The objective of this program was to establish a technical data base to support future development of GO2/GH2 flight thrusters for a Space Station Auxiliary Propulsion System. Specific issues of concern were thruster performance and cycle life. To address these issues, NASA funded Aerojet to design, fabricate and altitude test two 25-lbf GO2.GH2 thrusters. The first thruster was designed to operate at a nominal mixture ratio (O/F) of 4.0 and expansion area ratio of 100:1. It was tested over a range of O/F from 2.0 to 8.0, achieving a range of specific impulse (Isp) from 440 to 310 lbf-sec/lbm. The second thruster was optimized for a nominal O/F of 8.0 at a lower nozzle expansion area ratio of 30:1. This second thruster was tested over an O/F range of 3.0 to 9.5, achieving an Isp range of 416 to 3323 lbf-sec/lbm, respectively. At O/F = 8.0, the Isp was 360 lbf-sec/lbm, as predicted.
Space Station Auxiliary Thrust Chamber Technology
1990
197 pages
Report
No indication
English
Manned Spacecraft , Rocket Engines & Motors , Thrusters , Data bases , Expansion , Life cycles , Mixtures , Performance(Engineering) , Ratios , Specific impulse , Space stations , Rocket propulsion , Auxiliary , Regeneration(Engineering) , Nozzle area ratio , Oxygen , Hydrogen , Reactive gases , Thrust chambers
Space station auxiliary thrust chamber technology
NTRS | 1987
|Space Station auxiliary thrust chamber technology
NTRS | 1990
|Space Station Auxiliary Thrust Chamber Technology
NTIS | 1987
|Advanced Rocket Thrust Chamber Technology
NTIS | 1970
|