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Designer: TRW. Propellants: MON/Hydrazine Thrust(vac): 46 kgf. Thrust(vac): 0.45 kN. Isp: 315 sec. Burn time: 3,600 sec. Mass Engine: 5 kg. Diameter: 0.3 m. Length: 0.6 m. Chambers: 1. Chamber Pressure: 7.00 bar. Area Ratio: 204.00. Country: USA. Status: In Production.
First Flight: April 1991. Mounting: fixed. Engine Cycle: pressure-fed at 15 atm. Oxidizer: MON 3-flow rate at 0.076 kg/sec. Fuel: high purity hydrazine-flow rate at 0.071 kg/sec. O/F Ratio: 1.070:1. Cooling Method: radiation. Ignition: hypergolic with initiation at 28 V electrical to an on/off bi-propellant torque motor valve. Burn Time: 24,000 sec total, with a 3600 sec maximum single burn.
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Last update 12 March 2001.
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© Mark Wade, 2001 .