This page no longer updated from 31 October 2001. Latest version can be found at www.astronautix.com
astronautix.com OMV Variable Thrust Engine
Designer: TRW. Propellants: N2O4/MMH Thrust(vac): 58 kgf. Thrust(vac): 0.58 kN. Burn time: 2,800 sec. Mass Engine: 7 kg. Diameter: 2.7 m. Length: 0.7 m. Chambers: 1. Chamber Pressure: 6.80 bar. Area Ratio: 125.00. Country: USA. Status: In Production.

Dry Mass: 6.8 kg. Length: 70.05 cm. Maximum Diameter: 27.13 cm. Mounting: fixed. Engine Cycle: pressure fed. Oxidizer: di-nitrogen tetraoxide at 0.119 kg/sec during maximum Thrust: . Fuel: MMH at 0.0745 kg/sec during maximum Thrust. O/F Ratio 1.64. Thrust: 57.8-578 N in vacuum, with a throttle range ratio of 10:1. Isp: 280-308 sec in vacuum. Expansion Ratio: 125:1. Cooling Method: radiative cooling. Chamber Pressure: 0.75-6.8 atm. Ignition: hypergolic. Burn Time: 28 hours total with a 2800 sec maximum single burn.

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Last update 12 March 2001.
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