIGHT 300 LBF I

00

W3000 --J

0 -. I .I I I--I -i i I I I I I I iI I I I

,-2000 -- -0?~

1000 j- ~A~0

I I I I I I I I I 1 1- " F

I SEARTI I

0 4 a 12 16 20 24 28 32TRAVEL-INCHES

- VELOCITY-TRAVEL RELATIONSHIP

--- STANDARD PROPELLED WEIGHT: 300 L8

80-

U. 25:

t 2- I------.- - - - - - TUBE'---"SSEARATION

o i l i l i i ! l l I

1 -1 -- 1- _A t_ _ 1A 1L

0 4 8 $2 16 20 24 28 32TRAVEL-INCHES

I: ! , VLOrVTRVL E1.O10I - -


Removors

REMOVER, AIRCRAFT CANOPY, M3A1

The M3A1 Remover is a two-tube ejection device containing an explosive cartridge, de-signed to forcibly jettison the canopy from high-speed aircraft to provide a safe path for theejection of the crewman from disabled aircraft.

The remover is approximately 31 inches long and 2.19 inches in diameter. The removerhas an initiator attached by a length of flexible hose. When the initiator is functioned, the gasdeveloped flows through the flexible hose exerting force against the remover firing pin. Thefiring pin is propelled forward and strikes and detonates the primer, thereby igniting the blackpewder and propellant in the M31AI Carcridge. The remover is unlocked by cam action as thefiring pin moves toward the primer, unlocking the block assembly and inside tube. The removerthrust which is developed from the expanding gases of the burning propellant, forces the insidetube outwa-d The block assembly and inside tube are jettisoned with the aircraft nopy. Thecap and outside tube remain with the aircraft.


Stroke 26.0 inchesWeight (total assy) 4.4 poundsPropelled Weight 300 poundsTemperature Limits -650 to + 1601FVelocity, min (at 700F) 20.5 fpsThrust, min (at 700F) 2600 poundsStroke Time (at 70*F) 0.150 secondsFiring Method Gas Actuation

{

~1

Prop)ellant Actuated Devices

Remover Aircraft Canopy, M3A1

00 G


Component Component

A Cap H rube, Outside and Pellet AssemblyB Plug I Tube, Insde and Pellet AssemblyC Screw, Cap, Socket Head, Self Locking J Tube, Bearing and Pellet Assembly

(Shown 900Out ef Position) K Seal, FixedD Pin, Shear L Ring, Stop and Pellet AssemblyE Latch M Pin, Firing

Pipe Plug (for shipping only) N BlockF Seal, Tamper Proof 0 Cartridge, Aircraft CanopyG "0" Ring Remover, M31A1

30.033 MAX29.983 MIN

3.157 MAX1.025 MAX 3.101 MIN

39 .974 MIN 1.866 MAX_. .959 MAX

: 33N *917 MIN

°14 .380 +.005 DIA

.350 +.005 2.187-.005 DA 2.328-.010 - 1.25-.01

F-2.34 .01 DIA.

Of 3E M1

ENVELOPE DRAWING

1-1.2

-----



THRUST-TIME RELATIONSHIPSTANDARD PROPELLED WEIGHT:300 LB

4000 I I.

-a3 0 0 0

I _ __

0 - 4 01 8 1. . 120 1

IT I- ILIoSOFNDS

STANDARD PROPELLE-: WEG: :o LB

1000..i -- ....-- -- -"

11.1

I/ IIT I

0 20 40 60 so 100 120 140 160

TIME- MILLISECONDS

- VELOCITY-TIME RELATIONSHIP--

-i :, STANDARD PROPELLED WEIGHT: 'i00 LB

1 1 F-: I F T F

0 20 40 60 80 100 120 140 160

TIMt--MILLISECOWIS

1.1

Propellant Actuated D'Acas

Remover, Aircrft Canopy, M3A1

THRUST-TRAVEL RELATIONSHIP

STANDARD PROPELLED WEIGHT: 300 LB

4000 " I I

-I - - - i-- - - - - - - - -

.0I

UUS

I '- - , a a .j

I000 ± I 1 F0E IF IT ON

0 4 8 12 16 20 24 28 32TRAVEL-INCHES

VELOCITY-TRAVEL RELATIONSHIP

STANDARD PROPELLED WEIGHT: 300 LB

25-

?0 TUSEo - -- - - ---- 8PARATION

I I I -1 1 -1 t II I

0 4 8 12 16 20 24 26 32TRAVEL- INCHES

.. ....

j.. .

Jl . .


Removers

REMOVER, AIRCRAFT CANOPY, M4

The M4 Remover is a three-tube, zelescoping ejection device containing an explosivecartridge, designed to forcibly jettison the canopy from high-speed ,ircraft to provide a safepath for the ejection of the crewman from disabled aircra.i.

The remover is approximately 14.67 inches long and 1.93 inches in diameter. The re-mover has an initiatci attached by a I :ngth of flexible hose. When the initiator is functiontd,the gas developed flows through the fl:xible hose exerting force against tl.e remover firing pin.

The firing pin is propelled forward ani strikes and detonates t1,2 primer, thereby igniting theblack powder and propellant in the M29A2 Cartrdge. During the forward motion of the firing pin,the locking keys slide inward, thus unlocking the remover. The remover thrust which is develop-ed from the expanding gases of zhe burning propellant, forces the outside tube to travel forward

unti! the washer engages the shoulder on the telescoping tube. The telescoping tube is thenpulled forward by the outer tube until it is free of the inside tube, and is jettisoned with thecanopy. The inside tube and firing head assembly remain with the aircraft.


Stroke 19.0 inchesWeight (total assy.) 3.84 poundsPropelled Weight 300 poundsTemperature Limits -65' to + 160°FVelocity, min (at 70*F) 20 fpsThrust, min (at 70'F) 2800 poundsStroke Time (at 70°F) 0.114 seconds

Firing Method Gas Actuation

1.4.


Ren,ovar, Aircraft Canopy, M4

G A

iI

CROSS-SECTION DkAWING

Component Component

A Pia, Sl.car (Shown 90' ou. of positien) L Stop, Firing PinB Ring, Retaining M WasherC Ring, Sealing N Key, Locking (2)D Tube, Outside o SleeveE Tube, Telesceping F C "O" RingF Tube, Inside Q Pin, FiringG Ring, SeeUing R Head, FiringH CGasket S Screw, Set (Shown 90 "out of position)J RinS, Sealing T Shipping PlugK Cartridge, Aircraft Canopy

Remover, M120

14.-5 MA

.. 63

1.93 DXA. V

1.00-,01 .257 2.125 DM.375 J 4 HOLES _

DMO 13.919 3.00 DIA.

N13.D49

ENVELOPE DRAWING

1.16


Remover, Aircraft Canopy, M4

THRUST-TIME RELAMIONSHIPSTANDARD PROPELLED WEIGHT 300 LB

4000 v0

0 5 10 15 20 25 30 35 40 45 50 55 60 65 70 75 S0 85 So q3 I00

"1ME-MILISECONDS

VELOCITY-TIMEr RELAT03f HIP

STWOAKO PROK"FO WEIUHT 300 1.6

, 1.17/1.18

*65


Removers

REMOVER, AIRCRAFT CANOPY, M5

The M5 Remover is a three-tube, telescoping ejection device containing an explosivecartridge, designed to forcibly jettison the canopy from high speed aircraft to provide a safepath for the ejection of the crewman from disabled aircraft.

" The remover is approximately 14.67 inches long and 1.93 inches in diameter. The re-mover has an initiator attached by a length of flexible hose. When the initiator is functioned,the gas developed flows through the flexible hose exerting force against the remover firing pin.The firing pin is propelled forward, strikes and detonates the primer, thereby igniting the blzckpowder and propellant in the M120 Cartridge. During the forward motion of the firing pin, thelocking keys slide inward, thus unlocking the remover. The remover thrust which is developedfrom the expanding gases of the burning propellant, forces the outside tube to travel forwarduntil the washer engages the shoulder on the telescoping tube. The telescoping tube is thenpulled forward by the outer tube until it is free of the inside tube and is jettisoned with thecanopy. The inside tube and firing head assembly remain with the aircraft.


Stroke 19.0 inchesWeight (total assy) 3.84 poundsPropelled Weight 1000 poundsTemperature Limits -65* to + 1601FVelocity, min (at 70'F) 10 fpsThrust, min (at 700 F) 4500 poundsFiring Method Gas Actuation

.

i : 1.19




Component Component

A Pin, Shear (Shown 900 out of position) L Stop, Firing PinB Rzrtg, Retaining M WasherC Ring, Sealing N Key, Locking (2)D Tube, Outside 0 SleeveE Trube, Telescoping P "0"V RingF Tube, Inside Q Pin, FiringG Ring, Sealing R Head, FiringH Caske S Screw, Set (Shown 900 out of position)

J Ring, Sealing T Shipping PlugK Cartridge, Aircraft Canop.>

Remover, M120

1 -. 461.5 A

L1.001-1 .257 DIA4 HOLES

13.919j 13.849

ENVELOPE DRAWING


Remnovers

REMOVER, AIRCRAFT CANOPY, 8AI

The M8A1 Remover is an electro-mechanical-ballistic, two tube telescoping device

designed to raise and lower the F106A aircraft canopy under normal conditions durinb groundoperation and to jettison the canopy prior to ejection of the pilot from the aircraft during

emergency escape in flight or on the ground.

The electro-mechanical portion of the remover consists of a reversible, intermittent

duty 26 volt direct curren- motor, a gear transmission with an indexing mechanism and torquelimit switch, a solenoid-operated clutch with an integral ratchet mechanism, and a ball-bearingscrew assembiy which is coaxial with the remover ballistic chamber. Raising and lowering theaircraft canopy is accomplished by electrically energizing the remover motor which transmitsrotary motion through the gear system to the clutch. As the ciutch rotates the ball-bearingscrew turn within a non-rotating ball nut, which is attached to the inside tube of the remover.Rotation ofthe ball-bearing screw drives the remover inside tube outward, raising the canopy;or inward, lowering the canopy, when the motor is electrically reversed. As the inside tubeextends 9.38 inches, power to the motor is shut off automatically by an extension limit switchwhich is actuated by the shoulder on the inside tube through a plunger. Upon retracting theremover inside tube and canopy, a torque li mit switch de-energizes the motor when the ca-iopyis rescrained by the fuselage and a tension load of 1000 to 1450 pounds is imposed on the ball-bearing screw assembly. This cinch-down load ensures that the canopy is properly seated onthe fuselage for locking by the pilot. A safety feature is incorporated in the clutch mechanismwhich prevents the canopy dropping to the closed position should the clutch inadvertentlydisengage during any position of remover stroke. The remover in the retracted position isapproximately 20.25 itches long between mounting points.

The ballistic portion of the remover is used to jettison the canopy prior to ejectionof the pilot from the disabled aircraft. The remover has an initiator attached by a length offlexible hose. When the initiator is functioned, the gas developed flows through the hose,exerting force against the remover firing pin. The firing pin is propelled forward and strikesand detonates the cartridge primer, thereby igniting the black powder and propellant in theM150 Cartridge. Propellant gas from the cartridge expands through the opening in the adapterhousing where it acts against the ballistic lock components and the inside tube. With theincrease in pressure the ballistic lock unlocks the inside tube and the gas pressure forcesthe inside tube outward. The inside tube which is pin-mounted to the canopy, clears the out-side tube and jettisons the canopy, clear of the aircraft.

1-21

Prupellant Actuated Devices

Removers

PRINCIPAL CHARACTERISTICS (MSA1 Contd)

f Weight (Total Assy) 22.5 pounds

Temperature Lmits -650 F to 2000 F

Electro-Mechanical

Electric Power 28 Volt D.C. SystemOperating Voltage Limit 18 to 29 VoltsOperating Loads

Overload 250 pounds (tension) to680 pounds (compression)

Normal load 380 pounds (compression)Overload 430 poinds (tension) to

940 pounds (tension)

Extension or Retraction Time 15 sec max; 5 sec. min.Clutch Engage Time, max. 0.500 sec.Clutch Disengage Time, max. 0.500 sec.Cinch-Down Load 1000 to 1450 poundsStroke 8.38 to 9.38 inches

Ballistic

Stroke 12.0 inchesPropelled Weight 350 poundsVelocity (at 70° F) 24.0 fpsPeak Thrust (at 700 F) 5400 pounds

Firing Method Gas ActuationStroke Time (at 700 F) 0.150 sec.

11.22I___


Rem~ver, Aircraft Canopy, M8A1

M

0

B/

Ap

CROSS-SECTION DRAWINGComponent Compont

A Clamp M Plug, ShippingB Washer N Pin, ShearC 5-Splice, Electric 0 HeadD Mo~tor P Cartridge, Aircraft Canopy Remover, M150E Cable Assembly Q AdapterF Screw R PinG Grommet S Ring, ShearH Cover T Tube, Outside, AssyI R ing U Tube, Inside, AssyJ "0"' Ring V HousingK Screw, Shear W 9-Splice, ElectricL Pin, Firing X Gear Box Assembly

C.070

J . i S R M Afe zG -. 0 1 R 1

EYT9 Wao9EWO N0

-3 0SZ 7NVinP

"'O'N r1N23


Remover, Aircraft Canopy, MPAI

THRUST-TIME RELATIONSHIP

STANDARD PROPEL' ED WEIGHT 350 LB

F- F

-65* F

o404060010 2 10 10 8 0

0 20 40 60 so 100 tO 140 ISO ISO 200TIME-MILLIIECONDS

41EOIYTM ELTOSISTNDR PRPELD.EGH 50L

_______________________________________5____


Remov4,rs

REMOVER, AIRCRAFT CANOPY M9

The M9 Remover is an electro-mechanical ballistic, three tube telescoping device design-ed to raise and lower the F106B au..taft canopy under normal conditions during ground operationand to jettison the canopy prior to ejection of the pilot from the aircraft during emergency ebzapein flight or on the ground.

The electro-mechanical portion of the remover consists of a reversible, intermittent duty,26 volt direct current motor, an electronic speed control box, a gear trensmission, a clutch mech-anism with an integral ratchet mechanism, mechanical clutch disengage mechanism, and a doubleball-bearing screw assembly which is coastal with the remover ballistic chamber. Raising andlowering the aircraft canopy is accomplished by electrically energizing the remover motor whichtransmit rotary motion through the gear system to the mechanically operated clutch. As the clutchrotates the ball-bearing screw turns within a non-rotating ball nut, which is attached to the insidetube of the remover through a bearing. Rotation of the ball-bearing screw drives the remover insidetubes outward, ra;sing the canopy; or inward, lowering the canopy, when the motor is electricallyreversed. As the inside tcbes extend approximately 45.86 inches, power to the motor is shut offautomatically by an extension limit switch which is cam actuated. Upon retracting the removerinside tubes and canopy, a torque limit switch de-energizes the motor when the canopy is estrainedby the fuselage and a tension load of 400 to 500 pounds is imposed on the ball-bearing screw assem-bly. This cinch-down load insures that the canopy is properly seated on the fuselage for lackingby the pilot. The electronic speed control box which is attached to the adapter housing is used toreduce the motor speed on the retraction stroke. A safety feature is incorporated in the clutchmechanism which prevents the canopy dropping to the closed position should the clutch inadvert-ently disengage during any position of remover stroke. The remover in the retracted position isapproximately 23.51 inches long between mounting points.

The ballistic portion of the remover is used to jettison the canopy prior to ejection of thepilot from the disabled aircraft. The remover has an initiator attached by a length of flexible hose.When the initiator is functioned, the gas developed flows through the hose, exerting force againstthe remover firing pin. The firing pin is propelled forward and strikes and detonates the cartridgeprimer, theLeby igniting the black powder and propellant in the M151 Cartridge. Propellant gas fromthe cartridge expands through the opening in the adapter housing where it acts against the ball-bearing screw assembly and the inside tube. With the increase in pressure the spring pin whichsecures the ball-bearing screw assembly to the bearing housing shears, and the continued produc-

tion of gas pressure forces the inside tube and ball-bearing assembly outward simultaneously. Theinside tube and ball-bearing assembly which is pin mounted to the canopy, clear the outside tubeand jettisons the canopy clear of the a-rcMft.


Weight (Total Assy) 35 porndsTemperature Limits -65 0F to 200OF

-41.25

Propellant Actuated Devicer,

Removers

PRINCIPAL CHARACTERISTICS (M9 Cont'd)

Electro-Mechanical

Electric Power 28 Volt D.C. SystemOperating Voltage Limit 18 to 29 Volts rOperating Loads

Overload 315 pounds (comipression) to398 pounds (compression)

Normal load 288 pounds (compression) to228 pounds (compression)

Overload 196 pounds (tension) to142 pounds (tension)

Extension or Retraction Time 20 sec. max; 10 sec. min.Clutch Disengage Load 7 to 11 poundsCinch-Down Load 400 to 500 poundsStroke 45.86 inches

Ballistic

Stroke 27.0 inchesPropelled Weight 300 poundsVelocity (at 70 0 F) 33.0 fps

Peak Thrust (at 701F) 6000 poundFiring Method Gas ActuationStroke Time (at 70 0F) 0.090 sec.

1-26



CRSHETO SERAWING-

CompnentCompnen

FGa ompAssenbyt Cartridenict Cnp

G Housing, CltBelease Cal Remou, hipin

H TubeprngK a, BallisticChme

MEVEOP DRAWINGFM

41-2


Remover, Aircraft Ctmopy, M9

THRUST-TIME RELATIONSHIPT

STANDARD PROPELLED WEIGHT 300 L83

WOO.

22

~~T___0 to 20 30 40 60 60 70 so0 90 0

TIME-MILLISECONDS

VELOCiTY-TIME RELATIONSHIPSTANDARD PROPELLED WEIGHT 300 LB

* 40

:uziniz i: :IIL 2 t~lJi~ti iLLLL FF0 7 0 9 O

TIME-MILLISECOND

1.28o


Thrusters

SECTION 11

THRUSTERS


Thrusters

(INTRODUCTION

Description:A thruster is a component part of an aircraft escape system, which is used to accom-

plish a certain task prior to implementing the final phases of escape procedure, for crewmanfrom a disabled aircraft. The basic parts of a thruster consist of a gas operated firing mechanism,cartridge, chamber and a piston. The main purpose of a thruster is to impart a thrust to a know.load or oppose a for-e through a given travel (stroke).

Each thruster is provided with an initial lock mechanism for the piston. This mechanismis released only when the cartridge functions. Thrusters have been developed with piston strokesbetween 1-1/2 and 13 inches. Unlike cor:eiponding parts of catapults and removers, the thrusterpiston does not separate from the thruster at the end of the piston stroke. Thus the thruster ita closed system.

Buffer or damper mechanisms are used in conjunction with thrusters to restrict thevelocity and acceleration of the propelled load because of limitations on aircraft structure andhuman physiology. The rate of applicaLion of thrust and maximum thrust are specified when athruster is used to positicn a crewman.

Operation:All thrusters are triggered by gas pressure supplied from another cartridge actuated

device. The firing pin of the thruster is held in position with a "shear pin". When gas pressureis supplied, the force applied on the firing pin will shear the "shear pin" and propel the firingpin against a cartridge containing a percussion-sensitive primer. The primer ignites the blackpowder and propellant contained in the cartridge. The cartridge ruptures at the itnsupportedarea, and propellant gas fills the thruster chamber and exerts a force on the face of the piston.The initial piston motion unlocks the thruster and a force is applied through the piston to theload, sutting it in motion. In some thrusters, there is a final lock to hold the piston in theextended position.

2-1/2.2. . - - ,.--


Thrusters

M1IA2 THRUSTER

The M1A2 Thruster was developed to either jettison a hatch or unltck a tail turret.In both applications, the thruster is required to complete a 2 inch stroke against a varying force.The opposing force distance is represented by several shear pins located with respect to initialpiston position. The diameter of each pin was selected so that the shear force at a givendistance is equal to the corresponding maximum opposing force in the above applications.Thruster performance data using this test system is presented below.

The thruster is cylindrical in shape, approximately 9-1/2 inches long and 1-13/16inches in diameter. The piston is initially locked in the chamber with 4 keys and is capableof withstanding a tensile load of 2000 pounds, without separation or mechanical failure.


Average Peak Thrust 6900 lbs.Coopleted Stroke 2 inches, min.Average Stroke Time 0.009 secondsAssembled Weight 3.2 lbs.Propelled Mass, Horizontal 20 lbs.Firing Method Propellant GasTemperature Limits -65 0 F to +160 0FRestraining Force 1000 lbs. @ .00 in. stroke;

6000 lbs. @ .25 in. strokeForce Required to Unlock Initial Lock 60 lbs.Actuation Force 750 psi, min.

2.3


Thruster, Cerfridge Actuated, M1A2

/RN-

CROSS-SECTION IPRAWING

Component Component

A Head X Spring, Piston Locking

B Pin, Firing L Body

C "0" Ring M Plug, Piston

D Cartridge, CAD, M42 N Ret-iiner, Cartridge

E "0,' Ring 0 Trunnion

F Piston P "0" Ring

G Key Q Guide, Firing Pin

H Sleeve, End R Pin, Shear

I Screw, Cap, Socket Head S Washer, LockJ *1Qp Ring

0

8.0-0.02o

f~ 0

a or

.41T4~I~ LI24 1 .140

0 0

N

ij 2.4 ENVELOPE DRAWING-

Propellcof ActuatoO~ Devices

Thruster, Cartridge Actuated, MIA2

-1+1I:THUT-IERLTOSI

20PUDWIH RPLE OINAL

4 LSEAR PNS

I

2-5/2-6


Thrusters

M2A2 THRUSTER

The M2A2 Thruster is a component part of an aircraft escape system whose purpose isto position the seat in an aircraft prior to ejection of the crewman. This device was designed tobe used with a damper supplied by the airframe manufacturer. The thruster is required to com-plete a 5.7 inch stroke against an opposing force. The opposing force represents an approvedejection seat that must be moved either upward or downward with a velocity that does not exceed12 feet per second.

The thruster is cylindrical in shape, approximately 13.7 inches long and 1-7/8 inchesin diameter. The piston is initially locked in the chamber with 4 keys and is capable of with-standing a tensile load of 2000 pounds without separation or mechanical failure. The thrusteralso has a final lock which holds the piston in the extended position and is capable of with-standing an 11,000 pound compressive load without unlocking.

The damper used with the M2A2 thruster is to control the acceleration of the propelled weight to limits consistent with human physiology limits and/or restrict the finalvelocity so that the impact does nor damage the aircraft structure.


Average Peak Thrust w/Seat in HorizontalPosition @ 70OF 6170 lbs.

Completed Stroke 5.7 inchesVelocity, Maximum 12 ft/secAssembled Weight 4.0 lbs.Propelled Mass, Horizontal 300 lbs.Firing Method Propellant GasTemperature Limits -651F to +165 0FAverage Stroke Time w/Seat in Horizontal

Position @ 70OF .410 secondsForce Required to Unlock Initial Lock 80 lbsActuation Force 750 psi, min.

2-

2.7

Thruster, Cartridge Actuated, M2A2


Component Component

A Pin, Shear J S :ew, Cap, Socket Head

B Trunnion K Key

C "O" Ring L Piston And Plug Assembly

D Body M Head

E Spring, Piston Locking N Ring, Holding

F Ring, Snap 0 Cartridge, CAD, M43

G "0" Ring P "O" RingH Washer Q Pin, Firing

I Sleeve, End

~x

.-.8 UNF-2A-

-c _ _ _

12.771 MAX.

gENVELOPE DRAWING

2-8



THUS-IME REILAIONSHI

4%,0

0 40 s0 120 ISO 200 240 20 320 360 400 440 40(IS .MILLISECONIDS

THUTTM RLTOSI

30PON WEGT OIZNA

COMPRESION AMPERORIFIE..122DIA0

Vwoo

4 i,


Thrusters

M3A3 THRUSTER

The M3A3 Thruster is a component part o: an aircraft escape system whose purpose isto release the control column stowage spring and supply sufficient energy to operate the seatactuator disconnect. The thruster is required to complete a 1-1/2 inch stroke against an opposingforce and supply 600 psi pressure, minimum, at the end of a 4 foot length of hose. The opposingforce is represeited by a 550 pound load that must be propelled vertically with sufficient forceso that the load continues to move after the piston reaches the end of its stroke. Thruster per-formance data using this test system is presented below.

,:he thruster is cylindrical in shape, approximately 9 inches log and 1-5/64 inches indiameter. The piston is initially locked in the chamber with 3 keys and is capable of withstandinga tensile load of 800 pounds, without separation or mechanical failure.


Average Peak Thrust Under Normal Load @ 70°F 1660 lhs.Completed Stroke 1-1/2 inches, min.Assembled We:, it 1.0 lb.Propelled Mass, Vertical 550 lbs.Firing Method Propellant GasTemperature Limits -65°F to +165 0 FBy-Pass Pressure P 70°F Under Normal Load at the

End of 4 Ft Length of # 4 Hose 600 psi, min.Average Stroke Tima .090 secondsForce Required to Unlock Initial Lock 20 lbs.Actuation Force 750 psi, min.

2.11



13 F


Component Component

A Trunnion J Sleeve, End

B "0" Ring K "0 Ring

C Retainer, Cartridge L Rod, Piston

D Body M Cartridge, M44A1

E "0"v Ring N Pin, Firing

F Cap, End 0 Screw, Set, Socket

G Key P Pin, Shear

H "0" Ring Q Breech

I Spring, Piston Locking

'-50 D -.002

-1.07 -.01 DIA 040I - _ _ _ 24NF 3~

6.555 MAX7.W07 MAX

I. &275 MAX

ENVELOPE DRAWING

2.12


Thruster, Cartridgo Actuated, M3A3

PEAK BY -PASS PRESSUREVS HOSE LENGTH

*t TEVMATURE -65*Fa. PROPELLED WEIGIT,

VERTICALLY, 550 L83

1500 HOSE MS287414

1000-

500 .

0 I 2 3 4 5 6 7 a 9 10 11 12HOSW LENGTH, FEET

THRUST-TIME RELATIONSHIP550 POUND WEIGHT

_J ImPROPELLED VERTICALLY UPWARD

2000

;.500 -

JI4.

4000

500

0 10 to so 40 50 60 70 s0 90 t0o 010 120

2.13/2.14

Propellant Actu(.ted Devices

Thrusters

M5A2 THRUSTER

The M5A2 Thruster is a component part of an aircraft escare systcm whose purpose is

to jettison the tail turret or to be used in v-rious aircraft canopy release systems. The thruster

is required to complete a 5 inch stroke against an opposing force. The opposing force is repre-

sented by a 500 pound carriage that must be propelled horizontally, after an initial restraining

force of 4000 pounds is ov. rcome. The initial restraining force is represented by a shear pin

1, ated at zero inches of stroke. Thruster performance data using this test system is presentedbelow.

The thruster is cylindrical in shape approximately 12.6 inches long and 1.4 inch in

diameter. The piston is initially locked in the chamber with 4 keys and is capable of with-standiag a tensile load of 2000 pounds without separation or mechanical failure.


Average Peak Thrust Under NormalLoad @ 70°F 6670 lbs.

Completed Stroke 5.0 inchesAverage Stroke Time Under Normal

Load @ 70'F .075 seconds

Assembled Weight 3.6 lbs.Propel',, Mass, Horizontal 500 lbs.Firing Method Propellant GasTemper.ture Limits --65'CF to + 165'FRestraining Forces 4000 lbs. @ .0 inches of stroke

1000 lbs. @ .5 inches of strokeActuation Force 750 psi, min.

2.15

VI




Component Component

A Head K Screw, Buffer

B "0" Ring L Key

C "0" Ring M Piston

D Cartridge, M73 N Trunnion

E "0" Ring 0 Retainer, Carridge

F Body P Pin, Firing

G Spring, Piston Locking Q Pin, Shear

11 "0"f Ring R Guide, Firing Pin

1 "0" Ring S Plug, Shipping

JSleeve, End T Cap, Shipping

_______________ 4.50

4.03Z

I ~ 01 01 N F2_ _ __

O) ..L . or

2.16 ENVELOPE DRAWING

2.1



THUTIME REILSTCONSHI

51 ON EGH RPLE HRZNAL

IA

4,000.11/I.I8


Thrusters

M6 THRUSTER

The M6 Thruster is a component part of an aircraft escape system whose purpose is toposition the gun sighting equipment prior to implementing the escape procedure from the aircraft.The thruster is required to complete a 1-1/2 inch stroke against an opposing force. The opposingforce is represented by a 60 pound weight that must be propelled horizontally, after an initialrestraining force of 400 pounds is overcome. The initial restraining force is a shear pin locatedat zero inches of stroke.

The thruster is cylindrical in shape, approximately 11.73 inches long and 1.07 inchesin diameter. The piston is initially locked in the chamber with 3 balls and is capable of with-standing a tensile load of 250 pounds, without separation or mechanical failure.


Average Peak Thrust Under Load @ 70°F 1100 lbs.Completed Stroke 1.5 in.Assembled Weight 1.0 lbs.Propelled Mass, Horizontal 60 lbs.Firing Method Propellant GasTemperature Limits -65°F to +165'FRestraining Force 400 lbs.Actuation Force 750 psi, min.

2.19

-C..',


Thruster, Cartridge Actuated, M6


Component Component

A Pin, Shear H Ball

B Screw, Socket, Set 1 "0" Ring

C Trunnion j Cartridge, Thruster, M67

D Body K Pin, Firing

E Piston L "Off Ring

F Spring, Piston Locking M Breech

G Sleeve, End

[2~.50-002 DIA

r~1072 DIA MAX, F- CI0A.

1.MA X

lISIS10,077 MAX

ENVELOPE DRAWING

2.20



100 tow w

AA

I 1U.

0 0. I. L.5 >.

Af - ---L -- -

01 00-YIA PERFORMA0CE-0IME CURVES

B- TYPICAL PERFORMNC- aVEURE

2.A(~2

- - - - - -


Thrusters

M7 THRUSTER

The M7 Thruster is a component part of an aircraft escape system whose purpose is tounlock and/or open a hatc'h. The thruster is required to complete a 2-1/2 inch stroke againstan opposing force. The opposing force is represented by an 11.6 pound weight that must bepropelled horizontally against constant 500 pound restraining force, which is simulated withan air cylinder.

The thruster is cylindrical in shape, approximately 10.2 inches long and 1.1 inchesin diameter. The piston is initially locked in the'chamber with 2 keys and is capable of with-standing a tensile load of 500 lbs., without separation or mechanical failure.


Average Peak Thrust Under Normal Load @ 700F 1600 lbs.Completed Stroke 2.5 inchesAverage Stroke Time .070 secondsAssembled Weight 1.08 lbs.Propelled Mass, Horizontal 11.6 lbs.

Firing Method Propellant GaaTemperature Limits -65°F to +165°FRestraining Force 500 lbs.Actuation Force 750 psi, min.

2

• 2.23




Component Component

A Pin, Shear J Key

4B Pin, Firing K Spring, Piston Locking

C Guide L Piston

Di Screw, Set Md Cartridge, Thruster, M67

E Body N "0" RiLZ

F Gasket, "0" Ring 0 Hiead

G Collar P (jasket, "0" Ring

H "0" Ring QSealI Sleeve, End

BOSS-AND10050-4-1O6MAX *-29 UNF-

I I MA

EEP

F ~ Q223 MAX

ENVELOPE DRAWING

2-24




Component Component

A Pin, Shear JKeyB Pin, Firing K Spring, Piston Locking

C Guide L Piston

D Screw, Set M Cartridge, Thruster, Md67

E Body N "0" Ring

F Gasket, "0", Ring 0 Read

G Collar P Gasket, "0", Ring

H "0" Ring Q Seal

I Sleeve, End

-LOSMAX. ~BOSS-AND 10050-4 k2UF3

3OR-00 DEEP

t~L24 2001005-.-j OO 9 Lill10223 MX

ENVELOPE DRAWING

2.24


Thruster, Cartridge Actuated, M7l

F J(D

W)I

LL.i

0 0 00

N0 - - 'f-1 _jSl~H

Cc5/.2

0 a

Propell ,t Actuated Dovicos

Thrusters

AM9 THRUSTER

The W9 Thruster is a component part of an aircraft escape system whose purpose is tounlatch the canopy of an aircraft prior to implementing the escape procedures of aircraft personnelfrom the aircraft. The thruster is required to complete a stroke of 3.6 inches against a constantresistive force and supply a 1000 psi minimum pressure at the end of a 42 inch length of hoseupon completion of its stroke. The force is represented by 50 pounds mass which is propelledagainst a 500 pound resistive force. Thruster performance data using this test system is pre-sented below.

The thruster is cylindrical in shape, approximately 9.1 inches long and 1.4 inches indiameter. The piston is initially locked in the chamber with two "shear pins" and will unlockupon the application of a tensile load of 96 ±10 pounds.


( Average Peak Thrust Under Load @ 70*F 2600 lbs.Completed Stroke 3.6 inches minimumOperating Time .080 secondsAssembled Weight 1.0 lbs.Propelled Mass, Horizontal 50 lbs.Firing Method Propellant GasTemperature Limits -65*F to +200*FResisting Force 500 lbs.By-Pass Pressure Under Normal Load

at the End of 42 Inch Length of#4 Hose 1000 psi

Actuation Force 750 psi, min.

-- p 2.27

I 4


Thruster, Cartridne Actuated, M9

CROSS-SECTION, DRAWING

Component Component

A Collar I Screw, Set (2)

B Pin, Shear, Firing Pin J Ring

C "0" Ring K Adapter and Pellet Assembly

D Trunnion L Pin, Shear, Piston (2)

E "0" Ring td Cartridge, Thruster, M119

F Body N Pin, Firing

G Piston 0 "0" Ring

H "0" Ring (2) P Breech

-L50 -1LS .64

5fAMP. WA9INM.

Li J

ENVELOPE DPAWING

2.28



15000 -

THRUST-TIME RELATIONSHIPLOAD PROPELLED HORIZONTALLY

4000 50-POUND WEIGHT500-POUND RESISTIVE FORCE

3000

2000 F1000 - -

0 10 20 30 40 50TIME (MS)

2.29/2.30

Propellant Acuated Devicef

Thruaters

M11 THRUSTER

The M11 Thruster is a component part of an aircraft escape system whose purpose isto jettison the canopy of an aircraft prior to implementing the escape procedures of aircraftpersonnel from the aircraft. The thruster is required to complete a stroke of 5-3/4 inches andpropel a simulated canopy through an arc of 90 degrees at a rate of 5 radians per second. Thesimulated canopy is represented by a 35 inch beam weighing 45 pounds. Thruster performancedata using this test system is presented below.

The thruster is cylindrical in shape, approximately 5.3 inches long and 1.25 inchesin diamete, This thruster differs from the orLinary thrusters because it has three telescopingtubes in lieu of a moving piston. The tubez, are initially locked with a shear screw, which willunlock upon the application of a tensile load of 160 ± 20 pounds.


Average Peak Thrust Under Normal Load @ 70°F 2272 lbs.Completed Stroke 5.75 inchesAssembled Weight .95 lbs.Propelled Mass, Radially 45 lbs.Firing Method Propellant GasTemperature Limits -65'F to +200'FVelocity of Propelled Mass, Min. 5 rad/secActuation Force 750 psi, min.

2.31

|oB



NN, ( V .


Component Component

A Pellet V Tube, Outside

B Head and Pellet Assembly L Tube, Inside

C "0" Ring M "0" Ring

D Cartridge, Thruster, M141 N Retainer and Pellet Assembly

E Ring, Segment 0 "0" Ring

F "0" Ring P Guide

G "0" Ring Q Pin, Firing

H Screw, Shear R "0" Ring

I Stop and Pellet Assembly S Pin, Shear

J Body T Washer, Curved

5.255 MAX

.50 +01 4.755 MAX

1.015 DI - 4.25 -. 01 -

- 1.250 DIA .7"-.937-.010 DIA

ENVELOPE DRAWING

2.32

-t

Propellant Actuated D.-vicus

Thruster, Casrtridge AcLoteII, PAU1

THRUST-TIME RELATIONSHIPTEMPERATURE 70*F

2500

2000

00

00

0 4 6 8a1 12 14

TIME (MS)

2 -33/2. 34

Propelled Actuated Devices

Thrusters

M13 THRUSTER

The M13 Thruster is a component part of an aircraft escape system whose purpose is tounlock the canopy of an aircraft prior to ejection of the crewman. The thruster is required tocomplete a stroke of 2.76 inches against an opposing force and supply 1000 psi pressure, mini-mum, at the end of a 6 foot length of hose. The opposing forces are represcnted by a 70 poundweight which is propelled vertically after an iritial restraining force of 2000 pounds is overcome.The initial restraining force is represented by a shear pin located at zero inches of stroke.Thruster performance data using this test system is presented below.

The thruster is cylindrical in shape, approxihrately 8.3 icches long and 1.2 inches indiameter. The piston is initially locked in the chamber with 2 shear pins and will unlock upovthe application of a tensile load of 96 pounds.


Thrust Under Load @ 70OF 2700 lbs.Completed Stroke 2.86 inches, max.Assembled Weight 1.07 lbs.Propelled Mass, Vertical 70 lbs.Firing Method Propellant GasTemperature Limits -65'F to +200*FBy-Pass Pressure Under Load@ 6 Foot of #4 Hose 1000 lbs., mir.Restraining Force 2000 lbs. @ "0" inches of strokeOperating Time .080 seconds, max.Actuation Force 750 psi, min.

2.35

V |




Component Component

A "0" Ring I Screw, Set (2)

B Pin, Shear, Firing Pin J Ring, Shear

C "0" Ring K Fastener, Piston -.nd Pellet Assembly

D Cartridge, Thruster, M119 L Pin, Shear, Piston (2)

E "O" Ring M Breech


G Piston 0 "O" Ring

H "0" Ring (2) P Cap, Base and Pellet Assembly

-2 -7 +.OZ -r~k STROWMS-.01 k.135-.Oao Z.40 -. 02S STROKE M " START

-00 Ov BY-Pkss. PReSURM

."74S +.,00

.70 °* .9s- .002

1.4- ".Q.

2.0C - .02 .'-

ENVELOPE DRAWING

2-36

Propellant Actuated Deices


4000 40

Ir 4200*F

II

-65°F- ' -AMBIaEN I'1 03C AMBIENT_.-\ .-,, .00

4200 - F

looc - - --3 U)

" 1000 :: -,1...t00

3 0

0 10 20 30 40 50 60 70 s0

TIME (MS)

" ' 2-37/2-38

Propeilant Actuated Devices

Thrusters

M15 THRUSTER

The M15 Thruster is a component part of an aircraft escape system whose purpose isto position the crewman's feet an i raise the leg guards of the ejection seat prior to ejection ofthe c;ewman. The thruster is required to complete a 4.42 inch stioke, with the piston being re-tracted into the cylinder, against an opposing force. The opposi , force is represented by an11 pound weight which must be propelled horizonally against a restraining force of 2250 poundsafter an initial restraining force of 3750 pounds is overcome. Silicone oil is employed for internaldamping to keep the acceleration of the propelled weight within limits consistent with humanphysiology. Thruster performance data usir g this test system is presented below.

The thruster is irregular in shape, approximately 16-7/8 inches from the end of theextended piston to opposite mounting end of the body. An external reservoir is attached to thebody for the accumulation of oil as it is metered from the body. The piston is initially lo, kedin the body with a "shear pin" which will ulock upon the application of a compressive loadof 1150 pounds. The thruster also has a final lock which holds the piston in the retractedpositior and is capable of withstanding a tensile load of 15,000 pounds without unlocking.


Approximate Thrust 6700 psiCompleted Stroke 4.42 inchesAssembled Weight 5.0 lbs.

Resistive Force (shear pin) 3750 lbs.Resistive Force (air !oad) 2250 poundsFiring Method Propellant GasTemperature Limits -65'F to 4 165'FPropelled Mass 11 lbs.Operating Time @ -65OF 500 milliseconds: approximatelyActuation Force 750 psi, min.

2-39


"hruster, Cartridge Actuated, M15

SEEIE AIW


Component Component

A Spacer M PistonB Body, Reservoir N BodyC Pin, Shear, Firing Pin 0 Cartridge, Thruster, M94D Ring, Back-Up (4) P Pin, Firing

z "0" Ring (2) Q tO"" RingF Spacer R Housing, Firing PinG Ring, Retaining S Screw, Cap, Socket Head (4)H Nut, Ring And T Screw, Hollow Lock

Pellet Assembly Plug, ReservoirI Rod, End GasketJ Rod, Piston U %0" RingK "0" Ring V Pin, Unlock ShearL "0" Ring (2) W Fluid, Silicone

tc .374 + .005 DIA HOLE

1/2 -7/16 R3.1/4

7/16 RC~+.O HOLEMI

- J6-J-Z ZJ/4

I4.430_± .01o

STROKE -9.125

-1.930 ±.010 15±0 015

ENVELOPE DRAWING

2-40



"-638016 -6450 LB

60 123NI

50-A -N ~ I /

2 ' -442 MSx

30 _ _ I - _ _ - _ _

20 -4- - - ___ -'--" 2250 LB

0.2 . .4 .5

HOT (160° F) TIME-COLD (-65L 0 F)

2.41/2-42

_...... I


Thrusters

M16 THRUSTER

The M16 Thruster is a component part oi an aircraft escape system whose purpose isto position the crewman's legs prior to implementing the escape procedure from the aircraft. Thethr.ster is required to conplete a stroke of 3 inches, min, when fired against a resistive loadsimulating a dorsal stabili/ing fin. Oil in the thruster cylinder acts as a damping medium to keepthe stroke time within the design requirements.

The thruster is cylindrical in shape, approximately 9.9 inches long and 1.19 inches indiameter. The piston is initially locked by a "shear pin" and will unlock upon applica.:on ofa tensile load of 130 ±10 pounds.

The oil damper is to control the acceleration of the propeled weight to limits con-sistent with human physiology limits and/or restrict the final ve.ocity so that the impact doesnot damage the aircraft structure.


Approximate Peak Thrust 200 lbs.Completed Stroke 3.137 max.Assembled Weight 1.6 Ibs.Firing Method Propellant GasTemperature Limits -65"F to +200°FOperating Time .070 sec. to .130 sec.Actuation Force 750 psi, min.

.-4

~2.43


Thruster, Cirtridge Actuated. M16


Component Coraponenr

A Screw, Set K Ring, Scaling

B Packing L Cylinder and Pellet Assembly

C Spring M "0" Ring

D Piston, Floating N Screw, Set

E Ring, Sealing (2) 0 Cartridge, Thruster, M146

F Pin, Locking P Head

G- Screw, Set Q Packing

H Nut, Lock R Pin, Shear

I Clevis S Pin, Firing

J Piston T Fluid, Silicone

8.971 MAX

-~ ftMDO~IA [1190

ENVELOPE DRAWING

2.44



14 90

FILM NO. 463ORIFICE DIA 0.038 IN.

WF 980 DEG/SEC

12 1_ _ _ _

FIN DISPLACEMENT-~~

10 8

'I)

w

0 OIL PRESSURE2 Iii

a. 4

0 20 40 608 2

TIME- MILLISECON'DS

2-45/2-46


Thusters

M17 THRUSTER

The M17 Thruster is a component part of an aircraft escape system whose purpose is toposition the seat in an aircraft prior to ejection of the crewman. The thruster is required to com-plete a 13-l,'4 inch stroke against an opposing force. The opposing force is rcpresented by a350 pound mass that must be propelled against a force that increases from 0 to 525 pounds.The thruster uses oil for an internal damping medium to keep the acceleration of the propelledweight within limits consistent with human physiology.

The thruster is cylindrical in shape-, approxmately 25.37 inches long and 1.82 inchesin diameter. The piston is initially locked in the chamber with shear discs and will unlock uponapplication of a 700 pound tensile load.


Average Peak Thrust Under Load l +165'F 1600 lbs.Completed Stroke 13-1/4 inchesMax Piston Velocity 12 ft/secAssembled Weight 13.0 lbs.Firing Method Propellant GasTemperature Limits -65'F to 160'FPropelled Mass, Horizontal 350 lbs.

Restraining Force 525 lbs.Actuation Force 750 psi, min.

2.47




Component Component

A Screw, Set K Piston, Rod, End AssemblyB Heud L "Oft RingC Washer N TubeD "0"~ Ring N PistonE Disc, Shear, Front 0 ScrewF Ring P BodyG Cap Q Cartridge, Thrust-, 1443H "0"1 Ring R Pin, FiringI 1 "0' Ring S "10" RingJ Fluid T Pin, Shear

25,372- .095-

45 ' 1.8 DIAMAX1.875 DIA MAX_ 4 1.2D6 A 1.637 DIA MAX4. 10-r13DA X

1.01 D4A __DMAX

ENVELOPE DRAWING

2.48


Thruster, Cartridge Actuated, MJ7

8

- I

__________ _ __ _ _ __

0

nL 0

0

011.

- -,,4.

0 o0 1 wZ

000- m N C

-I>k

U)

i- >

0h d rn 0 0

M

0

.4.

00

00

0

0 0 0 0 0 0 0 08 0 2 0 0 0 0 0 8 0

SBI - J.SfUHI

2-49/2-50

Propellant Actojated Devices

Thrusters

M18 THRUSTER

The M,18 Thruster is a component part of an aircraft escape system whose purpose is toposition the seat in an aircraft prior to ejection of the crewman. The thruster is required to com-plete a 9-1/2 inch stroke against an opposing force. The opposing force is represented by a 350pound mass that must be propelled against a force that increases from 0 to 525 pounds. Thethruster uses oil for an internal damping medium to keep the acceleration of the propelled weightwithin Fmits consistent with human physiology.

The thruster is cylindrical in shape, approximately 21.69 inches long and 1.:.2 inchesin diameter. The piston is initially locked in the chamber with shear discs and will unlockupon application of a 700 pound tensile load.


Average Thrust Under Load @ +165°F 1600 lbs.Completed Stroke 9-1/2 inchesMax Piston Velocity 12 ft/secAssembied Weight 12 lbs.Firing Method Proellant GasTemperature Limits -65°F to +160°FPropelled Mass 350 lbs.Retaining Force 525 lbs.Actuation Force 750 psi, min.

2.51

C


Thruster Cartridge Actuated, M18


Component Component

A Screw, Set K Piston, Rod End AssemblyB Head L "0" RingC Washer M TubeD " C" Ring N PistonE Disc, Shear, Front 0 ScrewF Ring P BodyG Cap Q Cartridge, Thruster, M43H "O" Ring R Pin, FiringI "0" Ring S "o" RingJ Fluid T Pin, Shear

21.686..097-

-2 1.875 D MAX 4.0 -64

111.821) MAX 1.637r'. MAX 1.0__ 1 13 0t) MAX

1.O11A~lU i II __ 4.~4 ~ AI 1,515 D MAX

16 1 UNF-3A 4 EI I

ENVELOPE DRAWING

2.52


Thrusters

A19 THRUSTER

The M19 Thruster is a component part of an aircraft escape system whose purpose isto unlock the canopy of an aircraft prior to implementing the escape procedures of aircraft per-sonnel from the aircraft. The thruster is required to complete a stroke of 2.76 inches against anopposing force and supply 1000 psi pressure, minimum, at the end of a 13 foot 6 inch length ofhose. The opposing forces distance is represented by two shear pins located with respect toinitial piston position. The diameter of each pin was selected so that the shear force at agiven .stance is equal to the corresponding maximum opposing force in the above application.Thruster performance data using this test system is presented below.

The.thruster is cylindrical in shape, approximately 8.3 inches long and 1.2 inches indiameter. The piston is initially locked in the chamber with 2 "shear pins" and will unlockupon the application of a tensile load of 96 pounds.


Peak Thrust Under Load @ 70OF 1470 lbs.Completed Stroke 2.86 inches max.Assembled Weight 1.07 lbs.

Propelled Mass 75 lbs.Firing Method Propellant GasTemperature Limits -65 0 F to +200'FBy-Pass Pressure Under Load 13 Feet

6 Inch Length of # 4 Hose 1000 psi

Restraining Force 25 lbs. @ "0" inch stroke,

500 lbs. @ "2.4" inch strokeOperating Time .080 seconds, max.Actuation Force 750 psi, min.

2.53




Component Component

A "0" Ring I Screw, Set (2)

B Pin, Shear, Firing Pin J Ring, Shear

C "0" Ring K Fastener, Piston and Pellet Assembly

D Cartridge, Thruster, M119 L Pin, Shear, Piston (2)

E "0"~ r~ing M Breech


G Piston 0 "0" Ring

H "0" Ring (2) P Cap, Base and Pellet Assembly

2.78 + .03 TOTAL STROKE2.40 +.03 STROKE TO START

- 7.63 -. 01 6.0+OSOF BlY-PASS PRESSURE

. 45+.0 10 . 5 9 S- .0 1 5 .9 0 -.0 1 ]

IF30'~ T .0, 375- .002

ENVELOP DRAWIN

2.54

Prope;lant Actuated Devices


160 -- - - 1100

1200 " *z0-

- -/a -

i-o ---- - - a. ' ,I

- - - - I-PRESURE AT END OF SHORT HOSE

40 -- PRIIURE AT END OF LONG H OE

0 to 40 00 0 100 WtO 140 ISOTIME (MS)

2.55/2-56


Thrusters

M20A1 THRUSTER

The M20,A 1 Thruster is a component part of an aircraft system whose purpose is tojettison the canopy of 1r. aircraft prior to implementing the escape procedure of aircraft per-sonnel from the ai:,.raft. The thru ,ter is required to complete a 5 inch stroke against a constant

force. With the thruster conne.ted to a 50 Found weight, the piston shall move a constant load of3000 pounds, horizontally, t,-roughout its entire 5 inch stroke.

The thruster is cylindrical in shape, approximately 12.6 inches long and 1.4 inches indiameter. The piston is initially locked_ by 4 keys in a locking groove and will withstand atensile load of 2000 pounds without separation or mechanical failure.


Average Peak Thrust Under Normal Load @ 70'F 5877 lbs.Completed Stroke 5.0 inchesAverage Stroke Time .046 sec.Assembled Weight 3.6 lbs.Propelled Mass, Horizontal 50 lbs.Firing Method Propellant GasTemperature Limits -65"F to +200"FRestraining Force 3000 lbs.Force Required to Unlock Initial Lock 60 lbs.Actuation Force 750 psi min

2.57

C

Prope!lant Actuated Devices

Thruster, Cartridge Actuated, M20AIiT

CrKOSS-SECTION DRAWING

Component Component

A Head J Screw, Buffer and Pellet Assembly

B Pin, Firing K Key (4)

C "0" Ring (2) L Do&y and Pellet Assembly

D Trunnion M Sle .ve

E Piston N Cartridge, Thruster, M127

F Spring 0 Guide Retainer Assembly

G "O" Ring P "0" Ring

H Sleeve, End Q Pin, Shear

I "0" Ring

-12.57

Z 2:LANF- 8 ' 140 a _ UN a7

ENVELOPE DRAWING

2.58

Propoliant Actuated Devices

Thrustor, Cartridge Actuated, M20A1

--- o-

0

m0

U) LL

iz

0

. Cl)

- __ 0 _ 0 0

0K 0CMl

iI- -

inn

I- 0

_____ 0

0 0 0

L 2.59

,II

NNSS-.SlH


Thrusters

M25 THRUSTER

The M25 Thruster is a component part of an aircraft system whose purpose is tojettison the canopy of an aircraft prior to implementing the escape procedure of aircraft per-sonnel from the aircraft. The thruster is required to complete a 5 inch stroke against a constantforce. With the thruster connected to a 50 pound weight, the piston shall move a constant load ofM0OU pounds, horizontally, throughout its entire 5 inch stroke.

The thruster is cylindrical in shape, approximately 12.6 inches long and 1.4 inches indiameter The piston is initially locked by 4 keys in a lock'ng groove and will withstand atessile load of 2000 pounds without separation or mechanical failure.


Average Peak Thrust Under Normal Load 70OF 5877 lbs.

Completed Stroke 5.0 inchesAverage Stroke Time .046 sec.

Assembled Weight 3.6 lbs.Propelled Mass, Horizontal 50 lbs.Firing Method Propellant Gas

Temperature Limits -65"F to +200"FRest-raining Force 3000 lbs.Force Required to Unlock Initial Lock 60 lbs.

Actuatiion Force 750 psi, min.

2.60




Component Component

A Head J Spring

B Pin, Firing K Pin, Spring

C "0" Ring (2) L "0" Ring

D Trunnion M Body

E Piston N Sleeve

F "0" Ring 0 Cai ridge Thruster

G Piston, Unlocking P Guide Retainer Assembly

Hf Key (3) Q "0" Ring

I Ring, Shear R Pin, Shear

12.573 3D

L--L 2O-UNF-3 2 A 1AO11 -i4 UNF2A

16 88

ENVELOPE DRAWING

2461



0

000

ww

0. wCn w

I0I I-

0

0_ _ g

0 0 0o 000 0 0

(LI2-62/2-63


Catapults

SECTION III

CATAPULITS

Propellant Act'ntd Dey!e-

Catapults

INTRODUCTION

Description

The catapult is a two or three tube telescoping device, containing an explosive compo-

nent, designed for upward or downward ejection of crewmen and their seat from high-speed aircraftto provide safe escape from disabled aircraft.

Operation

The catapult must impart to its 1 id (ejection seat with occupant), a velocity which willinsure its clearing the aircraft and reach sufficient height to permit full deployment of a parachute,at the same time keeping the acceleration within safe physiological limits.

Two additional types of catapults have been designed to indoctrinte USAF trainees inthe catapult ejection procedures; namely, one type which is used on a fixed vertical training towerand a mobile type which propells the seat and occupant along a guided vertical track.

3-1/3-2


Catapults

CATAPULT, AIRCRAFT EJECTION SEAT, MIA1

The first catapult developed for USAF was the mechanically actuated MIAl Catapult.The catapult is a three tube telescoping ejection device, containing an explosive cartridge, de-signed for upward ejection of crewmen and their seat from high speed aircraft to provide safeescape from disabled aircraft.

The catapult is approximately 39 inches long and 2.3 inches in diameter. Tha catapultis actuated by removal of the safety locking pin first and manual operation of the sear through apulley system connected to a lever on the pilot's seat. Rotation of the sear unlocks the catapulttubes and releases the spring loaded firing pin which strikes and detonates the primer, therbyigniting the black powder and propellant in the M28A1 Cartridge. The catapult thrust which isdeveloped from the expanding gases of the burning propellant, forces the inside and telescopingtubes to move simultaneously until the shoulder on the telescoping tube comes in contact withthe trunnion, thus restricting its movement. The continuous moving block assembly and insidetube are ejected with the seat. The outside and telescoping tubes remain with the aircraft.


Stroke 66.0 inchesWeight (total assembly) 8.2 poundsPropelled Weight 300.0 poundsTemperature Limits -65 0 F to +160*FMax Acceleration (at 700F) 20.0 gVelocity, min (at 700F) 60.0 fpsMax. Rate of Change of Acceleration

(at 700F) 170.0 g/secFiring method Mechanical ActuationStroke Time (at 70'F) 0.220 sec

I33.3

Propeilant Actuated Devices

Catapult, Aircraft Ejection Seat, MIAI

CROS-SECTION DRAWING

Component Component

A Pin, Locking I Tube, OutsideB Wirc, Lockiog J Tube, TelescopingC Spring, Firing Pin K Tube, InsideD Block Assembly L CapE Seal, Lead M Seal, PlainF Sear N Cartr~idge, Aircraft Ejection Seat,G Seni, Fixed Catapult, M28A1H Trunnion 0 Pin, Firing

P Pin, Safety, Assembly

135 2-57

332

HK~~ 32 _00.O S IA 4.3

ENVELOPE DRAWING

3-4


Catapult, Aircraft Ejection See MIAl

PwRESRE-TNE RELATINSH4IP S?A4OAR1W V1PELLED WEIGHT: 300 LI.

-~ --

-4-7

T--ITI

Propollanot Actuated Devices

Catapult, Aircraft Ejecvion Seat, MIAI

-H VELOCITY TRAVE RELATINSHIP STANDARD PROPELLED WEIGHT: 300 L6. J'

+ 77

70' F

- TUBE4--EPARATION~

- CELERATIO-TRAVEL RELATINSP STANARD PROPELLED WEIGHT: 30L0 -

3160

sI t- -

~~ac


Catapults

CATAPULT, AIRCRAFT EJECTION SEAT, TRAINING, M2

The Catapult, Aircraft Ejection Seat, Training, M2 with the Cartridge M30A1 was designed

to be used on a fixed vertical training tower for indoctrinating United States Air Force trainees inthe catapult ejection prQcedure. In this application, the catapult ejects the seat and occupant alonga guided track to about a height of 40 feet with moderate accelertion.

The training catapult is a three-tube, mechanically actuated unit which is constructed ofsteel. This catapult is approximately 39 inches long and 2.2 inches in diameter. After removal ofthe safety locking pin, the catapult is actuated by manual rotation of the sear through a pulley sys-tem connected to the actuating lever on the indoctrinee's seat. Rotation of the sear releases thespring-loaded firing pin which strikes and detonates the primer, thereby igniting the black powderand propellant in the M30A1 Cartridge. The Catapult thrust which is developed from the expanding

gases of the bu..'ng propellant, forces the iiside and telescoping tubes to move simultaneouslyuntil the shoulder or, the telescoping tube comes in contact with the trunnion, thus restricting iesmovement. The continuous moving block assembly and itbide tube are ejected with the seat. The

outside and teiescoping tubes remain with the simulated cockpit.

The catapult is designed for repeated use on a fixed tower iiistallation, with a new car-tridge inserted for each firing.


Stroke 60.0 inches

Weight (total assembly) 13.0 pounds

Propelled Weight 300.0 poundsTemperature Limits -65'F to +160'F

Max Acceleration (at 70'F) 12.0 gVelocity, min (at 70 0 F) 38 fpsMax Rate of Change of Accel (at 70'F) 150 g/secFiring Method Mechanical ActuationStroke Time (at 701F) 0.210 seconds

3.7

I


Catapult, Aircraft Ejection Seat, Training, M2

©Q

CROSSSECTON DAWIN

CompnentCompnen

A GiFrn ue usd

C Pin, Firing PiG Tube, Ouside

D Pin, Safety, Assembly J CapE Block Y. Cartridge, Aircraft Ejection SeatF Trunnion Catapult, M30AX -(Installed at

Training Base)

DI1A,

38.647 MAX______________-38.547 MIN

Yt__,, ___

ENVELOP DRAWIN

3? .1-.1DA473 5 A


Catapult, Aircraft Ejection Seat, Training, M2

-, PRESSURE-TRAVEL RELATIONSHIP STANDARD PR'OPELLED WEIGHT: 300 L13.

-ifI IIIFI200*

SIX JI1- 20 2I0~ 40 4 0

VELOCITY-TRAVEL RELATIONSHIP F rANDARQ PROPELLED WgIGHiT: 3dtOLB.

t1J.

I+EL I cHEL

43.

TU3


Catapult, Aircraft Election Seat, Training, M2

+ PRSSR-TM zooTINV 3TNAD RPLEDWXo: 0

7001

I Jil


Catupults

CATAPULT, AIRCRAFT EJECTION SEAT, M3A1

The M3A1 Catapult is a gas actuated three-tube telescoping device containing an explo-sive cartridge, designed to propel upward, an ejection seat together with a crewman from high-speed aitcraft to provide safe escape from disabled aircraft.

The catapult is approximately 51 inches long and 3.0 inches in diameter. The catapulthas an initiator attached by a length of flexible hose. When the initiator is functioned, the gasdeveloped flows through the flexible hose, exerting force against the catapult firing pin. Thefiring pin is propelled forward and strikes and detonates the primer, thereby igniting the blackpowder and propellant in the M36 Cartridge. The catapult is unlocked by cam action as the firingpin moves toward the primer, unlocking the block assembly and inside tube. The catapult thrustwhich is devdoped from the expanding gases of the burning propellant forces the inside andtelescoping tubes to move simultaneously until the shoulder on the telescoping tube comes incontact with the trunnion, thus restricting its movement. The continuous moving block assemblyand inside tube are ejected with the seat. The outside and telescoping tubes reaain with theaircraft.


Stroke 88.0 inchesWeight (total assembly) 24.9 poundsPropelled Weight 350.0 poundsTemperature Limits -65*F to +160*FMax Accel. (at 70'F) 20.0 gVelocity, min. (at 700F) 77.0 fpsMax Rate of Change of Accel

(at 700F) 180.0 g/secFiring Method Gas ActuationStroke Time (at 700F) 0.240 sec

3.11


Catapult, Aircraft Ejection Seat, M3A1

60

B ~9 SeS Pli 0iBlc

C Tube, Outside and Pellet N Plug, ShippingAssembly 0 ftQ" Ring

D Trunnion P Ring, Stop and Pellet AssemblyE Senl, Fixed R PlugF Seal, Plain S Cartridge, Aircraft EjectionG Washer, Shock Seat, Catapult, M36H Screw, Cap, Socket Head, T Tube, Inside and Pellet

Self-Locking (shown out of position) AssemblyI Pin, Shear U Tube, TelzscopingJ Latch (2) V SpacerK Seal, Tamper Proof

4 -a OIA-

3-41

4 2 4S -.0 S IA- .5 0+.oe1-0 -a

Propslant Actuated Devices


VEOSUR-TRAEL RELAIOSHP STNDARD PROPELLED WEGHT: 350 LIK 4+

TRfit . IN

E

;:rT'3T13


Catapult, Aircraft Ejection Seat, MWA

+ PESSURE-TIM~E RtELATIONSH4IP STANDARD PROPELLED WEIGHT: 350 LB. --

_ 31- - 7Ti~ I - -10FIf IT

1 'h ' ' .L-16Y 70'F'

2 Iioi -.-65 0 T F

21, 1r 1i~

3.404

SIC I

Propellont Actuated Devices

Catapults


The M4A1 Catapult is a gas actuateJ three-tube telescoping device, containing at explo-sive caztridge, designed to propel downward, an ejection seat together with a crewman from high-speed aircraft to provide safe escape from disabled aircraft.

The catapult is approximately 31 inches long and 2.6 inches in diameter. The catapulthas a., initiator attached by a length of flexible hose. When the initiator is functioned, the gasdeveloped flows through the flexible hose, exerting force against the catapult firing pin. Thefiring pin is propelled forward and strikes and detonates the primer, thereby igniting the blackpowder and propellant ii the M37 Cartridge. The catapult is unlocked by cam action as the firingpin moves toward the p.imer, unlocking the block assembly and inside tube. The catapult thrustwhich is deveJoped from the expanding gases of the burning propellant, forces the inside andtelescoping tubes to move simultaniously until the shoulder on the telescoping tube comes incontact with the ring tube stop, thus restricting its movement. The continuous moving blockassembly and inside tube are ejected with the seat. The outside and telescoping tubes remainwith the aircraft.


Stroke 45.0 inchesWeight (total assembly) 6.7 poundsPropelled Weight 325.0 poundsTemperature Limits -65°F to +160°FMax Accel (at 70*F) 12.5 gVelocity, min. (at 70 0F) 38.0 fpsMax rate of change of Accel

(at 70'F) 100.0 g/secFiring Method Gas Actuation

Stroke Time (at 700F) 0.240 sec

3. 5

Propellant Actucted Devicot



Component Component

A Riag, Compression M "0"p RingB $pacer N Seal, T~zper Prc ofC Tube, Outside 0 Latch (2)D Tube, Telescoping & Pellet Assembly P PlusE Seal, Plain Q Washer, ShockF Ring, Tube Stop & Pellet Assembly R Seal, FixedG Screw, Cap, Socket Head, Self-Locking S Tube, lIrside & Pellet AssemblyH Pin, Shear T Seal, PlainI Ring, Stop & Pellet Assembly U Cap & Pellet AssemblyJ Pin, Firing V Cartridge,1Aircraft Ejection SeatK Block Catapult, M37L Plug, Shipping

2.500 C .IAVI

r238-.010

U 2.63 -. 01 VIA JI -2.6.3-.01- .33610 A

~ ~ - '. r

Propellant AMtated Devices


PrMESUIR!-TIME flELATIOtNP STANDARD PROPELLE WIeIT:325 La

I-I

0 so IsO no

AV.ERATO-TIME REMEWS~ STARO PROPS±EO WtIT 32 LI. T

1F'

I t4r21-6

i t 1

0 so 100 IS~O 2w20

ACMEATIO-TIE REATINSMPSTADARDPROELLE WENT3-017


Catapult, Aircraft Election Seat, M4.1

MSL -RVLRLTOS TNDR RPLE E T 2 I

o ~ ~ ~ 6 F U '

T:;jL IkCI I

bi Z--3 -

- ~ ~ ~ ~ ~ ~ 0 F;----- - ~.


Catapult


The M5A1 Catapult is a gas actuated three-tube telescoping device containing an explo-sive cartridge, designed to propel upward an ejection seat together with a crewman from high-speed aircraft to provide safe escape from disabled aircraft.

The catapult is approximately 39 inches long and 2.3 inches in diameter. The catapulthas an initiator attached by a length of flexible hose. When the initiator is functioned, the gasdeveloped flows through the flexible hose, exerting force against the catapult firing pin. Thefiring pin is propelled forward and strikes and detonates the primer, thereby igniting the blackpowder and propellant in the M28A1 Cartridge. The catapult is unlocked by cam action as thefiring pin moves toward the primer, unlocking the block assembly and inside tube. The catapultthrust which is developed from the expanding gases of the burning propellant forces the insideand telescopipg tubes to move simultaniously until the shoulder on the telescoping tube comesin contact with the trunnion, thus restricting its movement. The continuous moving block assem-bly and inside tube are ejected with the seat. The outside and telescoping tubes remain withthe aircraft.


Stroke 66.0 inchesWeight (total assy) 8.2 poundsPropelled Weight 300.0 poundsTemperature limits --65'F to + 160°FMax Accel (at 70 0F) 20.0 gVelocity, min (at 70 0F) 60.0 fpsMax rate of change of accel

(at 70'F) 170.0 g/secFiring Method Gas ActuationStroke Tic (at 700F) 0.220 sec

1 319




Component Componest

A Cap J Pin, ShearB Seal, Plain K Ring, Stop & Pallet AssemblyC Tube, 9utside & Pellet L tq0" Ring

Assembly hi BlockD Tube, Telescoping N Pipe Plug, ShippingE Tube, Inside & Pellet 0 Pin, Firing

Assembly P Seal, Tamper ProofF Seal, Fixed Q Latch (2)G Trunnion R PlugH Washer, Shock S Cartridge, Aircraft Ejection SeatI Screw, Cap, Socket Head, Catapult, M28AI

Self-Locking T Seal, Plain

0.

IZ L3.0014A

ENVELOPE DRAWING

3.20

Propellaint Actuoted Devices

Catapult, Aircraft Election Seat, M5AI

VRELOSUR-TRWEL RELA11TISW STAAR PROPELLED *11HT' BOLL.

1-4 -- -

T-VL 174FL15

0i



ACCELSEAT-TIME RELATIONSHIP STANDARD PROPELLED WEIGHT: 300 L

~I I rE

It+I

0 0 100 10 tooBoThME-MSIOW"

3.22

Propellant AcTuated Devices

Catapults

CATAPULT, AIRCRAFT EJECTION SEAT, TRAINING, M6A1

The M6A1 Catapult with the Cartridge, Aircraft Ejection Seat Catapult, Training, M57was designed to be used in the MH-15 Ejection Seat, Indoctrination Trainer (Mobile Type) for

indoctrinating U. S. Air Force trainees in the catapult ejection procedures. In this application,the catapult ejects the seat and occupant along a guided track to abou! a height of 12 feet with

moderate acceleration.

The training catapult is a two-tube, mechanically actuated, short stroke unit whichis constructed of steel. The catapult is approximately 50.0 inches long. After actuation of thesafety plate, the catapult is actuated by mechanical operation by the indoctrinee by means of agrip on the arm rest which is convected to the firing arm by a cable. Squeezing the grip rotatesthe firing arm and releases the spring loaded firing pin which strikes and detonates the primer,thereby igniting the black powder and propellant in the M57 Cartridge. The catapult thrustwhich is developed from the expanding gases of the burning propellant propels the seat andoccupant up the tower. The inside tube and firing head assembly, which are attached to the

seat, separate from the outside tube and are carried with the seat on ascent. The outside tube

and its permanently attached parts remain in the cockpit of the trainer.

There are two safety systems connected to the catapult. The first system consistingof a plate prevents firing of the catapult inadvertendy by the trainee, while the second preventsseat movement in the event of cartridge failure or other malfunctions. The latter safety systemis accomplished by rotating the catapult outside tube through a cable locking system located onthe trainer. This rotation causes the lugs of the bell cap located on top of the outside tube toengage corresponding protrusions inside the trunnion and securely locks both inner and outer

tubes together.

A ballistic safety value assembly, incorporating a pre-bulged rupture disc, is attachedto the lower end of the catapult outside tube and its purpose is to bleed off excessive gaspressure which might result in an excessive height of travel on the trainer.


Stroke 21.0 inchesWeight (total Assembly) 31.5 pounds

Propelled weight 300.0 pou.dsTemperature Limits 40OF to 125 0 F

Max accel (at 70 0 F) 8.5 gFiring Method Mechanical ActuationStroke Time (at 70 0 F) 0.163 sec

3.23


Catapult, Aircraft Election Seat, Training, M6A1


Component Component

A Valve, Safety Assembly K Spring, Firing Pin(shown out of position) L Ring, Sear

B Plate M Body, Breech

C Ring, Snap N Trunnion and Breech

D Cap, Breech Ring Assembly

E Firing Arm Assembly 0 Cap, BellF Ring, Snap, Retining, P Tube, Inside

Internal, Inverted Lug Q Tube, Outside

G Mount Assembly R Pin, Firing and Stop

H Handle AssemblyI Slide S Cartridge, Aircraft Ejection

J Spring, Sear, Rling Seat, Catapult, M57(Installed atTraining Base)

2 2 S DIA

/-z~~~~a o o .98:0,OU

1.07 DIA

49.995

ENVELOPE DRAWING

3.24,4

C.


Catapult, Aircraft Election Seat, Training, M6A1

ACCELERATION -TIME RELATIONSHIP

.4

0 20 40 60 80 100 120 140 160TIME (MILUSECONDS)

BOOE POUNDS PC0PELLSji 3.2.


ectapult, Aircraft Election Seat, Training, M6A1

TR*Icwk0U

ACEEAIN3TAE'ELTOSi

30 OUD POELE

II0

0, 2 0 C 1 6 t o

4


Catapults

CATAPULT, AIRCRAFT EJECTION SEAT, M8

The M8 Catapult is a rocket-assisted two tube telescoping device developed for use in

the F105 Aircraft to provide "off-the-deck" as well as high speed ejection capability from dis-

ab:led aircraft. The catapult is a two stage device; the initial booster phase and final rocket

motor phase.

The catapult is approximately 46.3 inches long and 2.89 inches in diameter. The cata-pult has an initiator attached by a length of flexible hose. When the initiator is functioned, thegas developed flows through the hose, exerting force against the catapult firing pin. The firingpin is propelled forward and strikes and detonates the primer contained in the primary igniter.This action initiates the firing of the booster phase. The primer ignites the pyrotechnic compo-sition contained in the igniter which flashes down the booster tube igniting the strip propellantbonded to the strip holder. The booster gas piessure moves the can, thereby permitting the tangsof the nozzle retainer to be cammed inward, unlocking the unit. Continued booster gas productionpropels the rocket motor and the seat vertically. At a point prior to motor tube separation, thecable, which is attached to the can, engages rhe cable guide on the strip holder assembly andforces the piston slider valve downward uncovering the gas by-pass ports on the cylinder boostertube assembly. This allows the hot booster gases to dump into the motor chamber which ignitesthe auxiliary igniter and the rocket propellant grain. The burning propellant grain produces gasat a high rate, pressurizing the motor chamber. This pressure forces out the nozzle cups allow-ing the gas to exhaust through the nozzle ports, thus providing thrust which propels the seat andoccupant apward and forward. The nozzle is canLed 37030: so as to direct the rocket thnst throughthe center of gravity of the seat-man combination.


Weight (total assembly) 27.0 lbs.Propelled Weight 350.0 lbs.

Temperature Limits -65' to + 160 0F

Catapult (Booster Section)

Stroke 40 inches

Max Acceleration (at 70'F) 20.0 gVelocity (at 70 0F) 40.0 fpsI** D*S. t't. .... .

Acceleration (at 70 0F) 300.0 g/secStroke Time (at 70 0 F) 0.175 secFiring Method Gas Actuation

3.27


Catapults


Rocket (Sustainer Section)

Action Time, max (at 70 0 F) 0.400 sec.Impulse (resultant at 70 0 F) 1200 lb-sec.Pressure, max 4600 psi.Ignition Delay, max (at 70'F) 0.012 sec.

Nozzle Angle 37030 ,

3

A

I -A

Catapult, Aircraft Election Seat, MB

A Q D E F G Z EE i I K D E M (D N

DD CC S D BB AA DU T S R 0 P


Component Component

A Bt eech, Launcher P Plug, ShippingB Can, Bottom Q Sleeve, Firing PinC Holder, Cable Lower R Ring, RetainingD "0" Ring S Wire, LockE Screw, Set T Igniter, Primary AssemblyF Plate, Orifice U Igniter, Auxiliary AssemblyG Tube, Launcher And V Pin, Valve Shear (4)

Pellet Assembly W Screw (2)H Tabe, Motor X Washer (2)I Trunnion Y Cylinder, Slider Valve AndJ Piston, Slider Valve Tube Booster Assembly

K Spring, Grain Z Collar, GrainL Cap, Igniter AA Holder, Strip, Loaded AssemblyM Head, Motor Tube BB Propellant, Grain InhibitedN Pin, Firing CC Nozzle Assembly0 Pin, Shear DD Spring, Can

EE Screw, Set (4)

WO~4TOR TUBS Dix ±OA

I.58 1-.1 r

-43. 14 (REF)

ENVELOPE DRAWING

ft~ 3.29/33

PropoIlant Actuated Devices

Catzpults

CATAPULT, AIRCRAFT EJECTION SEAT, M9

The M9 Catapult is a rocket-assisted two tube teleccoping device developed for usein the T-38 Aircraft to provide "off-the-deck" as well as hiv!p speed ejection capability fromaisabled aircraft. The catapult is a two-stage device; the initial boost -r phase and final rocketmotor phase.

The catapult is approximately 41.9 inches long and 2.89 inches in diameter. The cata-pult has an initiator a.tached by a length of flexible hose. When the initiator is functioned, thegas developed flows through the hose, e':erting force against the catapult firing pin. The firingpin is propelled forward and strikes and detonates the priner contained in the primary igniter.This action initiates the firing of the bcoster phase. The primer ignites the pyrotechnic compo-sition contained in the igniter which flashes down the booster tube igniting the strip propellantbonded to the strip holder. The booster gas pressure moves the can, thereby permitting the tangsof the nozzle retainer to be carmed inward, unlocking the unit. Continued booster gas productionpropels the rocket motor and the seat vertically. At a point prior to motor tube separation, thecable, which is attached to the can, engages the cable guide on the strip hclder assembly andf,-r:es the piston slider valve downward uncovering the gas by-pass ports on the cylinder boostertube assembly. This allows the hot booster gases to dump into the motor chamber which ignitesthe auxiliary igniter and the rocket propellant grain. The burning propellant grain produces gasat a high rate, pressurizing the motor chamber. This pressure forces out the nozzle cups allow-ing the gas to exhaust through the nozzleports, thus providing thrust which propels the seata i occupant upward and forward. The nozzle is canted 470 30', so as to direct the rocket thrustthrough the center of gravity of the seat-nan combination.

PRINCI PAL CHARACTERISTICS

Weight (total Assembly) 24.0 lbs.Propelled Weight 350 lbs.Temperature Limits -65"F to +160 0 F


Stroke 35-3/4 inchesMax Accel. (at 70 0 F) 20.0 gVelocity (at 70'F) 40.0 fpsMax. Rate of Change of 300 g/sec

Accel. (at 70'F)Stroke Time (at 70'F) 0.160 secFiring Method (jas Actuauon

K


Catapults



Action Time, max (at 70'F) 0.350 secImpulse (resultant at 701F) 1100 lb-secPressure, max 4600 psiIgnition Delay, max (at 700F) 0.012 secNozzle Angle 47030 ,

3

.3

Propellant Actuated Devicez

Catapult, Aircraft Ejection Seat, M9

A a) LD N 0

CD D CC D 38 EE AA Z Y x W D V u T s R Q P


Component Component

A Breech, Launcher P Plug, ShippingB Can, Bottom Q Sleeve, Firing PinC holder, Cable Lower R Ring, ReteiningD "0" Ring S Wire, LockE Screw, Set T Igniter, Primary Assembly

F Plate, Orfice U Igniter, Auxiliary AssemblyG Tube, Launcher And V Pin, Valve Shear (4)

Pellet Assembly W Screw (2)H Tube, Motor X Washer (2)1 Trunnion And Pellet Assembly Y Cylinder, Slider Valve AndJ Piston, Slider Valve Tube Booster Assembly

K Spring, Grain Z Holder, Strip, Loaded AssemblyL Cap, Igniter AA Collar, GrainM Head, Motor Tube BB Propellant, Grain Inhibited

N Pin, Firing CC Nozzle Assembly0 Pin, Shear IDD Spring, Can

EE Screw, %et (4)

27800 A..500 + .002 DIA. - 3.00.-.01 12.72-8. .005 -iA 130D.- 3T

2. ~ ~ MOTO .01BEA 3.00 -. 01 32 .0 IA

-1.73S54.755 ~ i 6~

S6224.725 - .. 02 06.262

41.536 39.1~78 REr IA

41.342 t720ONF. 3B

ENVELOPE DRAWING

3.33

Prepellant Actuated Devices

Catapult, Aircraft Ejection Seat, M9

4000STANDARD PROPELLED WEIGHT 3.90 LB4000 " -

3000

C470°F i

. _0006- -

0 50 100 150 200 250 300 350 4C' 450 500 550 600 650 700 750

TIME - MILLISECONDS

VELOCITY TIME RELATIONSHIP[ __ ~ . FONOZZLE ANGLE 47030 "

STANDARD PROPELLED WEIGHT = 350 LBTOTAL HEIGHT OF TRAVEL 220 FT

VELOCITY = 104.33 FT/SEC

U 120 VELOCITY = 109.02 FT/SECw VELOCITY= 106 FT/SEC

9k. 100 1 - - -

H 60 - - - -_

4 J = CATAPULT VELOCIT Y = 44.2 FT/SEC

'C 40 - -CA...APULT VELOCITY1 = 40.0 FT/SECI I I ICATAPULT VrLOCITY 35S.2 FT/SEC

0 50 100 ,50 200 250 300 350 400 450 500 550 600 650 700 750

TIME - MILLISECONDS

ACCELERATION TIME RELATIONSHIPNOZZLE ANOLZ 47030STANDAPO PROPELLED WEIGHT =350 LB --

0

F E20 END OF CATAPULT STROKEUI ZND OF CATAPULT STROKEU ° -I 1 ,1 1 '

0 50 100 250 200 250 300 350 400 450 500 550 600 650 700 750

TIME - MLLI$ECONDS

3.34


Catapults

CATAPULT, AIRCRAFT EJECTION SEAT, M1O

The M10 Catapult is a rocket-assisted two tube telescoping device developed for usein the F104 Aircraft to provide "off-the-deck" as well as high speed ejection capability fromdisabled aircraft. The catapult is a two stage device; the initial bcoster phase and final rocketmotor phase.

The catapult is approximately 44.1 inches long and 2.89 ir.hes in diameter. The cata-pult has an initiator attached by a length of flexible hose. When the initiator is functioned, thegas developed flows through the hose, exerting force against the catapult firing pin. The firingpin is propelled forward and strikes and detonates the primer contained in the primary igniter.This action initiates t.: firing of the booster phase. The primer ignites the pyrotechnic compo-sition contained in the ignit.r which flashes down the booster tube igniting the strip propellantbonded to the strip holder. The booster gas pressure moves the can, thereby pe.,mitting the tangsof the nozzle retainer to be camred inward, unlocking the unit. Continued booster gas productionpropels the rocket motor and the seat vertically. At a point prior to motor tube separation thecable, which is attached to the can, engages the cable guide on the strip holder assembly andforces the piston slider valve downward uncoverrng the gas by-pass ports on the cylinder boostertube assembly. This allows the hot booster gases to dump into the motor chamber which ignitethe auxiliary igniter and the rocket propellant grain. The burning propellant grain produces gasat a high rate, pressurizing the motor chamber., This pressure forces out the nozzle cups allow-ing the gas to exhaust through the nozzle ports, thus providing thrust which propels the seat andoccupant upward and forward. The nozzle is canted 3620, so as to direct the rocket thrustthrough the center of gravity of the seat-man combination.


Weight (Total Assy) 26.0 poundsPropelled Weight 400.0 poundsTemperature Limits -65*F to + 160*F


Stroke 34.0 inchesMax. Acceleration (at 700F) 20.0 gVelocity (at 700 F) 40.0 fpsMax. Rate of Change of 350.0 g/sec

Acceleration (at 700F)Stroke time (Ut 700F) 0.155 secFiritig Method Gas Actuation

3-35


Catapults

PRINCIPAL CHARACTERISTICS (MIO Cont'd)


Action Time, max. (at 70'F) 0.400 sec

Impulse (resultant, at 70 0F) 1100 lb-secPressure, max. 4600 psiIgnition Delay, max. (at 70'F) 0.012 secNozzle Angle 360 20'

3


Catapult, Aircraft Ejection Sout, M10

A 8BC D \GH I J K N MO 0 Li T PR


Component Component

4A Breech, Launcher Trunnion QPin, ShearB Can, Bottom R~ Head, Motor TubeC Holder, Cable Lower S Plug, ShippingD "0,'f Ring T Pin, FiringE Screw, Set U Sleeve, Firing Pit.F Plate, Orifice V Cap, Igniter RetainingG Propellant Grain, IVhibited W Wire, LockH Tube, Launcher X Igniter, Auxiliary AssemblyI Tube, Motor Y Pin, Valve, Shear (4)J Screw (2) Z Cylinder, Slider Valve And

K Washer (2) Tube Booster AssemblyL Sleeve, Head AA Holder, Strip Loade~d AssemblyM Spring, Grain BB Collar, GrainN Piston, Slider Valve CC Nozzle Assembly

40 Igniter, Primary Assembly DD Spring, CanP Ring, Retaining EE Screw Set (4)

____%_ 2.029

- .0

V1,2rO

0.03 +N.06 +00

________ 3.0DI.-A.C

1.505 - 0-4b 40.864 REP 27.BDA4.4954138A

ENVELOPE DRAWING

3.37


Catapult, Aircraft Ejection Seat, M1O

- -PRESSURE TIME RELATIONSHIPi 400 'STANDARD PROPELLED WEIGT =400

3000 C -1-0

000

04 1000

0 50 100 150 200 250 300 350 400 450 500 550 600 650 700

TIME - MILLISECONDS

VELOCITY TIME RELATIONSHIP

NOZZLE ANGLE 36 020STANDARD PROPELLED WEIGHT = 400 -...

TOTAL HEIGHT OF TRAVEL = 237 FT

I I I I

UVELOCITY - 117.6 FT/SEC

VELOCITY = 113.2 FT/SEC

120

1- 00 i / " -\ -160o F-"

0

50 -,---CATAPULT VELOCITY =44.8 FT/SEC

< - -- CATAPULT VELOCITY = 40.0 FT/SEC40 = "".. . -CATAPULT VELOCITY = 34.0 ... I FT/SEC

0 e0 100 150 200 250 300 350 40U 450 500 550 600 650 700

TIME - MILLISECONDS

ACCELERATION TIME RELATIONSHIP

NOZZLE ANGLE 36020 '.r - -.-- STANDARD PROPELLED WEIGHT 400 LB

Z 30 EN O

END OF CATAPULT STROKE

Ix02100 15 200 25I0 I.3ND OF CATAPULT SRK

-65 0F

50 100 150 200 250 300 350 400 450 500 550 600 650 700

TIME - MILLISECONDS

<3.38


Catapults

CATAPULT, AIRCRAFT EJECTION SEAT, XM38

The XM38 catapult is a rocket-assisted two-tube telescoping device developed as a re-placement for the M9 catapult currently installed in the F5/T38 aircraft. The catapult is a two-stage device; the initial booster phase and final rocket motor phase.

The catapult is approximately 42.6 inches long and 3.125 inches in diameter. Thecatapult is ignited by an initiator attached by a length of flexible hese. When the initiator isfunctioned, the gas developed flows through the hose, exerting force against the catapult firingpin. The firing pin is propelled forward and strikes and de onates the primer contained in thebooster cartridge. This action initiates the firing of the booster phase. The primer ignites thepropellant charge contained in the cartridge. The booster tube gas pressure moves a piston,thereby permitting locking keys to be cammed inward, unlocking the unit. Continued booster gasproduction propels the rocket motor and the seat vertically. At the point of booster tube separa-tion, the hot booster gases are introduced into the motor chamber and ignite the rocket propellantgrain. The burning propellant grain produces gas at a high rate, pressurizing the motor chamber.The resulting pressure acts on a piston which rotates the nozzle to a preset position, thus pro-viding thrust which prepals the seat and occupant upward and forward. The nozzle angle whichis controlled by seat position is adjustable from 39 degrees to 52 degrces so as to direct therocket thrust through the center of g'avity of the seat-man combination.


Weight (total assemLly) 33.0 poundsPropelled Weight 363 pounds (50 percentile man)Temperature Iimits -65cF to + 1650 F

Catapult (Booster Section'/

Stroke 34 inchesMax Acceleration (at 700 F) 18 gVelocity (at 700 F) 47 fpsMax Rate of Change of

Acceleration (at 700 F) 300 g/secStroke Time (at 70' F) .170 secFiring Method Gas Actuation

Rocket (Sustain Section)

Action Time, max (at 700 F) A10 secImpulse (resultant ac 700 F) 125G lb-secPressure, average 3200 psiIgnition Delay, max (at 70 ° F) .025 secNozzle Angle Adjustment Range 390 to 520

3-39

, !


Catapult, Aircraft Ejection Seat, XM38

NRS.ETO DRAWIN

B ~I ReesY irLc2

C Cam T "0"' RingD Lug (2) U Tube, BoasterE Sleeve V Tube, MotorF Retainer W Cartridge, Impulse, XM270,G "0" Ring (2) AssemblyH Wisher X Propellant, Grain InhibitedI Tune, Launcher Y Ring, RetainerJ Plate Z "'0" Rini,K Spring, Grain AA "0" RingL Screw BB "0" RingM Screw CC KeyN Pin, Shear DD Nozzle0 Heed EE "0" Ring (2)P PluS&, Shipping FF MountQ "0"f Ring GG Spring Pin

.4905 + I 3.48 + D00 3.125 +.000 DA- 162 +.000

-.0200 -.010 -01

1.78- e8 +.00

.__02__+__005 41.709 MAX -. 03

.502 8 41.546 MIN

ENVELOPE DRAWING

3-40

Pro.Irent Actuatod Jnevicts

Initiators

)6

INITIATORb

Prop)IIant Actuated Devices

Initiators

iNTRODUCTION

Description:

An initiator is an actuating energy source for the operation of the firing mechanisms ofother propellant actuated device components of aircrew escape systems. It is a cylindrical

device consisting of a chamber with a pressure outlet port, a firing mechanism and a cartridge.

Initiator devices are classified in accordance with the following characteristics:

(1) Method of Actuation - mechanical or gas pressure; (2) Function Time - nondelay or delay;and (3) Performance - low or high pressure energy.

Operation:

Actuation of the mechanical initiaeor is accomplished by an axial load application to

the initiator pin. The firing pin, which is locked to the initiator pin with steel balls, compressesthe spring enclosed in the firing pin housing and initiator cap, upon initiator pin withdrawal.When the firing pin enters the relieved section of the spring enclosure, the balls move outward,

disengaging the initiator pin which is withdra.n from the device. The released firing pin is

then propelled against the cartridge percussion primer by the exerted force cf the compressed

spring.

Actuation of the gas-fired initiator is accomplished when gas pressure, supplied byanother propellant actuated device is introduced into the initiator inlet port, exerting a forceagainst the firing pin which is retained in position by a shear pin. The resultant force appli-

cation, causing shearing' of the pin, propels the firing pin against the cartridge percussion primer.

4-1/4.2


In!tiators

INITIATOR, CARTRIDGE ACTUATED, M3A1C

The M3AlC Initiator consists o1 a constant volume chamber with a pressure outlet portincorporating a standard pressure fitting, a mecharacally operated t iring mechanism and an M73Cartridge. A length -f tube or hose connecr the iritiator to another remotely installed propellantactuated device.

Upon cartridge function, the gas produced by the burning of the propellant and blackpowder charge flows through the tube to the gas pressure actuated firing mechanism of the otherpropelJant actuated device, exerting a force which propels the firing pin against the cartridgecontained in that device. The length of the connecting tube and/or hose, or the distance thatthe initiator can be mounted from the other device, is limited by the firing pin energy requiredfor reliable operation of the device.


Actuation Method MechanicalActuation Force 40 lbs. min.Temperature Limits -65'F to +160 0 FAssembled Weight 0.9 lb.Mounting Integral Lugs

TYPICAL PERFORMANCE

Gage Chamber Vol. =.062 in3

Flexible Hose MS 28741.470OF

2 12 6 2

C,.

Tube length (ft)

4.3


Initiator, Cartridge Actuated, M3AJC

CROSS-SECTION DRAWI1NG

Component Component

A Pin, Initiator G Cap, Shi4'pingB Pin, Safety H Retainer, CartridgeC "0" Ring IPin, FiringD Spring, Initiator I Housinj, Firing PinE Balls (3) K Cap, InitiatorF Chamber, Initiator L Cartridge, Initiator, M73 Assembly

Al Seal

1.657 MAX--4.0MA137

.088 4 DsA56C.005 8 I- A

T ~188 +*ODIA+-1 I

.4

SAFTYPI- 2SAK.MINIA

INSERT IN EITHIER POS. 2 110LES

ENVELOPE DRAWING


In!itiators

INITIATOR, CARTRIDGE ACTUATED, M3A2

"he M3A2 Initiator consists of a constant volume chamber wih a pressure outlet port

incorporating a ,tandard pressure fitting, a mechanically operated firing mechanism and an M73Cartridge. A length of tube or hose connects the initiator to another remotely instelled propellantactuated device.

Upon cartridge function. the gas produced by the burning of the propellant and blackpowder charge flows rl -ough tht tube to the gas pressure actuated firing mechanism of the otherpropellant actuated d,. v.ce, exerting a force which propels the firing pin against the cartridgecontained in that device. Thf- length of the connecting tube and/or hose, or the distance thatthe initiator can be mounted from the other device, is limited by the firing pin energy requiredfor reliable operation of the device.


Actuation Method MechanicalActuation Force 40 lbs. min.Temperature Limits -65'F to +160"FAssembled Weight 0.9 lb.Mounting Integral Lugs

TYPICAL PERFORMANCE

Gage Chamber Vol. -. 062 in3

Flexible Hose MS 28741-470OF

C)

6

V:

I: :u 2 F-.

0 4 8 12 16 20

Tube length (ft)

4.5


Initiater, Cartridge Actuated, M3A2

A B C

7 E


Component Component

A Pin, Initiator G Cap, ShippingB Pin, Safety H Retainer, CartridgeC "O" Ring I Pin, FiringD Spring, Initiator J Housing, Firing PinE Ball K Cap, InitiatorF Chamber, Initiator L Cartridge, Initiator, M73 Assembly

M Seal

1.6S7 MAX. f- 4.340 MAX

76- 1.085 MAX.

7 sA .565

3 DIA- 05MAX

.53 088 A DIA

-"Co "

ITI

L mN-

Nil

TRAVEL + "20 UNF- 3A

... ,_)., M, .259 +.o l EA.SAYETY PIN- I.w,7 .29"-

INSERT IN EITHER POS. 2 MOLES

ENVELOPE DR:AWING

4-6

Propellent Actuated Devices

Initiators

INITIATOR CARTRIDGE ACTUATED, DELAY, M4A1

The M4A1 Initiator consists of a constant volume chamber with a pressure outlet Portincorporating a standard pressure fitting, a mechanically operated firing mechanism arid an M46Delay Cartridge. A length of tube or hose connects the initiator to another remotely installedpropellant actuated device.

Upon cartridge function, an M5 Delay Element contoined in the cartridge burns for 2seconds, after which the propellant and black powder are ignited. The gas produced by theburning of the propellant and black powder charge flows through the tube to the g'is ?ressureactuated firing mechanism of the other propellant actuated device, exerting a force which pro-pels th, firing pin against the cartridge contained in that device. The length of the connectingtube and/or hose. or the distance that the initiator can be mounted from the other device, islimited by the firing pin energy required for reliable operation of the device.


Actuation Method MechanicalActuation Force 40 lbs. min.Temperature Limits -65'F to +160'FAssembled Weight 1.0 lb.Delay Time 2.0 seconds

Mounting Integral Lugs

TYPICAL PERFORMANCE


Flexible Hose MS2874".470OF

0o -: I

0.- ii

.i Lllit l +llllliI 1 I -i I I I I 1I . ! I IIII1ES _L i" iilAI4JII

0 2 4 6 8 t0

Tube length (ft.)

4-7

Propellant Actuated Devico,.

Initiator, Cartridge Actuated, Delay, M4A1


Component Component

A Sp:ing, Initiator H Housing, Firing PinB "0" Ring I CapC Sail J Pin, SafetyD Chamber, Initiator K Pin, InitiatorE Cap, Shipping L Cartridge, Initiator,F Retainer, Ca.-tridge Delay M46 AssemblyG Pin, Firing M Seal

4- 1.657 MAX. 5.03 MAX137 4.89 MIN~13 -1.085 MAX.

_DIA --

8 {00 5

_ D I A_ _ {

--- I.&" ,I-- .w-

7

TRAVEL]- -20 UNF- 3A

188 1.002 3,0 A

SAFETY PIN- 250 I NIA

INSERT IN EITHIER POS. 2 HOLES

11 --- lu , H i .

RENVELOPE DRAWING

4-8

• 4


Initiators

INITIATOR, CARTRIDGE ACTUATED, M5A2

The M5A2 Initiator consists of a constant volume chamber with a pressure outlet portinccrporating a standard pressure fitting, a gas pressure actuated firing mechansim and an M73Cartridge. A length of tube or hose connects the initiator to another remotely installed propellantactuated device.

Upon cartridge function, the gas produced by the burning of the propellant and blackpowder charge flows through the tube to the gas pressure actuated firing mechanism of the otherpropellant actuated device, exerting a force which propels the firing pin against the cartridgecontained in that device. The length of connecting tube and/ol hose, or the distance that theinitiator can be mounted from the other device, is limited by the firing pin energy required forreliable operation of the device.


Actuation Method Gas PressureActuation Force 750 psi min.Temperature Limits -65 0 F to +160 0 FAssembled Weight 0.9" lb.

TYPICAL PERFORMANCE


Flexible Hose MS 28741-4-8 700 F00

x6 l

42- I I

I- ' I0 4 8 i2 16 20

Tube length (ft)

4.9

PiopeI1ant Actuated Devices

Initietor, Cartridge Acruated, M5A2

C D EF

BI


Component Component

A Plug, Shipping F Cap, ShippingB Pin, Shear G Chamber, Initiator

C Cap H Fetainer, CartridgeD Pin, Firing I "0" Ring

E Housing, Firing Pin I Cartridge, Initiator, M73 Assembly

411 MAXIMUM LIjNOTHII. I 4.318 MINIMUM LEW2TH

7 L-20~ UNF -38

-M3 MAX

.1- 20 UNr-3A3116

ENVELOPE DRAWING

4-10


Initiators

INITIATOR, CARTRIDGE ACTUATED, DELAY, M6A1

The M6A I Delay Initiator consists of a constant volume chamber with a pressure outletport incorporating a standard pressure fitting, a gas pressure actuated firing mechenism andan M46 Dt.ay Cartridge. A length of tube or hose connects the initiator to another remotelyinstalled propellant actuated device.

Upon cartridge function, an M5 Delay Element contained in the cartridge biv::s for twoseconds, after which the propellant and k1ack powder are ignited. The gas produced by theburning of the propellant and black powder charge flows through &!e tube to the gas pressureactuated firing mechanism of the other propellart actuated device, exerting a force which propelsthe firing pin against the cartridge contained in that device. Thc length of the connecting tubeand/or hose, or the distance that the initiator can be mourted from the other device, is limitedby the firing pin energy required for teliable operation of the device.


Actuation Method Gas PressureActuation Force 750 psi min.Temperature Limits -65*F to +160 0FAssembled Weight 0.9 lb.

TYPICAL PERFORMANCE

Gage Chamber Vol. ,.062 in3

Flexible Hose MS28741-470OF

/4-I

0 4 6 8 I0Tatbe length (ft.)

t.

Praollant Actuated Devices

,nitiator, Cartridge Actuated, Delay, M6A1


Componhent Component

A Pin, Shear G Retainer, CartridgeB Cap H (Housing, Firing PinC tolRn "0" Ring t~D Pin, Firing J Plug ShippingE Cap, 9hipping K Cartridge, Initiator, D ~lay,F Chamber, Initiator M46 Assembly

_________________________8 P06 MAX

1'0190 Ulm

N~e 4

LC

4-12-


Initiators

INITIATOR, CARTIiDGE ACTUATED, M8

The M8 Initiator is a cylindrical constant volume device consisting of a mechanicallyoperated firing mechanism, a chamber and end cap with a pressure outlet port incorporating astandard pressure fitting and an M68 Cartridge. A length of tube or hose connects the initiator toanother rermotely installed propellant actuated device.

Upon cartridge function, the gas produced by burring of the propellant and black powdercharge flows through the tube to the gas pressure actuated firing mechanism of the other propel-

lant actuated device, exertiqg a force which propels the firing pin against the cartridge containedin that device. The length of connecting tube and/or hose, or the distance that the initiator can bemounted from the other device, is limited by the firing pin energy required for reliable operation ofthe device. The MS Initiator is capable of delivering to an .062 in terminal chamber volume at theend of a 30 foot length of MS28741-4 hose, pressure within the limits of 1000 psi minimum and

3000 psi maximum.


Actuation Method MechanicalActuation Force 40 lbs min

Temperature Limits -65'F to +160 0 FAssembled Weight 3.2 lbs.

4-13


Initiator, Cartridge Actuated, MB


Component Component

A Gaide, Firing Pin 3Cap, EndB Spring, Firing K Cap, ShippingC Ball I. BodyD Guide, Firing Pin Ni StrapE Pin, Firing N StandF Screw, Set 0 Wire LockG Cartridge, M468 P Pin, SaetyH "0 " Ring Q Cap, InitiatorI Filter

3-

1.072 MAC .290 + .OOS DIA -1- DIA

.228 DIA + .

Ez +

.15MAX t - I

Ii TRAVEL

ENVELOPE DRAWING

4.4

J1

Propellant Actuated DevicesInitiatory

INITIATOR, CARTRIDGE ACTUATED, M9

The M9 Initiator is a cylindrical constant volume device consisting of a gas pressureactuated firing mechanism, a chamber and end cap with a pressure outlet port incorporating astandard pressure fitting and an M69 Cartridge. A length of tube or hose connects the initiatorto another remotely installed propellant actuated device.

Upon cartridge function, the gas produced by burning of the propellant and black powdercharge flows through the tube to the gas pressure actuated firing mechanism of the other propel-lant actuated device, exerting a force which propels the firing pin against the cartridge containedin that device. The length of connecting tube and/or hose, or the distance that the initiator can bemounted from the other device, is limited by the firing pin energy required for reliable operation ofthe device. The M9 Initiator is capable of delivering to an .062 in3 terminal chamber volume at theend of a 30 foot length of MS28741-4 hose, pressure within the limits of 1000 psi minimum and3000 psi maximum.


Actuation Method Gas PressureActuation Force 750 psi minTem' perature Limits -65'F to +160 0 FAssembled Weight 3.2 lbs.

4.15

------


Initiator, CartrIdga Actuated, M9


Component Componenit

A Cap, Initiator H FilterB Stand I Cap, ShippingC Wire, Lock J Cap, EndD Pin, Firing K BodyE Cartridge, Initiator, L Strap

M69 Assembly M Pin, Shear AndF Screw, Set Screw, SetG "0" Ring

L3_________________ 7.091 MAX

45 6.967 MIN

16 UNF. 3A.565 MAX

.5871290 +.005 DIA. 1321A

1.82 DIA

-7.20UNP~~~ .1 20020 UNF. 3

ENVELOPE DRAWING


J Initiators

INIT:ATOR, CARTRIDGE ACTUATED, DELAY, M1O

The MI0 Delay Initiator consists of a constant volume chamber with a pressure outletport incorporating a standard pressure fitting, a gas pressure actuated firing mechanism and anM70 Delay Cartridge. A length of tube or hose connects the initiator to another remotcly in-stalled propellant actuated device.

Upon cartridge function, an M5 Delay Elemen conained in the cartridge bums for twoseconds, aftet which the propellant and black powder are ignited. The gas produced by the burn-ing of the propellant and black powder charge flows through the tube to the gas pressure actuatedfiring mechanism of the other propellant actuated device, exerting a force which propels the firingpin against the cartridge contained in that device. The length of the connecting tube and/or hose,sr the distance that the initiator can be mounted from the other device, is limited by the firing pin

energy for reliable operation of the device.


Actuation Method Gas PressureActuation Force 750 psi minTemperature Limits -65'F to +160'FAssembled Weight 0.9 lb.Delay Time 2,0 seconds

TYPICAL PERFORMANCE


Flexible Hose MS28741.470OF

-

0 4 8 12 16 20Tube length (ft)

4-17


Initiator, Cartridge Actuated, Delay, M1O


Component Component

A Pin, Shear F Cartridge, Initiator,B "0"~ Ring Delay, M70 AssemblyC Pin, Firing G Retainet, Cartridge

D Cap, Shipping H Housing, Firing PinE Chamber, Initiator I Cap

J Plug, Shipping

.812 .05537±U

16

~M VAX

4184

1Wf~wX

Propellnnt Actuated Devices

Initiators

INITIATOR CARTRIDGE ACTUATED, DELAY, M12AI

The M12AI1 Initiator consists of a constant volume chamber with a pressure outlet portincorporating a standard pressure fitting, a mechanically operated firing mechanism and an M71Delay Cartridge. A length of tube or hose connects the initiator to another remotely installeipropellant actuated device.

Upon cartridge function, an M8 Delay Element contained in the cartridge burns for 1second, after which the propellant and black powder are ignited. The gas produced by theburiiing of the propellant and black powder charge flows through the tube to the gas pressureactuated firing mechanism of the other propellant actuated device, exerting a force which propelsthe firing pin against the cartridge contained in that device. The length of the connecting tubeand/or hose, or the distance that the initiator can be mounted from the other device, is limitedby the firing pin energy required for reliable operation of the device.


Actuation Method MechanicalActuation Force 40 lbs. min.Temperature Limits -05'F to +160 0FAssembled Weight 1.0 lb.Delay Time 1.0 secondMounting Integral Lugs

TYPICAL PERFORMANCE

Gage Chamber Vol. - 062 in3

- Flexible Hose MS28741-470°F

0

20

i ! I I I+H

0 2 4 6 8 !0

Tube length (ft.)

4-49


Initiator, Cartridge Actuated, Delay', M12AI

+ _ _


Component Component

A Spring, Initiator H Housing, Firing Pin

B "0" Ring I CapC Ball J Pin, SafetyD Chamber, Initiator K Pin, InitiatorE Cap, Shipping L Cartridge, Initiator,F Retainer, Cartridge Delay, M71 Assembly

G Pin, Firing M Seal

4 1.657 MAX-P 5.03 MAX13 4.89 MIN

d* g-f - 1.085 MAX.

00 3 VIA -8

r Q 088 316 MAX

TRVE 20N-3

do- 1.261 .259 +.008__ ____ __D__A.

Propellant Actuated Devicos

Initiators

INITIATORS, CARTRIDGE ACTUATED, DELAY, M14

The M14 Delay Initiator, a miniature version of the M45A1 belay Initiator, consists ofa constant volume chamber with a pressure outlet port incorporating a standard pressure fit,'ing, amechanically operated firing mechanism and an M84 Delay Cartridge. A lengthi of tube or ho, econnects the initiato. i another re.aotely installed propellant actuated device.

Upon cartridge function, an M25 Delay Element contained in the cartridge, burns for3 seconds, after which the propellant and black powder are ignited. The gas produced by the burn-ing of the propellant and black powder charge flows through the tube to the gas piessure actuatedfiring mechanism of the other propellant actuated device, exerting a force which propels the firingpin against the cartridge contained in that device. The length of the connecting tube and/or hose,or distance that the initiator can be mounted from the other device, is limited by the firing pinenergy required for reliable operation of the device.


Actuation Method MechanicalActuation Force 40 lbs minTemperature Limits -65'F to +160'FAssembled Weight 0.39 lb.Delay Time 3.0 secondsMounting Integral Lugs

TYPICAL PERFORMANCE

Gage Chamber Vol. =.062 In35 I Flexible Hose M$28741-4

70OF

4 ld iI'lll

0 2G 8 10

Tube length (ft.)

'114.21

Propellant A ctuated Devices

Initiator, Cartridge Actuated, Doloy, M14

A a;


Coteponent Component

A Seal G Pin, FiringB Spring, Initiator H Balls (3)C Housing, Firing Pin I Cap, InitiatorD Filter J Pin, SafetyE Cap, Shipping K Pin, InitiatorF Chamber, Initiator L Cartridge, Initiator, Delay,

M84 Assembly

.O -.o . . , AX --------- M

ACROSS FLATS

-20UNF 3A- TI2005 f5ENVELOPE DRAWING

4-22Cr

C,, .


Initicters

INITIATOR, CARTRIDGE ACTUATED, DELAY, M15

The M15 Delay Initiator, a miniature version of the M44 Delay Initiator, consists of aconstaot volume chamber with a pressure outlet incorporating a standard presst-Te fitting, a gaspressure actuated firing mechanism and an M84 Delay Cartridge. A length of tube or hoseconnects the initiator to another remotely installed propellant actuated device.

Upon cartridge function, an M25 Delay Element contained in the cartridge burns for 3seconds, after which the propellant and black powder are ignited. The gas produced by the burn-ing of the propellant and black powder charge flows through the tube to the gas pressure actuatedfiring mechanism of the other propellant actuated device, exerting a force which propels the firingpin against the cartridge contained in that device. The length of the connecting tube and/or hose,or the distance that the initiator can be mounted from the other device is limited by th firing pinenergy for reliable operation of the devire.


Actuation Method2 Gas PressureActuation Foce 750 psi minTemperature Limits -65'F to + 160'FAssembled Weight 0.39 lb.Delay Time 3.0 secondsMounting Integral Lugs

TYPICAL PERFORMANCE

Gge Chamber Vol. .062 in3

5 Flexible Hlose MS28741.470°F

o __ II i l l l m

4


4.23

3L I K! I I II! I I 1.-

L.I- I I I1i I I I I !


Initiator, Cartligo Actuated, Delay, M15


Component Component

A "0 Ring F Cartridge, Initiator,B Pin, Firing Delay, M84 AssemblyC Chamber, Iniziator G Pin, ShearD Cap, Shipping H Cap, InitiaorE Fix:er I Plug, Shipping

.10 5. 143SNAA

jI-044 Ft- '105 OIA4AA

ENVELOP DRAWIN

4.-04


initiators


The M16 Delay Initiator, a miniature version of the M43 Delay Initiator, consists of aconstant volume chamber with a pressure outlet port incorporating a standard pressure fitting, amechanically operated firing mechanism and an M85 Delay Cartridge. A length of tube or hoseconnects the initiator to another remotely installed propellant actuated device.

Upon cartridge function, an M25 Deiay Element contained in the cartridge, burns for3 seconds, after which the propellant and black powder are ignited. The gas produced by the burn-ing of the propellant and black powder charge flows through the tube to the gas pressure actuatedfiring mechanism of the other propellant actuated device, exerting a force which piopels the firingpin against the cartridge contained in that device. The length of the connecting tube and/or hose,or distance that the initiator can be mounted from the other device, is limited by the firing pin en-ergy required for reliable operation of the device.


Actuation Method MechanicalActuation Force 40 lbs minTemperature Limits -65'F to +.160 0FAssembled Weight 0.39 lb.Delay Time 3.0 secondsMounting Integral Lugs

TYPICAL PERFORMANCE


Flexible Hose MS 28741.4^ e i 70o0 0O

0To tf

x 6

.... flhI , I_ i:H ±± 1Ii !11

4 a 12 16 20Tube length (ft)

4-25


Initiator, Cartridqe Actuated, Delay, M16

A E


Comonent Component

A Seal G Pin, FiringB Spring, Initiator H Balls (3)C Housing, Firing Pin I Cap, InitiatorD Filter J Pin, SafetyE Cap, Shipping K Pin, IritiatorF Chamber, Initiator L Cartridge, Intiator, Delay,

M85 Assembly

64±___ S.2 1.3 M AXDt

.188 #-. 00 2

1.342-405 ?~~2UF3#.- NAIMUM TRAVEL I1.- ::I MA ~ \,93.0 DA

_.1 , MS'mm 2 OLE

ENVELOPE DRAWING

4-26


Initiators

INITIATOR, CARTRIDGE ACTUATED, DELAY, XM17

The XM17 Delay Initiator, a miniature version of the M43 Delay Initiator, consists of a

constant volume chamber with a pressure outlet po. incorporating a standard pressure fitting, a

gas pressure actuated firing mechanism and an M85 Delay Cartridge. A length of tube or hose

connects the initiator to another remotely installed propellant actuated device.

Upon cartridge function, an M25 Delay Element contained in the cartridge, burns for

3 seconds, after which the propellant and black powder are ignited. The gas produced by the burn-

ing of the propellant and black powder charge flows through the tube to the gas pressure actuated

firing mechanism of the other propellant actuated device, exerting a force which propels the firing

pin against the cartridge contained in that device. The length of the connecting cube and/or hose,or distance that the initiator can be mounted from the other device, is limited by the firing pin en-

ergy required for reliable operation of the device.


Actuation LVethod Gas Pressure

Actuation Force 750 psi, min.Temperature Limits -65 0 F to +160 0 F

Assembled Weight 0.39 lb.Delay Time 3.0 secondsMounting Integral Lugs

TYPICAL PERFORMANCE


*_ Flexible Hose MS 28741 4F

071O'- 1 . I l1 ...

x6 +*' II I!I 14 1 I

g 'M II I I tI i 1. I

8 12 1$ 20

Tube length (ft)

4.27

Propellojit Actuated Devices

Initiator, Cartridge Actuated, Delay, XM17


Component Component

A "0" Ring F Cartridge, Initiator,B Pin, Firing Delay, M85 AssemblyC Chamber, Initiator G Pin, ShearD Cap, Shipping H Cap, InitiatorE Filter I Plug, Shipping

--- 0

. 5 .O 435MAX7I

07~07- 20 UNF-3A

~651.O \ -].186 DP, L 1.13 5 MAX 0AJ

' : : \ .,o o, ,.,o.,,o,,

ENVELOPE DRAWING

4-28


Initiators

INITIATORS, CARTRIDGE ACTUATED, DELAY, XM18

The XM18 Delay Initiator, a miniature, vr-±on of the M45A1 Delay Initiator, consists ofa constant volume chamber with a pressure outlet port incorporating a standard pressure fitting, amechanically operated firing mechanism and an XM86 Delay Cartridge. A length of tube or hoseconnects the initiator to another remotely installed propellant actuated device.

Upon cartridge function, an XM23 Delay Element contained in the cartridge, bums for1 second, after which the propellant and black powder are ignited. The gas produced by the burn-ing of the propellant and black powder charge flows through the tube to the gas pressurc actuatedfiring mechanism of the other propellant actuated device, exerting a force which propels the firingpin against the cartridge contained in that device. The length of the connecting tube and/or hose,

or distance that the initiator can be mounted from the other device, is limited by the firing pinenergy required for reliable operation of the device.


Actuation Method MechanicalActuation Force 40 lbs minTemperature Limits -65'F to + 160 0 FAssembled Weight 0.39 lb.Delay Time 1 secondMounting Integral Lugs

TYPICAL PERFORMANCE

Gage Chamber Vol. = .062 in3

5 Flexible Hose MS28741.4070OF

=-~~~ ,-,jiI I I

& 2 4 6 8 10I _ ,,I ,l L, i--- 'Tube length (ft.)

t 4 29




Cemponent Component

A "0" Ring G Pin, SafetyB Pin, Firing H Cap, InitiatorC Chamber, Initiator I Pin, InitiatorD Cap, Shipping J Spring, InitiatorE Filter K Balls (3)F Cartridge, Initiator, L Housing, Firing Pin

Delay XM86 Assembly M Seal

Me MAX~

ACXOSS FLATS*'~~~1 -.- F 546 MAX.020t f 135 AX ofA 867

.188+.002 CIA- K

.!934005 CI

04" INIMUM R~TL. 6%.~ MIN 1 2 OE

~ 1 ENVELOPE DRAWING

I ________________30________________


Initiators

INITIATORS, CARTRIDGE ACTUATED, DELAY, XM19

The XM19 Delay Initiator, a miniature version of the M45A1 Delay Initiator, consists ofa constant volume-chamnber with a pressure outlet port incorporating a standard pressure fitting, agas pressure actuated firing mechanism and an XM86 Delay Cartridge. A length of tube or hoseconnects the initiator to another remotely installed propellant actuated device.

Upon cartridge function, an XM23 Delay Element contained in the cartridge, burns for1 second, after which the propellant and black powder are ignited. The gas produced by the burn-ing of the propellant and black powder charge flows through the tube to the gas pressure actuatedfiring mechanism of the other propellant actuated device, exerting a force which propels the firingpin against the cartridge contained in that device. The length of the connecting tube and/or hose,or distance that the initiator can be mounted from the other device, is limited by the firing pinenergy required for reliable operation of the device.


Actuation Method Gas Pressure

Actuation Force 750 psi, min.Temperature Limits -65°F to + 160'FAssembled Weight 0.39 lb.Delay Time 1 secondMounting Integral Lugs

TYPICAL PERFORMANCE


5 Flexible Hose MS28741-4- 70°F

CL

0

0 2 4 6 a 10

Tube length (ft.)

4-31



CROSS.SECTMON DRAWING

Component Component

A "0" Ring F Cartridge, Initiator,B Pin, Firing Delay, XM86 AssemblyC Chamber, Initiator G Pin, ShearD Cap, Shipping H Cap, InitiatorE Filter I Plug, Shipping

a5.1'455/3g.1.4

.165-,00 5 5-o 00 0 5 -. Z ., 4 1A

7 .T20 U2F-3A

7851~O5O .166 011k 6-.135 MAX DIA

ENVELOPE DRAWING

S 4-32


Initiators


The XM20 Dclay Initiator, a miniature version of the M43A1 Delay Initiator, consists ofa constant volume chamber with a pressure outlet port incorporating a standard pressure fitting, amechanically operated firing mechanism and an XM87 Delay Cartridge. A length of tube or hoseconnects the initiator to another remotely installed propellant actuated device.

Upon cartridge function, an XM23 Delay Element contained in the cartridge, bums for1 second, after which the propellant and black powder are ignited. The gas produced by the burn-ing of the propellant and black powdee charge flows through the tube to the gas pressure actuatedfiring mechanism of the other propellant actuated device, exerting a force which propels the firingpin against the cartridge contained in that device. The length of the connecting tube and/or hose,or distance that the initiator can be mounted from the other device, is limited by the firing pin en-ergy required for reliable operation of the device.


Actuation Method MechanicalAc.tuation Force 40 Ibs minTemperature Limits -650F to +160'FAssembled Weight 0.39 lb.Delay Time 1 secondMounting Integral Lugs

TYPICAL PERFORMANCE

Gage Chamber Vol. w.062 in3

Flexible Hose MS 28741.4700 F

0

21

k - u-


4-33

\ t



J A C


Component Component

A "0" Ring G Pin, SafetyB Pin, Firing H Cap, InitiatorC Chamber, Initiator I Pin, IniiatorD Cap, Shipping J Spring, IniatorE Filter K Balls (3)

F Cartridge, Initiator, L Housing, Firing PinDelay, XM87 Assembly N1 Seal

• 9.--- .755 M9AX

ACROSS FLATS

1.18 .. 546 MAX

-. 020I1.135 MAX WA .

.18 f.0 DIA ;z~

ENVELOPE DRAWING

S434

-20UF-3

.32+0

WCH KNM- TRVE \+ .... --+5 D


Initiators

INITIATOR, CARTRIDGE ACTUATED, DELAI, XM21

The XM21 Delay Initiatoz, a miniature version of the M43A1 Delay Initiator, consists ofa constant volume chamber with a pressure outlet port incorporating a standard pressure fitting, agas pressure actuated firing mechanism and an XM87 Delay Cartridge. A length of tube or hoseconnects the initiator to another remotely installed propellant actuated device.

Upon cartridge function, an XM23 Delay Element contained in the cartridge, burns for1 second, after which the propellant and black powder are ignited. The gas produced by the burn-ing of th2 propellant and black powder charge flows through the tube to the gas pressure actuatedfiring mechanism of the other propellant actuated device, exerting a force which propels the firi:,qpin against the cartridge contained in that device. The length of the connecting tube and/or hose,or distance that the initiator can be mounted from tie other device, is limited by the firing pin en-ergy required for reliable operation of the device. ".


Actuation Method Gas PressureActuati )n Force 750 psi, min.Temperature Limits - 650F to + 160OFAssembled Weight 0.39 lb.Delay Time 1 secondMounting Integral Lugs

TYPICAL PERFORMANCE


Flexible Hose MS22741-4

G0

I I C I 14 11

4 8 2 16 2Tube length (ft)

- _ ilil II til5




Component Compoiaent

A "0" Ring F Cartridge, Initiator,P Pin, Firing Delay, XM87 AssemblyC Chamber, Initiator G Pin, ShearD Cap, Shipping H Cap, InitiatorE Filter I Plug, Shipping

5.1435MAX

II

76 20 UNF -3A\

, I

,c .551 ) ooso fo IN .35MAXD . G A MA -I

ENVELOPE DRAWING

j 4-36

A " ,I'-- -- ' . . . . " +


Initiators


The XM22 Delay Initiator, a miniature version of the M44 Delay Initiator, consists of aconstant volume chamber with a pressure outlet incorporating a standard pressure fitting, a mechanically

operated firing mechanism and an XM88 Delay Cartridge. A length of tube or hoseconnects the initiator to another remotely installed propellant actuated device.

Upon cartridge function, an XM24 Delay Element contained in the cartridge burns for 2seconds, after which the propellant and black powder are ignited. The gas produced by the burn-ing of the propellant and black powder cLarge flows through the tube to the gas pressure actuatedfiring mechanism of the other propellant actuated device, exerting a force waich propels the firingpin against the cartridge contained in that device. The length of the connecting tube and/or hose,or the distance that the initiator can be mounted from the other device is limited by the firing pinenergy for reliable opera:ion of the device.

PRINCIPAL. CHARACTERISTICS

Actuation Method MechanicalActuation Force 40 lbs. min.Temperature Limits -65 0 F to +160 0 FAssembled Weight 0.39 lb.Delay Time 2 secondsMounting Iat.gral Lugs

TYPICAL PERFORMANCE

5 Gage Chamber Vol. -. 062 in3

Flexible Hose MS287410470°F

.. I I I I l . I I I

0 2 4 6 a 10

Tube length (ft.)

4.37


Initiator, Cartriege Actuated, Delay XM22


Component Component

A "0" Ring G Pin, SafetyB Pin, Firing H Cap, InitiatorC Chamber, Initiator I Pin, InitiatorD Cap, Shipping J Spring, Initiator

E Filter K Balls (3)F Cartridge, Initiator, L Housing, Firing Pin

Delay, XM88 Assembly M Seal

-1-- " ° .2815"N'--1I755i VAX

1OSS FLATS

las 1 .342-00

4-38 ENVELOPE DRAWING1 _ 4-

L r


Initiators


The XM23 Delay Initiator, a miniature version of the M44 Delay Initiator, consists of a

constant volume chamber with a pressure outlet incorporating a standard pressure fitting, a gas

pcessure actuated firing mechanism and an XM88 Delay Cartridge. A length of tube or hose

connects the initiator to another remotely installed propellant actuated device.

Upon cartridge function, an XM24 Delay Element contained in the cartridge burns for 2seconds, after which the propellant and black powder are ignited. The gas produced by the burn-

ing of the propellant atd black powder charge flows through the tube to the gas pressure actuatedfiring mechanism of the other propellant actuated device, exerting a force which propels the firing

pin against the cartridge contained in that device. The length of the connecting tube and/or hose,or the distance that the initiator can be mounted from the other device is limited by the firing pinenergy for reliable operation of the device.


Actuation Method Gas PiessureActuation Force 750 psi minTemperature Limits -65"F to +160 0 FAssembled Weight 0.39 lb.Delay Time 2 secondsMounting Integral Lugs

TYPICAL PERFORMANCE


Flexible Hose MS28741.470°F

oo 4 ] ~I i '.1 .ll

. AL I I J H iT -

'~ 2 Tube lengh (ft.),lJJ , , i4'.39



tC


Component Component

A "0" Ring F Cartridge, Initiator,B Pin, Firing Delay, XM88 AssemblyC Chamber, Initiator G Pin, ShearD Cap, Shipping H Cap, InitiatorE Filter I Plug, Shipping

0

Jac, 01A 1.13 5 MAX 01A A

I -itsZ05 .8Oh. 01A MAX-

ENVELOPE DRAWING

4-40


Initiators


The XM24 Delay Initiator, a miniature version of the M43A1 Delay Initiator, consists ofa constant volume chamber with a pressure outlet port incorporating a standard pressure fitting, amechanically operated firing mechanism and an M89 Delay Cartridge. A length of tube or hoseconnects the initiator to another remotely installed propellant actuated device.

Upon cartridge function, an XM24 Delay Element contained in the cartridge, burns for2 seconds, after which the propellant and black powder are ignited. The gas produced by the burn-ing of the propellant and black powder charge flows through the tube to the gas pressure actuatedfiring mechanism of the other propellant actuated device, exerting a for(.e which propels the firingpin against the cartridge contained in that device. The length of the connecting tube and/or hose,or distance that the initiator can be mounted from the other device, is limited by the firing pin en-ergy required for reliable operation of the device.


Actuation Method MechanicalActuation Force 40 lbs minTemperature Limits -65"F to +160'FAssembled Weight 0.39 lb.Delay Time 2 secondsMounting Integral Lugs

TYPICAL PERFORMANCE


Flexible Hose MS 28741.470OF

I I XI I I I

0- f i IIl IiiII{ 41 Hfl1H4 8 12 16 20

Tube length (ft)

4-41

PmoeIant Actuated Devices


CROSS-SECTION DIAWING

Component Component

A "0" Ring GPin, Safety

B Pn, Firing H Cap, InitiatorC Chamber, Initiator I Pin, InitiatorD Cap, Shipping J Spring, InitiatorE Filter K Balls (3)F Cartridge, Initiator, L. Housing, Firing Pin

Delay, M89 Assembly M Seal

-- 5.28M MAX

J 4, 7

ACR 0- c.

46MA

-0 01.13 5 M A X 1A . 7

o tflFi 4

ENVELOPE DRAWING

\4,J


Initiators


The XM25 Delay Initiator, a miniature version of the M43A1 Delay Initiator, consists ofa constant volume chamber with a pressure outlet port incorporating a standard pressure fitting, a

gas pressure actuated firing mechanism and an M89 Delay Cartridge. A length of tube or hoseconnects the initiator to another remotely installed propellant actuated device.

Upon cartridge function,. an XM24 Delay Element conrained in the cartridge, burns for2 seconds, after which the propellant and black powder are Ignited. The gas produced by the burn-ing of the propellant and black powder charge flows through the tube to the gas pressure actuatedfiring mechanism of the other propellant actuated device, exerting a force which propels the firingpin against the cartridge contained in that device. The length of the connecting tube and/or hose,or distance that the initiator can be mounted from the other device, is limited by the firing pin en-ergy required for reliable operation of the device.


Actuation Method Gas PressureActuation Force 750 psi, min.Temperature Limits -65"F to + 160*FAssembled Weight 0.39 lb.Delay Time 2 secondsMounting Integral Lugs

TYPICAL PERFORMANCE

Gage Chamber Vol. -. 062 'iFlexible Hose MS 28741.470OF

0

I I II

11 III0

4 a 12 16 20Tube length (ft)

4.43




Component Component

A "0"p Ring F Cartridge, Initiator,B Pin, Firing Delay, M89, AssemblyC Chamber, Initiator G Pin, ShearD Cap, Shipping H Cap, InitiatorE Filter I Plug, Shipping

w. .14 A~

~1 Lff IIO O0

6T 20 UNF3A\

JBG 01..' 1.135 MAX DIA .G I A

ENVELOPE DRAWING

444

_ _r- -


Initiators


The M26 Delay Initiator consists of a constant volume chamber with a pressure outletport incorporating a standard pressure fitting, a gas pressure actuated firing mechanism and anM90 Delay Cartridge. A length of tube or hose connects the initiator to another remotely insta'dpropellant actuated device.

Upon cartridge function, an M14 Delay Element contained in the cartridge bums for 0.3second, after which the propellant and black powder are ignited. The gas produced by the burningof the propellant and black powder chaige flows through the tube to the gas pressure actuatedfiring mechanism of the other propellant actuated device, exerting a foice which propels thefiring pin against the cartridge contained in tha. device. The length of the connecting tube and/orhose, or the distance that the initiator can be mounted from the other device, is limited by thefiring pin energy required for reliable operation of the device.


Actuation Method Gas PressureActuation Force 750 psi min.Temperature Limits -65'F to +160°FAssembled Weight 0.9 lb.Delay Time 0.3 second

TYPICAL PERFORMANCE


Flexible Hose M$28741-470OF

[ I : IlII F: -

4= . . .4 4I

I I I I I

0 2 4 6 8 1O

-Tube length (ft.)

4.45

Propellant Actuated Dvvic~s

Initiator, Cartridge Actuated, Delay, M26


Component Component

A Pin, Shear G Retainer, CirtridgeB Cap H Housing, Firing PinC Itoff Ring I ef0" RingD Pin, Firing J Plug, ShippingE Cap, -Shipping K Cartridge, Initiator, Delay,F Chamber, Initiator M90 Ausembly

-Pa-0Uf 36-lO I

Lli

ENVELOPE DRAWING

Propellant Artuated Devices

Initiators

I1I4TIATCR, CARTRIDGE ACTUATED, M27

The M27 Iritiator, a miniature version of the M3A1 Initiator, consists of a constant vol-ume chamber with a press.ure outlet port iicorporating a standard pressure fitting, a rechanicallyoperated firing mechanism and an M91 Cartridge. A length of tube or hose connects the initia'or toanother remotely insta~hed propellant actuated device.

Upon cartridge functiun, the gas produced by the burnin% of the propellant add black pow-der charge flows througa the tube to the gas pressure actuated firing mechanism of the other pro-pellant actuated device, exerting a force which propels the firing pin against the cartridge contained in that device. The length of the connecting tube and/or hw.e, or distance that the initiator.an be mounted from the other device, is limited by the firing pin energy required for reliable oper-ation of the device.


Actuation Method MechanicalActuation Zorce 40 lbs minTemperature Limits -65' to + 160'FAssembled Weight 0.33 lb.Mounting Integral Lugs

TYPICAL PERFORMANCE

Gage Chmmber Vol. -. 062 in3

Flexible Hose MS28741.4e 70°F

x 6

4 4L t--L1IU II I0 4 a 12 16 20

1'ube length (ft)

4.47

01* 2 6 2

Prtpetllant Actuated Dtvicos

Intiator, Cartridge Actuctod, M2'


Component C-mpon ent

A Seal H Pin, FiringB Spring, Initiator I BallC Housing, Firing Pin j Cap, InitiatorD Filter K Pin, SafetyE Cap, Shipping L Pin, InitiatorF Chamber, Initiator M Cartridge, Impulse, M91 AssemblyG "0" Ring

.14.14MA

- .I1.14.00? OCIA

.I6 CIAfiM41MIMUU MrS.t .!iM~. A*? MAX CIA]

1. IY

ENVLO E' W NG


Initiators

INITI ATOR, CARTRIDGE ACTUATED, M28

The M28 Initiator, a miniature version of the M5A2 Initiator, consists of a constant vol-time chamber with a pressure outlet port incorporating a standard pressure fitting, a gas pressure

actuated firing mechanism and an M91 Cartridge. A length of tube or hose connects the initiatorto ar.other remotely installed propellant device.

Upon cartridge functivli, the gas produced by the burning of the propellant and black pow-der charge flows through the tube to the gas pressure actuated firing mechanism of the other pro-pellant actuated device, exerting a force which propels the firing pin against the cartridge con-tained in that device. The length of connecting tube and/or h.,se, or the distance that the initiatorcan be mounted from the otber device, is limited by the firing pin energy required for reliable oper..ation of the device.



Actuation Force 750 psi ain

Temperature Limits -65'F to +160 0 FAssembled Weight 0.3 lb.Mounting Integral Lugs

TYPICAL PERFORMANCE


Flexible Hose MS28741.4, 8 70OF

OU- I fI-

IJ)lll I

0. 111'1i"il4 14M 1ALI 8 12 16 20

Tube length (ft)

4-49


Initiator, Cartridge Actuated, M28

CROSS-SECTION~ DRAWING

Comnponent Component

A "0" Ring F FilterB Pin, Firing G Cartridge, Impulse, M9i AssemblyC "0" Ring H Pin, ShearD Chamber, Initiator I Cap, InitiatorE Cap, Shipping JPlug, Shipping

Ii--m 1.752 MAX 4.-5 A .546 MAX

7. 20 UNP -3A 'S

L.625 -8 IACROSS .. 2 .5 A IFLATS 745115 A I

A ~. 20 UNP - 3B

_____________ENVELOPE DRAWING

4.50


Initiators


The M29 Initiator consists of a constant volume chamber with a pressure outlet port

incorporating a standard pressure fitting, a mechanically operated firing mechanism, an M73

Cartridge, an integral arming mechan;sm with a gas intake port and a manual override, and in-tegral mounting lugs. A length of tube or hose connects the initiator to another remotely in-

stalled propellant actuated device.

Actuation of this initiator is accomplished when gas pressure supplied by another pro-pellant actuated device 4s introduced into the intakc port of the arming mechanism, causing the

arming mechanism to disengage with the. preloade'. initiator pin. The sequence of actuation eventsfollowing are the same ris those for the conventional mechanical initiator.

Upon cartridge finction, the gas produced by the burning of the propellant and black pow-

der charge flows through the tube to the gas pressure actuated firing mechanism of the other pro-

pellant actuated device, exerting a force which propels the firing pin against the cartridge contained

in that device. The length of the connecting tube and/or hose, or the distance that the initiator can

be mounted from the other device, is limited by the firing pin energy required for reliable operation

of the device.


Actuation Method Gas Pressure w/manual overrideActuation Force 750 psi minInitiator Pin Preload 40 lbs minManual Override Force 25 lbs minTemperature Limits -65*F to +1601FAssembled Weight 1.75 lbs.

TYPICAL PERFORMANCE


Flexible Hose MS 28741.4: 70OF 2C)'C

X,. 6 : J 7 I I

4I-L11

0' 12 16 20 ! i-Tubellnt (ft) l

I I !' I ] l I i 1, 1.1


Initiator, Cairtridge Actuated, M29

Q E SECIO

SECEO A-AIN -


Component Component

A Gasket J Pin, InitiatorB Balls (3) K Stop, PistonC Retainer, Cartridge L PistonD Cartridge, Impulse, M73 M GasketE Pin, Firing N GasketF Spring, Initiator 0 Spring, r-.xactorG Housing, Firing Pin P Ring, LockingH Gasket Q GasketI Gasket R Gasket

E3 .380 PUN TRAVEL

64 .400 MAX TRAVEL

-' 64

* ta8D+002

-6 20 UN 03

-- 259D 4,0111 2 HOLE6

TRAVZL 5.295 MAX

ENVELOPE DRAWING

4.52


Initiators

INITIATORCARTRIDGE ACTUATED, DELAY, M30A1

The M30A1 Initiator consists of a constant volume chamber with a pressure outlet portincorporating a standard pressure fitting, a mechanically operated firing mechanism and an M70Delay Cartridge. A length of tube or hose connects the initiator to another remotely installedpropellant actuated device.

Upon cartridge function, an M5 Delay Element contained in the cartridge bums for 2seconds, after which the propellant and black powder are ignited. The gas produced by the burn-ing of the propellant and black powder charge flows through the tube to the gas pressure actuated

firing mechanism of the other propellant actuated device, exerting a force which propels the firingpin against the cartridge contained in that device. The length of the connecting tube and/or hose,or the distance that the initiator can be mounted from the other device, is limited by the firing pinenergy required for reliable operation of the device.


Actuation Method MechanicalActuation Force 40 lbs minTemperature Limits -65 0 F to + 160 0FAssembled Weight 1.0 lb.Delay Time 2.0 secondsMounting Integral Lugs

TYPICAL PERFORMANCE

Gage Chamber Val. = .062 in3

7 Flexible Hose MS28741-470°F

0o --o -ttII flI II

0 4 8 12 16 20

Tube length (ft)

4-53


Initiator, Cartridge Actuuted, Delay, M30AI

77 7, g\


Component Component


B "0" Ring I CapC Balls (3) J Pin, SafetyD Chamber, Initiator K Pin, InitiatorE Cap, Shipping L Cartridge, Initiator,

F Retainer, Cartridge Delay, M70 AssemblyG Pin, Firing M Seal

1.657 MAX. - .II U

131 1.085 MAX.

45 j.565

Q.080 3 16 -- 0MAXDIA-

188+O.-DIA 1 tD-A

10

Lie,

4 7

L F 259k DOA.SAFETY PIN- 110I

11SERT IN EITHER POS. 2 HOLES

ENVELOPE DRAWING

4-54


Initiators


The M31 Delay Initiator consists of a constant volume chamber with R pressure outletport incorporating a standard pressure fitting, a gas pressure actuated firing mechan ism and an

M93 Delay Cartridge. A length of tube or hose connects the initiator to another remotely in-


Upon cartridge function, an M8 Delay Element contained in the cartridge burns for 1second, after which the propellant and black powder are ignited. The gas produced by the buming of the propellant and black powder charge flows through the tube to the gas pressure actu-

ated firing mechanism of the other propellant actuated device, exerting a force which propels thefiring pin against the cartridge contained in that device. The length of the connecting tube and/

or hose, or the distance that the initiator can be mounted from the other device, is limited by

the firing pin energy for reliable operation of the device.

PRINCIPAL CHARACTERISTICS'

Actuation Method Gas PressureActuation Force 750 psi min

Temperature Limits -65'F to + 160OFAssembled Weight 0.9 lb.Delay Time 1.0 second

TYPICAL PERFORMANCE


Flexible Hose MS 28741-48 70OF

0

X It

:21Ip1 I H G I4 Ii I'klI ! i J L I -I. J

0 a 12 16

Tube length (ft)

4.55


Initiator, Cartridge Actuated, DeIay,-M31

B

CROSS-SECTION DRAWIMG

Component Component

A Pin, Shear F Cartridge, Imp lscB "0" Ring Delay, M93 AssemblyC Pin, Firing G Retainer, CartridgeD Cap, Shipping H Housing, Firing PinE Chamber, Initiator I Cap

J Plug, Shipping

5.491 MAX5.375 I.iN

SILI

t--f

Aro ao

ENVELOPE DRAWING

4-56


Initiators

INITIATOR,CARTRIDGE ACTUATED, DELAY, M32A1

The M32A1 Initiator consists of a constant v-lume chamber with a pressure outlet port in-corporating a standard pressure fitting, a mechanically operated firing mechanism and an M93Delay Cartridge. A length of tube or hose connects the initiator to another remotely installed pro-pellam actuated device.

Upon cartridge function, an M8 Delay Element contained in the cartridge burns for 1second, after which the propellant and black powder are ignited. The gas produced by the burn-ing of the propellant an-' black powder charge flows through the tube to the gas pressure actuatedfiring mechanism of the other propellant actuated device, exerting a force which propels the firingpin against the cartridge contained in that device. The length of the connecting tube and/or hose,or the distance that the initiator can be mounted from the other device, is limited by the firing pinenergy required for reliable operation of the device.


Actuation Method MechanicalALLiation Force 40 lbs. min.Temperature Limits -65°F to +160 0FAssembled Weight 1.0 lb.Delay Time 1.0 secondMounting Integral Lugs

TYICAL PERFORMANCE

Gage Chaonber Vol. - .062 in3

Flexible Hoso MS28741.470OF

C11

:<6~ ~ I 1_1

qj4 +Pj Il

0 4 8 12 16 20

Tube length (ft)

4-57


Initiator, Cartridge Actuated, Delay, M32AI


coone Component


B "0" Ring I Cap

C Balls (3) J Pin. Safety

D Chamber, Initiator K Pin, InitiatorE Cap, Shipping L Cartridge,

F Retainer, Cartridge Delay, 1493 Assembly


5- . S7 MAX.- S~.320 M&Y '1 ~ 1.085 MAX.41~

4 5 6.p088 3 M6tAX

.188 +00?OIA-1 I

+ 3

ENVE1.C+ LRWN '6 -20UNF- 3A


Initlators

INITIATOR, CARTPIDGE ACTUATED, DELAY, M3

The M33 Delay Initiator consists of a constant volume chamber with a pressure outletport incorporating a standard pressure fitting, a gas pressure actuated firing mechani,.u and ar,M7± Delay Cartridge. A length of tube or hose connects the initiator to another remotely installedpropellant actuated device.

Upon cartridge function, an M8 Delay Element contained in the cartridge burns for 1second, after which .he propellant and black powder are ignited. The gas produced by the burningof the propellant and black powder charge flows through the tube to the gas pressure actuatedfiring mechanism of the other propellant actuated device, exerting a force which propels thefiring pin against the cartridge contained in that device. The length of the connecting tube and/orhose, or the distance that the initiator can be mountel from the other device, is limited by thefiring pin energy required for reliable operation of the device.


Actuation Method Gas PressureActuation Force 750 psi min.Temperatue Lirits -65*F to +160 0 FAssembled Weight 0.9 lb.Delay Time 1.0 second

TYPICAL PERFORMANCE


Flexible Hose MS28741.470OF

4 t, IITl 1iIIJ Ii !I.

-- !! ! !! ! !N_ TT-r-rTT 1"t5 14*

!-1.-LL 4..LIA II I IIi !I J [II I I! iI I ! ./ _1 []I

S0 2 4 6 o

Tube length (ft.)

4-59

Pfromllant Actuatod DvYic.s

In.itiator, Cartridge Actuated, Delay, M33

A B

H K


Component Component

A Pin, Shear G Retainer, CartridgeB Cap H Housing, Firing PinC "0" Ring I "0 ' Ring) Pin, Firing J Plug, ShippingE Cap, Shipping K Cartridge, Initiator, Delay,F Chamber, Initiator M71 Asaembly

*'bI9011 MAX

ITT

Iok-" x

ENVELOPE DRAWING

4-60


Initiators


The M42 Delay Initiator consists of % constant volume chamber with a pressure outletport incorporating a standard pressure fitting, a gas pressure actuated firing mechanism and anM1 13 Delay Cartridge. A length of tube or hose connects the initiator to another remotely in-stalled propellant actuated device.

Upon cartridge function, an M13 Delay Element contained in the cartridge burns for 3seconds, after which the propellant and black powder are ignited. The gas produced by the burn-ing of the propellant and black powder charge flows through the tube to the gas pressure actuatedfiring mechanism of the other propellant actuated device, exerting a force whivh propels the firingpin against the cartridge contained in that device. The length of the connectinj tube and/or hose,or the distance that the initiator can be mounted from the other device, is limited by the firing pinenergy for reliable operation of the device.


Actuation Method Gas PressureActuation Force 750 psi min.Temperature Limits -65*F to +160°FAssembled Weight 0.9 lb.Delay Time 3.0 seconds

TYPICAL PERFORMANCE


Flexible Hose M$28741.470OF

0

x641

I 2 IItI i'iiH i4 I i0 4 8 12 16 20

Tube leqgch (ft)

4-61

I I

Propellant Attuated Devices



Component Component

A Pin, Shear F Cartridge, Initiator,B "0" Ring Delay, Mli 13 AssemblyC Pin, Firing G Retainer, CartridgeD Cap, Shipping H Housing, Firing PinE Chamber, Initiator X Cap

Plug, Shipping

.- 7 MkV "- A MAA

ENVELOPE DRAWING

4.62


Initiators

INITIATOR, CARTRIDGE ACTUATED, DELAY, M43A1

The M43A1 Initiator consists of a constant volume chamber with a pressure outlet port in-corporating a standard pressure fitting, a mechanically operated firing mechanism and an M113Delay Cartridge. A length of tube or hose connects the initiator to another remotely installed pro-pellant actuated device.

Upon cartridge function, an M13 Delay Element contained in the cartridge bums for 3seconds, after which the propellant and black powder are ignited. The gas produced by the burn-ing of the propellant and black powder charge flows through the tube to the gas pressure actuatedfiring mechanism of the other propellant actuated device, exerting a force which propels the firing

pin against the cartridge contained in that device. The length of the connecting tube and/or hose,or the distance that the initiator can be mounted from the other device, is limited by the firing pinenergy required for reliable operation of the device.


Actuation Method MechanicalActuation Force 40 lbs. min.

Temperature Limits -65'F to + 160*FAssembled Weight 1.0 lb.Delay Time 3.0 secondsMounting Integral Lugs

TYPICAL Pr' FORMANCE


Flexible Hose MS 28741.4.-8 70 0 Fa00

< ._j....C. .. . ..

, 12 16 20Tube length (ft)

4-63


Inidoator, Cartridge Actuated, Delay, M43AI

a CE

CROSS-SECT!ON DRAWING

Component Comtonent


B "0" Ring I CapC Balls (3) 1 Pin, SafetyD Chamber, Initiator K Pin, InitiatorE Cap, Shipping L Cartridge,F Retainer, Cartridge Delay, M93 AssemblyG Pin, Firing M Seal

d 1.657 MAX.P0 5..3$0 MA.U13 143 1.85 MAX.

4 _ 565

088- 16 MAX001 -DIA --1884't002DIA 1M

!WN 7TRAVL 2UNF. 3A

SAFEY PN. 259 + O008 DIA.

INSERT VT EITHER POS. 2 HOLZSJ

ENVELOPE DRAWING

4-64

A


Iniflotors


The M44 Delay Initiator consists of a constant volume chamber with a pressure outletport incorporating a standard pressure fitting, a gas pressure actuated firing mechanism and an

M1l14 Delay Cartridge. A length of tube or hose connects the initiator to another remotely installed

propellant actuated device.

Upon cartridge function, an M13 Delay Element contained in the cartridge burns for 3seconds, after which the propellant and black powder are ignited. The gas produced by the

burning of the propeliant and black powder charge flows through the tube to the gas pressureactuated firing mechanism of the other propellant actuated device, exerting a force which propelsthe firing pin against the cartridge contained in that device. The length of the connecting tubeand/or hose, or the distance that the initiator can be mounted from the other device, is limitedby the firing pin energy required for reliable operation of the device.


Actuation Method Gas PressureActuation Force 750 psi min.Temperature Limits -65'F to +160'FAssembled Weight 0.9 lb.

Delay Time 3.0 seconds

TYPICAL PERFORMANCE


5 Flexible Hos% MS28741-4

70OF

4.6

o I...1. _li~_L tI ; I I H'i t t tlI. I!IIII_ TI~ -

!1 i ll lHt 1 1! 1IJl i !I - ~ .li 1I

3 .I 2 4j I l l.! I! 1 1 1F

: III I '1 t!! J!! ! : ! ! ! 4.65I




Component Component

A Pin, Shear G Retainer, CartridgeB Cap H Housing, Firing PinC 't0" Ring I "0"l RingD Pin, Firing j Plug, ShippingE Cap, Shipping K Cartridge, Initiator, Delay,F Chamber, Initiator M114 Assembly

_________________________ 206 MAX

3090 M;N

20 U I-

-u MMAX

4.66


Initiators


The M45A1 Initiator consists of a constant volume chamber with a pr,.ssure outlet portincorporating a standard pressure fitting, a meci'anically operated firing mechanism and an M114Delay Cartridge. A length of tube or hose connects the initiator to another remotely installedpropellant actuated device.

Upon cartridge function, an M13 Delay Element contained in the cartridge bums for 3seconds, after which the propellant and black powder are ignited. The gas produced by theLurning of the propellant and black powder charge flows through the tube to the gas pressureactuated firing mechanism of the other propellant actuated device, exerting a force whichpropels the firing pin against the cartridge contained in that device. The length of the connectingtube and/or hose, or the distance that the initiator can be mounted from the other device, islimited by the firing pin energy required for reliable operation of the device.


Actuation Method MechanicalActuation Force 40 lbs. min.Temperature Limits -65 0 F to +160 0 FAssembled Weight 1.0 lb.Delay Time 3.0 secondsMounting In.egral Lugs

TYPICAL PERFORMANCE


Flexible Hose MS28741-4

70OF

04 2 4 6 8 10

Tube length (ft.)

4.67

Propollent Actuated Devices

Initiator, Cartridge Actuated, Delay, M45A1


Component Component

A Spring, Initiator H Housing, Firing Oin

B "0" Ring I CapC Ball J Pin, SafetyD Chamber, Initiator K Pin, InitiatorE Cap, Shipping L Cartridge, Initiator,

F Retainer, Carcridge Delay, M114 Assembly


0 1.657 MAX- ...5.03 MAX

13 7 4.89 MIN- ~.--------~ 1.085 MAX.

188+w 20DIA 7 -+ ___ DI

1.06s MAD25IA.0 DA

+.ETI ETE 002 2 3OE

ENVELOP DRAWINGA

TRAVE 201N 1


Initiators


The M49A1 Initiator consists of a o.,stant volume chamber with a pressure outlet portincorporating a standard pressure fitting, a mechanically operated firing mechanism and an M90Delay Cartridge. A length of tube or hose connects the initiator to another remotely installedpropellant actuated device.

Upon cartridge function, an M14 Delay Element contained in the cartridge burns for0.2 second, after which the propellant and black powder are ignited. The gas ptiduced by theburning of the propellant and black powder charge flows through the tube to the gas pressureactuated firing mechanism of the other propellant actuated device, exerting a force which propelsthe firing pin against the cartridge contained in that device. The len,- h of the conecting tubeand/or hose, or the distance that the initiator can be mounted from the other device, is limitedby the firing pin energy required for reliable operation of the device.


Actuation Method MechanicalActuation Force 40 lbs. min.Temperature Limits -651F to +160*FAssembled Weight 1.0 lb.Delay Time 0.3 second

Mounting Integral Lugs

TYPICAL PERFORMANCE


5 Flexible Hose MS28741-470OF0

ttmm

fl IflIIiTl'T11 t

0 2 4 6 a 10

Tube length (ft.

4.69

I 1 I I I I I l I --1I I I I I i,


Initiator, Cartridge Actuated, Delay, M49A)

A k C D E

CROSS-SECTION DRAW!NG

Cornponent Component

A Spring, Initiator H Housing, Firing PinB "0" Ring I CapC Ball J Pin, SafetyD Chamber, Initiator K Pin, InitiatorE Cap, Shipping L Cartridge, Initiator,F Retainer, Cartridge Delay, U90 AssemiblyG Pin, Firing M Seal

.657 MAX4.89 MIN

IT-6 1.085 MAX.

~DIA4 156

.088316AX-005 DA

717

.. 261 MAX2I .2+ -130 DIA

INET IN EITHER POS. 2 HOLES

ENVELOPE DRAWING

4.70

Propellant Actunted Devices

Initiators


The M51 Delay Initiator consists of a constant volume chamber with a pressure outlet in-corporatiag a standard pressure fitting, a gas pressure actuated firing mechanism and in M89Delay Cartridge. A length of tube or hose connects the initiator to another remotely installed pro-pellant actuated device.

Upon cartridge function, an XM24 Delay Element contah4ed in the cartridge bums for 2-.onds, after which the propell nt and black powder are ignited. The gas produced by the burn-

ing of the propellant and black powder charge flows through the tube to the gas &ressure actuatedfiring mechanism of the other propellant actuated device, exerting a force which propels the firingpin against the cartridge conta'ned in that device. The length of the connecting tube and/or hose,or the distance that the initiator can be mounted trom the nther device is limited by the firing pinenergy for reliable operation of the device.


Actuation Method Gas PressureActuation Force 750 psi min.Temperature Limits -65°F to +160'FAssembled Weight 0.39 lb.Delay Time 2.0 secondsMounting Integral Threads

TYPICAL PERFORMANCE

Gage Chamber Vol -. 062 in3

Flexible Hose M$28741.470°F

0

o I : , Iii V I li.- ,~~4 I IiIIII44II

8 12 1I 20Tube length (ft)

4-71

4r

eI i l i I I ! I I i




Component Component

A "0" Ring H Cartridge, Initiator, Delay,B Pin, Firing M89 AssemblyC "0" Ring 1 "0" RingD Screw, Set J Cap, InitiatorE Filter K Pin, ShearF Cap, Shipping L Plug, ShippingG Chamber, Initiator

5.1435 MAX

1.752 MAX -. 546 MAX

.305 +.010 - .70S-.020 7

.866 MAX DIAoi.G26 - o0s

-U J A.CROSS FLA ,T 1.135 MAX DIA

ENVELOPE DRAWING

' 4-72


Initiators


The M52 Delay Initiator consists of a constant volume chamber with a pressure outlet

port incorporating a standard pressure fitting, a mechanically operated firing mechanism and an

M128 Delay Cartridge A length of tube or hor - connects !he initiator to another remotely in-


Upon cartridge function, an M27 Delay Element contained in the cartridge, burnsfor 5seconds, after which the propellant and black powder are ignited. The gas produced by the barn-

ing of the propellant and black powder charge flows through the tube to the gas pressure actuatedfiring mechanism of the other propellant actuaed device, exerting a force which propels the firing

pin against the cartridge contained in that device. The length of the connecting tube and/or hose,or distance that the initiator can be mounted from the other device, is limited by the firing pinenergy required for reliable operation of the device.

PrINCIPAL CHARACTERISTICS

Actuation Method MechanicalActuation Force 40 lb. min.

Temperature Limits --651F to f- 1 60'FAssembled Weight 0.39 lb.Delay Time 5.0 seconds

Mounting Integral Threads

TYPICAL PERFORMANCE

Gage Chamber Vcl. -.062 in3

--- EFlexible Hose MS 28741.4--. 70OF

--- .4..

". - - ,--,

4 C I-4 -. EE .

,m - '- II

it0 4 8 12 16 20

Tube length (ft)

4-73

PropelIan, Actuated Devi, es


.- -- ~ - - -7 -. . . . --,


Component Component

A Seal H1 Pin, FiringB Spring, Initiator I BallC Housing, Firing Pin J Cap, InitiatorD Filter K Pin, SafetyE Cap, Shipping L Pir ImpulseF Chamber, Initiator M Cartridge, Delay, M!28G "0" Ring

-1QS A DIA, .196 +00a MIA ~2UIW5KAAX 01k.

Ma

10, - %A,

Mk' .54GMAY.

Z.IG7 AC.a

ENVELOPE DRAWING

4-74

I


Initiotois

4 INITIATOR, CARTRIDGE AC rUATED, M53

The M53 Initiator, a miniature version of the M3A2 Initiator, consists of a constant vol-ume chamber with a pre:'sure outlet port incorporating a standard pressure fitting, a gas pressureaccuated firing mechanism and an M91 Cartridge. A length of tube or hose connects the initiator toanother remotely installed propells ,t actuated device.

Upon cartridge function, the gas produced by the burning of the propellant and black pow-der charge flows throug, rl-e tube to h, gas pressure actuated firing mechanism of the other pro-pellant actuated device, - .-rting a force which propels the tiring pin against the cartridge con-tained in that device. The length of the connecting tube and/or ho:e, or distance that the initiazorcan be mounted from the other device, is limited by the firig pin energy required for reliable oper-ation of the device.


Actuation Method Gas PressureActuation Force 750 psi, minTemperature Limits - 65' to + 160'FAssembled Weight 0.33 lb.Mounting Integral Lugs

TYPICAL PERFORMANCE

Gag# Chamber Vol. = .062 ir3

Flexible Hose MS28741-4.70OF

0 -- , - - -

0

2 E L I IIII I

0 8 .12 16 20

Tube length (ft)

4.75

Ptopellant Actuated D~evices



Component Component

A "0'" Ring G Chamber, Initiator

B Pin, Firing H Cartridge, ImpulseC Plug, Shipping N191 AssemblyD Screw, Set 1 "0" RingE F ilter J Cap, InitiatorF Cap, Shipping K Pin, Shear

4 0185S MAX

-C - 1.752 MAX -. 546 MAX

.305 +.010 .705 - .020 7 2UN-J

T 16

.875 MAX DIA

.625 .0151. 135 MAX DIA16 UNFACROSFLATS

ENVELOPt DRAWING

4-76


Initiators


The M54 Delay !nitiator consists of a constant olumc chamber %ith a pressuie outletport incorporating a standard presure :itting, a mechanically operated firing mechanism and anM128 Delay Cartridge. A length of tube or hose connects the initiator to another remotely in-stalled propellant actuated device.

Upon cartridge function, an M27 Delay Element contained in the cartridge, burns for5 seconds, after which thL. propellant and black powder are ignited. The gas produced by the burn-ing of the propellant and black powder charge flows through the tube to the gas pressure actuatedfiring mechanism of the other propellant actuated device, exerting a force which propels the firingpin against the cartridge contained in that device. The length ol the connecting tube and/or hose,or distance that the initiator can be mounted from the other device, is limited by the firing pin en-ergy required for reliable ope-ation of the device.


Actuation Method MechanicalActuation Force 40 lbs min

Temperature Limits -65'F to 4 160'FAssembled Weight 0.39 lb.Delay Time 5.0 secondsMounting Integral Lugs

TYPICAL PERFORM NCE

Gage Chaibe- Vol. = .062 in3

Flexible Hose MS28741.48 - -- 70OF

C

-4

X J I I I I I I l

I I W I 4I

0 4 8 12 16 20

Tube length (ft)

4-77



K. L


Component Component

A Seal G Pin, FiringB Spring, Initiatc.r H Balls (3)C Housing, Firing Pin I Cap, InitiatorD Filter J Pin, Safety

E Cap, Shipping K Pin, InitiatorF Cham, r, Initiator L Cartridge, Delay, M128

1.755 MAX

' .t--hi.5 -. 50-0#

ACROSS FLATS I

If 2 .,'- ti-4 ~6 1.HJNMt tR5V MA DI -. 6M67;')1+05

5 42-005 2UF3

43 le MV 2 AOL

5

ENVELOPE DRAWING

4-78

>


Initiators


The XM64 Delay Initiator consists of a constant volume chamber with a pressure outlet in-corporating a standard pressure fitting, a mechanically operated firing mechanism and an XM148Delay Cartridge. A length of tube or hose connects the initiator to another remotely installed pro-pellant actuated device.

Upon cartridge function, an XM44 Delay Element contained in the cartri.lge burns for 3/4second, after which the propellant and black powder are ignited. The gas produced by the burn--ng of the propellant and black powder charge flows through the tube to the gas pressure actuatedfiring mechanism of the nther propellant actuated device, exerting a force which propels the firingpin against the cartridge contained in that device. The length of the connecting tube and/or hose,or the distance that the initiator can be mounted from the other device is limited by the firing pinenergy for reliable operation of the device.


Actuation Method ?echanicalActuation Force 40 lbs. min.Temperature Limits -65'F to 4 160'FAssembled Weight 0.39 lb.Delay Time 3/4 secondMounting Integral Threads

TYPICAL PERFORMANCE

1 Gage Chamber Vol. = .062 in3

Flexible Hose MS 28741.48 BJ 70o9

0 4 8 12 16 20

'rube length (ft)

4-19


Initiator, Cartridge Actuated, Delay, YA64


Component Component

A Seal G Pin, FiringB Spring, Initiator H Balls (3)C Housing, Firing Pin I Cap, InitiatorD Filter J Pia, SafetyE Cap, Shipping K Pin, InitiatorF Chamber, Initiator L Cartridge, Initiator, XM148

M "0" Ring

-5.167 MAX-

It75 MAX

+' W -. 546 MAX

N'R~0 -M 0IA 115 MAX DIA .867

f-2.OUNF- 3A

3-4H,hIVUM 7RAVEL - 0----

ENVELOPE DRAWING

4.80


Initiators


The M72 Delay Initiator consists of a constant volume chamber with a pressure outletport incorporating a standard pressure fitting, a gas pressure actupted firing mechanism and anM155 Delay Cartridge. A length of tube or hose connects the initiator to another remotely in-stalled propellant actuated device.

Upon cartridge function, an M28 Delay Element contained in the cartridge bu.ns for 1/2second, after which the propellant and black powder are ignited. The gas produced b, the burn-ing of the propellant and black powder charge flows through the tube to the gas pressure actuatedfiring mechanism of the other propellant actuated device, exerting a force which propels the firingpin against the cartridge contained in that device. The length of the connectipg tube and/or hose.or the distance that the initiator can be mounted from the other device, is limited by the firing pinenergy for reliable operation of the device.

PRINCIPAL CH kRACTERISTICS

Actuation Mehod Gas PressureActuation Force 750 psi minTemperature Limits -65 0 F to +200' FAssembled Weight 1.0 lb.Delay Time 1/2 secondMounting Integral Lugs

TYPICAL PERFORMANCE


Flexible Hose MS28741.470°F

1 1,,1 1 1? L I I I I I I " I IT

' Liii,,,i$4! tI I!ill II~-

0 4 8 12 16 20

Tube length (ft)

4-81


Inilator, Cartridge Actuated, Delay, M72

tK


Com.poncnt Component

A Pin, Shear F Cartridge, Initiator,B "0" Ring Delay, M155 AssemblyC Pin,., Firing G Retainer, CartridgeD Caji, Shipping H1 Housing, Firing PinE Cnamber, Initiator I Cap

J Plug, Shipping

K Set Screw

F~~ 1) DIA M

"20U - 2 HOLE

G~~~56 MAXMt'A~

4.82


Initiators


The M80 Initiator is a sealed M9 type Initiator which restricts toxic gas leakage to pre-vent atmospheric contam~ination exceeding concentration limits safe for human occupancy in en-capsulated environments. It consists of a gas pressure actuated firing mechanism, a chamber andend cap witn a pressure outlet port incorporating a standard pressure fitting and an M69 Cartridge.A length of tube or hose connects the initiator to another remotely installed propellant actuateddevice.

Upon cartridge function, the gas produced by burning of the propellant and black powdercharge flows thrvug the tube to the bas pressure actuated firing mechanism of the other propellantactuated devict., exerting a force which propels the firing pin against the cartridge contained inthat device. The length of the connecting tub- and/or hose, or the distance that the initiator canbe mounted from the other device, is limited by the firing pin energy required for reliable operation

of the device. The M80 Ini-iator is capable of delivering to an .062 in3 terminal chamber volumeat the end of a 30 foot length of MS28741-4 hose, pressure within the limits of 1000 psi minimum

and 3000 psi maximum.


Actuation Method Gas PressureActuation Force 750 psi min.

Temperature Limits -65 0 F to + 160'FAssembled Weight 3.2 lbs.

4-83

Propellant Ac uated -Devices


I G


Component Component

A Cap, Shipping F CapB Pin, Firing G Cap, ShippingC t"0" Ring H Fil terD Cap, initator 1 "0" RingE Body J Cartridge, Initiator, M69 Assembly

7.091 MAYJ

z.7 I

-- 5 .OlktA I L IA

r-.8 -zour-

ENEOE7RWN

4-84-


Initiators


The M86 Initiator consists of a constant volume chamber with a pressure outlet portincorporating a standard pressure fitting, a mechanically operated firing inechanism and an' M169Cartridge. A length of tube or hose connects the initiator to anothei remotely installed propellantactuated device.

Upon cartridge function, the gas produced by the burning of the propellant and black pow-der charge, flows through the tube to the gas pressure actuated firing mechanism of the other pro-pellant actuated device, exerting a force which propels the firing pin against the cartridge con-tained in that device. The length of the connecting tube and/or hose, or distance that the initiatcrcan be monted from the other device, is limited by the firing pin energy required for reliable oper-ation of the device.


Actuation Method MechanicalActuation Force 40 lbs. min.Temperature Limits -65OF to + 160'FAssembled Weight 0.3 lb.Mounting Integral Thread

TYPICAL PERFORMANCE


SFlexble Hose MS28741-470°F

o4o

zIXtH HI f J

.I _I.I I I I I I I I III0 2 4 6 8 10

Tube length (ft.)

4.85


Initiator, Cartrilge Actuatedi, M86


Component Component

A Seal H Pin, Firing

B Spring, Initiator I BallC Housing, Firing Pin J Cap, Initiator

D Filter K Pin, SafetyE Cap, Shipping L Pin, Initiator

F Chamber, Initiator M Cartridge, Impulse, M169

G "0", Ring

[ I.IBS MVIXI IA. 156.002 Di . z wr s.~MAX IlA~.

.706, -. 020

MINA-7 b.v4G MAY

ENVELOPE DRAWING

4.86


Initiators


The M87 Initiator is a sealed M27 type Initiator which restricts coxic propellant gasleakage to prevent atmospheric contaminaion exceeding concentration limits safe for humanoccupancy in encapsulated enironments. It consists of a constant volume chamber with a pres-sure outlet port incorporating a standard pressure fitting, a mechanically operated firing mechan-ism and an M173 Cartridge. A length of tube or hose connects the initiator to another remotelyinstalled propellant actuated device.

Upon cartridge function, the gas produced by the burning of the propellant and blackpowder charge flows through the tube to the gas pressure actuated firing mechanism of the otherpropellant actuated device, exerting a force which propels the firing pin against the cartridgecontained in that device. The length of the connecting tube and/or hose, or distance that theinitiator can be mounted from the other device is limited by the firing pin energy required forreliable operation of the device.


Actuation Method MechanicalActuation Force 40 lbs. min.Temperature limits -65OF to + 160'FAssembled Weight 0.33 lb.Mounting Integral Lugs

TYPICAL PERFORMANCE

Gage Chamber Vol. - .062 in3

[" Flexible Hose MS28741.4.-, 8 70OFD _ _..'.. .

"I I' IA 'J N i l i ~~: 1 il ._

1 1. I I II F 1444 1

0 4 8 12 16 20

Tube length (ft)

4-87

C.

Propellant Actuated Dovicez



Component Component

A Seal G Pin, FiringB Spring, Initiator H BallC Housing, Firing Pin I Cap, InitiatorD Filter J Pin, SafetyE Cap, Shipping K Pin, InitiatorF Chamber, Initiator L Cartridge, Impulse, M173

4.033klAX - ."L.06 , -. OO

±. 1.135 MAX IA - .6MAX

nI4H MINIMUM 7R~L -

i t MIN 2 4 lO tS

.185.00 OIA MMi01.

I.IENVELOPE DRAWING

4.88

Propellant ActLated Devices

In iators


The M88 Initiator is a sealed M51 :ype Initiator wh;ch restricts toxic propellant gas

leakage to prevent atmospheric contamination exceeding concentration limits safe for human

occupancy in encapsulated environments. It consists of a constant volume chamber with a pres-

sure outlet port incorporating a standard pressure fitting, a gas pressure actuated firing mechan-ism and an M174 Delay Cartridge. A length of tube or hose connects the initiator to ariother re-

motely installed propellant actuated device.

Upon cartrtdge function, an XM24 Delay Element contained in the cartridge burns for 2seconds, after which the propellant and black powder are ignited. The gas produced by the burn-ing of the propellant and black powder charge flows through the tube to the gas pressure actuatedfiring mechanism of the other propellant actuated device, exerting a force which propels the firingpin against the cartridge contained in that device. The length of the connecting tube and/or hone,or the distance that the initiator can be mounted from the other device is limited by the firing pinenergy required for reliable operation of the device.


Actuptioi, Method Gas Pressure

Actuation Force 750 psi, min.

Temperature Limits -65'F to +160 0 FAssembled Weight 0.39 lbs.Delay Time 2.0 secondsMounting Integral Threads

TYPICAL PERFORMANCE

UT-1 Gage Chamber Vol. ,.062 in3

S1.Flexible Hose MS 28741.470OF

I

' J1tfluiI:lU41 iii I I I I

4 8 12 16 20

Tube length (ft)

4o89

I I


Initiator, Cartridge Actuated, Deloy, M88

K D O


Component Component

A "0" Ring G Chamber, Initiator

B Pin, Firing H Cartridge, Initiator, Delay,C Plug, Shipping N1174 AssemblyD Screw, Set 1 "0"1 Ring

E Filter j Cap, Initiar_F Cap, Shipping K Pin, Shear

_________________________-5.1435 MAX

-N 1.752 MAX .546 MAX

.305 +010---.705 - .0207

.866 MAX DIA

1.OOFAT 1. 135 MAX DIA

ENVELOPE DRAWING

4.90


initiators

INITIATOR, CARTRIDGE ACiUATED, DELAY, M89

The M89 Initiator is a sealed M54 type Initiator which restricts toxic gas to preventatmospheric contamination exceeding concentration limits safe for human occupancy in encap-sulated environments. It consists of a constant volume chamber with a pressure outlet port i,,-corporating a standard pressure fitting, a mechanically operated firing mechanism and an MI.Delay Cartridge. A lel.bth of tube or hose connects the initiator to another remotely installedpropellant actuated device.

Upon cartridge function, an M27 Delay Element contained in the cartridge burns for5 seconds, after which the propellant and black powder are ignited. The gas produced by theburning of the propellant and black powder charge flows through the tube to the gas pressureactuated firing mechanism of the other propellant actuated device, exerting a force which pro-pels the firing pin against the cartridge contained in that device. The length of the connectingtube and/or hose, or the distance that the initiator can be mounted from the other device islimited by the firing pin energy required for reliable operation of the device.


Actuation Method MechanicalActuation Force 40 lbs. min.Temperature Limits -65"F to + 160'FAssembled Weight 0.39 lb.Deley Time 5.0 secondsMounting Integral Lugs

TYPICAL PERFORMANCE

-i U Gag* Chamber Vol. -. 062 in3

Flexible Hose MS 28741-4-. 8 - 70OF

0

X 6

o , ; ll,_9i;=~

0 4 8 12 16 20Tube lengh (ft)

4-91

I I I.I



\AE

Q Oo

!= / /

CROSS.SECTION DRAWING

Component Component

A Seal H BallB Spring, Initiator I Cap, Initiator

C Housing, Firing Pin J Pin, SafetyD Filter K Pin, InitiatorE Cap, Shipping L Cartridge, Delay, M175 Assembly

F Chamber, InitiatorG Pin, Firing

5467 MAX

1115 ACROSS FLATS

.. -- ,,,35MAXDIA .546 MAX

,, A,

u- _60,-

MAX DIA -- 20W4-3A

ENVELOPE DRAWING

' 4-92

Proppllant Actuated Devices

Initiators

INITIATOR, CARTrIDGE ACTUATED, M98

The M98 Initiator consists of a constant volume chamber witv a pressure outlet portincorporating a standard pressure fitting, a mechanically operated firing mechanism and an XM201

Cartridge. A length of tube or hose connects the initiator to another remotely in.called propellantactuated device.

Upon cartridge function, the gas produced by the burnig of the propellant and blackpowder charge flows through the tube to the gas pressure actuated firing mechanism of the otherpropellant actuated device, exerting a force which propels the firing pin against the cartridgecontained in that device. Tne lergth of the connecting tube and/or hose, or t):' distance thatthe initiator can be mounted from the other device, is limited by the firing pin energy requiredfor reliable operation of the device.


Actuation Method MechanicalActuation Fo,-ce 40 lbs. min.Temperature Limits -65'F to +160'F

Acsemb!ed Weight 0.9 lb.Mounting Integral

TYPICAL PERFORMANCE

G agt Chamber Vol. =.062 in3

Flexible Hose MS 287414-

70O

2 -- lIl1IIII1 : : _ _

, ]1 I' "** I i I I


4-93

) £

Propellant Actuaot*d Devices


A B M d~

CROS$-SECTION DRAWING

Component Component

A Seal H Balls (3)B Spring, Initiator I Cap, InitiatorC Housing, Firing Pin JPin, SafetyD Filter K Pin, InitiatorE Cap, Shipping L Cartridge, Initiator,F Chamber, Initiator XM201 AssemblyG Pin, Firing M "0" Ring

4.033 MAX

.oe50.ool

*"~ 1~ ~ Ils AftSSFLr--"'.35 MAX DIA .--54604AX

oe 1 -.QZ -- &-

MAX DA Z.3

ENVELOPE DRAWING

4-94

A


Initiators


The M99 Initiator, a miniature version of the M3A2 Initiator, consists of a constant vol-ume chamber with a pressure outlet port incorporating a standard pressure fitting, a meLhanicallyoperated firing mechanism and an M91 Cartridge, A length of tube or hose connects the initiator toanother remotely installed propellant actuated device.

Upon cartridge function, the gas produc, I 1, the burning of the propellant and black pow-der charge flows through the tube o the gas pressure actuated firing mechanism ot the other pro-pellant actuated device, exerting a force which propels the firing pin against the cartridge con-tained in that device. The length of the connecting tube and/or hose, or distance that tuie initiatorcan be mot.ated from the other device, is limited by the firing pin energy required for reliable oper-ation of the device.


Actuation Method MechanicalActuation Force 40 lbs minTemiperature Limits -65' to + 160°FAssembled Weight 0.33 lb.Mounting Integral Lugs

TYPICAL PERFORMANCE


Flexible Hose MS 28741-48 70OF

4 6

2I

0 4 8 12 16 20Tube length (ft,

4-95




Component Component

A Seal G Pin, FiringB Spring, Initiator H Balls (3)C Housing, Firing Pin I Cap, InitiatorD Filter J Pin, Safety

E Cap, Shipping K Pin, IritiatorF Chamber, Initiator L Cartridge, Impulse

M91 AssemblyM "0,Ring

-4.156 UAX

1.7') MAX

705 to, 546 MAX

88 6 002 0A

-20VNF 3A

INCH MINIMUM TRAVEL-

ENVELOPE DRAWING

4-96


Initiators

INITIATOR, CARTRIDGE ACTUATED, XMI07

The XM107 Initiator, a miniature version of the M3A2 Initiator, consists of a constant vol-ume chamber with a pressure outlet port incorporating a standard pressure fitting, a mechanicallyoperated firing mechanism and an M91 Cartridge. i length of tube or hose connects the initiatoi toanother remotely installed propellant actuated device.

Upon cartridge function, the gas produced by the bi.:ning of the propellant and black pow-der charge flows through the tube to the gas pressure actuated firing mechanism of the other pro-pellant actuated device, exerting a force which propels the firing pin against the cartridge con-tained in that device. The length of the connecting tube and/or hose, or distance that the initiatorcan be mounted from the other device, is limited by the firing pin energy required for reliable oper-

ation of the device.


Actuation Method MechanicalActuation Force 40 lbs minTemperature Limits - 650 to + 160OFAssembled Weight 0.33 lb.Mounting Integral Lugs

TYPICAL PERFORMANCE


Flexible Host MS 28741-470°F

0

46 . 4 :1- I P

I II- I - i

0 4 8 12 16 20Tube length (t)

4-97



II L


Component Component

A Seal G Pin, Firing

P3 Spring, Initiator H Balls (3)

C Housing, Firing Pin I Cap, Initiator

D Filter J Pin, CotterE Cap, !3hipping K Pin, Initiator

F Chamber, Initiator L Cartridge, Impulse, M91 Assy

M "0" RingN Set Screw

4.1575 MAX-

1.755 MAX

1,.o135 + -'1.35 32 64 3/8

+. ,004 ,, -

37 ti 00 1.135 MAX CIA .46 7

.188 +.002 DIA .86

-20UNF-3 A.750-.015 DIA " 342 -.005 .62-5-.010

3/4 INCH MINIMUM TRAVEL ACROSSPLATS

ENVELOPE DRAWING

4.98

Propellant Actuated Devicer

Initiators

INITIATOR, CARTRIDGE ACTUATED, DELAY, XM11O

The XM1l0 Delay Initiator, a miniature version of the M44 Delay Initiator, consists of aconstant volume chamber with a pressure outlet incorpoiating a standard pressure fitting, a gaspressure actuated firing mechanism and an XM271 Delay Cartridge. A length of tube or hoseconnects the initiator to another remotely installed propellant actuated device.

Upon cartridge function, an XM69 Delay Element contained in the cartridge burns for 1.4seconds, after which the propellant and black powder are ignited. The gas produced by the burn-ing of the propellant and black powder charge flows through the tube to the gas pressure actuatedfiring mechanism of the other propellant actuated device, exerting a force which propels the firingpin against the cartridge contained in that device. The length of the connecting tube and/,or hose,or the distance that the initiator can be mounted from the other device is limited by the firing pinenergy for reliable operation of the device.



Actuation Force 750 psi minTemperature Limits -65"F to +160 0 FAssembled Weight 0.39 lb.Delay Time 1.4 secondsMounting Integral Lugs

TYPICAL PERFORMANCE

5 Gage Chamber Vol. = .062 in3

Flexib!e Hose MS28741.470OF

CD

--1 1 1 tI i -j I I I I 'I I I Ii l l 1 1 1

W % 1 14 Il 1 11 ILJJL .

3 I I

~~~

2 4i 6 ii I I

Tube length (ft.)

4.99

j, IIl ll ~ 11I

Propellart Actuated Devices

initiator, Cartridge Actuated, Delay, XMl 10


Component Component

A "0" Ring F Cartridge Delay,B Pin, Firing XM271 AssemblyC Chamber, Initiator G Pin, ShearD Cap, Shipping H Cap, InitiatorE Filter I Plug, Shipping

a 5. 1435 MAX

00 /.z -4 44

.625 I ~. 20 UNF.3A .

[*7655t0050 .8br 01A~~ I MAX

ENVELOPE DRAWING

4-100

Propellant Actuated Devlcts

Cutters

* SECTION V

CUTTERS


Cutters

INTRODUCTION

Description:

A cutter is a Propellant Actuated Device that is used in aerial delivery systems for

cargo and drone recovery, or to sever wires or cables.

Cutters are classified in accordance with the following characteristics: (1) Method of

Actuation-mechanical or gas pressure, and (2) Function Time-nondelay or delay.

Operation:

Actuation of the mechanical cutter is accomplished by applying a pull force to thecable or lanyard with seat attached. The lanyard seat is engaged in the firing pin; therefore, thepull of the lanyard applies a load to the firing pin spring. Compression of the firing pin spring andthe release of the firing pin are accomplished with one motion when the firing pin moves rear-ward. The sear moves outward to the section having an enlarged internal diameter, which then

permits the sear to move sideward to release t'ie firing pin. The firing pin is propelled forwardunder the actuation of a spring force and strikes the primer, which ignites the delay element, ifapplicable, and then the propellant. Under the force of the propellant gas pressure, the cutterblade separates from the cartridge case and is propelled into the bore of the housing. The wires

or cables are severed when the blade impacts the anvil.

5-1/5-2


Cutter

CUTTER M8

The M8 Cable Cutter is a component part of an aircraft escape system whose purposeis to sever wires or cables prior to implementing the escape procedure of aircraft personnel

from the aircraft. The cutter is capable of severing either a bundle of coaxial cables or abundle of wires. The blade of the cutter is c:ated to prevent shorting as the blade passes

through the cables or wires.

The cutter is cylindrical in shape, approximately 5.8 inches long and -. 3 inches indiameter. The blade of the cutter is held in position by a "shear pin" which will shear in+

double shear when a load of 2160-200 pounds is applied.

The cutter incorporates a propellant gas operated firing mechanism. It is actuatedby gas pressure supplied from another propellant actuated device.


Stroke 1.25 inches

Assembled Weight .75 lbs.*Blades average depth of

penetration into anvil whenfired at 70'F .004 inches

Firing Method Propellant GasTemperature Limits -65'F to +200'FMaterial Severed

Cable Assembly .060 inch thick vinyl sheath around

9 RG-62 A/u Coax Cables (MIL-C-17/30)

Wire Bundle .060 inch thick vinyl sheath around

27 stands #22 wire (MIL-TW-8777)6 strands #18 wire (MIL-W-8777)8 strands #20 wire (MIL-W-12349)

* Depth of penetration of the blade into the anvil is a rough measure of the kinetic energy

remaining in the blade after it has cut the cable. It is also an indication of the margin of

sat.cty insurifg Elhat the cable will he severed.

5-3


Cutter,.,Cartridge Actuated, M8


Component Component

A Head L AnvilB Plug, Shipping MI Swivel AssemblyC Cartridge, Cutter N1122 N "0" RingD Body Assembly 0 Pin, Shear UnlockE Nut, Mounting P "0" RingF Gasket Q "0" RingG Blade R Screw, SetH Pellet (Shown 220 30' S Pin, Shear

out of Position) T "0" RingI Cap U Pin, FiringJ Clip, Cable Holder V Seal, CarK Pin, Cotter

i1

0 7 SAX-F 0NF-3 2 _

694 - 126

2.06S D MAX [.4 /

V 18 NS.3A

ENVELOPE DRAWING

5-4


CUTTER, 149

The 1A) Cutter is a component part of an aerial delivery system for cargo and dronerecovery. ls purpose is to sever cords or wites. It consists of an M129 Delay Cartridge whichis fired mechanically by applying a force to a cable or lanyard.

Upon actuation of the device, an XM29 Delay Element contained in the cartridge bumsfor 2 seconds, after which the propellant is ignited. Thg.gas produced by the burning of the pro-pellant exerps a force on the cutter blade. The cutter blade separates from the case and is pro-pelled in the bore of the housing which contains the cords or wires to be severed. The cords orwires are severed when the blade impacts upon the anvil.


Assembly Weight 4.0 OuncesTemperature limits -950 F to + 2500 FFiring Method Mechanical lanyardShock 750gAcceleration 400gMaterial Severed Two 1/2-inch 1000 lb

tubular nylon linesDelay Time 2 Seconds

5.5

Propellant Actuated Dr.vices

Cuttor, Powd!er Actuated, M9

CROSS-SCTI~WADRAWIG

A "0" BEFgRG PinIFirin

D SealACHHousinO

E ntIo K+ni

F "in, Cotte L Tag, Wring

2.0'- .01 D- 29.

7.218 MIAX

ENVELOPE DRAWING

5-6

Prope~unt Actuated Devices

Cutters

CUTTER, XM1O

The XM10 Cutter is a component part of an aerial delivery system for cargo and dronerecovery. Its purpose is to sever cords or wires. It consists of an XM130 Delay Cartridge whichis fired mechanically by applying a force to a cable or lanyard.

Upon actuation of the device, an XM30 Delay Element contained in the cartridge burnsfor -i seconds, after which the propellant is ignited. The gas produced by the burning of the pro-pellant exerts a force on the cutter blade. The cutter blade separates from the case and is pro-pelled in the bore of the housing which contains the cords or wires to be severed. The cords orwires are severed when the blade impacts upon the anvil.


Assembly Weight 4.0 OuncesTemperature limits -950 F to +2500 FFiring Method Mechanical lanyardShock 750gAcceleration 4 00gMaterial Severed Two 1/2-inch 1000 lb


5-7


Cutter, Powder Actuated, XM10

CROSS-ECTIONDRAWIN

A 8 0" RingV GOTE PiIirnB~~~~SR WasherG HIiigHadAsNl

F iCotpnte CoTapWannt

. A5 "0 Rig010n irn

2.1 - .01 .29 .0

7.2181MAX

ENVELOPE DR~AWING

5-8


Cutters

CUTTER, XM11

The XMll Cutter is a component part of an aerial delivery system for cargo and dronerecovery. Its purpose is to sever cords or wires. It consists of an XM131 Delay Cartridge which

is fired mechanically by applying a force to a cable or lanyard.

Upon actuation of the device, an XM31 Delay Element contained in the cartridge burnsfor 6 seconds, after which the propellant is ignited. The gas produced by the burning of the pro-pellant exerts a force on the cutter blade. The cutter blade separates from the case and is pro-pelled in the bore of the housing which contains the cords or wires to be severed. The cords orwires are severed when the blade impacts uoon the anvil,


Assembly Weight 4.0 OuncesTemperature limits -950 F to 2500 FFiring Method Mechanical lanyardShock 750g

Acceleration 4 00g

Material Severed Two 1/2-inch 1000 lbtubular nylon lines

Delay Time 6 Secondsi

5.9


Cutter, Powder Actuated, XM1 1

CROSS-ECTIONDRAWIN

A "0" RingRG PinIFirin

I U

CRNS-ECON DRAWING

Copoen omonn


Cutters

CUTTER, XM12

The XM12 Cutter is a component part of an aerial delivery system for cargo and dronerecovery. Its purpose is to sever cords or wires. It consists of an XM132 Delay Cartridge whichis fired mechanically by applying a force to a cable or lanyard.

Upon actuation of the device, an XM32 Delay Element contained in the cartridge burnsfor 8 seconds, after which the propellant is ignited. The gas produced by the burning of the pro-pellant exerts a force on the cutter blade. The cutter blade separates from the case and is pro-pelled in the bore of the housing which contains the cords or wires to be severed. The cords orwires are severed when the blade impacts upon the anvil.


Asse,nbly Weight 4.0 OuncesTemperature limits -950 F to + 2500 FFiring Method Mechanical lanyardShock 750g

Acceleration 400gMaterial Severed Two 1/2-inch 1000 lb




CROSS-ECTIONDRAWIN

A D0 RingV GOTE PiIirn

D SealACHHousing

ME fntitKAni

F P0 in oGe PiTa, Wring

2.31 -. 01 .29-.0

-7..70-MAX

ENVLOP DRAIN

5-12

;3

Propellant Actuated Dovices

Cutters

CUTTER, M13

The M13 Cutter is a component part of an aerial delivery system for cargo and dronerecovery. Its purpose is to sever cords or wires. It consists of an M133 Delay Cartridge whichis fireu mechanically by applying a force to a cable or lanyard.

Upon actuation of the device, an XM33 Delay Element contained in the cartridge burnsfor 10 seconds, after which the propellant is ignited. The gas produced by the burning of the pro-

pellant exerts a force on the cutter blade. The cutter blade separates from the case and is pro-pelled in the bore of the housing which contains the cords or wires to be severed. The cords orwires are severed when the blade impacts upon the anvil.


Assembly Weight 4.0 OuncesTemperature limits -95' F to +2500 FFiring Method Mechanical lanyardShock 750gAcceleration 400gMaterial Severed Two 1/2-inch 1000 lb


5-13


Cutter, Powder Actuated, M13

CROSS-ECTIONDRAWIN

A C0 RingV GOTE PiINrn

E Entao ni

ENVS-EO DRAWING

5.14etCopnet

Propllant Actuated Devices

Cutters

CUTTER, M21

The M21 Cutter'is a component part of an aerial delivery system for cargo and drone

recovery. If purpose is to sever cords or wires. Ii'consists of a delay cartridge which is fired

mechanically by applying a force to a lanyard. Upon actuation of the device, a delay element

c,'tained in the cartridge bums for 2 seconds, after which the propellant is ignited. The gasproduced by the burning of the propellant exerts a force on the cutter blade. The cutter blade

separates from the case and is propelled in :he bore of the housing which contains the cords orwires/to be severed. The cords or wires are severed when the blade impacts upon the anvil.


Assembly weight 4.5 ouncesTemperature limits -65 0 F to +160'FFiring Method Mechanical lanyardShock 750g

Material severed Two 1/2-inch 1000 lb tubularnylon lines

Delay Time 2 Seconds

5-15

S


Cutter, Powder Actuated, M21

~REMOVE COTTER PIN~BEFORE FINAL

( PACKING BUT .i , ~AFTER ASSEMBLiNG ,

CUTE TO EN ITE.Mik

A F.


Component Componen:

A "0" Ring G Gasket '7O" RingB Pin, Firing H Screw, Machine, Slotted, Round HeadC Spring I Pin, CotterD Knife Delay Assembly J RetainerE Case K Lanyard AssemblyF Screw, Machine, Slotted, Hex Head L Tag, Warning

-0020

845- 010DIA

- 800NAX-- - 0 - -4.803 .010F5.38- 01 ___________ ___~~8 000 MA XIL

ENVELOPE DRAWING

5-16


Cutters

CUTTER, M22

The M22 Cutter is a component part of an aerial delivery system for cargo and dronerecovery. If purpose is to sever cords or wires. It consists of a delay cartridge which is firedmechanically by applying a force to a lanyard. Upon actuation of the device, a delay elementcontained in the cartridge bums for 10 seconds, aftier which the propellant is ignited. The ga,3produced by the burning of the propellant exerts a force on the c "tter blade. The cutter bladeseparates from the case and is propelled in the bore of the housing which contains the cords orwires to be severed. The cords or wires are severed when the blade impacts upon the anvil.

PWINCIPAL CHARACTERiSTICS

Assembly weight 4.5 ouncesTemperature limits -65"F to +160'FFiring Method Mechanical lanyardShock 7 50 gMaterial severed Two 1/2-inch 1000 lb tubular

nylon linesDelay Time 10 seconds

5.17


Cutter, Powder Ac.#doted, M22

R4EMOVE COTTER PIN

CROSTECIO DRAWMBLNN

Component Component

A "0"~ Ring G Screw, Mlachine, Slotted, Round Head

B Pin, Firing 11 Pin, CotterC Spring 1 Retainer

D Knife Delay A s sern b!y J Lanyard Assembly

E Case K Tag, Warning

F Gasket "0" Ring

885 -020

107 -020

5568 - 00

'$12 MAX

ENVELOPE CtRAWIN5

5- 18


Cutters

CUTTER, XM23

The XM23 Cutter is a component part of an aerial delivery system for cargo and dronerecovery. Its purpose is to sever cords or wires. It consists of an M129 Delay Cartridge whichis fired mechanically by applying a force to a cable or lanyard.

Upon actuation of the device, an XM29 Delay Element contained in the cartridge burns

for 2 seconds, after which the propellant is ignited. The gas produced by the burning of the pro-pellant exerts a force on the cutter blade. The cutter blade separates from the case and is pro-pelled in the bore of the housing which contains the cords or wires to be severed. The cords orwires are severed when the blade impacts upon the anvil.

?RINCIPAL CHARACTERISTICS

Assembly Weight 4.0 OuncesTemperature limits -65 0 F to +I160 0FFiring Method Mechanical lanyardShock 750gAcceleration 400gMaterial Severed Two k/2-inch 1000 lb


3-19



CROSS.ECTIWADRAWIN

A 0" RinOV GOTE PiIiNn

D SealACHHoEsing

F- E

ENVS-EO DRAWING

CopnnAopnn

Propellant Actuated Devices\

Mkrcellaneous

- SECTION VI

MAISCr*A( Im-0 ANJFCMISboy UN q IV *.mm aw


Accessory For Pad

RELEASE, FIRING PIN, MIAI

The MlAl Firing Pin Release is a gas pres-ure actuated device which performs firingpin release function for such devices as the M1A3 Remover. It is a piston and cylinder unit, ac-tuated by propellant gas pressure supplied from another propellant actuated device. As gaspressure is introduced through the intake port, a force is exerted on the unlockng piston result-ing in its displacement and tfte release of the rod and piston assembly. Upon release, the rodand piston assembly is propelled by gas pressure through the cylinder causing withdrawal ofthe extended rod into the unit.


Actuation Method Gas PressureActuation Force 250 psi min.


Release, Firing Pin, Gas Actuated, Ml'A1

CROSS-SECTION DRAWIN4G

Component Component

A Rod, Piston Assembly E CylinderB Spring, Piston Assembly F DiscC "0O" Ring (2) G Piston AssemblyD Ball H Howling, Piston Assembly

-~DIA

5.599 MAX

ENVELOPE DRAY4NG

.6-2


Gas Generator

GAS GENERATOR, M17

The M17 Gas Generator consists of a constant volume chamber with a pressure outletport, a gas pressure actuated firing mechanism and an M37 Cartridge.

The gas generator is actuated by gas pressure supplied from another cartridge actuateddevice. The firing pin of the gas generator is held in position with a shear pin. When gas pressureis supplied, the force applied on the firing pin will shear the shear pin and propel the firing pinagainst the cartridge containing a percussion -sensitive primer. The primer ignites the blackpowder and propellant contained in the cartridge. The cartridge ruptures at the unsuppor ted areaand the propellant gas is utilized to pre ssurize another device.


Actuation Method Gas PressureTemperature limits -65 0 F to +160'FAssembly Weight 2.2 lbsFunction Time 200 MillisecondsActuation Foice 750 psi, min.

6-3


Generator, Gas Pressure, M17

I H


Component Component

A Cap, Shipping F "O" RingB Pin, Firing G Cap, ShippingC "'" Ring H SetscrewD Cap, Initi to I Cartridge Assembly, M57E Body, Chamber J Pin, Shear

10.93 MAXt_: 0.5 MAX }NA

1.32 - .01 DA

ENVELC. IRAWING

6.4

k~


Electric Ignition Element

ELECTRIC IGNITION ELEMENT, M21

The M21 Electric Ignition Element is designed to be the actuating cnergy sourcefor other gas actuated Propellant Actuated Devices (PAD). This ignition element has a fourpin electrical connector. Two of these pins accommodate a :heckout circuit and two pinsare used in a firing circu.t. The external shell consists of the electrical connector on oneend, a hexagonal center section and a 7/16 inch thread on the other end. The threadedportion mates with the gas inlet port of the PAD to be operated. Application of the FireStimulus to the firing circuit ignites the propellant charge. The gas generated exerts aforce against the firing pin of the other PAD driving it forward to strike its primer therebycausing the device to function.


Actuation Method ElectricBridge Circuit Resistance 0.11 ± .03 ohmTemperature limits -651 F to +2001FNo Fire Stimulus 1.5 amp for 60 secondsFir- Stimulus 5.0 amp for 50 milliseconds, max.Pressure Output 2000 to 6000 psi (measured in

an 0.062 in. 3 vol.)Assembled Weight 10.05 gm

6-5


Ignition Elemeitt, Electric, M21


Component Component

A Gasket E Disc, InnerB Sleeve F Body AssemblyC Washer G Shunt AssemblyD Disc, Outer

r-20 UNF-3A (REF)

9HFX (KEF) 49A

d0 929 MAX

ENVELOPE DRAWING

6-6

Propeliont Actuated Devices

Electric Ignition Element

ELECTRIC IGNITION ELEMENT, M55

The M55 Electric Ignition Element is designed to be the actuating energy sourcefor other gas actuated Propellant Actuated Devices (PAD). This ignition element has asingle pin coaxial electrical connector. The external shell consists of the electrical con-nector on one end, a hexagonal center section and a 3/8 inch thread on the other end. Thethreaded portion mates with the gas inlet port of the PAD to be operated. Application ofthe Fire Stimulus ignites the propellant charge, The gas generated exerts a force againstthe firing pin of the other PAD driving it forward to strike izs primer thereby causing thedevice to function.


Actuation Method ElectricBridge Circuit Resistance 0.11 ± .03 ohmTemperature limits -65 0 F to i-200'FNo Fire Stimulus 1.5 amp for 60 secondsFire Stimulus 5.0 amp for 50 milliseconds, max.Pressure Output 2000 to 6000 psi (measured in

an 0.062 in. 3 vol.)Assembled Weight 8.30 gm

6-7

'I


Ignition Element, Eloctric, M55

CR65S-SECTION DRAWING

Component Component

A Insert D RingB S!eeve E Body AssemblyC Di.c F Shunt Assembly

' - 1.04 MAX

-x*- .750 MAX -

f6 (RF.F). .335 MAX

ENVELOPE DRAWING

6-8

SUncassi fied.4ecurjv Clas~ification

DOCUMENT CONTROL DATA- R & D(Srcurily clastil. tion of title. body c'I b-tIact and Indexng annotation must be entered when the overall report is elpsullad

I "INATIt. ACTIVITY (Corporate author; 20. REPORT SECLFAI'rY CLASSIFICATION

Frankford Arsenal U UnclassifiedJ Philadelphia, Pa. 19137 2b. GROUi

3. REPORT TITLE

Propellant Actuated Devices Engineering Manual

4. DESCRIPTIVE NOTES (7 ,p of eport and Inclusive date*)

Technical ManualAUTHOR(S) (First name, middle JnItial, last name)

6. REPORT DATE: Ia. TOTAL NO. OF PAGr 7b. NO. OF REFS

June 1969 259St. CONTRACT OR GRANT NO. ga. ORI(INATOnVS REPORT NUM-IER(S)

IEP 65-63- 0-8 .Rev-Ab. PROJECT NO.

C. 9b. OTHER REPORT NO(3) (Any other numbera that may be asianodthis report)

d.

10 DISTRIUUTION STATEMENT

This document is subject to special export controls and each transmittal to foreigngovernment or foreign nationals may be made only with prior approval of the Command-ing Officer, Frankford Arsenal, Philadelphia, Pa., ATTN: SMUFA-J5000..UPPLEMCTARY NOTCS 12. SPON.ORING MILITARY ACTIVITY

U. S. Army Munitions Command

13. OSTRACT

This engineering manual provides a description, principal characteristics, cross3ectional and envelope drawings, and typical performance of Propellant ActuatedDevices (PA D). Sections are included on removers, thrusters, personnel ejectioncatapults, initiators, cutters, and miscellaneous devices.

V% IT vlEP. nAGES 00Q POA.N 1.73. 1 JAN 44. wmIrm is

I Nov 0.4 7 OSS')LKE' FOR ARMY USK. Uncl1assi fie~dzSocursty Classificaion

UnclassifiedSecurity C]assificalian

14.KEY WOno5 LINK A LINK I) I LIN,. C

ROLL W7 FtOLL. WT J io

Propellant Actuated Devices (PAD)RemoversThrustersRocket CatapultsCatapultsInitiatorsCuttersInterior BallisticsSolid Propellant

I Secugi f i HSecuwity Classification

Propellant Actuated Devices

Documents

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