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MRE-15/OMV
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Designer: TRW. Propellants: Hydrazine. Thrust(vac): 89 N (20 lbf). Isp: 225 sec. Burn time: 2,000 sec. Mass Engine: 1.13 kg (2.49 lb). Length: 0.27 m (0.88 ft). Chambers: 1. Chamber Pressure: 27.00 bar. Thrust to Weight Ratio: 7.96. 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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© Mark Wade, 1997 - 2007 except where otherwise noted.
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