Encyclopedia Astronautica
OMV Variable Thrust Engine

TRW N2O4/MMH rocket engine. 0.578 kN. 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.

Engine: 6.80 kg (14.90 lb). Chamber Pressure: 6.90 bar. Area Ratio: 125. Thrust to Weight Ratio: 8.52.

Status: In Production.
Unfuelled mass: 6.80 kg (14.90 lb).
Height: 0.70 m (2.30 ft).
Diameter: 2.71 m (8.90 ft).
Thrust: 578 N (129 lbf).
Burn time: 2,800 s.

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Associated Manufacturers and Agencies
  • TRW American manufacturer of rockets, spacecraft, and rocket engines. TRW Corporation, Redondo Beach, CA, USA. More...

Associated Propellants
  • N2O4/MMH Nitrogen tetroxide became the storable liquid propellant of choice from the late 1950's. Monomethylhydrazine (CH3NHNH2) is a storable liquid fuel that found favour in the United States for use in orbital spacecraft engines. Its advantages in comparison to UDMH are higher density and slightly higher performance. More...

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