MR-111

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MR-111

Part of MR-100 engine series

MR-111E
Credit: Aerojet Redmond

Redmond hydrazine monopropellant rocket engine. Attitude control, Intelsat 5, ERBS, ACTS, Radarsat, MMAS 4000, 5000, and. 7000, Wind/Polar Landsat, and Mars Observer. In Production. First flight 1980.

Status: In Production. Thrust: 4.41 N (0.99 lbf). Unfuelled mass: 0.35 kg (0.76 lb). Specific impulse: 229 s. Burn time: 54,000 s. Height: 0.17 m (0.55 ft). Diameter: 0.36 m (1.17 ft).

First Flown: Intelsat 5 (December 1980). Flown: 348 (499 produced) planned to end-1995. Dry Mass: 345 gm. Length: 16.7 cm. Max Diameter: 35.6 cm. Mounting Method: bolted three places. Propellant: hydrazine at 0.19-2.4 gm/sec (Shell 405 catalytic decomposition). Feed Method: GN2 or He at 4.08-27.2 atm through Wright Components 9 W dual seat. solenoid valve. Thrust: 0.44-5.34 N (2.2-4.4 nominal). Isp: 213-229 sec vacuum. Time to Full (millisec). 150 to 90% PC. Expansion Ratio: 200:1. Nozzle Length: 2.18 cm. Nozzle Cooling Method: radiative. Combustion Chamber Pressure: 3.1-13.9 atm. Combustion Chamber Temperature: 800 Celsius. Combustion Chamber Cooling Method: radiative. Duty Cycle: 0.020 sec minimum to 15 hr maximum. 420,000 pulses. Itotal: 260.21 kNs.

Engine: 0.35 kg (0.76 lb). Chamber Pressure: 14.10 bar. Area Ratio: 200. Thrust to Weight Ratio: 1.3.

Family: Monopropellant. Country: USA. Agency: Redmond.

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MR-111C
Credit: Aerojet Redmond

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