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MRE-5/Compton Observatory
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Designer: TRW. Propellants: N2O4/MMH. Thrust(vac): 25 N (6 lbf). Isp: 240 sec. Mass Engine: 1.13 kg (2.49 lb). Chambers: 1. Chamber Pressure: 32.00 bar. Thrust to Weight Ratio: 2.21. Country: USA. Status: In Production. First Flight: 1991. Mono-propellant Hydrazine Thrusters. Applications: missions requiring duty cycle flexibility. First Flight: 1991. Number Produced: 22. Mass: 1.13 kg. Length: 21 cm. Engine Cycle: decomposition of hydrazine over heated shell catalyst. Thrust: 12-24.5 N in vacuum. Isp: 232-240 sec in vacuum at steady state conditions. Inlet Pressure: 6.8-31.6 atm. Burn Time: 0.050 sec up to several hours. Minimum Firing Bit: 0.025 sec. Total Cycles: 50,000. Random Vibration: 21 g rms.
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© Mark Wade, 1997 - 2007 except where otherwise noted.
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