A space simulation procedure was developed for studying rocket plume contamination effects using a 5-lb bipropellant reaction control system thrustor. Vacuum chamber pressures of 0.00003 torr (70 miles altitude) were achieved with the thrustor firing in pulse trains consisting of eight pulses - 50 msec on, 100 msec off, and seven minutes between pulse trains. The final vacuum was achieved by cooling all vacuum chamber surfaces to liquid-helium temperature and by introducing a continuous argon leak of 48 std. cc/sec into the test chamber. Fast time response liquid flow rate measurements showed that large variations occurred in the ratio of oxidizer to fuel flow for pulse-on times up to 120 msec. These variations could lead to poor combustion efficiency and the production of contamination.
Space simulation experiments on reaction control system thruster plumes.
Joint Propulsion Specialist Conference ; 1972 ; New Orleans, LA, US
1972-11-01
Conference paper
No indication
English
Visible Spectra of Thruster Plumes from the Space Shuttle Primary Reaction Control System
Online Contents | 1993
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