Advanced H2/O2 space engine parametricsEngine 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.
Document ID
19890059484
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Schneider, J. A. (Aerojet TechSystems Co. Sacramento, CA, United States)