NASA - Launch Vehicle Performance Using Metallized Propellants

8/11/2019 NASA - Launch Vehicle Performance Using Metallized Propellants

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AIAA 91-2050Launch Vehicle Performance UsingMetalk e d Prop e an sBryan PalaszewskiNASA Lewis Research CenterCleveland, OH

Richard PowellNASA Langley Research CenterHampton, VA

AI AA/S AE/ASM E/ASEE27th Joint Propulsion Conference

June 24-27,1991 / Sacramento, CA

For permission to co py or republish, contact the American Institute of Aeronautics and As tronautics370 L Enfant Prom enade, S.W., Washing ton ,D.C. 20024


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LAUNCH VEHI CLE PERFORMANCE USI NG METALLI ZED PROPELLANTS

Br yan Pal aszewski *, "Nat i onal Aer onaut i cs and Space Adm ni st r ati on

Lew s Resear ch- Cent erCl evel and, OH

andRi chard Powel l **

Nat i onal Aeronaut i cs and Space Adm ni st r ati onLangl ey Resear ch Cent er

Hampt on, VA

Abst r act A- 50 Aerozi ne- 50

Met al l i zed pr opel l ant pr opul si on syst ems ar econsi der ed as r epl acement s f or t he sol i dr ocket boost er s and l i qui d sust ai ner st ageson t he curr ent l aunch vehi cl es: bot h t heSpace Tr anspor t at i on Syst em ( STS) and t heTi t an I V. Li qui d Rocket Boost er s f or t he STSwere anal yzed as r epl acement s f or t hecur r ent Sol i d Rocket Boost er s. Theseboost ers can pr ovi de a l i qui d pr opul si onsyst em w t hi n t he vol ume const r ai nt s of aSol i d Rocket Boost er . A repl acement f or t heSpace Shut t l e Mai n Engi nes usi ng metal l i zed02/ H / A1 was st udi ed. The l i qui d st ages oft he Ti t an I V wer e al so i nvest i gat ed: t he A-5 0 f uel was r epl aced w t h met al l i zedst or abl e A- 50/ A1.

A met al l i zed pr opel l ant i s si m l ar t o at r adi t i onal l i qui d propel l ant . However , i thas met al par t i cl es, such as al um num t hatar e suspended i n a gel l ed f uel , such ashydrogen, RP- 1, Aerozi ne- 50 A- 50) ormonomet hvl hvdrazi ne f MMH . The f uel s t hen

-. .

under yo Acomh; st i on wi t h 1 , q u i d oxygen orni t r ogen t r t r oxi de ( P I T O ) .

ET

GLOW

H

1 6 ,

LRB

MECO

ML

MPS

NTO

MMH

NLS

0

OMS

External Tank

Gr oss Li f t Of f Wei ght

Hydr ogen

Speci f i c I mpul se (l b, -s/l bm

Li qui d Rocket Boost er

Mai n Engi ne Cut Of f

Metal Loadi ng

Mai n Pr opul si on Subsyst em

Ni t r ogen Tet r oxi de

Monomet hyl Hydr azi ne

Nat i onal Launch Syst em

Oxygen

Or bi t al Maneuver i ng Subsyst em

These pr opel l ant s pr ovi de opt i ons f or RP- 1 Rocket Pr opel l ant - 1

i ncr easi ng t he per f or mance of exi st i ngl aunch vehi cl e chemcal pr opul si on syst ems SRB Sol i d Rocket Boost erby i ncreasi ng f uel densi t y or speci f i ci mpul se I e s ) , or bot h. These i ncr eases i n SRM Sol i d Rocket Motordensi t y and I,, can si gni f i cant l y r educe t hepr opul si on syst em l i f t of f wei ght and al l ow SSME Space Shut t l e Mai n Engi nesa l i uui d rocket boost er t o f i t i nt o t he samevol ume as an exi st i ng sol i d rocket booster .Al so, because gel l ed f uel s ar e aki n t ol i qui d pr opel l ant s, met al l i zed syst ems can STS- C Space Transpor t at i on Syst em Cargo

STS Space Transpor t ati on syst em

nr ovi de enhanced cont r ol l abi l i t v over sol i dpr opul si on syst ems. Gel l i ni of t he VAB Vehi cl e Assembl y Bui l di ngpr opel l ant al so reduces t he sensi t i vi t y t oi mpacts and consequentl y r educes t he AV Vel oci t y Change (ms)pr opel l ant expl osi on hazar d

Nomencl at ure

ALS Advanced Launch syst em

A1 Al umnum

* Progr amManager , ' Met al l i zed Pr opel l antProgr am

** AI AA Member

Copyiigln 991 by the Aiiierican lnrfi iurcof Aeronauticsand Awon;>utics. lnc. N O opyright is ~ s r e n e d o the

Uailed Sinlei iintlcr Tit le 17, U.S. Code. Thc U.S. Govcrn~iiient has P royo l iy~f reei c e n v 10 c x c r c i w a l l r i gh t% nderthc copyright claimed herein for Coveinmenid piirposec.

A I olhcr righl i are reserved by the copyright ~ w l i e r .

I nt r oducti on

Fut ur e l aunch vehi cl es w l l del i veri ncr easi ngl y l arger and more massi vepayl oads t o or bi t . Exi st i ng l aunch vehi cl es

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w l l r equi r e cont i nui ng upgr ades i nper f or mance t o accommodat e t he i ncreasi ngpayl oad needs of NASA m ssi ons. Commerci all aunch vehi cl e manuf act ur er s are l ooki na t oi ncrease t he payl oad capabi l i t y of t 6ei rf ut ur e desi gns ( Ref s. 1 and 2) . The NASA andAi r For ce pl ans f or t he Nat i onal LaunchSyst em ( NLi ) , t he Advanced Launch Syst em( ALS) and t he Space Transpor t ati on Syst emCargo ( STS- C) demand payl oads t o orbi t equalt o or exceedi ng 68, 000 kg. ( Ref s. 3 and 4 ) .These payl oads woul d be r equi r ed f or l argepi l ot ed l unar base f l i ght s and Marsexpl or at i on m ssi ons (Ref . 5) as wel l as f orsome aspect s of t he pr oposed Str ategi cDef ense I ni t i at i ve oper at i ons (Ref . 6).

As payl oad masses i ncr ease, t he pr opel l antneeded f or t he l aunch vehi cl e al so ri ses.The l ar ger pr opel l ant l oads l ead t o l ar gerand l ar ger st age l engths and vol umes. Todel i ver hi gher payl oad masses t o or bi t ,hi gher per f ormance and hi gher I,, r ocketengi nes w l l be r equi r ed. Al so, t o mai nt ai nt hese vehi cl es di mensi ons w t hi n r easonabl esi zes and t o r educe t he vol ume of t hevehi cl e s st ages, hi gher densi t y pr opel l ant sw l l be des i rabl e.

The urooul si on technol oai es t hat ar eavai l abl e t o meet t hese pe; f ormance and/ orvol ume demands ar e many and vari ed: l i qui d,sol i d and hybr i d pr opul si on are t he pr i mar yal t er nat i ves f or l aunch vehi cl es. Forexampl e, t he Advanced Sol i d Rocket Mot or(ASRM) i s under consi der at i on f or enhanci ngt he STS ( Ref . 7). Sol i ds and hybr i ds ar e t woof t he t echnol ogi es f or i ncreasi ngpr opel l ant densi t y. Thei r del i ver ed speci f i ci mpul se i s t ypi cal l y not as hi gh as a l i qui dpr opul si on al t er nat i ve. Wt h advanced l i qui dpr opul si on, many di f f er ent t ypes ofpr opel l ant s can be devel oped t o i ncr easeper f ormance.

Pot ent i al l y, one of t he most - at t r acti vel i qui d pr opel l ant opt i ons i s met al l i zedpr opel l ant s. Met al l i zed pr opel l ant s candel i ver hi gh I,, or hi gh f uel densi t y, orbot h. I n t he succeedi ng sect i ons some of t hedesi gn f eat ur es and at t r i but es of met al l i zedpr opel l ant s w l l be di scussed and anal yzed.

Li qui d Rocket Boosters ( LRB) f or t he STSwere anal yzed as r epl acement s f or t hecur r ent Sol i d Rocket Boost er s ( SRB) . Ar epl acement f or t he Space Shut t l e Mai nEngi nes usi ng metal l i zed 02/i , /A1 was al sost udi ed. The l i qui d st ages of t he Ti t an I Vwer e al so i nvest i gated; t he A- 50 f uel wasr epl aced w t h met al l i zed st or abl e A- 50/ A1.

Summar y of Resul t s

Wt h t he STS Li qui d Rocket Boost er s,met al l i zed 02/ RP- 1/ Al and NTO/ MMH/ Al ar eabl e t o provi de an LRB t hat i s shor t er t hant he exi st i ng SRB. Even when i ncl udi ng t hepotent i al l osses caused by t wo- phase f l owl osses i n engi ne anal ysi s, t he met al l i zedLRB i s abl e t o del i ver t he basel i ne STSpayl oad of 22, 527 kq ( 49, 664 l bm. I f t het wo- phase f l ow l osses ar e m ni m zed, t he STSpayl oad may be i ncr eased t o 25, 674 kq

1 5 6 . 6 0 0 ka\ w t h O / RP- l / Al . A Davl oad of1 - - - - > , -30, 482 kq ( 67, 200 lb) i c pr oj ect hi usi ng amet al l i zed NTO/ MMH/ Al LRB. The vol ume of anLRB or an Ext ernal Tank usi ng 02/ Hz/ A1 wer emuch l arger t han t he exi st i ng SRB andExt ernal Tank vol ume. The Ti t an IV payl oad( w t h no upper st age) was i ncr eased by 11. 2t o 11. 6 per cent over t he exi st i ng desi gn.Thi s Ti t an used NTO/ A- 5O/ Al pr opel l ant s onl yi n t he cor e vehi cl e.

Backar ound

Why Met al l i zed Propel l ant s?

One advanced pr opul si on opt i on t hat canpr ovi de benef i t s f or Ear t h t o Or bi t vehi cl esuses met al l i zed pr opel l ant s. Thesepr opel l ant s of f er i ncreases i n t he over al lpr opel l ant densi t y and/ or t he I,, of apr opul si on syst em These i ncr eases canenabl e si gni f i cant l aunch mass r educt i ons orpavl oad i ncr eases over convent i onal chem calpr bpel l ant s. Met al 1 zed pr opel l ant s ar epr opel l ant s w t h met al added to t he f uel ort he oxi di zer. Typi cal l y, t he met al i s i n t hef or m of m cron- si zed part i cl es. They ar esuspended i n a gel l ed pr opel l ant t o i ncr easei t s combust i on ener gy or i t s densi t y, orboth. The I., of an engi ne i s pr opor t i onalto:

I., T / MW

wher e:

T Combust i on Temperat ur e

w Mol ecul ar Wei ght of Combust i on

A comhi nat i on of i ncreased combust i ont emperat ur e, or r educt i ons i n the mol ecul arwei ght of t he exhaust pr oduct s, or bot h,i ncr eases t he I,, of t he pr opul si on syst emI ncr eased I,, r educes t he pr opel l ant r equi r edfo r a gi ven mssi on. The i ncr eases i npr opel l ant densi t y al so r educe t he t ankagevol ume and mass. Because many of t hepr opul si on syst emel ement s are dependent , ont he pr opel l ant mass and vol ume, i ncr easi ngt he propel l ant densi t y decreases componentand t ankage wei ght s, t hus al l ow ng l ar ger educt i ons i n t he over al l dr y mass.

To i ncr ease t he payl oad capabi l i t y ofexi st i ng l aunch vehi cl es and t hei r upperst ages, hi gher I,, syst ems or hi gher densi t ypr opel l ant s, or bot h, w l l be needed.Previ ous st udi es of Mars and l unar m ssi ons( Ref s. E , 9 and lo), t he STS LRBs ( Ref . 11

and 12) and STS and STS- C upper st ages ( Ref .1 3 ) have deter m ned t hat metal l i zedpr opel l ant s ar e an at t r act i ve al t er nat i ve t ot r adi t i onal pr opel l ant s f or f ut ur e spacet r anspor t at i on syst ems.

Li aui d Rocket Boast ers

Two st udi es have been conduct ed t o determ net he benef i t s of LRBs ( Ref s. 11 and 12) overt he curr ent SRB f or t he Space Transpor t ati onSyst em (STS). There are several i mpor t antf eat ur es of an LRB. These i ncl ude added

Product s


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payl oad to or bi t , t hrust cont r ol l abi l i t y,l aunch vehi cl e i n- f l i ght saf et y and l aunchoper at i ons saf et y.

I n t he LRB st udi es. a Davl oad of UD t o.-31, 979 kg ( 70, 500 l bi ) was desi r ed. Thf s i s- a si zabl e bol st er i ng of t he STS over t hecur r ent capabi l i t y of 22, 680 t o 24, 948 kg( 50, 000 t o 55, 000 lb, Ref . 15). Such aDavl oad aai n can be a or eat benef i t f or>ukur e SGace St ati on f i i ght s and f ut ur eexpl orat i on m ssi on support . The LRB canal so pr ovi de a cont r ol l abl e and var i abl et hr ust l evel . Thi s cont r ol i ncreases m ssi onf l exi bi l i t y. Dur i ng t he ascent t o or bi t , t heabi l i t y t o cont r ol t he t hr ust l evel of aboost er st age i s i mpor t ant f or saf et y. I f apr obl em were t o occur w t h a r ocket engi ne,t he engi ne coul d be thr ot t l ed down t om ni m ze the danger t o t he l aunch vehi cl eand t he cr ew An LRB can al so be commandedt o t er m nat e i ts f i r i ng i f a probl em ar osedur i ng t he l aunch: t hi s opt i on i s notavai l abl e w t h the SRB.

I n addi t i on t o the saf et y of t he vehi cl e andt he f l i ght cr ew dur i ng l aunch, t he saf et y oft he l aunch f aci l i t i es i s al so cr i t i cal .

cur r ent l y, t he segment s of t he sol i d rocketmot or s are assembl ed i n t he Vehi cl e Assembl yBui l di ng ( VAB) . Thi s pr ocedur e i nt r oduces apotent i al hazar d i n the assembl y of t he STShardware. By usi ng an LRB, potent i al l yhazar dous f uel s are t aken out of t he VAB andkept near t he l aunch pad. W t h NTO/ MMH/ Alpropel l ant s, t he pr ocessi ng at t he pad mayr equi r e addi t i onal consi der at i on due t o i t st oxi ci t y over 02/ RP-1/ A1 and 02/ H / A1.

W t h met al l i zed pr opel l ant s, t her e i s anadded saf et y advantage i n handl i ng. Becauset he f uel i s gel l ed, i t prevent s w despr eadspi l l age i f i t wer e rel eased f rom t hepr opel l ant t ank ( Ref . 14) . Cl eanup of t hespi l l i s easi er because t he spi l l i srest r i cted t o a more conf i ned ar ea. Thi s i spar t i cul ar l y t r ue of st or abl e met al l i zedf uel s. Al so, t he gel makes t he pr opel l ant sl ess sensi t i ve t o hi gh- ener gy par t i cl es t hatpenet r at e t he pr opel l ant t ank ( Ref . 14). I fa pr oj ect i l e penetr ates t he t ank ( such as awr ench dr opped dur i ng gr ound assembl y,m cr omet eor oi ds, space debr i s, et c. ), t hegel l ed pr opel l ant w l l pr event acat ast r ophi c expl osi on.

Bot h LRB st udi es al so gave some prel i m naryconsi der at i on t o met al l i zed pr opul si onsyst ems f or t he LRB. The boost er desi gnsused NTO/ MMH/ Al and 02/ RP- l / Al . Of al l oft he LRB t ypes s t udi ed, t he met al l i zedboost er s were abl e t o f i t most cl osel yw t hi n t he exi st i ng Sol i d Rocket Boost er( SRB) di mensi ons. Thi s al l ows LRBs t o beconsi der ed f or t he cur r ent STS w t h mni malchanges t o t he exi st i ng l aunch f aci l i t i es.St r i ct geomet r i c const r ai nt s ar e i mposed byt he cur r ent STS l aunch f aci l i t i es. I f t heboost er s have di mensi ons whi ch are ot hert han t hat of t he cur r ent SRB, si gni f i cantal t er at i ons may have t o be made t o manyl aunch f aci l i t i es, i ncl udi ng t he Mobi l e- Launch Pl at f orm t he l aunch pad' s f l amet r ench and t he access pl at f orms on the

...

Rot at i ng and t he Fi xed Ser vi ce St r uct ur es ofLaunch Compl ex 39 A and B. I nt r oduci ng a newpr opul si on technol ogy w l l be mor e- easi l yef f ect ed i f t he changes t o t he exi st i ngl aunch systems and f aci l i t i es ar e m ni mal .

I n t hi s st udy, t he STS and Ti t an I v l aunchvehi cl e desi gns were st udi ed i n how t heycoul d accommodate metal l i zed propel l ant s.For t he STS, t he SRBs were r epl aced w t hLRBs usi ng met al l i zed f uel s: RP- l / Al , W/ A 1and HJ Al . Al so i nvest i gat ed were anExt ernal Tank ( ET) and Space Shut t l e Mai nEngi nes ( SSME) t hat used metal l i zed H Af uel . The Ti t an l aunch vehi cl e was modi f i edso t hat t he l i qui d- f uel ed cor e usedmet al l i zed A- 50/ Al .

To est abl i sh t he benef i t s of met al l i zedpr opel l ant f or l aunch vehi cl es, t he m ssi onsand pr opul si on syst em desi gns must beconsi der ed t ogether and anal yzed. Thesucceedi ng sect i ons w l l di scuss theseaspect s and t he r esul t s of t he over al lsyst ems anal ysi s.

Propul si on Syst ems Anal yses

I n det er m ni ng the pot ent i al per f or manceadvant aaes of met al l i zed Dr ooel l ant s. aser i es 6f r adc st udi es cere' per f ormed.These st udi es used t he l aunch mass and/ orvol ume const r ai nt s of a ser i es of STS andTi t an l aunch vehi cl e opt i ons t o def i ne t hecapabi l i t y of f ut ur e vehi cl e desi gns. Af t erdet er m ni ng t he l aunch vehi cl e const r ai nt sand f or mul ati ng t he m ssi ons and gener i cdesi gns of t hei r boost er s and st ages, t heseel ement s can be f ol ded together t o f i nd t heper f or mance of t he t ot al vehi cl e f or t hevar yi ng m ssi on requi r ement s.

I n t he anal yses pr esent ed her e, severalf i gur es of mer i t ar e consi der ed. These ar et he payl oad del i ver y mass t o an Eart h orbi t ,t he l engt h and di amet er of t he vehi cl e andt he Gr oss Li f t Of f Wei ght ( GLOW.

To comput e t he f i gur es of meri t , t he r ocketequat i on was used:

AV = I,, 9 I n (m/m)

wher e:

AV Vel oci t y Change

16P Speci f i c I mpul se

9 Gr avi t at i onal Accel er at i on

m I ni t i al Mass

m Fi nal Mass

Two di f f erent methods of anal ysi s were usedt o anal yze the STS and t he Ti t an I V. Ther ocket equati on was used f or t he STSanal ysi s and f or t he Ti t an I V, a t r aj ectoryanal ysi s code was used. Fact or i ng i n t hel aunch vehi cl e const r ai nt s, t he engi neper f ormance and t he l aunch vehi cl e st agemass- scal i ng equat i ons, t he si ze of t he


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boost ers and st ages f or var i ous payl oads canbe cal cul at ed. I n t he f ol l ow ng secti ons,t he const r ai nt s on t he l aunch vehi cl e For t he STS LRBs, both Pump- and Pressure-desi gns ar e di scussed. f ed boost er s were anal yzed. Al l of t he

r emai ni ng engi ne desi gns f or t he STS SSMEand Ti t an st ages' engi nes are pump- f ed. SomeLaunch Vehi cl e Desi un Const r ai nt s of t he desi gn parameter s f or t he engi nes

LRB st udi es

Pr ODUl Si On SVStemDesi un

I n t he anal yses of t he STS per f omance, t he were gui ded by t he r esul t s of t he pr evi ousUl vsses l aunch m ssi on oar amet er s wer e usedas- a gui de ( Ref . 15). - The ul ysses m ssi oni s a unmanned spacecr af t t hat w l l expl ore

out si de of t he ecl i pt i c pl ane of t he Sol arsyst em I t was l aunched t owar d J upi t er w t ha t wo- st age I US and an addi t i onal Payl oadAssi st Modul e ( PAM) upper st age depl oyedf r omt he STS. Thi s m ssi on i s t he heavi estSTS payl oad t o dat e. The STS vehi cl e has t wol arge SRBs f l anki ng t he combi ned Ext er nalTank ( ET) and Or bi t er. The vehi cl e andDr oDel l ant masses of t he basel i ne STS~ L ~~~~~~

m ssi on ar e l i sted i n Tabl e I . The~t ot alpayl oad mass del i ver ed t o orbi t was 22, 527kg ( 49, 664 l bm. Thi s mass i ncl udes 20, 873kg ( 46, 017 lb) of payl oad and 1, 654 kg13. 647 lb of Manaaer ' s Reser ves ( orpayl oad coi t i ngency. RLf . 15) . The l engt hand di amet er of t he SRB ar e 149 f t and 12. 2f t , r especti vel y (Ref . 16). For t he ET, t hel ength and di amet er ar e 153. 8 f t and 27. 6f t , r especti vel y. To use met al l i zedpropel l ant s, t he ET desi gn must be modi f i ed.The ET uses t he oxygen t ank as par t of t henose sect i on. Because of t he aer odynam cshapi ng of t he oxygen t ank, t he ET w t hmetal l i zed pr opel l ant s was compared t o t heexi st i ng ET based on vol ume of t he newmet al l i zed pr opel l ant t ank rat her t han t hel engt h of t he t ank. The t otal vol ume of t heexi sti ng ET i s 2069 m3 ( 73, 081 ft 3).

The basel i ne payl oad t o or bi t f or t he Ti t anI V i s 14, 643 kg ( 32, 282 l bm. The Ti t an i scomposed of t wo l arge sol i d rocket boostersf or the i ni t i al l i f t of f (Stage 0), a cor evehi cl e w t h two boost er st ages ( St ages 1and 2) and no addi t i onal upper st age. Thecor e and t he boost er s are 3. 05 m ( 10 f t ) i ndi ameter . The Stage 1 t ankage vol ume i s129. 7 m3 (4, 581. 7 f t 3) and t he vol ume ofStage 2 i s 29. 4 m3 ( 1037. 3 ft'). Met al l i zedpr opel l ant s were onl y i nvest i gat ed f or t her epl acement of t he cor e vehi cl e pr opel l ant s.

Tabl e IBasel i ne STS Mass summar y

Subsyst em Mass ( kg)

Payl oad 22, 527. 4Or bi t er 93 - 762. 2External Tank

ET O JH , Pr oDel l antW t h Resi dual s 36, 050. 1

719, 539. 1Two sREi s Pl i s Non- Propul si ve

Losses 171, 397. 5SRB Propel l ant 1, 008. 892. 0

Tot al 2, 052, 168. 3

Enqi ne- Per f or mam Usi ng a compuccrsi mul at i on code ( Ref . 17) , t he engi neperf ormance of t he met al l i zed pr opel l antcombi nat i ons was est i mat ed. The propel l ant swer e provi ded t o t he combust i on chamber i nt he l i qui d stat e. A di f f er ent E was chosenf or t he pump- and pr essure- f ed engi nes. Af i xed ar ea was avai l abl e at t he base of t heLRB. The chamber pressure of t he pump- f edengi ne al l owed f our engi nes, each w t h a30: l expansi on r at i o nozzl e t o f i t w t hi nt he LRB base area. The engi ne chamberpressur e was 1000 psi a. For t he pr essur e- f edboost ers, t he 350- psi a chamber pressur eal l owed an E of onl y 7: l t o f i t w thi n t hear ea at t he base of t he LRB. As w t h t hepump- f ed LRB, f our engi nes wer e used. Thesechamber pressures wer e sel ect ed based upon

t he desi gns of t he var i ous engi nes underconsi der at i on f or f ut ur e l aunch vehi cl es( Ref s. 11 and 12). The SSME w t h metal l i zedpr opel l ant s had a 3000- psi a chamber pressureand a 77. 5: l expansi on r at i o. These val uesare t he desi gn poi nt of t he SSME. Wt h t heTi t an I V engi nes, t he met al l i zed engi nesused t he same engi ne E and chamber pr essureas t he curr ent Ti t an desi gns: 15: l and 857psi a f or St age 1 and 49. 2: l and 860 psi a f ort he second stage.

Tabl e I 1 cont r ast s t he pr edi ct ed per f or manceof sever al pr opul si on syst ems w t h and

Tabl e 11

Non- Met al l i zed and Met al l i zedEngi ne Perf ormance

Vehi cl e and Is, I sp Ef f i ci encyPr opel l ant (l bt- s/ b) 11 )

No Metal Metal *

STS: Boost er Opt i ons - Pump- Fed:SRB 265. 5 n/a n/ aO / RP-l 324. 5 317. 3 0 . 920NTO/ MMH 307. 7 318. 9 0. 920OJH, 410. 2 419. 0 0. 940

Pr essur e- Fed:O / RP-l 289. 4 284. 8 0. 920NTO/ MMH 280. 4 278. 3 0. 920Mai n Pr opul si on Opt i ons -Oz/ 452. 66 460. 6 0. 974

Ti t an I v:St aae 1 oot i ons -NTO A- 50 301. 0 310. 2 0. 914

Stage 2 Opt i ons -NTO/ A- 50 316. 0 330. 0 0. 906

W

* Al um num i s added t o the f uel

4


7/17

w t hout met al l i zed f uel . The i ncreases i n I, ,are t ypi cal l y sever al l b,- s/l b, . An engi ne I.,ef f i ci ency q ) was used t o modi f y t he code-pr edi ct ed I sp. The Tabl e I 1 I , , , val ues havei ncl uded i n t hemt he q The 1) i s t he r at i oof t he engi ne per f ormance shown i n Tabl e 11 and t he code- pr edi ct ed I sp. he r educt i on duet o 11 r ef l ects t he l osses f rom t he nozzl eboundar y l ayer , engi ne cycl e i nef f i ci enci esand ot her pr opul si on syst em l osses. Theengi ne ef f i ci enci es were der i ved usi ng t heper f or mance est i mat es f r om l i qui d engi nesys t ems (Ref erences 18 t hr ough 21) andcompar i sons w t h t he vacuum S p pr edi ct ed byt he engi ne code. I n t hi s anal ysi s,metal l i zed propel l ant s were gi ven t he sameengi ne ef f i ci ency as t he non- met al l i zedsyst ems. Ther e ar e addi t i onal l osses t hathave not been i ncl uded i n t hi s anal ysi s t hatmay pot ent i al l y penal i ze t he met al l i zedpr opel l ant cases, such as t wo- phase f l owl osses i n t he exhaust and t he nozzl eboundar y l ayer, and nozzl e er osi on.Numer i cal model l i ng, pr opel l ant r heol ogyexperi ment s and hot - f i r e engi ne t est i ng havebeen conduct ed t o determ ne t he potent i alengi ne ef f i ci ency of met al l i zed pr opel l ant s( Ref s. 22 t hr ough 26) . The ef f ect of l ower

t han pr edi ct ed I , , ef f i ci ency w l l bedi scussed l at er i n the paper .

The m xtur e rat i os and t he met al l oadi ng fort hese pr opul si on desi gns are gi ven i n Tabl e111. The metal l oadi ng repr esents t hef r act i on (by mass) of al um numi n t he t ot almass of t he f uel . The m xt ur e r at i o i sdef i ned as i t i s f or tr adi t i onal chem calpr opul si on: t he rati o of t he tot al oxi di zermass t o t he t ot al f uel mass. I n sel ect i ngt he "best " met al l i zed system desi gn, t hepr opel l ant met al l oadi ng, i t s ef f ect s on t heengi ne I , , and t he propul si on syst emdr y mass

Tabl e I 11Rocket Engi ne Metal Loadi ngs

and M xtur e Rat i os

Vehi cl e and Met al M xt ur ePr opel l ant Loadi ng Rat i o

( % ) Met al No Met al

Boost er opt i ons - Pump- Fed:O / RP-1 5 5 1. 1 2. 7

O J z 60 0 . 9 6. 0

Pressur e- Fed:02/ RP- 1 5 5 1. 1 2. 5

NTO/ MMH 4 0 0. 9 2. 0

NTO/ MMH 50 1. 0 2. 0Mai n Pr opul si on Opt i ons -O2H7 70 0. 8 6. 0

Ti t an I V:St age 1 Opt i ons -NTO/ A-50 35 0. 69 1. 91

st age 2 Opt i ons -NTO/ A-50 4 0 0 6 8 1. 78

Metal Loadi ng = Per cent of Fuel Mass

5

must be anal yzed. Some of t he i ssues t hatare i mpor t ant i n deter m ni ng t he appr opr i at edesi gn f or a met al l i zed pr opul si on syst emar e di scussed bel ow t he pr opel l ant densi t y,t he per f ormance and t he syst emdr y mass.

A w de range of met al l oadi ngs wer econsi dered f or 0, / H2/ A1, OdRP- l / Al andNTO/ MMH/ Al . Fi aur e 1 shows t he ef f ect of~~ ~~~~ ~ -

~~ ~~

met i i l oadi ng on I., f or Oz/ RP- l / Al ,NTO/ MMH/ Al and 02/H /A . The peak I., i spr oduced at di f f er ent met al l oadi ngs f oreach combi nat i on. The maxi mum I... poi nt s f ort he three pr opel l ant combi nat


8/17

vol ume avai l abl e f or t he LRB or otherboost er vol ume and not t he maxi mal I an.

The NTO/ MMH/ Al sys t ems ar e abl e t o del i vert he hi ghest I,, i ncr eases over t he non-met al l i zed cases. These r esul t s are shown i nTabl e 11. W t h t he pump- f ed LRB, t he I,, hasr i sen 11. 2 l bf - s/ l bm Al so, t he NTO/ A- SO/ Alpr opel l ant s f or t he Ti t an I V provi ded a 9. 2l b, -s/l b. I,, r i se f or St age 1 and a 14 l b,-s/l b, i ncr ease f or St age 2. The Ti t an engi neper f or mance usi ng metal l i zed NTO/ A- SO/ Alr equi r es a met al l oadi ng Of 35 t o 40 percentt o pr oduce t he maxi mum I., i ncrease f or t heseengi nes.

An i mpor t ant poi nt t o not e i s t hat t hemetal l i zed cases w t h Oz/ RP- l / A1 have a netI,, r educt i on over t he nonmetal l i zed 02/ RP-1 combi nat i on. A smal l I,, dr op al so occur sw t h t he pr essure- f ed NTO/ MMH/ Al syst emThough t he s p i s l ower ed w t h the addi t i onof t he met al , t he densi t y i ncr ease af f or dedw t h t he 55- percent A1 l oadi ng enabl esdenser packagi ng of t he boost er . Ther e w l lst i l l be a per f or mance gai n even w t h ar educt i on i n I sp.

The maxi mal metal l oadi ng consi der ed f orO/H /A was 70 percent of t he f uel mass. Themet al l oadi ng when consi der i ng of al l of t hepr opel l ant ( oxi di zer and f uel ) of t heOJ HJ A1 propul si on syst emwas 38. 9 percent(f or a mxtur e r at i o of 0. 8 w t h a 70per cent A1 l oadi ng) . The 02/H /A1 peak p was461. 2 l b, - s/ l b, at a met al l oadi ng of 65per cent of A1 i n t he H/A f uel , w t h an eof 77. 5: l and a m xtur e r at i o of 0. 7. Lat eri n t he paper , t he r easons f or sel ect ed anI,, ot her t han t he peak val ue w l l beanal yzed.

Wt h metal l i zed 02/H /A1 ( w t h 60- percent A1l oadi ng) f or t he LRB, an 8. 8- l b, - s/l bmi ncr ease i s enabl ed over O/,H ( shown i nTabl e 11). Thi s i s a l ar ger i ncrease t hant hat pr evi ousl y di scussed f or t hi spr opel l ant combi nat i on (Ref s. 8 and 9 ) . Thedi f f er ence st ems f r omt he f act t hat t he I ,fo r 0 2 H 2 and O/H/A ar e not bei ng compare3at t hei r r espect i ve maxi mum I s p poi nt s. Theopt i mum r at i o i s near 4 . 0 t o pr oduce t hemaxi mumO/H I,, at t he ver y l ow val ues of Eneeded f or t he LRB. The 6. 0 m xt ure rat i owas sel ect ed f or t he LRB based on t her esul t s of Ref er ences 11 and 12. I f t he I ,val ues of t he met al l i zed and nonmetal l i ze8syst ems wer e compared at t hei r r espect i vemaxi mum I,, poi nt s, t he per f or mance i ncr easef or met al l i zed pr opel l ant s woul d ber epr esent at i ve of t he smal l er di f f er encesr epor t ed i n Ref s. 8 and 9 .

Pr opel l ant Densi t y. Usi ng t he al um numl oadi ngs consi der ed i n t he engi neper f or mance cal cul at i ons, t he pr opel l antdensi t y f or t he RP- 1 can i ncr ease f r om 773kg/ m3 t o 1281 kg/ m3 ( 55 per cent al um numl oadi ng i n t he f uel ). For H2 f uel , t hedensi t y can i ncr ease f r om 70 kg/ m3 t o 220. 3kg/ m3 ( H2 w t h a 70- per cent al um numl oadi ng) . The densi t y i ncr ease i s comput edusi ng:

wher e:

P p . m Densi t y of Met al l i zed Fuel(k9/ m3)

ML Metal Loadi ng ( Fracti on ofFuel Mass)

m Densi t y of Met al i n t he Fuel( kg/ m3)

( kg/ m3P P Densi t yof Nonmetal l i zedFuel

sel ecti on of t he Best Densi t v- I , , Desi snPoints TO f i t t he LRB i nto t he vo1ul ; e of anSRB or del i ver t he maxi mal payl oad i ncr ease,t r ade st udi es must be conduct ed t o determ net he best I * , and densi t y f or eachpr opul si on system The sel ect i on of t hemetal l oadi ng was based on maxi m zi ng t hevehi cl e payl oad or t he abi l i ty t o f i t w thi nan exi st i ng vol ume const r ai nt .

At t he peak I,, desi gn poi nt f or O/H /A , t he

bul k densi t y decreases sl i ght l y over t hatf or O/H. The O/H/A propel l ant s mayr equi r e a heavi er pr opul si on syst emt han t henon- met al l i zed desi gn case. Ref erence 9compar es the pr opul si on mass s cal i ngequati ons f or sever al met al l oadi ngs. Therei s a smal l var i at i on i n t he t ot al mass oft he propul si on syst em w t h t he di f f er entmetal l oadi ngs. Based on t he Ref . 9 t r adest udi es, t he IS p hat i s repr esent at i ve of ametal l oadi ng of 60 per cent was i ni t i al l ysel ect ed f or t he 0 2 / H , / A l LRB. The metal l i zedET used a 70- percent met al l oadi ng. For al lof t he r emai ni ng met al l i zed combi nat i ons,t he met al l oadi ng was sel ect ed t o al l ow t hel i qui d boost er t o f i t w t hi n the vol umeconst r ai nt s of t he exi st i ng pr opul si ons-f stem. The r emai ni ns LRB vrooel l antcombi nat i ons pr oduce a overal l hensi t yi ncrease.

I f t he benef i t s of r educed GLOWor i ncr easedpayl oad are not desi r ed or si gni f i cant , t heef f ect s of i ncr eased pr opel l ant densi t y canst i l l be a benef i t t o l aunch vehi cl es.Because of t he i ncr eased densi t y, t hepr opel l ant t ankage si ze can be r educed,pot ent i al l y of f er i ng bet t er and smal l er t ankconf i gur at i ons. As an exampl e, f or t he LRBusi ng 02/ RP- 1/ A1, t he propel l ant t ank vol umei s r educed over t hat f or t he O / RP-1 case.In t he met al l i zed syst em ( w t h a 49, 664 l b,payl oad) , t he t otal pr o el l ant t ank vol ume

was r educed to304. 7

mfrom t he351. 1

m3r equi r ed f or t he non- met al l i zed O / RP-1case.

Al t hough t he t ankage vol ume decreased i n t heNTO/ MMH/ Al case, ot her appl i cat i ons ofmetal l i zed pr opel l ant s, such as 0, / H2/ A1,w l l show a smal l t ankage vol ume i ncrease.Thi s i s due t o the l ower m xture rat i o oft he metal l i zed O/H/A syst emover t he O Hzsyst em I n t he 02/ H / Al ET, t he t ot al 0 t ank


9/17

vol ume can be r educed f r om 553 . 9 m3 t o 3 1 0m3 f or t he metal l i zed case. The Hz t ankvol ume, however , i ncr eased f r om 1 5 1 5 . 2 t o2 0 2 2 . 8 m3 w t h met al l i zed pr opel l ant s.Over al l , t he tot al t ank vol ume i ncr easedfrom 2 0 6 9 t o 2333 m3 (a di f f er ence of 264m3 or 1 2 . 8 per cent ) . Thi s exampl e i s f or t hecase f or t he STS ET f or bot h t he met al l i zedand t he nonmetal l i zed O H, syst ems wher et he payl oad t o or bi t was 22 , 527 kg ( 49 , 664l b, ).

-

PumD- Fed and Pr essur e- Fed Syst ems. W t ht he very- hi gh per f ormance O/H syst ems bei ngconsi dered f or l aunch vehi cl es, a pump- f edengi ne may be r equi r ed. Pressure- f edpr opul si on syst ems ar e al so underconsi der at i on, but t hey t ypi cal l y r equi r el arger masses f or pr opel l ant t ankage andpr essur i zati on syst ems. Usi ng met al l i zedpr opel l ant s, t he pr opel l ant f eed syst emmustbe desi gned t o suppl y t he non- Newt oni an,t hi xot r opi c met al l i zed pr opel l ant w t h thesame r el i abi l i t y as t he non- met al l i zed H.Cur r ent l y, met al l i zed pr opel l ant s ar e f ed tosmal l pr opul si on syst ems w t h posi t i ve-di spl acement pr opel l ant expul si on devi ces( di aphr agms, et c. , Ref . 2 6 ) . A posi t i veexpul si on syst emand a pr essur e- f ed syst emhowever , are consi dered i mpr acti cal and t oomassi ve f or l ar ge pr opel l ant t anks. For t heext r emel y- l arge propel l ant l oads needed onl aunch vehi cl es, a way of ef f ecti vel y usi ngpump- f ed engi nes w l l be requi r ed.Prel i m nary pump and pr opel l ant expul si onwor k was conduct ed i n pr evi ous r esearchprogr ams ( Ref s. 27 and 2 8 ) . Thi s workdebonst r at ed t he f easi bi l i t y of pumpi ngmet al l i zed f uel s. Al so, t he r esear ch showedt hat ver y hi gh expul si on ef f i ci ency coul d beachi eved f or met al l i zed pr opel l ant s w t houtusi ng posi t i veexpul si on devi ces i n t hepr opel l ant t anks.

.-

Mass Scal i ns Equat i ons. I n det er m ni ngt he dry mass of t he l aunch vehi cl e st ages,t he f ol l ow ng gener al mass- scal i ng equat i onwas used:

mdrY = A + B m

wher e:

mdr Y Dr y Mass ( kg)

A, B Mass Par amet er s

mP Propel l ant Mass ( kg)

Tabl e I V l i st s t he pr opul si on mass- scal i ngpar amet er s f or al l of t he consi der edsyst ems. These paramet ers i ncl ude al l of t hemasses t hat ar e r equi r ed t o st ore anddel i ver propel l ant s to t he mai n engi nes.They i ncl ude t ankage, engi nes, f eed syst emt her mal cont r ol , st r uct ur e, r esi dual s andcont i ngency. Al so i ncl uded, i f needed, ar et he aer odynam c st r uct ur e of t he boost er s,such as t he nose cone and af t ski r t of t heLRB. These par amet ers were deri ved f romt heresul t s of t he LRB st udi es and the resul t sof pr opel l ant - t ank mass est i mat i on codesused i n pr evi ous studi es ( Ref s, 8 9 and

1 3 ) . The paramet er A of t he scal i ngequat i ons var i es due to t he di f f er entengi ne, nose cone and af t ski r t masses oft he di f f er i ng boost er s. The B par amet er i sdependent upon t he pr opel l ant m xt urer at i os, t he pr opel l ant met al l oadi ng andhence t he pr opel l ant densi t y. The speci f i cm xtur e r at i os and t he met al l oadi ngs ar el i sted i n Tabl e 111.

Al l of t he t ankage conf i gur at i ons consi der edi n t he st udy were based on t he abi l i t y t opackage t he boost er s w t hi n a cur r ent l aunchvehi cl e s l engt h and di amet er constr ai nt s.Typi cal l y t he mai n t ankage i s cyl i ndr i calw t h el l i psoi dal dome ends. Onl y thepr essur i zat i on syst ems used spher i calt ankage.

The pr opel l ant t ankage f or al l of t he pump-f ed syst ems i s desi gned f or a 50- psi amaxi mal operat i ng pr essur e. The pr opel l anti s st or ed at 30 psi a. Pressur e- f ed boost er shad hi gher maxi mum operat i ng pressur es of5 0 0 psi a. Al l of t he t ankage f or 0 H2 andRP- 1 i s composed of al um num al l oy ( 2 2 1 9 -T67). The LRB t anks f or NTO and MMH ar e madeof t i t ani um ( Ti - 6A1- 4V). The f l ange f actor

( f or mounti ng f l ange masses) and saf et yf act or ar e 1 . 4 and 2. 0, r especti vel y, f ort he pr opel l ant t anks. The saf et y f act or i sbased on t he t ank mat er i al ul t i mat e st r ess.The pr opel l ant r esi dual s and hol dup mass i s1 . 5 per cent of t he t ot al pr opel l ant mass.The per cent age accommodat es a smal l added

Tabl e I VPropul si on syst emMass- Scal i ng Par amet er s:

Dr y Mass Per Boost er

Vehi cl e and scal i ng Par ametersPr opel l ant A B

STS:Boost er opt i ons -Sol i d 6 5 , 6 9 8 . 8 0. 0Pump- Fed :02/RP 1 26,184.8Oz/ RP-l / A1 26 , 261 . 2NTO/ MMH 26 . 294 . 4NTO / MMH/ A~ 2 6 . 2 9 4 . 4

2 6 i 2 3 6 . 92 6 , 2 3 6 . 9

Pr essur e- Fed:OJ RP- 1 3 0 , 4 5 6 . QoS~RP- ~/ A~ 3 0 i 4 5 6 . 9NTO/ MMH 29 , 737 . 2NTO/ MMH/ Al 29,737.2

Mai n Pr opul si on Opt i ons -OdH, 3 6 , 0 5 0 . 1O J H z / A1 1 0 , 5 1 7 . 4

Ti t an Iv:Stage 1 Opti ons -NTO/ A- 5 0 9 , 2 3 5 . 2

Stage 2 Opti ons -NTO/ A- 50 4 , 1 3 7 . 3

0 . 0 7 4 70 . 0 7 1 50 . 0 6 5 00 . 0 6 4 20 . 09250.1016

0 . 2 0 0 90 . 1 7 6 70 . 1 4 6 30 . 1332

0.00 . 0469

0.0

0.0

7


10/17

pr opcl l anc mass f or cr yogeni c pr opel l antboi l of f . Because the st ages have pr opel l antgr ound suppor t up unt i l l i f t of f , no l ar geal l owance was made f or pr opel l ant l osses duet o boi l of f . The mas s cont i ngency f or t heboost ers was 20 percent of t he dry mass.

Each cr yogeni c O,/H, pr opul si on syst em usesaut ogenous pr essur i zat i on. The NT O/ msystem used r egul at ed pr essur i zati on. Thepr essur ant i s hel i um I n t he pr essur antt a?k, t he maxi mal operat i ng pressure i s 3722psi a. The st orage pr essur e i s 3444 psi a( Ref . 9 . The f l ange f act or and saf et yf act or f or t he pr essur ant t anks ar e 1. 1 and2. 0, r espect i vel y. For t he aut ogenoussystems, a smal l hel i um pr essur i zat i onsyst em i s i ncl uded. I t can pr essur i ze one-t ent h of t he tot al pr opel l ant t ank vol ume.For t her mal cont r ol . t he cr voaeni cpr opcl l nncs Oi and H 2 ) use a ' Gi gh-pcr f or nance mul ci l aycr i nsul at i on ( Ref . 9).The st or abl e pr opel l ant s onl y r equi r e al ower - per f or mance mul t i l ayer i nsul at i on.

The metal l i zed OJ HJ AI ET al so used the samedesi gn assumpt i ons as t he O / HdAI LRB. Therewere, however , t wo di f f erences bet ween t heLRB and t he ET. One was t hat t he r esi dualand hol dup mas s of t he ET was 1 per cent oft he t ot al pr opel l ant mass. A l s o , no smal lhel i umsyst emwas added. These changes overt he LRB assumpt i ons are based on t heexi st i ng ET desi gn.

M ssi on Anal vsi s

On t he STS m ssi ons, t he m ssi on i sdescr i bed w t h t wo AV val ues. These val uesf or t he Space Shut t l e m ssi ons car r yi ng a22, 527 kg ( 49, 664 lb) payl oad wer e 2. 49kms f or the f i rst - stage f i r i ng ( SSME/ SRBi gni t i on t o SRB separat i on) and 6. 74 km/sf or t he second st age ( SRB separat i on t o Mai nEngi ne Cut Of f [MECO]) . These AV val ues ar ebased on the per f ormance of t he Ul yssesl aunch m ssi on ( Ref . 15) and t he per f ormancepr edi ct ed i n past STS Li qui d Rocket Boosterst udi es ( Ref s. 11 and 12). The AV val ues f ort he ot her STS payl oads ar e l i st ed i n Tabl eV: 22, 527 t o 31, 979 kg ( 49, 664 t o 70, 500lb) . The f i nal or bi t of t he Or bi t er i s 296-km (160 naut i cal ml e) ci rcul ar orbi t w tha 28. 5- degr ee i ncl i nat i on, r epr esent at i ve ofa l aunch f r omt he Kennedy Space Cent er. Thef i r i ng t o pl ace t he STS i nto i ts f i nalci r cul ar or bi t i s pr ovi ded by t he Or bi t alManeuver i ng Subsyst em ( OMS) aboar d t heOr bi t er. The LRB- SSME per f ormance pl aces t hevehi cl e i nt o the same or bi t as t he ascentusi ng t he SRB- SSME combi nat i on. Because t heOMS f i r i ng i s t he same i n ei t her ascent ,t hi s maneuver i s not consi dered as part oft hi s anal ysi s.

On the Ti t an I V m ssi ons, t raj ector ysi mul at i ons were used t o pr edi ct t he m ssi onAV: t he Pr ogr am f or Opt i m zi ng Si mul at edTr aj ect or i es ( POST) t r aj ect or y code ( Ref .29) . The POST i s a general i zed event -ori ent ed pr ogr amt hat can be used t o anal yzeascent , on- or bi t and ent r y tr aj ectori es. I tcan be used t o opt i m ze any cal cul ated

var i abl e and the t r aj ect ory can beconst r ai ned t o meet speci f i ed r equi r ement .

The Ti t an I V vehi cl e used i n t he anal ysi s i scomposed of a t wo- st age l i qui d pr opel l antcore and t wo seven- segment sol i d rocketmot or s SRM) The conf i gur at i on has no upperstage. The vehi cl e l i f t s of f w t h onl y t heSRMs f i r i ng. Af ter SRM bur nout , t he l i qui dcore i s i gni t ed at appr oxi matel y 115 secondsaf ter l i f toff . I t s f i nal payl oad i s pl acedi n a ci rcul ar orbi t w th a 407 km ( 220naut i cal ml e) al t i t ude and an i ncl i nat i onof 28. 5 degr ees. The l aunch i s f r om t heEaster n Space and M ssi l e Cent er ( CapeCanaveral ) .

Resul t s

Suace Transuor t ati on Svst em

For t he STS, t wo t ypes of pr opul si on syst emchanges were st udi ed. The f i r st was t her epl acement of t he SRBs w t h met al l i zed andnon- met al l i zed LRBs. I n t he ot her st udy, t hechangeout of 0 / H z pr opel l ant s f or t he SSMEw t h met al l i zed 0dHJ A1 was anal yzed.

LRB f or SRB Reul acement

OJ RP- 1/ Al LRB. The r epl acement oft he SRB w t h O RP- l / Al al l owed denserpackagi ng of t he boost er w t hi n the SRBdi mensi ons. Fi gur e 2 cont r ast s t he LRBl enath and di amet er . The ~avl oad del i ver ed~

~

~ ~ ~~ ~ ~~

~~~~ ~ ~~

t o orbi t is 22, 527 kg (49, 664 lb , Ref . 15) .I f t he boost er i s const r ai ned t o thedi ameter of t he SRB, t he O / RP- l / AI boosteri s 43. 4 m ( 142. 3 f t ) l ong: 2 m (6. 7 f t )shor t er t han t he SRB. Usi ns O / RP- 1. t heboost er i s 47. 6 m ( 156. 3 i t) - l ong: . t hi sl engt h exceeds t he 45 m ( 149- f t ) SRB l engt h.

Because t he met al l i zed LRB was smal l er t han

t he exi st i ng SRB, t he sensi t i vi t y of boostersi ze to payl oad- t o- or bi t was consi der ed. I nFi gur e 3, t he LRB l engths are compared f orf our payl oad masses. Usi ng a metal l oadi ngof 55 percent i n t he Oz/ RP-l / A1 LRB al l owedt he boost er t o f i t w t hi n t he exi st i ng SRBdi ameter and l ength and del i ver al most

Tabl e vLaunch Vehi cl e Desi gn Assumpt i ons:

STS M ssi on AV Br eakdownf or LRB Si mul at i ons

St age AV ( kms)~~ ~

Payl oad 49. 7 60. 0 65. 0 70. 5(k1b. A

LRB 2. 4847 2. 5894 2. 6387 2. 6920MPS 6. 7362 6. 6315 6. 5822 6. 5289

* AV var i es f or MPS and SRB due t o f i xedr opel l ant l oad i n ET


11/17

0 2 RP-1 /AI PUMP-FED LAB170 PAYLOAD= 49,664 bm

160 11 191m19 RP-VAI: 55 A Izl 140 5 ~

w-I

U0,

4 '**130%, * %.,

"~.~.1.1.111.1.120

1 1 O j

100 2 14 16 18 20

LRBDIAMETER(ft)

i

Figure 2. LRB Length vs. Diameter With02/RP -l/AI: Payload = 49,664 Ib,

PRESSURE-FED LRB:PAYLOAD= 49,664 bm

- 21 RP-1: 00 AITO IMMH:00 AI02/ RP-1 /AI:55% AI

100

-2 14 16 18 20

LRB DIAMETER(ft)

55 AI: 70,500 Ibm00 AI: 49,664 Ibm

[I 5 5 AI: 65,000 Ibm160 .~ ' 55 AI: 60,000 Ibm- 5 AI: 49,664 Ibm

.I .

170

150

3 140

4 130

120

110

100

m

12 14 16 18 20

LRBDIAMETER(ft)

r

4

Figure 3. LRB Length vs. Diameter WithO*/RP-l/AI - Payload MassParametrics

170 lm 40% AI: 70,500 Ibm

0 AI:49,664 Ibm-0- 40% A t 65,000 Ibm

' 40% AI: 60,000 Ibm40% AI: 49,664 Ibm

NTO IMMH /AI PUMP-FEDLRB

12 14 16 18 20

LRBDIAMETER(ft)

Figure 4. LRB Length vs. Diameter With Figure 5. LRB Lengthvs. Diameter WithPressure-Fed Booster NT O/ MM H/AI Payload Mass

Parametrics

9


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27, 216 kg ( 60, 000 lb ) of payl oad; onl y 0. 9m (2. 9 ft ) of added l engt h i s requi r ed t odel i ver t hat payl oad. By al l ow ng t he LRBl engt h t o i ncrease t o 49. 3 m ( 161. 9 f t) , t hepayl oad t o orbi t can be i ncr eased t o 31, 979kg ( 70, 500 l bm . Thi s i s a 42 per centpayl oad i ncr ease over t he STS- w t h- SRBpayl oad capabi l i t y. whi l e these l engt hs dovi ol at e t he st r i ct SRB l engt h, t hese r esul t sare i ncl uded t o show t he pot ent i al payl oadadvant ages of l onger met al l i zed LRBs.

A pr essure- f ed O / RP- l / Al LRB was al soi nvest i gated. The l engt h and di ameter oft hese boost ers were not compati bl e w t h t heSRB const r ai nt s. The met al l i zed LRB i s ,however , subst ant i al l y shor t er t hant he non-met al l i zed boost er . Fi gur e 4 cont r ast s t hepr essur e- f ed boost er s w t h t he a 55- per centmetal l oadi ng. The LRB l ength ( when usi ngt he SRB di amet er) i s 56. 3 m 1184. 7 f t l . Thecor r espondi ng O /RP-1 LRB l engt h i s 65 m( 213. 4 f t) .

NTO/ MMH/ Al LRB. As w t h t he OJ RP-1/ Al boost er s, t he hi gher densi t y of t hemetal l i zed NTO/ MMH/ Al r esul t ed i n a ver ysmal l LRB: onl y 40. 8 m ( 134 f t ) l ong. I n

Fi gur e 5, t he boost er l engt h and di ameterare depi ct ed. The met al l oadi ng sel ect ed f ort he MMH was 40 percent . The NTO/ MMH/ Alboost er coul d del i ver a 31, 979 kg ( 70, 500lb ) payl oad i f t he boost er l engt h werei ncr eased t o 46. 2 m ( 151. 6 f t ) ; t hi s i s onl y0. 8 m ( 2. 6 f t) over t he exi st i ng SRBdi mensi ons.

The l engt h and di amet er of a pr essur e- f edNTO/ MMH/ Al boost er w t h a 50- per cent metall oadi ng i s shown i n Fi gur e 4. A hi gher met all oadi ng t han t hat f or t he pump- f ed boost erWas used i n t hi s LRB t o at t empt t o f i t i tw t hi n t he SRB si ze. At t hi s l oadi ng, t heboost er was unabl e t o f i t i n the SRB l engt hunl ess t he LRB di amet er was great er t han 4m ( 13 f t ) . The pr essur e- f ed LRB i s notconsi dered a pri me candi dat e f or an SRBr epl acement .

0,Lf12/A1 LRB. Ther e was l i t t l evol ume benef i t f r om t he pump- f ed O,/H, orOz/H /A1 LRB. Thi s LRB was not abl e t o meett he SRB si zi ng requi r ement . The l engt h oft he LRB w t hout met al l i zed pr opel l ant s was80. 6 m (264. 5 ft ) . W t h met al l i zed O/H/A( 60- per cent met al l oadi ng) , t he boost erl enqth was 96. 3 m (315. 8 f t ) . Thi s i ssubi t ant i al l y l onger t han the 45. 4- m ( 149-f t ) SRB l engt h. The met al l i zed boost erl engt h was equal t o the SRB onl y atdi ameter s much gr eat er t han 6. 1 m ( 20 f t ) .Thus, t he O z / H 2 and the Oz/H /A1 boost er s wer epoor per f ormers when usi ng t he SRB si zi ngconstr ai nt s.

For pump- f ed boost er engi nes, t he nozzl eexpansi on r ati o i s smal l : 30: l . When usi ngt he l ow expansi on r ati os requi r ed f or t heOz/H /A1 LRB engi nes, t he maxi mumI,, f or t hemet al l i zed pr opel l ant s occur at a l owm xt ur e rati o. Thi s l ow m xt ur e rati o f or cest he tank' s t ot al vol ume to be gr eat er t hant hat f or t he O H, systemat a 6: l oxi di zert o f uel rat i o.

I f t he vol ume const r ai nt s of t he LRB wer er el axed, OJ HJ A1 pr opel l ant s may pr ovi de apayl oad i ncrease and a GLOW r educti on.Fut ur e vehi cl e st udi es may t her ef or e f i ndt hese met al l i zed pr opel l ant s as anat t r acti ve opti on.

WLRB Masses. Tabl e VI compares t he

02/ RP- 1/A1 and NTO/ MMH/ Al LRB masses. Theseboost er s were si zed f or t he basel i ne payl oadm ssi on. Each of t he boost er s i ssubst ant i al l y l i ght er t han t he SRB. The GLOWof t hese opt i ons was t heref ore l ower t hant he st andar d STS- SRB vehi cl e. The Oz/ RP- l / A1case reduced t he GLOW by 19 per cent ( or394, 500 kg) and t he NTO/ MMH/ Al case was abl et o r educe t he GLOWby 20 per cent ( or 411, 881kg) A l ower GLOWcan make pr ocessi ng of t hevehi cl e easi er and t r anspor t at i on of t hevehi cl e el ement s easi er i n t he pr ocessi ngf l ow

Speci f i c I mpul se Ef f i ci ency (n ) Ef f ectsOn LRB Lenut h. The i nf l uence of 1) on t heperf ormance of t he met al l i zed l aunchGehi cl es was i nvest i gat ed. Due t o t he t wo-phase f l ow of t he met al l i zed pr opel l ant s i nt he combust i on chamber and nozzl e, t her e i sa

di f f erence between t he gas and sol i d-l i qui d par t i cl e vel oci t i es whi ch creat es aper f or mance l oss. The sol i d- l i qui d par t i cl esar e composed of sol i d and l i qui d al um numoxi de (A ,O ). Once t he pot ent i al l osses ofmet al l i zed pr opel l ant s are i nt r oduced i nt ot he anal ysi s, t he per f ormance may be muchl ower t han t hat pr evi ousl y pr edi ct ed. A

Tabl e VI WLi qui d Rocket Boost er Mass Summary:

Met al l i zed OZ/ RP- l / Aland NTO/ MMH/ Al Pr opel l ant s

Subsyst em Mass ( kg)

02/ RP- 1/ A1 NTO/ MMH/ AI

Oxi di zer Tank 1, 663. 0Fuel Tank 1, 349. 0Pressur i zat i on 1, 106. 5Engi nes and FeedSvst em 19. 538. 9Thermal Cont r ol 3i 421. 8

1, 698. 0ubsyst ems:Avi oni csSepar at i on Syst emPower

St r uct ur e: 7, 528. 0Nose Cone 745. 0

Resi dual s andHol dup 5, 211. 0Cont i ngency( 20% 8, 452. 2Tot al 50, 713. 4

Usabl ePr opel l ant 342, 180. 8

828. 31, 125. 2

91. 3

19, 538. 93, 363. 11, 698. 0

7, 398. 8745. 0

5, 121. 37, 982. 0

47, 891. 9

336, 310. 6

Tot al STS GLOWWt h LRB: 1, 657, 671. 0 1, 640, 287. 0

10


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ser i es of cases show ng t hi s i nf l uence ont he O RP- l / Al and NTO/ MMH/ Al syst ems wer eanal yzed and t he r esul t s are di scussedbel ow.

O RP- l / Al Ef f ects. Fi gur eprovi des ti ;e par amet r 2cs of LRB l ength andq f or 02/ RP- l / A1 pr opel l ant s. I n t he f i gur e,t he met al l i zed q i s var i ed f r om 0. 87 t o0.92. Thi s r ange r ef l ect s t he per f or mancepenal t i es t hat have been pr edi ct ed f ormet al l i zed pr opel l ant s: up t o a f i ve per centr educt i on i n q ( Ref s. 2 2 and 30) . The LRSl engt h i s 4 6 m ( 151 f t ) w t h t he wor st - case0. Even w t h an q penal t y of 4 percent q =0 . 8 8 ) , t he 02/ RP- 1/ A1 LRB i s abl e t o f i tw t hi n t he SRB l engt h requi r ement . Thi s casei s f or t he basel i ne payl oad of 22 , 527 kg( 4 9 , 6 6 4 l bm.

NTO/ MMH/ Al Ef f ect s. The over al lef f ect of r educed q i s l east det ri ment al f orNTO/ MMH/ Al propel l ant s. Fi gur e pr ovi dest he par ametr i cs of boost er l engt h and q fo rNTO/ MMH/ Al . A q r ange of 0. 87 t o 0.92 wasused. As w t h the r esul t s f or 02/ RP- l / Aldi scussed above, t he NTO/ MMH/ Al boost er f ort he STS w t h t he basel i ne 22 , 527 kg ( 4 9 , 6 6 4

lb) payl oad i s abl e t o f i t w t hi n t he SRBl engt h and di amet er . W t h t he met al l i zedNTO/ MMH/ Al f or t he basel i ne payl oad, t hel engt h i s 43 . 2 m (141. 8 ft ) f or t he wor st-case penal t y of 11 = 0.87.

Cl earl y, t he q w l l have a ver y st r ongi nf l uence on reduci ng t he LRB si ze i n someof t he met al l i zed cases. Thi s i s especi al l yt r ue f or t he hi gher payl oad cases. A penal t yof t he magni t ude pr edi ct ed f or met al l i zedpr opel l ant s can ser i ousl y r educe t hei rbenef i t s. Smal l r educt i ons i n t he q ,however , can be absor bed w t h onl y a smal lbooster l engt h i ncrease. Research onr educi ng t he l osses associ at ed w t hmetal l i zed syst ems has been conducted ( Ref s,2 5 and 31) . Reduci ng t he A1,0, par t i cl e si zew l l r educe t he gas and sol i d- l i qui dvel oci t y di f f er ences, i mpr ove t he met al l i zedq and i mprove t he del i vered payl oad andr educe t he LRB si ze. I f t he met al l i zed LRBdoes exper i ence l arge q penal t i es, andcannot del i ver added payl oad, t here arest i l l benef i t s t o be gai ned. The i ncreasedsaf et y of f er ed by gel l ed met al l i zedpr opel l ant s and t he cont r ol l abi l i t y enabl edw t h an LRB makes a metal l i zed boost er ani mpor t ant saf et y enhancement

Mai n Pr opul si on Syst emReol acement

The per f or mance of an SSME usi ng met al l i zedO>/ H- / Al i s shown i n Fi crure 1. At a 7 0 -

,., -per cent A1 l oadi ng, t he I,, i s i ncreased f r om4 5 2 . 6 6 t o 460. 61 l b,- s/l b,. Thi s met all oadi ng was sel ect ed af t er anal yzi ng a r angeof l oadi ngs f r om 40 t o 7 0 per cent . A 7 0 -percent l oadi ng pr oduced t he smal l est vol umei ncr ease of t he ET. Fi gur e 7 depi ct s t heper f ormance of t he STS w t h t he met al l i zedSSMEs. . St andar d SRBs are used i n t hi sanal ysi s. Two l evel s of cont i ngency ( ormasses t hat ar e added t o t he ET dry mass)are shown: 0 and 20 per cent . The var i at i oni n cont i ngency was shown t o demonst r at e the

PAYLOAD= 49,664 Ibm

200

80

160

100 2 O L6 87 88 89 90 91 92 93

SPECIFIC IMPULSE EFFICIENCY

Figure 6. LRB Length vs. sp Efficiency

METAL LOADINGr70 PERCENTAL IN H21AI

20% COWING.- T VOLUME0 COWING.I2600

2000 , ' , ' I .45 50 55 60 65

PAYLOAD MASS(1000 Ibm)

Figure 7. MetallizedET Volume vs. Payload

11


14/17

i nf l uence of t he dry mass on perf ormance. Aper f ormance i ncrease was enabl ed w t hmet al l i zed O/H/A but not w t houti ncr easi ng t he ET vol ume. Wt h t hesepr opel l ant s, t he m xt ur e r at i o of t hepr opul si on syst ems was very l ow 0.8. Asw t h t he 02/H /A LRB anal ysi s, t he vol ume oft he met al l i zed ET i s l ar ger t han t hest andar d ET. Recause t he m xt ur e r ati o oft he 02/ H2/ A1 syst em ( w t h 70%A1 i n H2/ A1) i sso l ow, t he t ankage vol ume was i ncreased by8. 7 per cent over t he ET f or t he basel i nepayl oad ( 0- per cent cont i ngency) . Even w t ht he i ncreased densi t y of t he H /A , t hemet al l i zed syst emwas not abl e t o f i t w t hi nt he ET vol ume const r ai nt .

For t he cases wher e t he 20- per cent masscont i ngency was added t o t he dry mass of t hemet al l i zed ET, met al l i zed pr opel l ant sprovi ded a payl oad advant age but w t h al arger vol ume i ncr ease. Because of t hei mport ant i nf l uence of t he ET masscont i ngency on vehi cl e perf ormance, a bet t erunders t andi ng of t hi s mass i s needed. Oncet he desi gn f eat ur es of t hi s new t ank aremor e r ef i ned, t he anal yst w l l be abl e t omore cl earl y def i ne t he cont i ngency mass.More detai l ed payl oad anal yses can t hen beconduct ed t o f i nd t he benef i t of met al l i zedO H /A . The added vol ume of t he met al l i zedET, however , may make i t i mpract i cal t oi ncl ude met al l i zed O H2/ A1 i nt o t he cur r entSTS. Fut ur e ver si ons of heavy l i f t l aunchvehi cl es w t h mor e f l exi bl e vol umeconst r ai nt s may mor e r eadi l y benef i t f r omt he Z p i ncr ease af f or ded by met al l i zedH /A1.

Ti t an Iy

I n t he Ti t an I V si mul at i ons, t he tot alvehi cl e wei ght ( l aunch vehi cl e m nus t hepayl oad) r emai ned const ant . Thus, t hevehi cl e dr y mass and t he tot al pr opel l ant

l oads f or bot h t he metal l i zed and non-metal l i zed cor e st ages ar e t he same. Nor epl acement s of t he SRMs wer e consi dered.usi ng t hese pr opel l ant l oads, t he addedpayl oad t o or bi t was cal cul at ed. Tabl e VI 1compares t he payl oads f or t he t wo' cases.Usi ng metal l i zed NTO/ A- 50/ Al , t he payl oadwas i ncreased f r o m 14, 643. 0 t o 16, 336. 3 kg( an i ncr ease of 11. 6 per cent ) . I n acompar i son wher e t he GLOW of t he t wovehi cl es were equal , t he Ti t an payl oad wasi ncr eased t o 16, 286 kg, or 11. 2- per centhi gher t han t he non- met al l i zed case. Ananal ysi s of t he q ef f ect on t he Ti t anpayl oad was not conduct ed. As w t h t he LRB,even i f t he payl oad to or bi t i s notsi gni f i cant l y i ncr eased, t he added saf et ybenef i t s of gel l ed pr opel l ant s may be asi mpor t ant as pot ent i al payl oad i ncr eases.

To t ake advant age of met al l i zed pr opel l ant s,t he Ti t an I V woul d have t o have severalmaj or modi f i cati ons. Though t he same t ot alpr opel l ant mass i s used i n each of t hest aues. t he vol umes of t he oxi di zer and t hemet al l i zed A- 50/ Al f uel ar e di f f er ent f r omt hose f or t he A- 50 f uel . Wt h t he 0. 68m xt ure rat i o for t he met al l i zed Ti t an f i rst

Tabl e VI 1Ti t an I V Mass summar y:

NTO/ A- 50 and Met al l i zed NTO/ A- 50/ AlPr opel l ant s*

Vehi cl e Mass ( kg)

El ement No Met al Met al l i zed

Payl oad 14, 643. 0 16, 336. 3

St age 2:Propel l ant 34, 650. 3

4, 137. 3 4, 137. 334, 650. 3ry

St age 1:

Propel l ant 154, 465. 79, 235. 2 9, 235. 2

154, 465. 7r y

St age 0:Tot al Mass 631. 393. 0 631. 393. 0

Tot al 848, 524. 5 850, 217. 8

* Propel l ant Masses Aboar d t he Stages 1and 2 Ar e I dent i cal

121. 61 m3. The vol ume avai l abl e i n t he f i r stst age i s 126. 72 m3. The vol ume spl i t of t heoxi di zer and f uel however i s i ncompat i bl ew t h t he exi st i ng t ankage vol umes.Theref ore, t he t ank dome l ocat i ons woul dhave t o be chanaed t o accommodat e t he newpr opel l ant s. The over al l st age di mensi ons,however , ar e unchanged.

Al so t he combust i on t emperature of t hemet al l i zed Ti t an engi nes w l l be somewhathi oher t han t he exi st i no enoi nes. For t hef i k t st age, t he prebi ct gd met al l i zedcombust i on t emper at ures ( 35- per cent A1 i n A-50/ A1) and t he exi st i ng Ti t an engi net emper at ures ar e 3, 419 and 3, 336 K

r especti vel y. Addi t i onal cool i ng w l l havet o be pr ovi ded t o t he engi ne. Ot hermodi f i cat i ons woul d be needed f or t hevehi cl e feed l i nes, pr opel l ant acqui si t i onsyst emand the engi ne t ur bomachi ner y.

Concl udi nu Remar ks

Met al l i zed pr opel l ant s of f er sever al opt i onsf or t he syst emdesi gner l ooki ng f or ways t oi mpr ove t he Space Shut t l e' s payl oad capaci t yand i t s saf et y. The benef i t s of met al l i zedpr opel l ant s f or t he STS LRB l i e i n t heabi l i ty t o f i t a l i qui d propul si on systemi nt o t he exi st i ng vol ume of t he SRB. Wt hmet al l oadi ngs that are gr eat er t han 55per cent , 02/ RP- l / A1 pr opel l ant s al l ow t heLRB t o f i t w t hi n t he exi sti ng SRB l engt hand di ameter . An NTO/ MMH/ Al LRB w t h a 4 0 -per cent metal l oadi ng coul d del i ver an evensmal l er LRB t han t he O / RP- l / Al boost er .Thi s case i s f or t he basel i ne payl oad of22, 527 kq ( 49, 664 l bm.

Even when t he Dot ent i al added two- phase f l owl osses w t h - met al l i zed propel i ant s ar ei ncl uded, t he LRB i s st i l l abl e t o f i tw t hi n t he SRB const r ai nt s. Even w t h an q

st age, t he t ot al pr opel l ant vol ume needed i s


15/17

penal t y of 4 per cent 7 = 0 . 8 8 , t he 02/ RP-l / Al LRB i s abl e t o fi t w t hi n t he SRBl engt h and di amet er r equi r ement . Thi s i s f ort he case usi na t he basel i ne STS wavl oad of22, 527 kg (49; GGS l b, ) . Si ml ar l y+ i i t h themet al l i zed N rOMMI /A f o r t he basel i ne STS- payl oad, t he l engt h i s wel l w t hi n t he SRBl engt h. The boost er l engt h i s onl y 43. 2 m( 141. 8 f t ) f or t he wor st - case penal t y of 1)

= 0. 87.

When t he l osses f r ommet al l i zed pr opel l ant sare m ni mal , t he LRB can be short er t han t hecur r ent SRB whi l e del i ver i na t he basel i ne~ ~~~~ ~~~~ ~ ~ ~~~~payl oad. I f t hemet al l i zed LRh used t he f ul ll ength of t he SRB, t he STS payl oad may bei ncr eased t o 25, 674 kg ( 56, 600 kg) w t hO / RP- l / Al . A wavl oad of 30. 482 ka ( 67. 200

~ ~ ~~~~ ~~~~ ~ ~ ~~~~

payl oad. I f t hemet al l i zed LRh used t he f ul ll ength of t he SRB, t he STS payl oad may bei ncr eased t o 25, 674 kg ( 56, 600 kg) w t hO / RP- l / Al . A wavl oad of 30. 482 ka ( 67. 200l G m i s proj ' e&ed usi ng' a metal l i zedNTO/ MMH/ Al LRB.

By r el axi ng t he SRB vol ume requi r ement s,t her e ar e si gni f i cant added payl oad benef i t senabl ed w t h met al l i zed pr opel l ant s f or t heSTS over t he exi st i ng SRB. I f t he LRB l engt hwer e i ncr eased 0. 9 m (2. 9 f t) , nearl y 27, 216kg ( 60, 000 l bm of payl oad coul d bedel i ver ed usi ng 02/ RP- 1/ Al r at her t han the

basel i ne payl oadof

22, 527 kg ( 49, 6641. 4).

Wt h NTO/ MMH/ Al , t he STS payl oad coul d gr owt o 31, 979 kg ( 70, 500 lb ) i f t he LRB were0 . 8 m 2 . 6 f t ) l onger t han t he cur r ent SRB.

Wt h met al l i zed pr opel l ant s f or t he LRB,pr opel l ant densi t y pl ays a cri t i cal r ol e i nal l ow ng l i qui d pr opul si on systems t o meett he demandi ng vol ume const r ai nt s of t he STSSRB. Even though t he r p of t he 02/ RP- 1/ Alengi ne suf f er s a reduct i on over i t s non-

+' met al l i zed count erpar t , bot h t hesepropel l ant s and NTO/ MMH/ Al ar e abl e t oenhance t he STS payl oad capabi l i t y whi l er emai ni ng w t hi n t he SRB vol ume. Fut uredesi gn st udi es of STS enhancement s may,t her ef or e, w sh t o i ncl ude met al l i zedpr opel 1, ant s as a ser i ous pr opul si on opt i on.usi ng metal l i zed 0, /H2/A1 ( w t h a 70- per centmet al l oadi ng i n t he H2/ A1) i n a der i vat i veof t he SSME can al so i ncr ease t he payl oadcapaci t y of t he STS. The vol ume of t heExter nal Tank usi ng met al l i zed pr opel l ant scoul d not f i t w t hi n t he cur r ent t ank vol umeconst r ai nt s. Fut ur e l aunch vehi cl es t hathave l e s s - s t r i ngent v ol ume const r ai nt s coul dmore- readi l y benef i t f rom metal l i zedOdHdAl .

An 11. 2 t o 11. 6- per cent i ncr ease i n t heTi t an I V payl oad t o LEO i s enabl ed w t hmetal l i zed NTO/ A- 5O/ Al pr opel l ant s. Sever almodi f i cat i ons w l l have t o be made t o theTi t an st age t o accommodate metal l i zed NTO/ A-50/ A1. The most si gni f i cant of t hese ar e t her el ocat i on of t he t ank domes t o r esi ze t hepr opel l ant t anks and t he engi nemodi f i cat i ons f or i ncr eased combust i ont emperatur e.

Acknow edsement

We woul d l i ke to t hank Mr. Ed Hooks ofMar t i n Mari et t a Manned Space Syst ems f or- pr ovi di ngmass and conf i gur at i on i nf or mat i onon t he STS External Tank.

~

13

Ref erences

Mever s. J. F. . "Del t a I1 - A NewGcner aci on Begi ns, " McDonnel l Dougl as,A I M Paper 89- 7740, pr esent ed a t t heAI AA/ ASME/ SAE/ hSEE 25t h J oi ntPropul si on Conf er ence, Mont erey, CA,J ul y 10- 12, 1989.

"Phase A Repor t : Prel i m nar y Assessmentof Space Tr anspor t at i on Al t er nat i vesFor Pl anet ary M ssi ons, " J et Pr opul si onLabor at or y, J PL Document D- 3332, May15, 1986.

Worm ngt on, J . , "Techni cal Basel i neDocument , Advanced Launch Syst em( ALS) , U. S . Ai r For ce Ast r onaut i csLaborat ory, May 15, 1988.

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NASAational Aeronauticsand Report Documentation PageSpa- AdminirVation

2. Government Accession NoReport No. NASA TM 104456AIAA - 9 1-2050

, Title and Subtitle

Launch Vehicle Performance Using Metallized Propellants

, Author($)

Bryan Palaszcw ski and Richard Powell

. Performing Organization Nam eand Address

National Aeronautics and Space A dministrationLewis Research CenterCleveland, Ohio 44135-3191

'. Sponsoring Agency Name and Address

National Aeronautics and S p c c AdministrationWashington, D C 20546-0001

3. Recipicnt 's Catalog No.

5. Report Date

6. Performing OrganizationCode

8. Performing Organization ReportNo.

E - 6 2 9 1

0. Work UnitNo.

506-42

1. ContractorGrant N o

13. Type of Report and Period Covered

Technical Memorandum

14. Sponsoring AgencyCode

Supplementary Notes

Prepared for thc 27th Joint Propulsion Confere nce cosponsored by the AIA A, SAE , ASME , and ASEE , Sacram ento,California, June 24-27, 1991. Bryan Palaszewski, NAS A Lewis Research Center . Richard Po well, NASA LangleyRcscarch Center, Ham pton, Virginia 236 -5225 . Responsible person, Bryan Palaszcwski, (2 16) 433- 2439 .

i. Abstract

Mctallizcd propellant propulsion systems are considered as replacements for thesolid rocket boosters an d liquidsustainer stages on the current launch vehicles: both the Space Transportation S ystem (STS) and the Titan IV. LiquidRockct Boosters for the STS wcrc analyzed as replacements fo r the current Solid Rocket Boosters. Thes e hoostcrs canprovidc a liquid propulsion sy stem within the volume c onstraints ofa Solid Rocket Booster. A replacement for theSpace Shuttle Main Engines using metallized 02/H2 /AI was studied. The liquid stages of the TitanIV were alsoinvestigated; the A-5 0 fuel was replaced with metallized stora ble A-50/AI.A metallized propellant is simila r toittraditional liquid propellant. However, it has metal particles, such as aluminum, that are suspended ina gelled fuel,such as hydrogen, RP-1, A erozin e-50 (A-SO)or monom ethyl hydrazine (MM H). Th e fuels then undergo combustionwith liquid oxygen or nitrogen tetroxide (N TO) . The se propcllants provide options for increasing the pcrformaiiccofcxisting launch vchicle chemical propulsion system s by increasing fue l density or specific impulse (I), or both Tlicscincreases in density an dISp can significantly re duce the propulsion system liftoff weight a nd allow a liquid rockcthoostcr to fit into the sam e volum e as an existing solid rocket booster. Also, because gelled fuelsarc akin to liquidpropellants, metallized syste ms can providc ch a n c e d controllability over solid propulsionsystems. Gelling of thepropellant als o reduces th e sensitivityto impacts and consequently reduces the propellant explosion hazard.

SP

Launch vehicles; Metal propellants; Liquid rocketpropcllants; Liquid propellant rocket e ngines;Missionplanning

Unclassified - UnlimitedSubject Category 20

a s s , . 0 IS page

Unclassified Unclassified

A F O A M i 6 2 6E T 8 6

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NASA - Launch Vehicle Performance Using Metallized Propellants