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astronautix.com MRE-15/OMV


Designer: TRW. Propellants: Hydrazine Thrust(vac): 9 kgf. Thrust(vac): 0.09 kN. Isp: 225 sec. Burn time: 2,000 sec. Mass Engine: 1 kg. Length: 0.3 m. Chambers: 1. Country: USA. Status: In Production.

Mono-propellant Hydrazine Thrusters. Mass: 1.13 kg. Length: 26.9 cm. Engine Cycle: decomposition of hydrazine over heated shell catalyst. Thrust: 44.5-89 N in vacuum. Isp: 225 sec in vacuum at steady state conditions. Inlet Pressure: 12-27 atm. Burn Time: 0.020 sec. Total Cycles: 100,000.


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Last update 12 March 2001.
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