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vehLcla Sizing Data for 1995

Vehicle Name: Strav_an I Conftg_=atLon :S105015V.S00

Program Name: Air Augmented Rocket

Date: 12-03-1987

Nose Cone Data:

LenqF;h - 9.8'

Nose Cap Radius - 1'

HaJo= Outside Diameter - 4.5'

Netted _ea - 98 sqf_

Structure Weight - 179 Ib

C.G. - Sta 67.4

Czew _._az_nant Data:

Length - 17.8'

Minor Outside Diameter - 4.5'

Major Outside Diameter - 9.5'

Wetted Area - 393 sqft

Structure Weight - 719 Ib

C.G. - $ta 237.3

Fixed weight - 3,000 Ib

C.G. - Sta 190.5

Crew Weight - 440 ib

C.G. - Sta 292.9

Oxidize= Azaa Data:

Len_h - 30.2'

Hinoz Outside Diame_eE - 9.5'

Major Outside Diameter - 18.0'

We_ted Area - 1,316 sqft

Structure Weight . 2,408 Ib C.G. m S_a 531.1

Tank weight - 531 ib C.G. - Sta 596.5

Oxidizer Weight - 258,011 lb C.G. - Sta I;04.1

Tank Insulation Weight - 1,602 ib C.G. - Sta596.5

Small Dome Height - 3.5'

Small Dome Diameter (I.D.) - i0.0'

Tank Frustum Length - 21.0'

Large Dome Height - 5.6'

Large Dome Diameter (I.D.) - 15.9'

Tank Volume = 3,741 cuff

1995 T.ad) Vehicle Sizing Dam with Liquid Hydrogen

28-42

Con_£g_:at£oa :SlOSOlSV.500 P_|re 2

Fuel Azea Data:

Length - 82.6'M/no: Outsidm Diameter - 18.0'

Major Outside Diameter - 33.6'Surface Area . G,842 sqft

Structure Weight - 12,$21 lb

Tank Weight - 4,018 lb

Fuel Weight - 121,359 Ib

Tank Insulatlon Weight - 8,183 Ib

Small Dome Height - 6.9'

Small Dome Diameter (I.D.) - 19.4'

Tank Frustum Length - 48.7'

Large Dome Height - 16.5"

Large Dome Diameter (I.D.) - 33.1'

Tank Volume - 28,306 cult

C.G. - Sta 1233.7

C.G. - Sta 1175.1

C.6. - Sis 1199.2

C.G, - Sta 1175.1

Pa_loadBayAzea:

Len_h - I0'

Wetted Area - 648 8qft

Structural Weight - 1,186 Lb

C.G. - Sta 0.0

Payload C. G. - Sta 1619.1

Engine A._a Data:

Engine Type - 10# of Engines - 8

Total Engine Weight - 40,880 lb C.G. -Sta 1275.4

St_ake Area Data:

Strake Length - 58.5'

Surface Area (ea) - 568 sqft

Total WeLght - 8,309 lb

C.G. - Sta 749.4

1995 TAD Vehicle Sizing Dam withLiquidHydr_,gcn(conL)

28-43

Co_g_:ation :S20S015V.500 Page 3

Mime. Ccaponent Data:

APU Weight - S,000 lb C.G. - Sta

Landing Gear Weight - 10,000 ib

Wiring Weight - 382 ib

RCS & Control Weight - 454 Ib

Ovezall Vehicle Data:

Len_h - 140.4'

Tank Structure O.D. - 33.6'

Diameter to Outside of Strekes -

Dian_ter to Outside of Engines -

Max. Fuselage Diameter - 50.4'

Nose Cone Angle - 16.0 deg.

Tail Cone Angle - 20.0 deg.

Sizing based on Liquid Fuel

PEol_ll.l.a._t: Weight & Vol-m_ BEeak Down

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Ascent 115,505 ib 26,132 cult

Hohman Transfer 329 Ib 74 cult

ACS 25 lb 6 cult

Retrofire 351 Ib 79 CUlt

Boiloff & Resvs 149 Ib 34 cult

Flyback 5,000 Ib 1,131 cult

Total 121,359 ib 27,457 cult

O=LdlzI=:

Ascent 252,928 lb 3,557 cult

Hohman Transfer 1,917 Ib 27 cult

ACS 152 ib 2 cult

Retrofire 2,122 Ib 30 cult

Boiloff & Resvs 891 Ib 13 cult

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C.G. " Sta 1395.6

Total 258,011 ib 3,629 cult

Ascent Fuel Weight Includes :

1% Addition for Residuals and Unusable Fluids

1.5% Addition of the Usable Fuel for the APU, RCS, and ECS

1995 TAD Vehicle Sizing Data with Liquid Hydrogen (cont.)

2s-44

Con_iguJ:ttion :$105015V.500 Ptge 4

vehicle Weight SuJmazy:

Co_onentName

Fuselage & TPS

Strakes

Tanks(02 & H2i

Insulation

Fixed . "

RCS & Controls

Wiring

APU

Engines & Xnst

Landing Gear

Dry Weight

Propellant

Payload

Net

Flyback

Crew

Gross Veh. Weight

Componen_

Weight (lb)

17,012 ib

8,309 ib

4,549 Ib

9,?85 Ib

3,000 ib

454 lb

382 Ib

5,000 lb

40,860 Ib

10,000 1,b

99,370 ib

374,370 Ib

20,820 Ib

5,000 Ib

440 Ib

500,000 Zb

Fuel Mass Fraction - 75.9 %

Payload/Glow Ratio - 0.053

Payload/Dry weight Ratio - 0.264

Dry Weight C.G. - Sta 1064.7

Gross Weight C.G. - Sta 882.1

1995 TAD Vehicle Sizing Data with Liquid Hydrogen (cont.)

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Igg5 TAD PAYLOAD vs. Z I_ 0::VEHICLEB4PTY WEIGHT WITHOUT PAYLOAD FR_ BRSELII,E WEIGHTESTIMATE - FULL CI:PI'LI_8 ROO<ET | M=I6 - VTOHL

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Payload vs. TOGW and Eneine Tvoe

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Payload vs. Full Caoture Mach Number for Engines #10, #30 and #32

28-52

OF ATrFCX vs. 14:O4NLJ.GE_1995TF[]- FUJ_ CFPTLRE8 ROCKET (IH=15

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STRR<ESIZE. [Z of Hull HoximumDiometer]

Payload v_. Strake Size for the Ba_;eline Vq:hicle

28-53

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Effect of+/- 10% [so Variation on Payload fQr the Baseline Vehicle

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1995 TFU I_YI.0FD ve. PERCENT C_ IN (RIB500K VEHICLE - riO - 50Z _ - VTOHL

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Payload vs. % Change in Drag Estimates for the Baseline Vehicle

28-54

E_ vs. CRUISE MFICHNUMBER - 5001<V_ICLEFLLL CFPTIJRE8 _ # M=I5 - ZBZ STI_KES - VTO

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RFIt,b-'Evs. O:BJI_ MQCH _ - 5001<VEHICLEFULL CFPTLRE 8 ROCKET | M-15 - _Z STR_,'ES - v'ro

1995 TQI]- (WITHOUT ORBITQL LDX)

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Comparison to a common set of orbitaltransportation system requirements is

required using a common set ofanalysis tools and methodologies.


Rocket Ejector Based IInitial Accelerator ITurbo BasedInitial Accelerator


Rocket Ejector Based]Initial Accelerator

Rocket Ejector Based IInitial Accelerator


I Rocket Ejecti0r Basedll

All-Rocket

Multi-Stage

All-Rocket !Single Stage

Non-Axisymmetdc

Multi-Cycle

Multi-Stage

Multi-Cycle

Single Stage

Axisymmetric

Multi-CycleMulti-Stage

Multi-Cycle ISingle Stage

Non-Axisymmetric


Combined Cycle _

Sin_lle Sta_e

,_,_:-:;Ax!sym met n__.i_

Combined Cycle

+ Rocket Multi-Stage.

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Winner ?Winners ?

i_i_i:ii:i_::::_ii:iii:i:i_i_i ThisStudy

28-58

REFERENCES

CURRENT REFERENCES

PcmeL ILW., Escl_r, WJ.D., and Robinson, J.W., Air Ant, mented Rocket Provulsion Corn:ever. FinalRepo_ USAF Asu_naufics Laboratory Report AFAL-TR-88-004, April 1988

Foster, R.W., Escher, WJ.D., and Robinson, I.R., SPldi_+s of an Extensively Axkwnmelric Rocket BasedCombined Cycle (RBCC) __nalne Powered SSTO Vehicle. AIAA Paper 89-2294,A/AA/ASME,_AJ_ASEE 25111Joint Propulsion Conference, Monte.tey, CA, July 1989

r.oa., R.w., of me i.. Pock. Sued CombinedEn_ne Powered SSTO Vehicle. AIAA Paper 89-2295, AIAA/ASME/SAE/ASEE 25th Joint _ --4r--

Coherence. Monterey, CA, July 1989

AFAL STUDY REFERENCES

Dixon, S.C., lq_,SA R&T for Aerommce Plane Vehicles. Langley Research Center, NASA Technical

Memorandum 86429, May 1985.

Esther, WJ.D., and Flomes, B. J., et el, A Study of Comoosite Proeulsion Svslems for Advanced I..mnch

Vehicle Am>licafions, Final Report on NASA Contract NAS7-3TI, The Manluardt Corporation, Van Nuys,

CA, April 1967

Anon, Pre-m'ovosal Contractor Briefin2 package. ,t1_q. System Contract #ID4701-87-C-0101.

USAF/AFSC, HQ Space Division, Los Angeles, CA, $ May 1987

Simonson, A.J. and Schmeer, J.W., S_tic Thnzst Augmentation of a Rocket Eiector System with a Heated

Sueentonic Primary Jet. Langley Research Center, NASA TND-1261, May 1962

Mossman, E.A., Rozycki, R.C., and Holle, G.F., A Summary of R__e_.__rchon s Nozzle-Electro" Svsmrn.Martin Denver Research Report R-60-31, October 1960

Torten, J.K., Final Summary Technical Reuort on the t_lendar Year 1963 Advanced Ramjet Techndo_v

I_izgzlI/II, The Marquardt Company Final Technical Repo_ under the Aeropropulsion Laboratory Contract

AF 33(657)12146

Congelliere, J., Prevatte, N. and Lime, J., Advam'___ Ramjets Conceots. Vol U Eiector ScramietThe Marquardt Corporation, Report No. AFAPL-TR-67-118, May, 1968

Anon., HvversonicResearch Engine Proiect O_ba_ 113.End Oral Review Technical Presentation.Gmett

AiResearch Report No. 75-1/338, NASA Contract NASI-6666, 23 March 1975

Anon., Final Revort - Hvdro,zen Turbofan Study. Garrett AiResearch Coq_ration for the LockheedCalifornia Co. under NASA Langley Research Cente_ Conlract NAS-1-14614, NASA CR-145369, Vol. I,

pp. 32-95July 1978

Kumar, A., and Anderson, G. Y., _tudv of Hvversonic Inlet Flow Fields with a Three.Dimensional Navier-

Stokes Code". AIAA Paper AIAA-86-1426, June 1986

Anon, YF-12 Exv¢fiments Svmvosium, NASA Conference Publication 2054, Dryden Research C.onter,

September 1978

28-59

"Puono,J.W., SERJ Fan Inmmmdon Study.FinalRencmuThe Marqum_ Coqxmuion,ReportNo. 2.5279,AD500754,February1969

Hosack, O. A. and Stroms_ R. R., Performance of the Aembell Kxtmdlble Nozzle, A[_$_raft, Vol. 6,No. 12,pp 1416-1423,December 1969

CougeUiere, J., et al, 196S Advanced Rainier Conceots Proaram Final Reoort Vol. HI - ElectorSCRAM/ET Analysis. The Marquardt _ AFAPL,.TR-66-49, August 1966

Com_ell/ere,J.,Prevatte,N. and Lime, J.,Advanced RamjetsCcmemms. Vol 11 ElectorScramim

Tbe lvlalquardt C_tio_, Report 1_. AFAI_TR-67-118, l_y 1968

Flomes, B. J., and Davids_, O. R., Advmw,ed Rmn_ Comma. Vol VIll. IhnLACE/SCRAMLA(_

PmvuLqlon Svszms Analysis and Desian, Technical Re.p_ AFAPL-TR-67-1f_, Vol. VII, The MunlusrdtCorporation, Van Nuys, CA, February 1968

Stall, F. D., Useful Scram_ Curves. a technical graph p,¢ka_ obtained hum the author, WPAPL, October1984

Anon, Alternate VehicleJProoulsion Study, Boeing kfilitsry Aisplane Compmy and Rockwell IntemafiomdSpace Transportation Systems Division presentation psclU_, Jua 1985

Billig, F. S., and Beach, L. D., H_vpcr_ic Pro__Iskm. AIAA Sponsored Short Course Notes, Huntsville,AL, June 1985

Escher, W. J. D., and Doughty, D. L., Assessment of (3rvofenic Hvdroeen-lnduced Air LiouefactionFinal Repon to Science Applications Intmmioml C.mlx_fion under Subconmct No." 1_

860020-82, Se4)t_mber 1986

Smith, L.R., Summary of Ae_,smce Pm_'am for 1963. The Maxqum_ 1963 Annual Project Report underUSA/: Contract AF33(657)10796, Report No. APL-TDR-64-32, Janemy 1964

McCan_, R.D., Hold, J. and Roder, 14. M., Selected Pxooerties of H_ _Emdneerina Dedcn DataLNational Bureau of Standards Monograph, National Engineering Labora_o ]Booklet, CO, USGPO 1981

Watson, K. A, DOF36 Pint,ram Users Guide, Air Force Wright Aeronautical Laboratories, Dayum, OH,April 1986

Watson, K. A., Analysis Develovment - 6-DOF Traiect0rv Simulsdon, Air Force Wright AeronauticalLaboratory, Dayton, OH, 1986

/

Freeman, Delma A., Advanced Since Transportation $1udies Peer Review. NASA LaRC, 28 July 1987

Hoerner, SighaxdF., Fluid Dynamic Dra_, Hoemer Fluid DyMmics, Brick Town, NJ., 1975

Polhamus, Edward C., Predictions of Vortex-Lift (_nc_.stics by a Lending Edge Suction Analogy,April 1971, Vol 8, No. 4, pp 193-199

Berdn, John J. and Smith, Michael L, Aerodynamics for Endnenen, Prentice Hall, Englewood Cliffs, NJ.,1979

Lindenbaum, B.,V/STOL Concepts and Develoved Aircraft F'mal Report,AFWAL-TR-86-3071, AirForce Wright Aeronautical Laboratories, November 1986

28-60

Anon, St_cial Short Course in VJSTOL AircrafL AGARD Report AGARD-R-710, Noc,h Atlantic TreatyOrlpmization Advisory Group for Aerospace Research and Development, May 1984

28-61

ra'm Aopa_,mREPORT DOCUMENTATION PAGE ouB so.0zo,-o;_gn4_ nmw_imOlu_o,nloths mOOo_ o#_o_ m enmmmo_ m mwaOo I mum"pot mepomo. InclJdmN)Ibmm _ _ _ _ _ _ _.0alheem0_ m_Mewnang_, tunanm0e¢l,w_e cmmpaebe_)_ nwwM_,0 _ oolloclmona#mknMmcm Ikmd _ nmgm_nl)_ Ixardm*mmmm _ my olhi'ml=,Ct_ _m_cuon _ mlomumon._dmg s_lgemmm kx md_ong eus b_O*n. _ Wom_ng_n _ Se_iO_. Dm_omm lot _omnaon Ol_mmw a_l Rel_m. 121S J_lomon_Hql_,wsy. S_mm 1204.Aa_mgmn.VA z220_a_0:.)._mm, Oq_dmm0mw_,_lk_m.l_p,mu_RemmmPmi_(0704mm).w_ _ e06m

1. AGENCY USE ONLY (Leave _nk) i 2. REPORT DATE

I 1992

4. TTTLE AND SUBTITLE

Rocket-Based Combined-Cycle (RBCC) Propulsion

Technology WorkshopTutorial Session

L AUTHOr(S)

7. PF.qFORMING OR(_IIZ_TION IMAliE(S) _ ADOR_)

National Aeronautics and Space AdministrationLewis Research Center

Cleveland, Ohio 44135 - 3191

9. SPONSORiNG/MONITORINGAGENCYNAMES(S)ANDADDRESS(F.S)

National Aeronautics and Space Administration

Washington, D.C. 20546-0001

3. REPORT TYPE AND DATES COVEREDConferonce Publication

WU-$90-21-I1

it. _ ORGANIZATIONREPORT _

E-6929

10. SPONSOR II/GNONITORINGAGENCY REPORT NUMBER

NASA CP- 10090

11. SUPm.eMENT_qYNOTI[S

Responsible person, William Escher, (202)453-2858.

128. DISTFIIBUTIOIq/AVAiUABILITYSTATEMENT

Unclassified - Unlimited

Subject Categories 15, D6, and 20

12b. DISTRiUTtON CODE

13. ABSTRACT(Maxlmum 200 words)

A Rocket-Based Combined-Cycle Propulsion Workshop is held at the University of Alabama in Huntsville under

NASA Headquarters sponsorship. The goal of this workshop is to illuminate the Nation's space transportation and

propulsion engineering community on the potential of hypersonic combined-cycle (airbreathing/rocket) propulsionsystems for future space transportation applications. Appropriate background is provided at the workshop to"

participants and documented in this advanced conference proceedings. "l]ncWorkshop's deliberative findings will he

documented in subsequent proceedings.

14. SUBJECTTERMS

Rocket engine; Combined cycle; Propulsion; Transportation; Space

17. SECURITY CLASSIFICATIONOF REPORT

Unclassified

lB. SECURITY CLASSIFICATION I 19.OF THIS PAGE

Unclassified

NSN 7540-01-280-5500

SECURITY CLASSIFiCATiONOF ABSTRACT

Unclassified

15. NUMBER OF PAGES

28316. PRICE COOE

AI3

20. LIMiTATiON OF ABSTRACT

Standard Form 298 (Rev. 2-89)

Prescribed by ANSI 81KL_-111298-1o2

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