| MR-111 | ||
Designer: Rocket Research. Application: Attitude control, Intelsat 5, ERBS, ACTS, Radarsat, MMAS 4000, 5000, and. 7000, Wind/Polar Landsat, and Mars Observer. Propellants: Hydrazine. Thrust(vac): 4.41 N (0.99 lbf). Isp: 229 sec. Burn time: 54,000 sec. Mass Engine: 0.35 kg (0.76 lb). Diameter: 0.36 m (1.17 ft). Length: 0.17 m (0.55 ft). Chambers: 1. Chamber Pressure: 14.10 bar. Area Ratio: 200.00. Thrust to Weight Ratio: 1.30. Country: USA. Status: In Production. First Flight: 1980. Last Flight: 1995. 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.
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