Liquid propulsion design options for orbital transfer vehicles (OTV) were analyzed for various upper stage applications. High and low pressure earth storable propellant system technology and high performance, low thrust cryogenic concepts were investigated for payload stages of 39000 lbm to 57300 lbm low earth orbit (LEO) class launch vehicles. The design criteria was baselined for a specific impulse of 340 seconds and mass fraction of 0.90 with LEO altitude of 110 nm. Performance results were computed for a range of mass fraction between 0.88 and 0.92 and ISP between 320 and 500 sec.
Liquid propulsion technology for expendable and STS launch vehicle transfer stages
Fluessigtreibstofftechnologie fuer nicht wiederverwendbare und Raumfaehrenstartstufen
AIAA-Papers ; Jul ; 1-5
1987
5 Seiten, 10 Bilder
Conference paper
English
Expendable Launch Vehicle Propulsion
NTIS | 1991
|Expendable launch vehicle propulsion
NTRS | 1991
|Propulsion technology for modular expendable launch vehicles
Tema Archive | 1987
|