8/11/2019 NASA - Evaluation of Innovative Rocket Engines for Single Stage Earth-To-Orbit Vehicles

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AIAA=88=2819

Evaluation of Innovative

Rocket Engines

fo r

Single Stage Earth-to=Orbit Vehicles

De

ef

Mans

ki

DFVLR Lampoldhausen

Federal

Republic

of Germany

and

James A.

Martin

NASA

Langley Research Center

Hampton,

VA

AlAAlSAElASMElASEE 24th Joint

Propulsion Conference

July

11-1

3, 1988/Boston, Massachusetts

For

permission o copy

or

republ ish, contact the American Institu te

of

Aeronautics and Astronautics

370 L Enfant Promenade, S.W., Washington, D.C. 20024

8/11/2019 NASA - Evaluation of Innovative Rocket Engines for Single Stage Earth-To-Orbit Vehicles

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EVALUATI ON OF I NNOVATI VE ROCKET ENGI NES FOR SI NGLE- STAGE

EARTH- TO- ORBI T VEHI CLES

Detl ef Manski *

DFVLR Ger man Aerospace Resear ch Est abl i shment

D 71 1

Lampol dshausen, Feder al Republ i c of Germany

J ames

A .

Mart i n**

NASA Langl ey Resear ch Cent er

Mai l Stop

365.

Hampt on, VA

23665

ABSTRACT

Comput er model s Of r ocket engi nes and si ngl e-

Stage- t o- orbi t vehi cl es t hat were devel oped by t he

aut hor s at DFVLR and NASA have been combi ned. The

r esul t i ng code consi st s of engi ne mass. perf or-

mance, t r aj ector y and vehi cl e Si zi ng model s. The

engi ne mass model i ncl udes equat i ons f or each

subsyst emand descr i bes thei r dependences on

var i ous propul si on parameters. The engi ne per f or-

mance model Consi st s of mul t i di mensi onal set s of

t heoret i cal pr opul si on propert i es and a compl et e

t her modynam c anal ysi s of t he engi ne cycl e. The

vehi cl e anal yses i ncl ude

an

opt i m zed t raj ectory

anal ysi s. mas8 est i mati on, and vehi cl e si zi ng.

A ver t i cal - takeof f , hor i zonta l - l andi ng,

si ngl e- st age, wi nged, manned, f ul l y r eusabl e

vehi cl e w t h a payl oad capabi l i t y of 13.6 Mg

30, 000

b)

to l ow Eart h or bi t was sel ected.

Hydr ogen. met hane, propane, and dual - f uel engi nes

were st udi ed w t h st aged- combust i cn. gas-

generat or, dual bel l , and t he dual - expander

cycl es. M xture rat i o, chamber pr essure, nozzl e

Oxi t pr essur e, l i f t of f accel erati on, and dual f uel

- pr opul si ve parameter s wer e opt i m zed.

I NTHCDUCf ' I ON

Over t he past sever al year s. model s have been

devel oped

and

appl i ed at t he DFVLR I nst i t ute of

Chem cal Pr opul si on t o compar e the perf ormance of

expendabl e l aunch vehi cl es w t h var i ous rocket

engi nes. The emphasi s of t hi s work was on t he

cal cul at i on of engi ne perf ormance and

mass.

Dur i ng thi s same t i me. model s w e r e bei ng devel oped

at t he NASl i Langl ey Resear ch Cent er t o eval uat e

t he ef ' f ecti veness of var i ous Pocket engi nes on

reusable Eart h- t o- orb i t vehi c l es, w th the engi ne

dat a pr ovi ded by engi ne manuf act ur i ng compani es.

Duri ng t he past 1- year peri od, t he aut hor s have

been

worki ng t oget her at t he NASA Langl ey Resear ch

Cent eP to combi ne t he capabi l i t i es f r om t he two

nati onal space organi zati ons.

Thi s Combi ned ef f or t has provi ded a

capabi l i t y t o Opti m ze the Pocket engl nc and

vehi cl e i nt eracti on i n

a

way t hat has not pr e-

vi ousl y been pos9i hl e. w t h the capabi l i t y to

eval uat e t he ef f ects of numerous pwamet er s on t he

vehi c l e desi gn. Wt hi n the exi st i ng l i m t at i ons of

t i me and r esour ccs, Opt i m zat i on of onl y t he most

i mpor t ant par amet ers

was

att empt ed i n t hi s i nves-

t i gat i on. Tni s paper descr i bes the j oi nt ef f ort ,

t he met hods and capabi l i t i es

of

t he programs

devel oped. and the r esul t s of t he anal yses. The

r esul t s al l ow a compar i son of numer ous engi ne

concept s w th a consi st ent anal ysi s.

*Aerospace Engi neer , I nst i t ut e for Chemcal

Pr opu1si on. Member , AI AA.

**Aer ospace Engi neer, Space Syst ems Di vi si on.

Associ ate Fel l ow, AI AA.

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