This page no longer updated from 31 October 2001. Latest version can be found at www.astronautix.com
astronautix.com MRE-5/Compton Observatory
Designer: TRW. Propellants: N2O4/MMH Thrust(vac): 3 kgf. Thrust(vac): 0.02 kN. Isp: 240 sec. Mass Engine: 1 kg. Chambers: 1. Country: USA. Status: In Production.

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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Last update 12 March 2001.
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