propulsion the key to moon travel

8/4/2019 Propulsion the Key to Moon Travel

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ROC-ETDYNE

A OIVISIUM OF NORTH AMERICAN ROCKWELL CORPORATION

6 6 3 3 CANOGA AVENUE. CANOGA PARK. CALIFORNIA 9 1 3 0 4



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TABLE OF CO N T E N T S

Ch3.rt:

Number

T k o r -De l t aA t l a s F i r i n g

F r i c n d s h Q '"?u

M e r c u r y - A t h s Launch

W-2 Englilc

3'-1 F i r i s g

5-2 Engine

Rocketdyne Large Engine I'rrograrn

B a s i c C h a r a c t e r i s t i c s

Solid Pr~pe l lmt o ck e t M o t o r s

Solid Pro p u l s i o n Perchlorates

Liquid Propa!lar,b. $>ace Engines

Space E n g i n es 2 ro d u c t Areas

P r o j e c t Gemii~i ro p u l s i o n Systems

R e s e a r c h - Present an d Futlire

Electron N i e r o s c o g y

E n g i n e e r ic g C h e m i s t r y R e s e a r c h

S p e c t r o m e t r y

Nu z l i o n i c s

Nuclear Rocket Engice

I n t e r p l a n e t a r y Zxplorcztioil



Rznger , Surveyor, Lunsr Orbiter, and finally, Apollo--these a r e the steps thzt

wi l l take us to the ?doon.

Ranger w i l l crash-La~dns't'triz;l~t.ntson the Moon. Surveyor will soft land abor;t

250 pounds of instrumerits on tile Tmar surface, It may be equipped with a drill

to san pic the lunar surface for chemical and phy~ica!mdysis , Lunar 0;'biter

v~i3ilmY-Jey the I u n z r surfscz fo r s s e anding are as , There's x u c h to be learned.

Some Cia?, soon, m3r-i IS g o i ~ ~ go have to survi.ac there.

Th e Moon p~eset?"; .a aspeci~dchzliengc. Uniike t h e Eart'n, the ?door*--with itslack of at=osphtr.e z:ld sceoi-r~~z~~yi:~i j ;inds and rains to ezuse 8,-osion--has

preserved a recor.6 os' the soiar sysc;?r~sarly history,

Technologic21 progress is m ele-ri;e~t f ~trcrigth i~oi?gations. The r2ce tothe Moon has become 2 r ~ 2 [ i o ri;c;iczto~" f the technological progress achieved

within two cornpsting Idaiaziez .

I n additlor, to adding ~fgclfic;tl?t!yLO n1z.n'~ cientific knowledge, Troject Rpoibwill provide mazy 111ate:sial bsnef i t s- -new power sources, new discoveries and

technical acil-iis~~ements,ew joks, new f-iorizono.



SPACE MISSIONS

You a r e living in what is probably th e most exciting time man ha s ever known.

New and amaz ing information about the universe is being collected with every

spac e probe launched. Almost ever y scientific discipline is expmdii~gts field

of knowledge as a reslllt of the National Space Program.

This year, longer earth orbital :lights we r e planned zfid attained. Soon the two-

man spacecraft, Gemini, will be launched for training of astronauts in rendez-

vous and docking. The Apollo-Saturn Project of manned flight t o th e Noon will

g e l underway in z??r3uC,wo y e u s with training flights in ear th orbi t. Following

&is, a manned circumlunu flight will be made with a landing sched~ledy th e

end of this decade.



SATUXN CONFIGURATIONS

Now let's look at the vehicles tha tw il l have the enormous power needed for the

lunar launching, Saturn I, Blocli: H: S-I stage of eightRocketdyne H-I engines

of 188,000 pounds thr us t each and S- N stage with si x engines of 15,000 pounds

thrust each.

M e r initial flights of the Xabarn I, it will beuprated "L the Saturn IB configura-

tion by substituting S-LYBwith one Rocketdyne 5- 2 engine for the second stage .

This new stage has over twice "Lhe thrust of the earl ier stage. This launch vehicle

vrUl be used to place the kL~ol lo%oiler plzteHspczcecra.ft and the Lunar Excu2-

sion Module, o r LZM, in earth orbit for cre w tra ining in weightless environ-

ment, and rendezvous and doclcing techniques. In addition, the Saturn IB could

launch a lunar logistics system spacecraft.

The Saturn Td will provide power for lacnchicg the spac ecraft. The pad weight

of this vehicle is 6 million pounds.

S d u r ~ ; will l u n c h 45 t o ~ snto lunar orbit trajector y, This vehicle is almost

'as all 2s the Los AngeLes City Ejll . B would extend the length of the field i n

Los Al~gelesColiseum.

One F-l engine for the Satam V develops as much thrust as dl eight engines s f

the S8iuzln P version. Pf the Mercury spacecrait, weighing one and one-halftons, is used fo r e ~ ~ p s r i s o n ,hese figures show launch capabiltties fo r low

altitude earthorbit:

Sdurn i '7 Mercury Spacecraft

S&un IB I1 Mercury Spacecrzdt

S a i ~ r n 80 Mercury Sgacecraft

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SATURN CONFIGURATIONS

SATURN I UPRATED SATURN I SATURN PPAYLOAD, LOW ALTITUDE ORBIT-------22,500 LB ---------------------- 36,000 LB ...................... 280,000 LB

DIRECT ESCAPE~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~- - 95,000 LB



TYPICAL MPAIL'NZD LUNAE, %TB310N--PR3JECT ABOLLO

The Saturn V launch r;eli~ic:e 1vZ1 be cs,ssen"nlec! and checkea ou t ir, the Vertical

Assembly Suilding (VA3) . This building, f i f ty stcries high, hzs b u r bays,

each equipped t o assemble a d check oui: one vehicle, The door on the VABis 450 feeti high pihe worid2sC*zliss:Goor) The mis s i l z wl'ii Sc r n o r e d t o Launch

Cor~pXex s Cape Kennedy, Florida, on a moving piatform th e size of a base-

ball dialmond.

Pad weight of the Sahm V is a& million poiax~ds,o r as much as a n ~ c l c uub-

mar i n e o r i ~ v o azen jet airliners, This w~igIr?"!~ i c l ~ d e she prepe l l aa t s , the

s t r u c t u r e , and th e Apollc, spacecrafi,

Spacecraft Ch~xacterstics

Spacecrdt ' ~ 7?iTlX7 v-7 Dimensions-

Command hvCo2ule 10,000 lbs. 154 in , diameter at base146 in. from base to top

Servicc Module 50,000 lb s. 154 in , diameter182 in, long

Lunar Excursion 30,900 Ibs. 130 in . diameter

Module (LE1;Q Height180

i n , on fou r l egs

LEM 6%UG99 126 in, diamete r

102 in. high

LEM c'lander9' Four legs zndtank sect ion

Total. Apollo Spacecraft: 90,030 ibs,

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The first (S-IC) stage, poweseA by rive P-1 engines rate d z& 7-1/2 mill!on pou.r.ds of thrust, will fire

fo r 1.51 seconcis, Durfx.ig this first stage firiag 50 railway tank cars of propellafits wiil be consurncd

zt the rate of 1000 galicrn~ e r second. At cctoff the Saturn V ve5icle will have reached an altikL?de i203,OOO feet and a velocity of 7500 feez per second. bm ed ia te ly after cutoff tha S-I1 ulk ge rockefs

ar e fired mci a shaped charge is ignYed which peels away the interstage str uctur e between ihe firs t(S-IC) and second stages (S-a). E i g h t 103,003 pound solid propellant retr o-ro cket s ar e then fired

fo r less than 1 second whjeh causes the first stage to deceler &e m.d sepLara.te from the second stage.

Eight 26,000 pound th rus t, solid prop elimt ullage rock ets wi!: be fired for 3 , 8 scconds to se ttle the

propellants to in sure proper igngion of the five J - 2 engiries that power this s e e , This stage, wit11

one million pounds total t hru st, w i l l Tire fo r 3 91 seconds to boost th e vehicle to an dti tud e of 99 rnilcsand a speed of 22,008 fe et pe r secsad, Foilowing c~ to ff f the five J - 2 engines, the S-&WR u1l2.ge

engines fi re followed by four solid propellant retro -rocket motors mounted on the in te rs twe struck~irc,rated zt 35,000 pounds eacli, will fire for 1 .5 to 2 seconds and scpay&e the second and third s t q ~ e s ,

A s the third (S-WE) stage is ~ e p u z t e d ro m "ihe second (53-10 s t a g e , tw o 1'150 goland thrust, liquid

propellant (nitrogen tetroxide-rnoilrsmethyl hydrazine) rocket engines continue to fire to sett1.e the

main engine propel lants during ignition of the single 5-2 exigine, The 5-2 engine will lire for 160secandc;md injects the third stage with. its Apollo spacery reC nto an earth or52 iLt avelscity of 25 , 55 5feet per s ~ c o f i d ~ his pac;k~?~gehe11wi l l orbit th9 earth approximately 1-1/2 tim es, aiiowing ampie

t ime to accuratel y deterrr,ine f i e o-bit and make various other checks i n preparation f u r emljaz2ring

on a trajectory t o w a d the moon, A second fir ing of 340 seconds will obtain a velocity of 35,680 f ee t

per second for the lun'w traj ect ory , Alctitude c o ~ t r o l s maintained during th e orbi t period by twomodules mounted 180" 2pmt on th e aft portioil of the S-WB s a g e , Each module contains an aft-facing,

1750 pourlc! t h ru s t ci!zge mu b o prcvioiisly mentiisai~ed; "LJQ mgerr t idly oriented, 8 50 pound-thrust-- motors, and one radially oriented, 150 pound motor. By pulsing the 150 pound chzi.rn5ers in pr op er

cornbinations and sewences, yaw, pitch and rol l control wi l l be maintained during the coast periods ,

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Shortly after e ~ z t e ~ i n ghe Ilznar flight trajectory, a four-section fziiring zi.,,dapter is jettisoned frcm

the LEX by shaged charges. E7nenfairings are cleai-, the Apolio Command a~ckService Tvlodvles arerotated 180 degrees mcl joined nose to nese with the &EM mounted ord the forwcwd section of the

S - F J B . The complets Apollo spacecraft is the11 separ ated f r om the S-,VB stage by firin g explosivebolts o

Approximately thr ee mid-cour se correcticzs zre a~ticipatedor a total change in velocity of appsox-imai;ely 200-300 feet per second. The flight to t he Moon wG1 require 7'2 hours.

Before proceeding further, !et9s exarniiic the remaining Apollo Pzopulsion System:

Propellants*

Service Module Engine 22,OCO ponnds thru st, ablativs thru st chamber NTO/ 50- 50

Serv ice R4odule .4t".,tude Sixteen BCO-pound-thrust , adiation-cooled

sad &$aneurer ng $ystern thrust chambers

Commmd Mod~ileAttitude

LEM Mo6a1e Engines

"Bugp9 Attitude andiMane;zvering

Lunar Ascent

Lunar Descent

L T308-186-196-3

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[,jl(~AD I V I S I O N OF N O R T H A M E R IC A N AVIATION . I N C .

Twelve 91-pound-thrust , ablative thrust chambers NTO/MME

Twelve "%8-pound-thrust, radiation- cooledNTO/

50- 50thrust chambers

4,000-pound-thrust, ablative thr ust chamber NTO/ 50- 50

Throttteable, 1 ?, 500 to 105Qpounds thrust NZ'O/~O-50



At the preci se momenit de termined by th e ,giidance sys tem the Serv ice Module engine w i l l be firecl

for 324 seconds to decelerate the Apollo spacecraft by 3150 feet pe r second, This deceleration will

place the spacecraft into a i u l l a - orbit. Shortly &er entering orbit two of the crew w i l l t ransfer tothe EEM.

The LEA4 will then be s~3paateij.rom the res t of the Apollo vehicle an d will be put into an ellipticd.

orbit which pa ss es within 50,090 feet of the lunar sur face by firing the descent engine ;or alx111t3%seconds. The Apollo Commar;d 2nd Service Modules will remain in an a.pproximatelg c i r c ~ l a r u t ~ w

orbit with 3 velocity of 5500 feet par second, while awaiting th e ret urn of th e LE34 module. ,4s the

LZM passes the lo w orbit point of 50,000 feet, the dcscer-.t engine will tnen re-ignite and fire fo z 32 6

seconds, which will change the velocity 5700 feet pe r second, md will bring the LEM to a hovering

position about 1060 feet above t h e lunar surface. Fro m th is point the astronauts wlli select their

landingsite

and then maneuverth e

LE Mt o

the moon's su rface by controlling thet h r us t

(I f

t h edescent

engine and use of the zittitrade control sys tem.

The probable landing a r ea will be in the w e a west of the Sasof Tranquilit y, CompositionoE the luna r

silrfzce md knowledge of t he lunar environment will have been gained through eariier Surveyor artd

Prospector flights, Hall'-way point in t h i s hjstoric flight will now have been 'eached, In he specid.

protective suits the ast ro na ~t swill tak e tu rn s mziking up to f our hour excurs ions inta the nearby

lunarscapc. It is planned that twenty-four to forty-five hours will be spent on the moon.

After th e astronauts have compl&ed their exploration of the l x n u surface, they will re-embark ir,

the LEM and at the propei: moment to intercept the Apollo modules i n lunar orbit they will :ire theascent engine. The LL laade r 97ortion of the EEM is used as a launch pad %nd remai ns on the ?moor,,

The ascen t port ion of the LEM Imown as the EBbug9Pccelerates to a 5500 foot per second orbit by

firing the asceni engine for zibaut 430 seconds, a~c!hen maneuvers to intercept the Apo110 Commaxd

and Service Modules. The two lunar astronauts will then rejoin thei r companion in the Command

Module for th e re tur n passage to earth. Tie abandoned L4b~g'Pemains in l u n a orbit



The ret urn tr ip to eaxth, whish will require about 7'6 hours, will he accomplished 2s

follows: The Service Mo6ule engine will be fired for 157' seconds which increasesth e velocity by 3200 feet per second and puts the Apollo into a? earth-return trajec-

tory. On arrival zt the earth-return corridor, approxim&ely 80 nautical miles abovethe earth, th e Serv ice Module e n z f n s is used to accur&ely position the Apollo for finalre-entry into the ear th' s atmosp!~e ra. The Service $Aociule will then 5e jettisoned and

th e Command Module maneuvered by its attitude control syste m to prsperi y orient itfo r re- entry,

The Comma~tlid ehicle will us e a skip-type re-entry path to keep heai and " g j 9 ioaGswithin tolerable limits. This skip-type re-entry path will be controlled by orienting

the modtiic by meals of the a*itit.;dc control rockets toprovide the l i f t and drag char-acteristics which will produce t h e corr ect re-entry traje ctory. The aerodynamic

ehwacteris t icsof the Command Module (L/D = 0.5) z e uch that changes in attitudewili er~itblethe rew to sclect any landing si te within a ell ipse 5000 mi le s long and 506

i s Cu r r e n t planning calls fo r a "waterM landing,

Final descent will be done by releasing a drogue chute at 25,000 feet, followed by

111ortitr deployment of three large chutes at 15,000 feet which wi l l decelerate thespacecraft to a safe landing ve?ocity.

T308-186-196-5

g,LA DIV IS IO N O r N O I T I I AHLR IS AN AY IA I1 O N INS .



The Saturn V wi l l provide power to mske a lunar landing possible. This chut shows

the spacecraft which will provide life s q p o r t for the crew. The Apolio

spacecraft consists of three major units: The Command Module, the Service Module

and the Lunar Excursion Module eoir*posec3, oi" he two-man 4CbcgvBn.d the '"andervP.

Propulsion syste a s incl?:de attitude con trc l sys tem s for th e Comr*?zndand Service

Modules, The Servi ce Module us es oce engine fo r lunar orbit injection, ejectior, into

earth re turn "Lajec t~ ry rid mid-course correct ions. The 64b;g'9 has an attitude and

malleurering propu!sion system a:~da l u n a r take-of1 engine, The luna r descent. eiigine

is a p a t of the which be left on th e Moon, Rocketdyne is developing

the attitude .control system fo r the Command Module and the descent engine for the

Lunar Excursion Pvlodule o r LEM as it is called. The total weight of these thr ee mod-

ules will be 45 tons. The Saturn V 1a.uneh vehicle must accelerate this weight to ove r

26,000 mph for t:?e luxla flight,

Note t'nie nozzles of thrust chamb ers mounted on the sid es of the LEM and Service

Modxiles for attitude control.

T304-186-89A

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A D I V I S I O N O W NO - V Y AL ICRICAN AVIAT ION. INC .



ROCKETDYNE

A D I V I S I O N OF N O R T H A U E F I tC A N A V I A T IO N I N C



A P O LLO A SCE N T

The manned flight to tile Moon will b e a c c o ~ g l i s h e d y the lun a r orb i t concept,

That is , the Apollo spacecraf t , inc luding the Lunar Excurs ion Moduleor LEN,

will be launched by Saturn V to x l u n a r orbit,

The f i r s t stage d e v e l o ~ i n g -1/2 mill ion pounds t hru s t wil l burn for 150 seconds

and the second s tage wil l burn 393 seconds , The th i r d s tage m7il]. burn for 169

seconcis, shut -down, coast , arid t h en r e i g n i te t o r u n f o r a to ta l of 400 secondst o in~par t ' veloc ity of 36,000 f e e t p e r s ec o nd ( 26 ,6 0 0 n p h ) r e q u i r e d t o p l a ce

the Apollo spa cecraf t into 2n ear t h escap e t ra j ec to ry towaxd the Mooa,

hjected i nt o s p a c e a r e t h e third (S-Dl) stage (now dry) and the Apollo space-

c r a f t still at tached to and mounted on top of the S-NB s tage .



TBANS POSITION

Shortly after entering the lunar trajectory, s h a p d c h arge s peel away

the fairing, leaving the Apoilo in free flight. The spacecraft is then

turned by means of tha &tituck engines to dock, nose-to-nose, with

the LEM ridiag ir, th e forxarcl portion of the third stags. Explosive

bolts m e then f i x 3 t o sepaa.te the LEM f r om th e th i rd stage which

is left behind.

f3 ~ i r l ~ ~ x ~ T ~ T u C m ? E

&,,iD l V l S l O N O C l O D T U AMC* lCAN AV IAT IO N. INC.



APOLLO LUNAR APPROACH

Two or more midcourse correction s will be supplied by the main engine

of t he Service Mo&dle Cluing tlne P -P / 2 day flight t o the Moon, A s the

Moon is appraachsd, greater and greater gravitational pull is exerted

on the spacec rafto Computers on eart h and in th e spacecraft determine

th e moment when the Sezvice Pdodule engine is fired to slow the space-

craft Into the lunar orbit at 5500 feet per second.

! n k ~SLOCKEZTDYXWSL,,:A A DIV IS ION OC N 0 1 T W A H S f i IO A N A Y # A T IO N . I N C



APOLLB LUNAR ORBIT

On approach to the l a d i n g s i te, two of the crew transfer to th e LEhri

and detach f r om the Comms.nc? Module. The descentengine will be

E k e d b r i e Q to place the LZTV: in an elliptical orbit which passes wiYnin

50,000 feet of the Moon, The orbit of th e LEA4 passes nea r the C o n -

mand Module every two hours so that st rendezvous may be possible

ia case of an a.bori-.



LUNPh1 DESCENT

At 50,000 Peet, the Bescc-$ engine will be fired and thrott led as r e q ~ i r e d

to propcl the LEM vi%Aii: 18G0 feet of the l u n z s ur fa ce , The LEM is then

righted to hover over the zrca to select the final. l a d i n g s i te . T he LEM

may translarle ap ta 1000 foe: i-n select ing the ialdirag s i t e . hrnedi&ely

after landicg, the crew will conduct pre-launch checkouts,



ROCKETDYNE



This char t shows the &ton L6tTlzg99eaving the Moon afte r

a two day exploration. Note that the %ton lander used as

a launching pad is left behind.



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i \ ROCDKETDYNE

A D l V l S l O N O F N O R T H A M E R I C A N A V I A TI O N I N C..



AND SERVICE

& n a o c K E x - D YmE :A

D l V l l l O N O F N O R T HA M E W I C A N A V I A T I O N . 1 N t



AP3LLO RE - E N T RY

Atm osph eric bra'xing w i l l be used for r e t o r n of th e Command idodule to

e u t h g s aur f sce . A t t i k d s engines of t h e Cornmmd Module control the ,

r e -en t ry pa th so that any l a d i n g site within a 5,000 by 50 0 mi le area .

may be selected. Pk 25,000 feet, a drogue cllute w i l l deploy f o r slow-

ing t h e c r a i t . M o r t a r s ar c used to deploy three chutes at 5,000 f e e t f o r

lowering th e tree to earth.



~ ROCKETDYNE

A D l V l S l O N O F N O R T H A M E R l C A N A V IA T I O N I N C



DEVELOPMENT PROBLEMS PaSED BY SPACE ENVIROPU'hlENT

A spacecraft in an earth escape trajectory is exposed to a hostile environment. Design of the

spacecraft must take into account the vae2:um, th e high-velocity met eor ite s, high-energy par-

ticies, temperature extremes, and sol ar zsdiation.

The following table summarizes the space environment and its effect on propuisiolz systems:

Zero Gravity Positive e qu ls io n devices must be ~ zsed xe to the tendency of pro-

pellan ts to separat-e into globules which float inside the.p ropei lant

tank,

Solar. Radiation Shielding qai ns t solar f l u e s is curr entl y imp racticaltl. The Apollo

tri p will 23e scheduled when solar activity is not an%!cip&eci, A pso-

gram of orE"Si;7<ngs(ila3' observatories is expected to provide data

which wi l l make th is scheduling possible,

'CJacuum

Meteorites

Due to the l ack cf 2 cooling medium and the start- shop requirements

piaced on a asace engine, new cooling te ch ni q~ ~e sor thrust chsxi-

hers ne,?Ceci, Xzdiztion cooled thrust charfibers axe ur,der de-

velopmezt .

Design of the propulsion system =ust provide for the possibility of

damzge by meteorites.

Lunar Environme~lt Lunar probes u e cheduled for debermining the composition of the

lunar surface. The sunlight side of the Ifison re aches zbout 265 3

while th e dark side is a minus 24 0 F,

High-Energy Particles Electrical a2d eiec trsn ic control equipment a r e effected by these

high energy part icle s,



ROCECFTDYNE

A D I V I S I O N OF N O R T H A M E R I C A N A V I A T IO N I N C



FLIGHTS LAUNCKED BY ROCKETDYT\,TEENGINES

The accomplishments of Rocketdyne propelled vehicles are shown.

Redstone was first flig;~tteestedr., 1953 . Thi s dependable 75,000-pound-thrust

engize failed only once i n seventy-four flights. It lauriched the first United

States satelli te and the fi rs t manned-flight with Alan Shepard.

Tilor is the curr ent space launch worlthorse. Thor launched these spacecraft:

Pioneer, Tiros, Anna, and OSO.

Jupiter launched early Explorer Satellites.

The Atlas Ageria is capable of hurling 5000-pounds payload illto a 308 nzcticd

mile orbit. This is more than thr ee tim es the Thor-Agenacapability. Achieve-

melits includc: Pio nee r, h'lercury, Ranger, ar,d Mariner.

Saturn ha s had six successful launches. The vehicle is powered by eight B-1

e ~ g i n c s ,which a r e simplified, improved vers ions of earlie r booster enghes.

Vir tzd ly all rnzjor space payloads to date h ~ v e een boosted by Rocketdyne

engines.



ROCKETDYNE

& D!V#SDON0 N0.T. A M E W C A N R O CN W EL L C O R P O ~ A T O N



ROCKETDYNE BOOSTED LAUNCH VEHICLES

Start ing with the At las, capable of launching the 3000-pound Mercu ry

spacecraft into orbit with 367,000 ponnds of thru st, this line up ex-

tends to the Saturn V which will be capable of placing 240,000 pounds

into orbit with 7,500,000 ~ o u n d sf thrust. Saturn

Iand Saturn IB

will be used to develop the Apollo spacecraft.



ROCKETDYNE BOOSTED

AAUNCq VEYPAYLOADd"IOBQ

IOQM MI

ESCAPE



;NIa;ly of th e rocke t propulsion s y s t em s that u7iI.l make this voyzge possible

are being develcped by Rocketdyne. In the rarnainder of this briefing, th e

ca2abilities of 3ocketdyne wi l l be described which resulted in this

being selected by NASA to d~velcp major portion of the rocket power s y s -

tems for the kpollo ElAission.



NORTH A?8XiiSCAN AVIATION, NC.

Rocketdyne is one of seven divisions of iil'ortn 'merican Aviation, Incorpora ted . This

division is charged with the development znd pso&ciction of rocket propulsion systems

ranging frorx less than one-tenth paund thzust to t he huge one ar,d one-half million.po~:nd

thrust F-1 engine. Preliminary desigr, is underway fo r engines developing several. mil-lion pounds of th rus t. Activities include liquid prope llant , solid propeliant, hybrid:

nuclear, and electrical prop lsi on.

Los Angeles Division is famous for World W a r 11 Trainer AT-6 (Navy SNJ), P- 51 , and

33-2 5 . The B-45 v~ashe first jst bomber developed in the U.S. The F-88 fighter was

famous in Korea followed by the F-108. Current projects bne th e Sabreliner, the X-15. rocket research aircraft, and th e RS-10.

Space and informat ion Dil-isioii prodaces the air- to -ai r Fiound Cog (GAM-77). Present

development includes the Saturn S-11 (eiizpioying five Rocketdyne J-2 engines), t he Apollospzc ecra ft, and the paraglider ior Gemini.

Autonetics produces inertial navisztisll syshems for the Columbus Division ASC, ai rc ra ft ,

ships, ~ ~ l a r i subn;zrines 2.11d guidance for Minuteman miss ile s. Also produced are com-

puter and technical data systems.

'tornlcs ~nternationals developing SNAP (System for Nuclear Auxiliary Power) Models 2 ,

8, ;.ad10. Nuclear power st3ticrns were built at Wallam, Nebraska and Piqua, Ohio.

Laboratory and r ~ s e ~ c heactors are located in irictcistry and universities.

Columbm produces Kavy A5C Vigilante, T2J Navy Trainer and ~ e d h e a d / ~ o a d r u n n e r

tu ge t drone.

The Science Center condccts basic re se ar ch on reques t by the operating divisions and asdirected by corpor ate management.

T301-186-1A

*? ~ O G E < E T D Y r n ~hr A D I V I - I O N QT N ~ l l t M IME*ICIN A V I A V ( 0 N IN C



TH AMERlCAN ROCKWELL CORPORATIONAEROSPACE AND SYSTEMS GROUP



ROCKETDYNE OPERATION

The Canoga Park Complex enco mpas ses Enginee ring, Xesearch and N",anufac.ti;ringfacilities for the Liquid ~oc ke"i ivis ion , Nuclionics and Researc h. The Atlas,

Thor , upiter , Redstone, ulc' B-1 propulsion sy stem s were developed hi re . Saturn

V engines, 3-2 and F-I. z e nder development. In addition, space engine prog-

r a m s and experilizentai work on advanced products ar e in prog res s, Ez~ginetestactivities are conducted at the nearby Santa Susana Field Laboratory (SSFL) and ;tt

t he i3igh Th rus t T es t A re a, ~ d w ~ d sield Laboratory, California. Resear ch test

firings, both liquid and solid, m e conhc t ed at SSFL with advanced high energy

propellant testingperformed at the new Nevada Field Laboratory near Reno, Nevada.

Van Nuys is th e location of the Space E:lgiae Operati ons, a d he Ordnance Engines

Oper~tion.

Solid propellant motor engineering, reseuei i and manufacture takes place at th e

Solid Rocltet Division near Vhco, Texas.

' Production %d test of At l a s Zoosteers, P-4 target drone engines, and H-1 engines

is accomplished at th e Neosho, IL?issouri pl mt in suppor t of Liquid Rocket Division.

Company reprcsefitatives are maintained at ixldicated locations.

Rocketdyne3s iota! employment Is over 18,000.

?t:> I E O e Z l C E T I I DY * i z EL;,\";~;L DIV IS 'O N OF nOmTM A M t Z n t C A N . IV IA)- ION INS.



AFIELD LABORATORIESr2 f .REGION AND

m * I;0

..SANTA SUSANA

EASTERN

/ * WASHINGTON

*K~ANOGAm8 rn .a CENTRALv i(L4--- P -- *DAYTON

oCLEVELANDrn

AFBSOUTHERN

NORTONa HUNTSVILLE

ETRE DW ARDS CAPE KENNEDY SOUTHWESTERN-VANDENBERG MSFC MAC OD/A

ARNOLD HUNTSVILLE ST. LOUIS SAN DIEGO @ HoUS~ N

MICHOUD-MISSISSIPPI DA C S&lD

TEST FACILITY TULSA OOWNEY

NEW ORLEANS SACRAMENTO SEAL BEACH

WTR SANTA MONICASANTA SUSANA

VANDENBERG AFB HUNTINGTON BEACH

WESTERN

eCANOGA PARK

LANCASTER

ROCKETDYNE

5531 CANOGA AVENUE CANOGCI P4RK CAL1FOONIA 91304



CANOGA COIdPLEX

The Iaur story hea dqu ate rs building is identified

with the Number I . On three sides of this bilild-

ing are Mar?.ufacturing fac ili tie s. The Vanowen

building in the foreground (Number 3) is the loca-

tion of Research and Nuclionics,

T2-63-186-P02C

fp OCMETDYNE

LiS,,u&A DIVISION OP NOR IM AMERICAN AY1ATION. INC



CANOGA FACILITY'

1 . ROCKETDYNE HEADQUARTERS 3. LABORATORIES 5 . WAREHOUSE

2 . ENGINEERING 4. MANUFACTURING6. RESEARCH

ROCWETDYNE* DIVISION OF NORTH &YERICAN RO CSWELL CORPORATION

6e33 CANOGA AVENUE CANOGI PARK CAL~FOINIA 9%-



SANTA EXkiSkSA FIELD LABORATORY

Teat firings s q p o r t both the development and t h e produckion program s. The

rlrgged te rra la 2nd isolated csnyon areas of SSFL, located 10 miles north-

west of the Canog-2 Plm'i, provide natural protection barriers between tesr.

starids. h4ore than two dozer; 1wge engine firing s Z;z~c ccn c~ndrtctecl n a

two sh i f tday . T:?e large ,=,",xds m i l l accommodate up t:, T,300,90f) ywctl~ds EJ ih~, r~s t .v ~ r e , ~ J X J ? ~ ~ Q Ingi;=ea,~ a c hs t:?e F-2, &,-e ired 2 E",dwai.c;2s, C d i ; ' -

ornia. Average daily C I S E ~ C:: 4e.O tons of liqxid oxygen, 120 tons 0 2 liq-aid

.*@ . /&vL beenitrogen, a d ons of liqclid hydrogen. Over 296,030 hat Lririye . i ;es i- ~̂F,rr3

conciucted here.

T404-I86-92C:.dL ;;-? ~ ~ ~ F , F , & ~ " ~ - ; ~ ~ ~ ~ ~!: yag.,rd-kOIV IS 1DN O r NO-TU AMER ICAN AVI*TlOFl INC



SSFb TEST AREAS

AREA UTILIZATION

CANYON,--,,-,,---1 ENGINE TEST

BOWL-,-,-----,--,-, 5-2 ENGINE TEST

ALFA .I,,,-,,-. ATLAS ENGl NE TEST

BRAVO.,,,,,,. F-1 TURBOPUMP TEST

COCA---,- -,-,---SATURN S-IT TEST

DELTA,,,,,, 5-2 ACCEPTANCETEST

LANCE ENGINE TEST

ROCKETDYNE

A D I V I S I O N O F N O R T H A M E R t C I N A V IA T IO N IN C



SSFL COI\XPONENT TEST LABORATORY

Exhaust g ase s supplied by the gas generator t o dri ve the turbopump

ar e fuel rich. The plumes seen her e burn the mixture as it leaves

the stack toremove any safe* haza rd . Ju s t as parts on an automo-

GCe engine W G ?ested, gas generators and turbopumps ar e hot f ired

a!ld cdibrateci before assernb!y on tiic engine. Tha test sYe in th e

Santa Sasana l ~ l o u n t a i n s ilcludcs five Con~ponentTest L a b ~ ~ a t o r i e s .

Taciiities u e available fo:: dzli;i"L.desirria!aiioi; firing of :;pace engine

sys t ema .

1

:;y3 ~ ~ ~ ~ ~ ~ ~ ~ ~ y . , r > - ~



S. S. F. L. .COMPONENT TEST L A B O R A T O R Y

COMPONENTS TEST LABORATORY

CTL PRIMARY ASSIGNMENT

1- -- TURBOPUMP DEVELOPMENT

2- - - TURBOPUMP AND GAS

GENERATOR TESTING

3-- - - 5-2 AND F-1 GAS GENERATOR

GEMINI ALTITUDE SIMULATION

4-- -- SPACE ENGINE TEST

5 -- -- - LIQUID HYDROGEN TURBOPUMP

TEST

SEARCH AREA

SOLID PROPULSION RESEARCH

LIQUID PROPULSION RESEARCH

COMBUSTION AND HEAT TRANSFER



LIQUID

PROPELLANT

ROCKET



THOR

Thor, Thor-&ena o r Thor-Delta combinatbons hzve Iaunched the greatest

n um b ~r f spacecraft to clail'ie. Th e Xgenz. is an up,uer-stage witti a f 5,555

pound thrust engine. Thc D d t e I s mzde up of tT?apper-stages. Among

th e space missions bcosted byvarious

Thor combinations are: Pi o~ ee r- -h n a r and int er pla eta ry probes; Tiros--me",orologic23 satellites for "e ras -

mitting TV pictures of cloud form~ions;OSO--orbiting solm observatory

and mil ihr y surveii lanc e sdel l i t e s.

E Z Q e 3 E Z Z : ~ T P ; ' ~ W ~ E ZO IV I. CI ON O P N B l T I I 4ML I I tS A N A V I 4T IO N I N C



The Atlas was ou r firs t operational ICBM. This propulsion systern is a one and

one-half stag e system with five engines: two boosters, a sustainer, and two

vernier engines, all igniting fo r lift off. After about 2 minutes the twa boost ers

a r e cut off and jettisoned along with the boat-tail f airin g. The sust ainer contin-

ues to burn until cut off at about 5 minutes, the vern ier engines coi~tinueo burn

fo r a few seconds for final attitude contro l. The payload is then separated from

the tank section and proceeds tcs the target in a ballistic trajectory. The missile

is deployed in silos and horizontal installations at operational site in sever al

states.

The Atlas, as a spac e launch. veh icle, is used for the following payloads; Pioneer-

-lufiar anc! interp laiie tary probe s; Iilercury--manned orb ita l flights; Ranger--

!ur,ar explorat ion with instrumexited package to be lznded on the Moon; Mariner-

-unmanned spacecraft for early interplan.eta-y missio ns to the vicinity of Mars

and Venus.



The excitement of thi s achievement was sh are d by people th e world

over. YGU ndoubtedly reme mber t he straight-forward, unres trict-

ed handi ng of this event. Contrasted with Russian secrec y this

milestone became a tribu te to democracy in action. John Glenn's

flignt 'isa st ep toward manned flight to the Moon and beyond.

T3-63-186-1977 4 .-%

; ! ) z - ~ ~ c z - c ~ - ~ ~ - w ~ Ei +k, $,- A OIVISlO?. O r H O I T M AMU I 1 CAN AV IA I ION INC.



MERC URY-ATLAS LAUNC H

Tha Atlas mis sil e srq~plieci 68,000 pounds of th r wt t o propel t h e 3 , Ci00 pound

Mercury spacecraft n~anned y John Glenn into a n earth orbit. Enormous

power will be required to propel a manned spacec raf t to th e Moon and beyond.

Rocketdyne developed the Atizs propulsion system and has under deveiopmeni:

the giant engines which wii! make th e Iunsr voyage possible. Prel imin ary de-

sign of huge engines for the voyzges beyond the Moon are i n progress.



Expe r i ence gained in the develcpment of t h e J u p i t e r, Thor, and A t l a s

propulsion systems led to the d l s v e i o p m e ~ tof t h e 31-1 engine. Eigh t

oi t h e s e engines are used in the S-I: stage of Saturn 1 and 13. A de-

. .velqpme~~trogram n rn pzogress to u p r a t e this eng ine to 200,000

pouads of thrust.



PROPELLANTS-.....OX/RP THRUST.... 65,000

IS..NOM ( 205K) 263 SEC DRY WEIGHT... 02

ROCKETDYNE



F-1 ENGINE

Five F-1 engines are use6 i n xhe S-PC booster stage of the Saturn V launch

vehicle. Th e Saturn, you wi l l recall, has been assigned the task o f bcosting

the ,4pollo spacecraft ininto c~ i ina~ rbit. Ia ssu-pplying one and one-hzlf million

pounds thrust for 2-1/2 minutes, each 3'-1 engine will burn approximately i0

rail road tank ca rs of propellants. P o w e r generation of this stage is equiva-

lent to t h a t slipplied by the ogerztion of 85 Hoover dams. The gas generator,

about the size of a st reet light globe, supplies power equivalent to more than

30 diesel rai lroad locomotives . The f-ciel pump is capable of forcing fuel to a

height of I mile.

T3-63-186-140,:.: , = " j ~ ~ p T . ; ~ T L F ~ ~ * ~ E

g,,-i A D I Y $ ~ I DN F NO l l T U A M E R I C A N A V 1A T10N I N C



4"-2 ENGINE

TI-~e -2 engine is 2 liquid oxygen/liguid hydrogen propellan t engine.

Through the us e of liquid bjdrogen, the thrust pe r pound of propellant

per second (specific i;zr;zise) is increased by dmu t 40% over iterosene

fuel engines. Five of these engines will power the second stage of the

Saturn V. One 5-2 engine will power th e third stage. An important

feature of the J - 2 wi l l be the capability of multiple restarts in space,

T309-178-23B

L OIVIBION O C N O l T l A u c n lo A N I V aA T IO N INC.



PROPELLANTS LOXIH2 SATURN - l B

THRUST 200,000 LBDRY WEIGHT 2600 LB

SATURN V

& ROCKETDYNE

A O l V l S l O N O C N O R T H A M E R I C A N A V I A T I ON . IN C

R0CKETD"r"XE L A R G E EXGL-E 2 2 0 G i 3 A M



The Ap0110 mission w i l l be mzcle possiale &de to the ineensive development of

highly reLiable colr,ponents which z e n t u r n assembled into reliable engines.

This chart shows some of the Rockctdyne engineswhich have p~ovide dine ex-

perience t h d w i l i lead to the sczcessfui develo3ment of th e man-ratted 3'-I

and 2- 2 engines.

Largest member of Rocketdyne's family is th e F-1 raked at 1,500,000 pounds

s f thrust. The 3-1 w as a sm al le r devel.opment engine which enabled us to

gain exgerience for the development of F-I.

Atlas engines, you rec all , boosted many of the nation's spac e probes. Sev-

era l squadrons of Ailzs missi les ar e deployed in the United Statss.

Eight 9-i engines boost the S a t ~ r n. This simplified e ~ g i n e as developed

from experience gained in prockcing the Atlas, Thor and Jupiter engines.

Thor and Jupiter use as space lzznch vehicles has been mentioned.

The Redstone enghe was the first high th rus t rocket engine developed in "Le

United States following World SVztr HI.



ENGINE PROGRAMS

REDSTONE JUPITER THOR ATLAS ATLAS

THRUSI ,

Is SECI NOM

PROPELLANTS

DESIGN YEAR

THRUST , KI , I OM I

PROPELLANTS

DESIGN YEAR

RdD SPACE

UPPER

STAGE

V -VACUUM B-BOOSTER ONLY s -SUSTAINER *WITH VERNIERS

BASIC CHARACTERISTICS



Both sol.id a n d liquid pro2ellaiz"L rackets &pen(? tipoll the combustion pro ces s of a fuelznd ancxidizer to pr~c?uceases which a r e ejected through th e nozzla a t high velocity.

This Cow of gases grodcces cz reactive force cal.lad thrust,

In the soli d propellarri:, the oxidizer is normally finely ground cr ys ta ls of ammoniumperchiorate or srnrno32~r;nni'c~ztevsrhicf-,have been mechanicali.; mixed with h fuelI?il;der (~srrziLii!y synti-ictie rubber csnrpx.mc;lj. This aixture is cast ar extruded into

a grain 2nd cured; a Iuocess not uzlike the mixing 2nd baking of a cake.

13 s ypical ijquid p::'~?p-"llac'; ock et en gi ne , the b e l 2nd oxidizer a re pumped to the

i ~ j e c t o r h e r e they cz;.c atoriiized, then burned in the c~mb usti on hamber to producegas es which ar e ejected through the nozzle. A gas generator js used to su~pply otgases to d ~ P i ehe Puinp $urbine, Fi:el is circulated throagh the tubes to regenma-

tively coo! the t h r ~ s i h m b e r . There are =any vari&ioris of th i s typical engine

which employ different prcsel2.ant and cooling methods.

The solid rocket Is si~xp-,ple d oes not need th e exkensive servicing and checkoutthat liquid rockets normally re qui re. However, once st ar ted, they cannot. readily Lie

shut down o r r e s t a ~ t e d . Thus 532, the liquid rocket s have received mor e develop-

rren-l effort mcl &reczpab!e o i prodiacing more thrust per pound of propellant b ~ r n e d ,Develo;?mefii efforts are undc2waj to pro$~cea very large salid n;lotor in s egme nts,

Ti1 th e Sa%trrl.rrn, olid prcpdlmt r o c k ~ t s re used t o settle lit+uidpro~e1jllill~CLs,i?p;i-ra te stages and to provide 22 ernzrgency escape systelxl,,

Several yv~dsticks %res e d

to determine the over-al! perfor mance capabilities of aroekebvehicle. The ~ C , Y ~ Sos t f reque~t fy sed a -e : --hrust, specific impulse,-x-hz';lst velocit-;, and mas s rzi;llo.

Thrust is f i e reactir?n eqoerfcnceci FJy an engine due ta th e ejection of high velocitygas& through the nozzle, Tkxsi ; of th e booster cietermines th e weight of the vehicle

which cail be lifted against the pull of g r ~ v i t y .



Specific, Impulse indicates th2 PXLO'L!IY~: of th rus t 'chat can be derived from each pou:ld-of progellait i n one secozd af s::?;:.nc o ~ e ~ z t i o n ,ndogorzs to ni!es per gallon Tor

an 'uton:abile, B is a measu'c of prol~ell-m'c ~ l d rigine efficiencies. An i n c r e ~ s e

in specific impulse re d~ le es l-s wsight of propellantrequired foi- a given mission

vritEi ti;e resultrii~f,weight re~ikctionof th e tanks thus permitting aa increase inpayload.

Ex%r~.st elocity is the s p e c h "2a-lper secene 2t which t he cornb~stfon ases- -expelled. Ex2iaus"Lveloci-&yan d mass ratio determine the fha1 attailxible velocity

I\.!Iass atio is "Le rztio of t he t o t a l loaded vehicle's m as s to its mass when all-rope i i aa t s zve been bursed.

T12-62-185-93 (2 of 2)

+ ~~~~~--~~-~~~,-~~L 4 , , a .IO4Yt * IOH OF NOnT" I Y F R I E A N AV1-710N IN C



SOLID PROPELLAKT ROCKET MOTORS

A sclid propellant rocket *;motor is shown bsosting an air cra ft to flying

speed from a launching platform. This sys tem is called ZEL or Zero

Length La~~nch, t burn-out of th e ZE L booster the aircraft has

reached a speed of about 2?0 knots. Solid mot ors on the Sahrn V

launch vehicle ar e used ior stage sep ara ion and for ullage motors.

Ullage motors provide ac c~ le rat io n orces to theu2per

sta ges of t he

vehicle to settle the pap ell ant s ir, the zftportion of th e tanks to insure

prope r propellant feed.



SOLID PROPELLANT ROCKET MOTORS

h mOCDKETDYNE

A D I V I S I O N O F N O R T H A M E R I C A N A V I A T IO N I N C



HIGH PPE3FOZhCANCE S O L E ROCKETS

Roel.:e*Lclyne's so:id propel ian i rfiotors includes the group shown. Pr o-

palsion for air-to-air rriissiles makes up most sf th i s group. The pro-

pellant formnlati~nor thcse motor s includes Flexadyne , 2 remarkable

fuel-binder developed 3y .Z:oc!tetdyne. The physicai characteristics af

F!esadyne enaSies the grs in to s ~s t a fnhe cold x ~ a kf extreme altitudes

followed by th e aerodynamic hezting of adi ve without a lterin g its burning

character stics .



PEODUCT AREAS

Rocket engiiles for s g i c e vehicles r e q ~ i r e ceh fza . tures as srnail, dis-

crete im pds e bits ; stzp or continuous ihottling; zero "g7' operatioor~s;

extendekcoz--skper"i6s wi th ixultiple ~ e s t a ~ tapzbilities and protection

from ihe hos~l l c r~~iironrizc?ntsre~~ions!y escribed . Engines with v s r -

ioss csrxbii~p-tionsf zi:e sblzve feat ures provide power needed for orbit

injection, escape trajeczcries, mid-course n~aneuv ering, upper-stage

a tt itude c ~n tr c l , e - e n t r y eont rol and lunar descent and ascent.

SPACECRAFT ENGINE



DIVISION

PRODUCT

AREAS



Rendezvous and dos!ri;lg techniques required fcr s ucce ss of the Apolio

mission will be developed ir, tile Gemini prograx. Two propulsion sys-

tems a re being su2plied Sg Rocketdyne Eo the Gemini progra m. The

re-entry module ineurporz~tes wo com2lete 'ttitude Reaction Control

Syste?ms, each consisking of eight 2 5-poun d-th~ust chambe rs for coil-

trolling the re-entry p t h . Hedunddxt systems are prcvided to ensure

i.c!iabi!ity during ths cr?ck%1portion of this mission. The a d ~ p t e r G G -

uli., which is jextlsoned prior to re-entry , in addition to incori?orlat.ir!g

tile mak1 oxygen supply an d electric al system, has the Orbsing Attitude

ani Maneuvering Sys' iea fcr use in rendezvous and docking mlaneuvers,

T!iis p r o p l s i o i ~ ystem includes eight 25-pound-.thrust chambers f o ~

attitude corltrcl, six I C0-paund-thrust chambers for latera l and vertical

ilzovez-ilentand vro 85-?omd-t:x=ust chambers for n-etro-firing, Propel-

lants are nit~ogenetroxidc and monomethyl hydrazine.



ROCKETDYNE

A DIVI# ION OC N O R T M A M L n l C A N A V IA T I ON . I N C .ILId

ZZESZARCE-- -P3ESENT AND FUTURE



Rocketdyne utilizes the streng th cf 2 s Research Organiz~~t5ono solve the problems

of roclret engiae deve10pme;~t. This streng th li es in i ts proles sional personriel anc!2s res ear ch facilities. Many sl' our research scientists er.joy an in&ustry wide

reputaticn in their special fields.

The requfrement for m ore pov?.erS'ul engines places demznds on re se ar ch to develop

higher performance propelianls , metal s which r etain t hei r strength at high tenz-

r;eratures a.nd materials for highly spec aliaed applicztions .

Each component of a rocket engine is cxpected io me et th e stringent re qir em e:~ ts

o i its own ope rat ing conditions as \?;ell as the rigorous envi ronnent of space. E q ~ i p -

mznt ir, rhe materiz..,ls Iaborz tory is s2~czbleof simulating the conciitions for spaceflight enabling ouz sc ien tis ts to cocGuct stad ies of mat er ial behavior under the se

extreme condi"iions.

The e,eremcs of operzting environment for a rocket engine ar e: propellants at-423°F adjaceiit to a ?OOCI°F G a s , ihe therm21 and physical shocks of s tzri ing an

engine, corr osiv e proyolla-its, t h e s p c e environmect of a vacuum, es"Lreme cold,

and the rzdic,tlen of the sun. Th e raz t e r i~ ls abora tory ?i;ts eq~i pmen t or testing

and eva1uat"cir.gn~ate riais nder tke extremes just stated. The nzte tria ls group con-

ducts a never ending search fo r me"2Js t o s tand ~p u n ~ e rhe rig ors of space travel,

methods of shap ing and joining these metals, and resear ch into the secrets of highstrength exhibited by certain meta l s under exctrernes of heat, cold and presscre.

-r-,.,

, ,: J

+ L '

wap,* O IV l i l C I N OC N O ~ T HM C h I C I N AVIATIDPI IN C



RESEARCH - PRESENT AND FUTURE



The si ze of a particle whizl-1can be seen by the eye through a microscope

is limited by the wkv2 lengths of light, The electron microscope is a

device which makes use o-f an elect ron beam to tr ac e a magnified image

on a coated pla te which can then be viewed. Simil arly an electr on beam

t r ~ c e s ic tu re s on you r TV screen. Since the electron is the smallest

known particle of rnztLer, extremely high magnification is possible. Thin

metal foil samples may be examined for dislocations. Examination of

these tiny building blocks provides metallurgists with knowledge leading

to t he development of higher strengt h me tals required for advanced rocket

engine systems .

-1: -S " , c J k ~ K ~ ~ ~ - ~ ~ % ~ Z l a ' ~

& DlYlPllON OF W C l T " I H T R I S A N A V Ib Tk O N 'N C



CROSCOPY

REFRACTOWMMETALS FLOW& FRACTURE PHENOMENON

THIN FOIL TRANSMISSION MICROSCOPY

811.6 x lae6 THICK TANTALUM FOlLFf4 10QyO(aOx MAGNlFlCATlONBq ATOMIC SlZE DISLOCATION MOVEMENT



ENGSNEERaTJG C"n'E1ViPSTRY RESEARCH

Combustion studies a& cc nd ~c te d ith the aid of two- dimensional, tra ns-

parent thrust chambers which provide data records through high-speed

instrumentation and permi t visualization of the combustion pro ces s through

high-speed pliotcgraphy. Advanced design concepts and u n i q ~ e ropellant

combinations a r e tested as an adjunct to research and development

programs.

~ - ~ C ~ ~ E V ~ ~ ~ 1 I J ~

wrl$i.* D#VlSBON OC N Q M T I C . W C * # C I N AVIATION INC.



7-62-186-57 FLAME FRONT CHARACTERISTICS



A shock tube located in this la bo r~ to rys rzsccl to st age cornbustion pro ces ses under

controlled conditions. Use of thi s device enables one to ar r es t complex reactio ns

and study the prod~x t s . This tooi ;makes it possible to prep are samples from vari-

ous s tage s of a combustion prOceSS. Vzr ious analytical techniques a r e utilized to

s tudy thes e products; one of thss e is spectrometry.

Astroonmy, the oidest scienze, m&ies use of a pr ism to break up the light from s

st ar into its various spectra; this is one type of spectrom etry. Through spectro-

metr y helium was discoverediz;

the spectra of th e sun before it was isolated onearth. ,Xost atoms interactiin a ~ ~ s r a c t e r i s t i canner with varioas forins of elec-

tromagnetic radiation: infrar ed, ultraviolet and radio frequencies. Knowledge of

these char acteristic s are used for ideiltificatiori of e lements of complex compounds

and their atomic structure t h o c s h spectrometry. Through use of the nuclear mag-

net ic resons r, ce ~ p e c t r c ~ e t e r ,tom4c and fiiolecular arrangemen t of a select group

of com~sundsmay be dctcrm"idd, This tool is often used to examinc the products

of col-nbustion s taged in the sk.t-,oc'ri tube. Nevrly synt hesized chemicals may be

examined so that their potential as zi propella.nt may be characterized.

f 7

f ' ; ; ; Z Z ~ D ~ ' * I ~ " T r D ~ J ~ E z

A OIY I a ION O C NORTY *HLR ICPN AV I I T I OM IN C

SPECTROMETRY



NUCLEAR MAGIVETIC RESONANCE SPECTROMETER

MASSC2H60

CH3-CH2-OH - ETHYL ALCOHOL

INFRA-RED

ULTRA VIOLET AND VISIBLECHs-O-CHs= DIMETHYL ETHER



U s e of nrrcle~r ngines as zpper-stages for Saturn boaster will permit

delivery of heavier payloads, a2proxima"Lsly twice that possible with

chemical stages, The anticlgslcd nuclear engine performance wi l l be

more than double that of chzmical engines in the thrust per ~ ~ 2 n df

propellant p ~ recond. Fk i c i e s r engines v ~ i l l e required for manned

i3lanctal.y e-xploration. In czi&;;kon, us e~f

a nuclear second stage forthe Saturn V vehicle for P T O ~ ~ C ~pol!~ is under study. B should be

noted ",at the fission o one pound of uranium is equivalent to the c o ~ -

bustion o f ove r one millioc p ~ u n d s f hydrogen and oxygen. T i s

amount of energy would produce about I60 KW of electric power for

one year.



NUCLEAR ROCKET ENGINE

The control. rods of t5e nuclear rea cto r a r e actuated to preheat a porttion of

(in th is instance) hydrogen (ave ry light-weight propellan t). Some heated

hydrogen is ther, bled off t o drive the turbine, Spinning of the turbine punlps

liquid hydrogen through the reactor where energy is absorbed, thus s q e r

heating the hydrogen ga s for ver y high velocity disc harge hzough the nozzle

to produce thrust. A portion of the heated hydrogen is continually bleed off

for turbine drive to sustzlir: operation, The engine is controlled through

sensor s in the reactor actuatinz the control rods as required , This method

izttains a v e r y h i g h specific impulse bvlt its u s e i s restr icted d u e to

contaminated exhaust pro&clcts.

NUCLEAR ROCKET ENGINE



CHARACTERISTICS

SPECIFIC IMPULSE 700-1200 SEC

SINGLE PROPELLANT

REACTOR HEAT SOURCE

NOZZLE

INTERPLANETAZY EXPLORATION AND SUMLL4Ry



Vis~ralizcdhere is a six msc rccennaisssnce of Mars and Venus in one "tip, a

Crozco mission narizsd for l r o l , Luigi Croceo of Princeton. A nuclear rocket

engine ~f 700,330 pounds thr:is'; is 2roposed for this tr ip , One hundrcd thirt een

days of tra vel to M w s , E 54 c2ays on to Vemxs and 98 days to return to Earth (365

days total). T h i s advc-xiure is being considered for the early seventies, A

Crocco rnissior, profile uses he r;iu"e?nali z t t r a e t i ~ nf the planets, t h e spacecraft

s ~ c the sun to colxplete a tri;: wi th a n~inimum 'qenditure of energy. Prop-

pdsicn woald be required as the spacecraft passes near the plmets to make

minor correctio ns for freefail flighi towardttl?,? next body an d retcrn. Drre to th e

excessive cosi of this program 2nd the very short tim e spent in th e vicinity of

the planets , t h i s typz cf v a y q ~ " ay not be used, Nuclear rocket engines,

i lowevcr , wi l l be required f o r ylsnetary exploration,

S 3MNAXY -- - Scme of R~c!c&dyne~srodccts have been shown and discussed.

Tne corning Szturn la:~neE? f f h s Apollo spacecraft for the l u n a r landing has been

depicted, Now we would like to close with this chart of th e next step in space,

Thank you.

propulsion the key to moon travel

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