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A new generation of high performance engines for spacecraft propulsionExperimental data validating advanced engine designs at three thrust levels (5, 15, and 100 lbF) is presented. All of the three engine designs considered employ a Moog bipropellant torque motor valve, platelet injector design, and iridium-lined rhenium combustion chamber. Attention is focused on the performance, robustness, duration, and flexibility characteristics of the engines. It is noted that the 5- and 15-lbF thrust engines can deliver a steady state specific impulse in excess of 310 lbF-sec/lbm at an area ratio of 150:1, while the 150-lbF thrust engines deliver a steady state specific impulse of 320 lbF-sec/lbm at an area ratio of 250:1. The hot-fire test results reveal specific impulse improvements of 15 to 25 sec over conventional fuel film cooled columbium chamber designs while operating at maximum chamber temperatures.
Document ID
19910057063
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Rosenberg, Sanders D.
(Aerojet-General Corp. Sacramento, CA, United States)
Schoenman, Leonard
(Aerojet, Propulsion Div., Sacramento CA, United States)
Date Acquired
August 15, 2013
Publication Date
June 1, 1991
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
AIAA PAPER 91-2039
Accession Number
91A41686
Funding Number(s)
CONTRACT_GRANT: NAS3-25646
CONTRACT_GRANT: NAS3-24643
Distribution Limits
Public
Copyright
Other

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