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astronautix.com MR-103
Designer: Rocket Research. Application: Attitude control thruster for Voyager, GPS, Intelsat 5, MMAS 3000, 4000,. 5000, and 7000, Mars Observer, ACTS, and Magellan. Used on spacecraft: Voyager, GPS, Intelsat 5, AS 3000, 4000, . 5000, and 7000, Mars Observer, ACTS, and Magellan. Propellants: Hydrazine Thrust(vac): 0 kgf. Thrust(vac): 0.00 kN. Isp: 227 sec. Mass Engine: 0 kg. Diameter: 0.0 m. Length: 0.1 m. Chambers: 1. Chamber Pressure: 23.90 bar. Area Ratio: 100.00. Country: USA. Status: In Production.

First Flown: ATS 6 commssat( May 1974 ). Flown: 1014 (1744 produced) planned to end-1997. Dry Mass: 332 gm. Length: 14.7 cm. Max Diameter: 3.43 cm. Mounting Method: bolted three places. Propellant: hydrazine at 0.091-0.499 gm/sec (Shell 405 catalytic decomposition). Feed Method: GN2 at 4.8-28.6 atm through 9 W solenoid dual seat valve. Thrust: 0.19-1.12 (0.89 nominal). Isp: 206-227 sec vacuum. Time to Full Thrust (millisec): 150 to 90%. Nozzle Area Ratio: 100:1. Nozzle Length: 0.98 cm. Nozzle Cooling Method: radiative. Combustion Chamber Pressure: 4.35-23.9 atm. Combustion Chamber Temperature: 800 Celsius. Combustion Chamber Cooling Method: radiative. Duty Cycle: 0.008 sec minimum to unlimited maximum burn. 750,000 pulses. Itotal: 158.46 kNs.

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Last update 12 March 2001.
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