Engine cycle analyses conducted on a 3000-lbf component testing model of an H2/O2-fueled advanced orbit-transfer vehicle engine employing a dual-expander cycle have yielded pressure and temperature trend predictions. On the basis of the results obtained, the dual-expander cycle is projected to be scalable to thrust levels of as much as 50,000 lbf, with chamber pressures of 2000 psi. The high chamber pressure, in conjunction with the use of a gas-gas injector element, facilitates 10:1-range continuously variable throttling. The preferred thrust level for supporting mission studies would be of the order of 20,000 lbf.
Advanced H2/O2 space engine parametrics
01.07.1989
Aufsatz (Konferenz)
Keine Angabe
Englisch
Advanced H2/O2 space engine parametrics
AIAA | 1989
|Kraftfahrwesen | 1992
|Practical parametrics of aerospace pricing
AIAA | 1976
|Maglev Cost and Performance Parametrics
British Library Conference Proceedings | 1993
|Parametrics of Nickel-hydrogen Cell Design
AIAA | 1987
|