The development of a reusable, attitude-control propulsion system for the space transportation system is discussed. A flight weight, gaseous oxygen attitude control thruster assembly was tested to obtain data on cyclic life, thermal and hydraulic characteristics, pulse response, and performance. The basic thruster components were tested in excess of 51,000 pulses and 660 seconds, steady state, with no degradation of the 93 percent characteristic exhaust velocity efficiency level. Nominal operating conditions were a chamber pressure of 207 N sq cm (300 psia), a mixture ratio of 4.0, a pulse width of 100 ms, and a pulse frequency of 2 Hz.
The 6670-Newton attitude-control thruster using hydrogen-oxygen propellant
1977-05-01
Report
No indication
English
lon-Thruster Propellant Utilization
AIAA | 1972
|Ion-thruster propellant utilization
TIBKAT | 1971
|Skylab thruster attitude control system
NTRS | 1974
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