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MR-50
MR-50S
MR-50S
Credit: Aerojet Redmond
Redmond hydrazine monopropellant rocket engine. Attitude control for SMS, Viking, Meteosat, GOES, Voyager, GPS, Intelsat 5,. Scatha, MMAS 5000, Delta Star, Magellan, Wind/Polar. In Production. First flight 1974.

Status: In Production. Thrust: 22 N (5 lbf). Unfuelled mass: 0.68 kg (1.49 lb). Specific impulse: 228 s. Height: 0.18 m (0.60 ft). Diameter: 0.0660 m (0.2160 ft).

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.

Engine: 0.68 kg (1.49 lb). Chamber Pressure: 11.40 bar. Area Ratio: 40. Thrust to Weight Ratio: 3.32.



Family: Monopropellant. Country: USA. Agency: Redmond.
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MR-50TMR-50T
Credit: Aerojet Redmond



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