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MRE-5/Compton Observatory
Part of MRE engine series Family
TRW N2O4/MMH rocket engine. In Production. Mono-propellant Hydrazine Thrusters. First flight 1991.

Status: In Production. Thrust: 25 N (6 lbf). Unfuelled mass: 1.13 kg (2.49 lb). Specific impulse: 240 s.

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.

Engine: 1.13 kg (2.49 lb). Chamber Pressure: 32.00 bar. Thrust to Weight Ratio: 2.21.



Family: Storable liquid. Country: USA. Propellants: N2O4/MMH. Agency: TRW.

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