Section II - h1 Engine System

7/23/2019 Section II - h1 Engine System

1/57

Volume

11

SECTION 11

H- ENGINE SYSTEhl

The

H-

1 Engine

is single s ta r t , constant-thrust,

bipropelkant rocket

engine

that develops

890,000

N 200 , 000

lbf)

of

thrust

at

s e a

level.

The pro-

pellant; lox and RP 1 fuel,is supplied to th thrust

chamber

by a turbopump,

A

gas generator , burning

the same propellant as the thrust

chamber ,

p o w e r s

the turbopump.

The eight engines used on the

S-IB

t a g e consist of our m o d e l

H-IC

engines inboard)

and four model

H-ID

engines outboard)

The out

board engines

dif fer f r o m the i nboard

engines

in

that

they are

equipped with

a hydraulic sys tem for vehicle s t eer ing and a t t i t ude control.

A

detailed

functional de script io n of the H-

engine

s y s t e m supported

by

a

simplified

schematic

i s

given in

sect ion If of Volume L

H- ENGINE SYSTEM INFORMATION

ILLUSTRATIONS

TITLE

PAGE

H- 1 Engine - Deta i led Schematic LI-5

H

1

Engine

P u r g e s and

Gearb o x

Pressur izat ion Detailed Schematic

11-6

H-1

ngine

Znforrslation

I l lu s t r a t io n

11-11

H l N G I N SYSTEM CALLOUT LIST

FIND

NO.

BZ

B3

B4

B5

8 7

8

B

BIO

B

COMPONENT

PART

90.

P AGE

Main

Lox

Valve Opening Control

Or i f ice

Explosive A c

tuated Conax

Valve

Gearbox P r e s su r i z a t i o n O r i fi c e

Fuel

Discharge

Orif ice

Gearbox Pres su r i za t i on

Check Valve

Lox Seal Pur ge Orif ice

Turbopump

Lox

D r a i n

Cap

Fuel

Drain Cap

Solid Prope l l an t Gas G en e r a to r

Initiator 2 Places)

Liquid P r o p e l l a n t Gas G e n e r a t o r Lox

Injector Manifold

Purge

Check

Valve

July

25 1966


2/57

Volume II

H- l

E N G I N E SYSTEM C L L O U T LIST CONT)

FIND

NO

COMPONENT

Lube

Drain

Relief

Valve

Lube

Sys tem

Filter

Fae l

Additive

Blender

U n i t

Dra i n

Plug

Additive ill

and Dra in Q D

Coupf ing

Fuel D r a i n Q D

oupling

Gas T ur b i ne

Solid Propella nt aa G e ne r a t o r

Lox

Boots t r ap

Ori f ice

Liquid

Pr

opcZlant

G a s

Genera to r

Combustion Chamber

Liqu id P rope l lan t

as G e ne r a t o r

Control

Valve

Unitized

Che

ck

Valve

Fuel

Jacket

Dra in Plug

4

Places)

Aspirator

Thrust Chamber

Heat Exchanger

Lox Orifice 3

Places

Heat r x c b a n g e r

Fuel

Jacket FiU Q D Coupling

Fuel

Boots t r ap Or i f i ce

Heat Exchanger

Lox Orifice

Plate

*

Partial

Aspi ra tor

Hypergol Cartr idge

F u e l Injector Macifold Pw g e

Check

Valve

Places

Ignition

Monitor

Valve

Niin

Fuel

Valve

Thrus t 0 K. Pressure Switch

3

places)

Liquid

Propel lant

as

Generator

Autoigniter

2

~ l a c c s )

Drain Plug

Lube D r a i n Manifold

Igniter

Fpel Valve

Lox Drain Manif old

Fuel

Bleed Orifice

Main Lox Valve

P A R T NO.

PAGE


3/57

Volume I1

H-1 E NG I N E

SYSTEM

C LLOUT LIST CONT)

FIND

NO.

COMPONENT

Tube

ssembly

Hose

ssembly

Tube ssembly

Bleed

Line

ssembly

Fuel Duct

Tube

s s

embly

Manifold

and Tube ssembly

Tubc

s scmbly

Line ssembly

Tube

s

embly

Tube

s

sembly

Manif

old

e

mbly

Manif old s embly

Tube ssembly

Manif

old

s s

mbly

Manif

old s embly

Cox

Line ssembly

H o s e

ssembly

Hose

ssembly

Tube s embly

Tube s sembly

Tube

s sembly

Tube

ssembly

Tube s s

e

mbly

Tube

s

mbly

Tube ssembly

Tube

s embly

Tube

s sembly

Tube

s sembly

Tube ssembly

Tube

ssembly

P RT

NO

P GE


4/57

Volume I

H l

ENGINE

SYSTEM

CALLOUT LIST

CONT

FIND

NO.

3

3

3

3 3

COMPONENT

Tube

s

aembly

Tube Assembly

Lube

Drain

Manifold

Manifold

s

sembly

Fuel Duct Assembly

Lox

Joint

Assembly

Tube s

s

embly

Tube

As embly

Tube

s

s mbly

Tube As mbly

Tube

A

ssembly

Turbine

Exhaust Duct

P A R T NO

Worth rne r i c an Aviat ion (NAA), Rocketdyne Division

* eroquip Corporat ion

P A G E

U-4 July 25 966


5/57

Volume

FIGURE I l T

-

TO EDGE O A SD IR A TOR

18271

O OUT D ENCIMES

TO

EDGE

OF TMRUS T

C H h U S E R R 2 3 ~

N

IHS EN GIN ES

F I G U R 11 1 H 1 ENGINE

DETAILED

SCHEMATIC

July

2 5

1966


6/57

Volume

I

FIGUR

LI-z

H i

NGIN

PURGES

AND GEARBOX P R E S S U R IZ T IO N

-

DETAILED SCHEMATLG Sheet

of

2

uly 25 1966


7/57

Volume If

FIGURE 11-2

H 1 ENGIXE P U R G E S AND GEARBOX PRESSURIZATION

D E T I L E D SCHEMATIC sheet

2 of 2

July

25

1966

U-7


8/57

Volume I1

~ 1

NGINE PURGES -AhZ , GEARBOX PRESSURIZATION

CALLOUT LIST

FIND

NO,

COMPONENT

Turbopump 8

places)

Liquid Propellant

Gas

Generator

Lox

Injector Manifold

Purge Check

Valve

8

places

Liquid

Propel lant Gas Generator

Combustion

Chamber

8

p laces

Liquid P ro p e l l a n t

Gas Genera tor

Control Valve

Unitized Check Valve

Fuel

Injector

Manifold

Purge

Check

Valve

( 2 4

places

Thrust 0 . Pressure Switch

2 4

places

Quick-Disconnect

Coupling

Quick-Disconnect

Coupling

Quick-

Disconnect Coupling

2

places)

Gearbox

Pr es s u r i za t i on and Lox

Seal

Purge

Orif ice

Quick-Disconnect Coupling

Tube Assembly

4

laces

Tube

Assembly

4 laces)

Manifold

As

emSly

4

places)

Tube

Assembly

3 places)

H o s e

Assembly

4 places

Manifold Asse m3ly

4

places

Tube

Assembly

4 places)

Hose Assembly 4

places

Tube Assembly 4 laces

Tube

As

sembly 4

places)

ose Assembly 4 places)

Tube Assembly 4 places

Tube Assembly

4 places)

Hose Assembly

4 places)

Tube As sembly

4

laces}

Manifold Assembly 8 ~ l a c e s

Tube A s s e m b l y 4 p laces

Tube As sembly 4 Places)

H o s e

Assembly

4 ~ l a c e s )

Manifold Assembly

4 places)

P A R T NO

3087 P O

55408 l *

ZQGOO

991

20C30141

6OG10764-1

60~10643-1

556348-ll*

bOClO681-1

20COO 522

5 5 6 2 8 5

lOC11423-1

20C00523

5 5 7 2 8

b

1 0 ~ 1 1 4 1 6 - 1

20C00523

557 6 3*

6OCl1939-1

6OC21612-1

557288*

308865*

60C10678 1

6 0 ~ 1 0 6 1 0 - 1

20C00521

556347-1 I


9/57

Volume 11

H-1

ENGINE P U R G E S

AND

G E A R B O X

PRESSURf Z A T I O N CALLOUT LIST

CONT)

Ff

ND

NO.

OMPONENT

Tube A s

sembly

4

places)

Tube AS embly 4 place s

H o s e

Assembly

4

places)

Manifold Assembly 4 Place

Tube

A s s e m b ly

4 places)

Tube Assembly 4

laces

Hose Assembly 4 places

Tube Assembly

4

laces

Tube As sembly 3 p l ace s

Tube

A s s e m b l y 4 laces

Hose Assembly 4

laces

Tube

Assembly

4

laces

Tube Assembly 4

places)

Tube

Assembly

4 p l aces )

Hose Assembly 4 places)

Tube

Assembly

4 Places)

Tube Assembly

Tube

Assembly

Tube Assembly

Tube

s

sembly

Tube Assembly

Tube

Assembly

Tube As sembly

T9be

Assembly

Tube As embly

Tube

Assembly

Tube

Assembly

Tube As embly

Tube

Assembly

Tube Assembly

Plate Assembly

Tube Assembly

Tube

s

stmbly

Tube

Assembly

Tube As sembly

Tube

As

sembly

Tube As

embly

Tube

Assembly

Plate

s

sernbly

P A R T NO.

b O C l O 6 7 7 1

bOClO607-1

20C00520

5 5 6 2 9 9

lOCl1407-1

IOC11405-1

20COO520

557287 *

lOC11408-1

IOC11411-1

2 C 52

557256*

60C11440

1

6OCl1944 1

6 0 c z r 6 1 2 3

552289

lOCll259-l

lOCl1409-1

20 COO 957

20COO

956

20COlO15-1

2 ~ 016-1

60C21603-l

6OC21602 - 1

20CO101.4-1

20CO1013-1

20C00954

2 C 955

20GO

1000

6

20CO 1000

-4

75C02767

20C01000-7

2 GO

1000

2

60Cl0520 1

20C01000 2

60C11942-1

6OCl1945-1

60Cl1943-1

7 5C 02 7 6 8

July 25,

1966


10/57

I

ENGINE

PURGES

ND

G E A R B O X

PRESSURIZATION CALLOUT

LIST

Tube Assembly

Tube As

embly

Tube Assembly

Tube Assembly

COMPONENT

PART NO,

North

American

Aviation

NAA)

Rocketdyne

Division

July

2 5

1966


11/57

Volume I1

FIGUR

11-3

H - l ENGINE INFORMATION

ILLUSTRATION

shee t of 2

July

25

1966


12/57

olume

G I M B AL I N S T A L LA T I O N V l E M

MAIM FUEL VALVE

SEE

F IGURE n.25

FOR INSTALLATION

VIE*)

FOR

IHSTALLATIOH

VI W

1GMIT IOH MONITOR VALVE

SEE

F IGURE E. f

FOR

INSTALLATIOM

W

EW

UQUlD P R O P E L L A H T

G A S

GEFIERATOR

S f A T l O H 9

m a

R O P E L L A N T

GAS

GENERATOR

DUD PROPELLANT

PAS GEMERATOR

IN IT IATOR 2 PLACES\

(SEE

F IGURE 11 31

FOR I N S T A L L A T I O N

l E m

STATION

July

2 5 ,

966


13/57

Volume

I

L I Q U I D PROPELLANT

GAS

GENERATOR

C O N T R O L

VALVE, P A R T NO. 308710

The liquid propellant gas

generator

LPGG)

con t ro l

valve

~ 2 3 ) ontrols

the flow of

propellant

R P - l fuel and lox) t o the LPGG combustion

chamber

~ 2 2 ) The LPGG control valve is opened by pre ssure sensed at

the thrust

chamber

fuel

injector manifold. This pressure

opens

the L P G G contro l valve

fuel

and

lox poppets,

allowing

the

bootstrap

propellant

to

flow

through

the

LPGC njec tor

and into the

combustion

chamber.

During engine shutdown,

fuel i n j e c to r manifold pressure decays a n d the

fue l and lox poppets

are

closed

by in ternal spring ?re

s

sure,

see figure I2-5 f o r ins ta l la t ion view. )

1. VENDOR: Rocketdyne Division; North Arne

r ica2

Aviation, Inc,

pa r t no. 3087 I 0)

2. LOCATION:

Station

8

3. SERVICE:

L o x and

R P 1

4

PRESSURE:

a

Cracking:

1)

Fuel:

7 2 . 4

*

13 .

8

~ / c r n ~ ~105

+

20

~ s i g

2 )

Lox:

137. 13.8 bT/crnZg (200 20

psig)

b.

Operating:

189.6h 1 7 . 2 ~ / e r n ~ ~2 7 5 * 25ps i g )

5. MIXTURE RATIO :

0

347 lox

to

RP- I

6. FLOW RATE:

a. Lox: 1 , 9 9 k g / s e c 4 . 3 9 1 b / s e c )

b. R P- l r

5 7 5

kg/sec 12.68 lb/sec]

LIQUID PROPELLANT GAS

GENERATOR

C O N T R O L

V A L P E INSTPALLATION

CALLOUT

LIST

FIND

N

0

COMPONENT

Bolt ( 2 places

Washer

2 places)

Manif

old -4

s s mbly

0-Ring 2 p laces )

Liquid Propel lant G a s Genera to r

Control

Valve 8 2 3 )

Fuel

Boota t rap

Orif ice ~ 3 2 )

Washer 4

p la c e s )

Bolt 4 p la c e s )

Bolt 8 places)

Washer 8 ~ l a c e s )

0-Ring

Roae

A s s e m b l y

Injector

Gasket

PART NO.


14/57

Volume I

LIQUID PROPELLANT

G S G E N E R T O R

CONTROL V L V E

INSTALLATION

CALLOUT LIST

(CONT)

F I N D

NO.

COMPONENT P R T NO

Fuel

Jacket Fill

Q-D Coupling ~ 3 1 )

P l ug

iquid

Propellant

Gas Genera tor

Combustion Chamber ~ 2 2 )

Nut

8 places

Washer 8 places

Gasket

Tube

As

sembly

Liquid Propellant Gas Generator

Check

Valve

B

2

Gasket

Plug

Nut

Gasket

Tube As embly

B

oZt 4

places)

Was h e r 4 ~ l a c e s ]

Seal

Lox Boots t rap Orifice

~ 2 1 )

Seal

Seal

Tube As embly

Reducer

Fitting

Packing

*NAA,

Rocketdyne

~ i v i s i o n

**AeroqtPip Corp.

***FlexitalZic

Gasket Co


15/57

M W A A

SECTION

A-h

ACTUATOR

INLET

PORT

LOX

LOX OUTLET

ORT

Vl W A A

pa

~r

POPPET

OUTLET

PORT

SE TION A A

ElQM

FIGURE II 4

LIQU I P R O P E L L N T

GAS GENER TOR

CONTROL

V-4LlrE

3 0 8 7 1 0

SECTION L VI W

July

2 5

966


16/57

Volume 11

FIGURE

11 5

LIQUID PROPELLANT

G S

GENER TOR

O N T R O L VALVE

3087

1 INSTALLATION V I E W

1

.

11 16 July 2 5 966


17/57

Volume

I

LIQUID PROPELLANT G A S

GENERATOR

COMBUSTION CHAMBER;

P A R T NO, 3 0 7 3 5 0 - 3 1

The bootstrap propellant, lox

and

R P - 1 is burned in

the LPGG corrAbustisn

ch mber BZZ)

and

th

resul tant

hot

gases

drive the g s turbine ~ 1 9 )

see

figure I I 6 f o r installation view.

1 VENDOR: Racketdyne Division, North American Aviation Inc. p r t

no 307350-311

2

LOCATION: Station 77

3.

TEMPERATURE: Operating:

656.1

i 8.

3 2

1,213

1 5 0 ~

4. PRESSURE: Operating: 433.

3

* 3. 2 ~ c m 628 .5

*

4.7 pis


18/57

Volume l

L I Q U I D

PROPELLANT

GAS GENERATOR

OR INSTALLATION V I E

RDI53*50Ol*0005

R E F E R TO APPENDIX

FQR

SPEC IA L TOR QU E VALUES

NAA,

ROCKETDYNE olvlsjon

U.S. BEARING GOUPORATION

EIOlPtE

FIGURE lf-6

LIQUI PROPELLANT

G S

GENERATOR COMBUSTION

CHAMBER 3 0 7 3 5 0 3 1 INSTALLATION VIEW


19/57

Volume 11

TURBOPUMP. PART

NO. 455450 -11

The

turbopump ~ 8 )

upplies

lox and

fu l

under pressure

t o the th rus t

chamber ~ 2 8 ) n d

t

the

LPGG

con t ro l valve

~ 2 3 )

The

turbopump consis ts

of a

fuel pump,

a

lox pump,

a gearbox, a gas t u r -

bine

~ 1 9 )

and

tw

accessory

drive adap te r s ,

The turbine

is

s ta r ted

by

hot

gasses f rom

the

sol id propellant

gas

genera to r [SPGG

BZO ) and i s dr iven

by

hot g a s s e s f rom

the

L P G G combustion chamber ~ 2 2 )

The

tu rb ine

o p e r a t e s

the

fuel and lox

pumps

and the

accessory

d r i v e

a d a p te r s

through the

gearbox.

On

outboard

engines;

one of

the

accessory

drivc adapter 3 is used to

supply

power

t o the main pump on

the

H - 1 engine hydraulic system, Refer

to

Section

111.)

Lubrication of the

gearbox is

accompl i shed b y a

mixture

of

fuel and a

high-

pressure

addit ive

supplied

by

the

fue l addit ive b lender unit

FABU) B

151,

see figure fI-8

for

installation

view ]

VENDOR:

Rocketdyne Division;

North

Amer ican Aviation Inc. Cpart

no

458450 -11 )

LOCATION:

Sta t ion 8 6

SERVICE Lox and R P - 1 fuel

PRESSURF:

a. .

Turbine:

1)

Inlet total) : 409 . 5 3T/crn2a 594psis)

2 )

InIet s ta t ic) : 355 . 1 ~ / c m ~ a 5 1 5 ~ s i a )

3 )

Exit:

2

3. 1 PJ cmLa 3 3 . 5 psia)

b. Lox Pump:

1)

h l e t operating: 44 8 DT/crnZa 6 5 psia)

2 )

Outlet operating: 654.

3 bJ/crn2a 949

pis

c.

Fuel

Pump:

1 ) nlet

operating:

39.

3

~ / c r n ~ a57

psis)

2 )

Outlet operating:

697.7

l4/crnzg 1012 psis)

LUBRICATf ON:

Rocketdyne add i t i v e

RB0 140

- 0 06

and

R P - 1 fuel

FLOWRATE:

3

a Lox pump: 12.87

m /min 340 1

gpm)

3

b. Fuel

punip:

7 .

9 9

m

/min

2 1 1 3

gpm

TURBINE

POWER:

2997 .

3

kw 40 9. 5 bhp)

ACCESSORY R I V E SPEED:

3 ,950

to

4 , 2 5 0 r p m

TURBOPUMP INSTALLATION V I EW CALLOUT LIST

FIND

NO.

COMPONENT

Nut

2 Clevis

3

Bolt

8

p laces )

4

Washer 8 Places

5 ox Joint Assembly

P A R T

NO.


20/57

Volume I

TURBOPUMP

INSTALLATION

VIEW

CALLOUT LIST onk.

FIN

NO.

COMPONENT

Sea l

Turbopump

(BS)

Fitting

Washer

4

places)

Bolt

4 places

Ball Se a t Washer

a l l

Socket ~ a s g e r

Bolt

Turbine

Exhaust Duct

~ 2 5 )

Bolt

44 Places

Washer 44

places)

Gasket

Gas Turbine

Washer 44

places)

Nut 44 Places

Fuel

Discharge Ori f ice ~ 4 )

Fuel Duct

Assembly

Washer 8 Places)

Bolt

8

places

h l o w t

Assembly

Bolt

4 Places

Washer 4

laces)

Fitting

*NAA

Racketdyne

Division

It-20

July 25, 1966

P RT

NO.

.-.

40 5744 *

[INBD)

3060

3 - 3 *

458450-ll*

4

39

30

MS20002C7

RDlll-4006-0709*

402040

4020 9

MS20012H22

30& 104*

NASLOO4- 14A

L~153-0013-0002*

8

-2857 1PNA*

459162 - 1

LD153-0010-OOlO*

MSZ0500

428

RD251-4013*

402785-31*

LDl53-00

3-0004*

RD111-4010-3622*

4 0 2 5 2 2 - 1 1*

RD111-4006-0709*

MS2OOO

C7

402795 *


21/57

Volume

I

SECTION A 4

s

R w E

ElOf PC

FIGURE

LI 7

TURBOPUMP

458450

11

SECTION L

VI W

July 25 966


22/57

Volume TI

FIGURE 11 8

TURBOP clMP, 458450 1

INSTALLATION VIETI

L t Z Z uly 25;

1966


23/57

Volume

HEAT

EXCHANGER, P A R T

NO

3 0 3 3 9 3 - 1

The heat exchanger ~ 3 6 ) onver t s lox t o ox for in-f l ight lox conta ine r

pressur izat ion.

The heat

exchanger

cons i s t s

o an outer

shell ,

n

nlet

flange,

an

outlet

f lange,

a

helix-wound four -co i l system, and

co i l

in le t and out le t manifolds.

Hot

exhaust gases f rom the

gas

turbine

~ 1 9 )

low through

the shell

t o heat the

coils,

Lox, under

pressure f r o m the turbopump ~ 8 )

flows through th ree oi ls

of

the

four-coi l

system and is conver ted to gox.

[see f i gu r e s 11-9

andI I -10

for

instal lat ian

view

)

1 VENDOR: Rocketdyne Division, North

Amer ican

Aviation Aviation, Inc.

Cpart

no. 3 0 3 3 9 3 - 1 1

2 LOCATION: Station 67

3,

LOX FLOWRATE: I 6 kg/sec

3

~ b / s e c

July 25

1966


24/57

Volume

LOC TION

M W

FIGUREII 9 INBOARDENGINEKEATEXCHANGER 3Q3393-11-

INST LL TION

V I W

II 24

uly

2 5 1966


25/57

Volume 11

L CCA T l ON

V IEW

EFER TO

APPEND IX 1

FOR SPECIRL

TORQUE

VALUES

4459-SFMA

LOX

LINE

HOSE ASSY

NA5-269Ja-I

SEE FIGURE 11 1 1

FOR lNSTALLATlON

VIEW1

NUT

MS20500-428

HEAT

EXCHANGER

136 PLACES

ASPlRATO

R.

208960

LD153401D4Ola*

NAA

ROCYETDYNE OIVtSION

FLEXITALLIC GASKET CO.

E 10780

F I GURE

11 10

OUTBO RD ENGINE

HE T EXCHANGER.

3 0 3 3 9 3

11 -

INSTALLATION V I W

uly

25

1966

11-25


26/57

Volume I

LD153-0010-2009

H E A T

EXCHANGER,

(SEE

FIGgRESII3

ANDD

FOQ

NSTALLATIOFI

VIEW)

WASHER,

NOTE:

EFER

TO APPENDIX

OR

SPECI R TORQUE VALUES

ElP781F

HOSE ASSY.

NA5-26370-I

yiT

WL

PLATE N O Z Z L E ,

FIGURE

ii

l l

LOX L I N E HOSE

SSEMBLY

NA5 26970 INSTALLATION

VI W

11 26

J U ~ Y

5

9 6 6


27/57

Volume I1

FLIGHT

GOX UN ASSY,

20C00059

OUTBD.)

6flCTiOSII (EN ; 5)

6 C21171

[ N G

6

6 CE l l B4

ENG St

GASKET,

BOLT

NAS1004-IQAIOUTBD)

NOTE:

EFER TCAPPENDIX

I _ .

FOR SPECIAL TORQUE

VALUES

*

NAA ROCKETDYNE DIVISION

F IGUR

L I 1 2

OX L IN SSEMBLY

-

INST LL TION V I E W

uly 25 1966


28/57

Volume I1

UNITIZED CHECK VALVE,

P A R T

NO,

554081

The unitized

check

valve ~ 2 4 )

consists of a lax dome purge check v lve

a and a

lox

l ine check valve in a

unitized

assembly.

GNz flows through the lox dome

purge

check valve and

into

the l o x

dome

to

prevent contaminants

f rom entering the

th rus t

chamber

nozzle and flowing to

the injector plate and the lox dome. The

GNZ

l so

prevents

mois ture f r o m con-

densing

in the

lox

dome,

The

check

valve i s closed by lox

p r e s s u r e

buildup

in

the lox

dome.

The

check

valve

s tops the

purge

and prevents th

backflow

of ox

into

the GNz purge line.

s e e

figure

If-

13 for

installation

view. )

Lox

f lows through the

lox

line check valve

to

the heat exchanger

B

30

The check valve prevents the backflow of

gox

in to the heat exchanger lox supply

line.

s e e

f igure

11-13

f o r installation

v iew .

1 VENDOR: Rocketdyne Division,

North American

Aviation Inc,

p r t

no.

554081 )

2. LOCATION: Station

77

3.

SERVICE:

GN

and ox

2

4

P R O O F

P R E S S UR E 1

34

+ 3 . 8

-

0 ~ / c m 15 +

20, -

psig

5. LEAKAGE: None

at proof

pressure

July 2 5 1966


29/57

Volume I

FIGUR El

3

UNITIZED CHECK VALVE 5 5 4 0 8 1 IXSTALLATION

VIE vr

July 25

966


30/57

I

FTGTJR IT- 4

GE RBOX PRESSURIZ TION

CHECK VALVE

N A ~ 2 8 1 5 1

INST LL TION VIEW

July

25

966


31/57

FLIGHT

OUTBOARD

N A A .

RO KETDYNE DIVISION Et J887D

F IGUR

TI

5

FUEL INJECT OR W KIFOLD PURGE CHECK

VALVE

NAS 28049 INST LL TION VIEW

uly 2 5

1966


32/57

Volume I1

LUBE DRAIN RELIEF VALVE P R T NO. 30 3624

The

lube drain rel ief valve

~ 1 3 )

s instal led

in the turbopump gearbox

lube

drain

manifold.

The relief valve maintains a po sitive pressure within th

gearbox t o prevent the lubricant

f rom

foaming

t al t i tude,

The

expended

gearbox lubrica nt and the

Nz

used for gearbox pressur iza t ion

flow

through the

re l ief valve into

a

single drain line and are vented t o atmosphere,

see f igure 11-16

for installation

view.)

1 VENDOR Rocketdyne

Division,

North American

Aviation

[part no.

30

36 24

2. LOCATION:

Station 80

2

3 PRESSURE: Operating:

1.4 t o

6 9

~ c m 2

to

10

p i g ]

FUEL CONTROL LINE ASSEMBLY,

P R T

NO.

501585

The fuel

control

line

assembly 6 )

directs high-pressure

fuel

t o the igniter

fuel valve ~46)the opening

con t ro l

por t on

the

m in lox valve ~ 4 9 ) the

explosive actuated conax) valve

BZ) the

F A B U ~ 1 5 )

and

the fuel suction

line.

When the explosive actuated valve

i s f i red ,

high p re

s

sure fuel

flows

through a branch

of

the fuel control line assembly t o the closing control p o r t

on the main lox valve.

s e e figure 11-17

for

instal lat ion

view.)

1. VENDOR: Rocketdyne Division,

North

Amer ican Aviation Inc. p a r t

IlD.

601585)

2.

SERVICE:

R P - fuel

July

25, 966


33/57

Volume

I

FLIGHT

:

.-.

LOCATION VIEW

GASKET,

955502*

G ASKET,

I . 454207

LUBE DRAIN LO153.0011-0013

MAHlFDLO ASSY,

456419

UP ENGINE

NOTE:

REFER TO APPENDIX I

FOR

S P E C I A LTO R Q U E VALUES

NAA, ROCKETQYHE DIV1SION

**AEROQUIP

CORP.

F IGURE

11-16 LUB E DZ IN RELIEF V A L V E

3 0 3 6 2 4 AND

LU E

DRAIN

MAN I F O L D

4564

INSTALLATION

VIEW

July 2 5 1966


34/57

Volume I

FIGURE

II l?

FU L

CONTROL LIME ASSEMBLY 6 1 5 8 5

INST LL TION

V I W sheet 1 of 2

July 2 5 . 1966


35/57

Volume I1

BOLT RAS1003-15A WASHER, RD153-5001-0003

SEAL

ASSY.

303963

ER,

R0153 5001 03048

P A C K IN G ,

MS29513-148

WASHER,

GASKET, MS29512-8

NOTE:

REFERTO

APPENDIX I

FOR SPECIAL TORQUEVALUES

* NAA,

ROCKETDYNE

DIVISION

** AEROQUlP CORP

FIGUR 11-17

FUEL ONTROL

LINE ASSEMBLY 6 0 1 5 8 5 -

INSTALLATION

V I W

sheet of 2

July 25 , 1966


36/57

Volume

FUEL ADDITIVE

BLENDER

UNIT, PART

NO.

5 5 5 2 3 2

The fuel.additive blender

unit

( A 15)

is

a fuel

-pre

s

sure

operated

lubr icant

blender that

injects an

additive

into

R P - fuel t o

form

lubricant.

The

lubri -

cant

is

supplied

t o the turbopump gearbox t o lubricate

and cool

the

turbopump

gearbox components.

The fuel additive blender unit is

equipped

with

a thermostat ical ly

control led

electr ic

heater tha t

i s used t o maintain

the correct

density range of the additive.

see f igure II

9

for installation view. )

1. VENDOR:

Rocketdyne

Division; North Amer ican Aviation Inc. part

no,

5 5 5 2 3 2 )

1 LOCATION: Station 64

3. SERVICE:

Additive ~ o c k e t d y n e

O

140

-00

) and R P - fuel

4, PRESSURE:

Fuel:

2

a.

Opening:

48

to

103.4

~ / c m

70

to

150

psig

b. closing:

34.

5 to 6 2 bI/crnZg 50 to 9 psig

5 .

FLOW RATE:

315.4

to 378. 5 crn3/min ( 5 to 6

gpm)

6 ELECTRICAL CHARACTERISTICS:

a. Heater

power: 300

30 W

b. Thermostat :

Th r e e ranges:

(1)

Control normal

operating)

Opens at

54,4 2. 2OC

130 t

OF)

; closes

at

49 , 4 2. 2OC (121

&

OF)

2 ) Under t empera tu re Opens at 40. 5 *

2 . 2 0 ~ 1 0 5 ~ 4 ~ ~ ) ;

l o s e s a t 4 5 . 5 k 2 . 2 * ~ ( 1 1 4 & 4 ~ ) -

(

3

Over temperature protect ive) : o p en s at 6 6 8 f

2. 2 ~

(

52

& 4O2?)

closes

a t 58, 9 & 2, ZC 1 8 4 ~ )

July

2 5 ,

1966


37/57

Volume I

FIGURE

.U

8

FUEL ADDITIVE L E N D E R

UNIT

5 5 5 2 3 2 SECTIONAL

VIEW

July 2 5 1966


38/57

Volume

I1

HEATER ASSY.

FUEL AODlT lVE

GASKET

MS29512-

LUBE

SUPPLY

TO

TURBOPUMP)

AA ROCKETOYWEDIVfPON REFER TO APPEflOlX

*

AEROQlllP CORP FOR SPECIAL TORQUE

VALUES.

* DEL

MAALIFACTURIIYG co.

* STOFFEL SEAL

CQ.

~ 4 4 7 ~

FIGUR 11 19

FU L

ADDITIVE LENDER UNIT 555 3

INSTALLATION

V I W

July

25

966


39/57

Volume

I1

TURWPUMP

HOUS ING

FLIGHT

NOTE:

F R

TO APPENDlX

FOR

SPECIAL

TORQUE

VALUES.

HAA.

ROCKETQYHE

DfVlS lOH

LOCAT

ON Y

I l

LUBE WSt M

FILT R

HAS-26723-

FIGUREII 20 LUBESYSTEMFILTER NAS-26723-1-INSTALLATION

V I W

uly

2 5 966


40/57

Volume

MAIN

LOX VALVE,

PART

NO.

409849

The main lox

valve

49)

controls the f l ow of lox to

the

t h rus t

charnbe r

~ 2 8 )

The norrnaily c loscd main lox valve is opcncd by fuel p u m p discharge

pressure, which i s

directed

to

the

valve

opening por t by

the

fuel cont ro l l ine

as

embly 6 )

As the main

lox

valve opens,

a

c a m

at tached

t the valve gate

shaft

opens

the

ign i te r

fuel

valve

(~46)

The

main

lox valve

remains

open

until

the

explosive

-actuated (conax)

valve (B )

is

fired, allowing fuel p u m p

discharge

pressure

to flpw

to the

main ox

valve clos ing port ,

Pressure at

the

closing ?art

equals pressure at the opening port and

the valve closes

under

in ternal spring pressure,

Simultaneously the c a m

inkage

causes the igniter

fuel

valve

to close

u n d e r spr ing

pressure.

The m in lox valve actuator cylilzder Is equipped w i th a the rmas ta t iea l ly

control led

electric heater

t o

prevent

the

actuator piston O-r ings f rom

f r e e z i n g

due t the ext reme low

tem pera tu re of the

lox. see figure 11-23 f o r installation

view

)

1

VENDOR:

R

ocketdyne Division,

North

American

Aviation

Inc. lpar t

no 409849)

2.

LOCATIONF

Sta t ion95

3. SERVICE:

Lox

CAUTION

Valve

cleaned for lox

service; do not

use

lubr icants

2

4

PRESSURE:

Operating: 206.8

& 34.

5 ~ / c m ( 300 & 50 psig

5. ELECTRICAL CHARACTERISTICS:

a. Heater power: 400 &

60

W

b. Thermostat :

1)

Closes

at

32.2& 2 . 8 O ~

90 5 ~)

2 )

Opens a t 43. 3

2.8 C(110&

5 * ~ )


41/57

Volume I

A A

SECTION B

FIGUR l I - 2 1

U I N OX VALVE 4 9849 SECTIONAL V I W

July

2 5

1966


42/57

Volume 11

IGNITER FUEL

VALVE P-4RT NO, 407789

The

igniter fuel

valve 346) is a

spring-loaded

normally c losed valve that

is

opened

by

cam

located

on

th main lox

valve

~49) ate

shaft.

During

engine s tart , the

igniter

f ue l valve leaves

the

closed pos i t i on when

he

main lox

valve

is

approximately

1-04

ad

60

d)

open

and

r e a c h e s

the

full-open

position

when

the

main

o x

valve

is

approximately 1.4 r a d 8 0

d)

open.

The i g n i t e r

fuel v lve remains open, permitting

high

pressure

fuel

to

flow to the

unitized

injector and hypergol

cartr idge

~ 3 6 ) and the ignit ion monitor valve

B 38)

for

-in fuel

valve

8 3 9 ) actuation.

During engine shutdown, as the main fox

v lve closes, the ign i te r fuel

valve

closes under internal

spring pressure,

shut-

ting off

the high-pressure

fuel flow

to

the

hypergol car t r idge ,

the

igni t ion

monitor

valve,

and the main fuel valve. see f i gure f - 2 3

for

insta l lat io n view. )

1 VENDOR: Rocketdyne Divis ion, N o r t h A m e r i c a n A v i a t i o n I n c . part

no

407789

2.

LOCATION:

Attached

to

main

lox

valve

at

station 9 5

3 SERVICE: RP- l fue l

4.

PRESSURE:

Proof : 1 3 7 9 ~ / c m ~ ~ 2 0 0 0 p s i ~ )

OUnET PORT

INLET

PORT

VENT

PORT

SPRING

SE TION 4 A

FIGURE

11 22

IGNITER

FUEL V A L V E ,

407789

- SECTIONAL VIEW

11-42

Ju ly

25

1966


43/57

Volume I1

*NAA AOCUETOYHE

OlYl5lON

* PARKER SEAL

CO

P CKING

RQ114-IW3-1M)4

UTILIZED

CH ECK V A L V E

(SEE

FIGURE 11-13

FOR

IHSTALLATlON YI

EM

RDlE3-9016003

RDlll-1011-n314

(4

PLACES

M A I N

LDX VALVE

RD153-5001-EW03

( 4 PLACES

F I G U R 1 1 2 3

MAIN

LOX

V A L V E 4 0 9 8 4 9 , AND IGNITER FU L VALVE,

407789

INSTALLATION

VIEW

sheet

o 2


44/57

Volume

11

BELT,

NAS1003-29A

3 PLACES)

F L l

GHT

MAN1FOLD AND

TUBE

ASM

303660

SEAL A s s Y ,

303964

MSZ4513-25

I G N I T E R FUEL

F U E t

CONTROL

L l W E ASSY,

(SEE

FIGURE

11 17

FOR

INSTALLATION

NAS679C3W

3 PLACES)

RU

153-5001-0003

14

PLACES)

TUBE SU

557268

REFER TO A P P E N D I X I

FOR SPECtAL

TORQUE

VALUES

AA, ROCKETDYNE DIVISION

IIWOE

FlCWREIL 23 MAINLOXVALVE 409849 ANDIGNlTERFUELVALVE

4 7789

INSTALLATION

V I W

Shcet

of

2

Ju ly 2 5 1966


45/57

Volume I1

MAIN FUEL VALVE P A R T NO. 409124

The main f u e l

valve

~ 3 9 ) s a normally closed butterfly-type valve

that

controls

the

f low of

fuel to

the

thrus t

chamber

~ 2 8 )

t engine start ;

the

i gn i t e r fueL

valve

~ 4 6 ) s opened

t al low

h i gh -p re s su re

fuel o flow to

the ignit ion

monitor

valve

~ 3 8 ) The ignit ion monitor valve s

then

opened

by

pressure

f r o m

the

fuel in jec tor manifold,

allowing

h igh - p r e s s u r e

fuel t o f l o w t o the opening

con t ro l

post of the main

fuel

valve ~ 3 9 )

A t

engine

shutdawn,

the h igh - p r e s s u r e fuel is vented

back through

the igni t ion

moni tor

valve

in to the hypergol cartridge

~ 3 6 )

nd

the

main

fuel valve c loses under

in ternal

valve

spring

pressure.

see f igure II 5 for insta l la t ion view. )

I.

VFNDOX: Rocketdyne

Divis ion , Nor th American

Aviation

Inc.

( p a r t

no. 409121

2

LOCATION:

Station

91

3. SERV f CE: R P- 1 fuel

4.

T E M P E R A T U R E :

Operating:

2

1.

1 t o 54 ~ O C70

to 1 3 0 O ~ )

5.

PRESSURE: Operating:

24

1

34.

5

~ / c r n ~ ~350

a

50

ps ig

IGNITION MONITOR VALVE P A R T NO. 554838

The ignition monitor

v alv e ~ 3 8 1 ,

t h ree

-way, pressure

-actuated valve,

monitors satisfactory

ignition before direc t ing high-pressure fuel to open the

main fuel valve ~ 3 9 ) Pressure

buildup sensed

at

the

thrust chamber fuel

injector manifold opens

the

ignit ion monitor valve allowing t he h igh-?ressure

fucl t o open the

main

fucl valve. ( see figure

U-27 for instal la t ion

view.

)

1,

VENDOR:

Rocketdyne

Division

N o r t h

A m e r i c a n Aviation

Inc,

pa r t

no

5 5 4 8

38)

2.

LOCATION: A t t a c h e d t o

main

fue l va l ve ~ 3 9 ) t stat ion 8 9 .

3 SERVICE: R P 1

fue l

4.

PRESSURE:

Operating: 10. 3 3 . 4 ~ / c r n ~15 5 psig)

Ju ly 25 , 1966


46/57

Volume

I

A-A

MDUHTING

POINT

FOR

EXPLOSIVE

ACTUATED

ICDAAXI

VALVE MANIFOLD PART

O FUEL

CONTROL

LIME

SSEMBLY)

VENT

POUT

FUEL PRESSY RE

SENSING

FORT

IT

THRUST

O.K.

PRESSURE

SWITCHES)

SECTION

A P

SECTION

B E107mC

F I GUR

11

24

MAIN

FUEL

VALVE

4 9124

SECTIONAL

VI W


47/57

Volume I

N G ROCKETDYNE DIVISION

FIGURE

11 25

V IN

FUEL

VALVE

4 9124

INSTALL-4TION fIE Zf

Ju ly 2 5 1966


48/57

Volume

V LVE

PRESSURE FROM

THRUST CH MBER

FU L N J E TOE

M NIFOLD

SECTION

F I G U R

11 26

I NITION

MONITOR VALVE 5548 8 SECTIONAL V I W


49/57

Volume

VUT.

MA l l

EL VALVE.

YAS679CS

SEE FIGURE

D 25

2 PLACES FOR

INSTALLATIOV

V I EW

* NAA . ROCKETOXME DIVISION

* SnLLMAN

RUBBER

IIIV.

ELECTRADA CORP.

FIGURE

11 27

IGNITION

MONITOR VALVE 554838

IKSTALLATION

V I W

July 2 5 966

II 49


50/57

Volume

IT

THRUST 0

K. PRESSURE

SW~TCH,

A R T

NO. NA5 - 2 7 4 4 6

The

t h e e

thrus t 0 . pressure switches ( ~ 4 1 )

monitor engine

t h rus t

s

a function

of fuel

pressure.

Pr io r to launch the switches

actuate

t o

in i t i a te

t h e

launch commit signal.

Should an

engine

malfunct ion during flight, as

ev idex tb

by

thrus t decay and subsequent loss

of

fuel pressure, the switches deactuate t c

initiate shutdown of

the

malfunctioning engine,

At S -1B stage

f l ight

te rminat iGn,

the

outboard engines

are

normally

shut

down

when

engine

thrust

decay,

re

ultir.,:

f r o m lox depletion, causes the outboard engine thrus t 0

K. pressure

swi tches

to deactuate

see figure

11-23

f a r installation v i ew , )

1

VENDOR: Southwe

stern Industr ies

Inc

part no,

~ ~ 5 8 0 7 :

00)

2. LOCATION: Station 100

3.

SERVICE:

R P - 1 fuel

4. TEMPERATURE: Operating:

- 5 4 to

74OC

- 6 5 to +

1 6 5 O ~

5 PRESSURE:

2

a

Operating: 69 ~ / c m 1000 psig) nominal

b.

Proof:

1 2 4

1 PJ/crntg 1800 p i g

min

c. Burst: 1655 ~ / c m

2430

psig)

m i n

d.

Static sctting:

5 5 2

10 ~ / c r n ~ ~ ( 8 0 0

5

p s i g ) '

at 10 to

3 2 ~

5 0

to 9 0 O ~

6. ELECTRICAL GHARACTERISTICS:

a. Switch: (SPRT)

5-A resistance

l oa d

at 6 0 ~ z

6 0 cps)

b,

Insulation

res i s tance :

5

megohm min at 500

to

600 V

c. Contact res is tance: 0. 1 5 ohm max

d.

Operating voltage:

1 6 t o 32

V

EXPLOSIVE-ACTUATED(CONAH

VALVE ,

P A R T

NO.

NA~-26594-1

The

normal ly

c losed ,

explosive -actuated conax valve (B blocks fue l

con t ro l pressure

to

the closing control por t

of the

main lox valve ~ 4 9 )

When he

valve

is

f i r ed , a

branch

of

the

fuel

control line

assembly 6)

con-

nected

t o the main lox

valve

do s i ng control p o r t is opened; permitting fuel

pressure to

close the

main

lox

valve.

( s e e

figure

l l -29

f o r

installation view.

1. VENDOR:

onax Corp.

( p r t no. I 80400 1 - 0

1 ~ )

2,

LOCATION:

Attached t o main fue l

valve

~ 3 9 )t station 9 2

3. SERVICE:

R P - 1

f ue l

4. TEMPERATURE:

- 34.4 to

148 .9 ~ -

3

to + 300 F)

5.

PRFSSURE:

2

a

Static: 6 8 9 5 ~ / c m

1

psigj

b. Proof:

1241. BI/crnZg

1800

psig

6 .

LEAKAGE None a l lowed

7.

ELECTRICAL

CHARACTERISTICS:

a.

N o f i r e c u r r e n t :

0 . 5 A f o r 3 0 + 2 sec

b. Al l f i r e current: 2 . 0 * 0. 1 A

f o r

0. 100 sec


51/57

Volume

FIGURE

11 28 THRUST

0

K. P R S S U R

SWITCH

N A 5 2 7 4 4 6

IN

ST LL TION

V I W

uly 25 1966 11 5


52/57

olumeII

FUEL CONTROL LINE

4SSY

SEE F I G U R E D I7

FOR

INSTALLATION VIEW)

NAS679C3W

4 PMCESE

NAA,

Rb E I T lY NE

DIVISION

E 2 24C

ROTE:

EFER

TO APPENDIX

I

FOR SPECIAL

TORQUE

VALUES

F I G U R E

11 29

EXPLOSIVE ACTUATED CONAX)

V A L V E

N A S 2 6 5 9 4 1

INSTALLATION

V I W

Lt 52 July 25 966


53/57

Volume

I1

HYPERGOL CA R TR I D G E ; P A R T NO, 6 5 1 150

The

hypergo1

c a r t r i d g e ( ~ 3 6 ) s

us e d t o es tab l i sh

pri ma ry ignition

in

the

th rus t

chamber

B 8) .

The hypergol ca r t r i dge contains

tsiethylalurninurn

(TEA) that

igni tes

spontaneously on contact

with

any

source of oxygen.

Fuel

control

pressure

f r o m

the igni ter fuel valve ruptures the burst

diaphragms

within the

car t r idge

and

forces the

TEA nto

the

thrust chamber

where ignit ion

with

previously injected lox occurs.

see f i gu r e 11-30

f o r

insta l la t ion view

CAUTION

Handle

and

i n s t a l l

the hypergol cartridge

in accordance with

Rocket

-

dyne

Specification RA 0 2

10 - 3 1

5 .

1 VENDOR:

Rocketdyne Divis ion, North A m e r i c a n Aviation Inc, (part

no. 651250


3 HAZARDOUS

MATERIAL:

TEA i gn i t es spontaneously upon cuntact

with any

source oE oxygen, a l s o reacts

violently

with water , alcohol,

acetone,

and chlorinated hydrocarbons.

4.

DIAPHRAGM

B U R S T

PRESSURE 207

1 7

bT/crnZg (

300

25

pig

5.

LUBR ICAT ION : Wet O-r ings with R P

1

fue l

o r

DC55 b ow corning)

p r io r

to

insta l la t ion

6

LEAKAGE: None

permit ted

7 . PHYSICAL PROPERTIES O F T EA :

a. Formula:

A1

C Z H ~ ) ~

b, Molecular

Weight

114, 5

c. F r e e z i n g Point: - 4 7 ~ - 5 3 O ~ )

d.

Boiling Point:

+

~s ;c(+

81 ~)

e.

Specific Gravity: 0 84

f.

Density:

838

kg/rn3 (7.0 2

~ b / ~ a l )

g. Energy

Release: 8,749,126

3/kg 18,300 B T U / ~ ~ )

h,

Flame

Tempera tu re :

+

644OC (+

1 ~ 0 0 ~ )

8. PREINSTALLATION INSPECTIOm

Rejec t

f o r any

of the following

causes:

a.

Fire or smoke when remov ing car t r idge f rom s ea l ed

package

b.

C a r t r i d g e

dropped

mare than

2, 5

cm

1

in.)

c.

Any

damage

to c a r t r i dge or O-ring

d

r o s s

weight deviat ion grea te r

than 0,000 3

kg 0,0007 lbm)

when

wiped

clean and weighed on a

scale

sensitive to

0 000 kg

(0.0 00

l b d

e

Age of

over 24 months rom date loaded

July

25,

1966


54/57

Volume

11

FUGHT

HYPERCOC

;y lm

OLT

(FROM

IGNITER

FUEL

V4LVE )

\

aL

MS20073-04-04

2 PLACES)

NOTE:

NAA, RPCKETDYHE DIVISION

FIGUR 11 30 HYPERGOL C A R T R I D G E

65

1150

INST LL TION VIEW

uly

2 5

1966


55/57

Volume 11

SQLID PROPELLANT GAS GENERATOR PA R T NO.

6

1240 -41

The solid propellant gas genera tor SPGG,B 20)

supplies hot, h i g h - p r e

s

sure

gases t o the

ga s t u r b ine B

19

for engine

start ing.

The

engine

s t a r t signal

energizes

two S P G G i n i t i a t o r s B 1

1) t o

ign i te the

solid

propellant.

As the

solid

prope l l an t

burns,

the

hot

gas

output spins

the

gas

turbine

and

a c c e l e r a t e s

the

turbopump

~ 8 )

s e e f i gu r e II-31 fo r

installat ion view.

)

1

VENDOR:

Rocketdyne

Division, North

American Aviation Inc

p r t

no. 6 5

1240 -4

1)


2

3.

PRESSURE: Operating burs t diaphragm

ruptures)

4 4 8 ~ / c m

650 p i g

4.

FL A ME

TEMPERATURE: Approximately

1 3 9 6 ~ 62544OF)

5. FLOW RATE: Approximate ly 2.13 kg/sec 4 . 7 lb/sec) f o r

approxi

rnately I sec

SOLID PROPELLANT GAS GENERAT OR INITIATOR P A R T

NO,

NA5-26737-4

The solid propellant

g a s

generator initiator B 11) an e lec t r ica l ly

ac

tivated pyrotechnic device,

produces

hat

par t ic les

and gases

to

igni te

the

so l id

propellant

charge of the SPGG ~ 2 0 ) see f i g u r e 11- 3 1 for installation view. )

1

VENDOR:

Special Devices

Inc part no. 100770)

2 LOCAT ION : Station 66

two

each

SPGG

3. ELECTRICAL

CHARACTERISTICS:

a.

N o

f i re :

250 V

60132 60

cps)

b. Fire: 500 V, 60

Hz

6 0 cps)

t

1. 5 A min

L IQUID P R O P ELLA N T GAS GENERATOR AUTOIGNITER, P A R T

NO.

6 5 1

139

The liquid propellant gas ge ne r a to r

LPGG}

autoigni ter ~ 4 2 ) s

a

pyr o -

technic

device

that

i s u s e d

t d

ensure

ignit ion

of

the

boot s t rap propellant in the

LPGG

combustion

chamber ~ 2 2 )

Two

auto igni te r s are used

on

each

LPGG.

The

autoigniters

a r e f i r e d by hot g s e s from the solid propel lant gas genera to r

~ 2 0 )

A two-A

firsible link,

connected to an e l ec t r i ca l con rec to r on

the

auto-

igni ter ,

burns

t h rough when

the autoigniter f i r e s to provide a

moni tor output

indication.

~ ef igure II

f o r

insta l la t ion view,

)

I.

VENDOR: R

ocketdyne Divis ion, North American Aviation

h c

art

no. 651139 o r 651175)

2. LOCATION: Station 7 7 two each LPGG


56/57

Volume

3 ELECTRICAL CHARACTERISTICS

a

Resistance between

pins

and B:

0 to 0. 15

o h m s

b

Resistance between

pin

and ground: Infinite

4 URN

TIME

a.

Part no 65

39:

2.0 sec min)

t o 5.0 sec max)

b.

art

no. 651175:

2

5

sec min)

o

5 5

sec m a x )

5 .

I NITION DELAY:

0

t a

500 m s


57/57

Volume

I

NUT,

RD114dCO3- IWY

AD761-2061-0338*

mLT

PROPELLPNT

GAS GENERATOR,

651175'

2 PLACES

5E

LIQUID PROPELLANT

GAS

GENERATOR

COMBbSTION

CHAMBER,

[SEE F IGURE

D-6

OR INSTALLATION VIEW

G ASKET AN30 +6C

2 PLACES

PROPELLANT

ROTE: GAS

GENERATOR

EFER TO APPENDIX I

FOR

SPECIAL

TORQUE VALUES

+ N A A . ROCKETDYNE DIV IS ION E l 2 I 2 5 ~

Section II - h1 Engine System

Documents

Transcript of Section II - h1 Engine System