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astronautix.com MR-50


Designer: Rocket Research. Application: Attitude control for SMS, Viking, Metosat, GOES, Voyager, GPS, Intelsat 5,. Scatha, MMAS 5000, Delta Star, Magellan, Wind/Polar. Used on spacecraft: SMS, Viking, Metosat, GOES, Voyager, GPS, Intelsat 5, . Scatha, MMAS 5000, Delta Star, Magellan, Wind/Pola. Propellants: Hydrazine Thrust(vac): 2 kgf. Thrust(vac): 0.02 kN. Isp: 228 sec. Mass Engine: 1 kg. Diameter: 0.1 m. Length: 0.2 m. Chambers: 1. Chamber Pressure: 11.30 bar. Area Ratio: 40.00. Country: USA. Status: In Production.

First Flown: SMS metsat (May 1974). Flown: 680 (744 produced) planned to end-1994. Dry Mass(gm): 680. Length(cm): 18.3. Max Diameter(cm): 6.6. Mounting Method: bolted three places. Propellant: hydrazine at 4.67 - 17.33 gm/sec (Shell 405 catalytic decomposition). Feed Method: G-dinitrogen or Ghe at 4.8 - 32.7 atm, through 29 W solenoid dual seat valve. Thrust: 9.79 - 38.7 N (22.2 nominal). Isp: 215 - 228 sec vacuum. Time to Full Thrust (millisec): 150 to 90% PC: . Nozzle Area Ratio: 40:1. Nozzle Length: 3.95 cm. Nozzle Cooling Method: radiative. Combustion Chamber Pressure: 2.9 - 11.3 atm. Combustion Chamber Temp.: 800 Celsius. Combustion Chamber Cooling Method: radiative. Duty Cycle(sec): 0.020 min to 5400 max. 471,000 pulses. It: 459.4 kNs.


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Last update 12 March 2001.
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