Engine Model: 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. Propellants: Hydrazine. Thrust(vac): 1.12 N (0.25 lbf). Isp: 227 sec. Mass Engine: 0.33 kg (0.73 lb). Diameter: 0.0343 m (0.1125 ft). Length: 0.15 m (0.48 ft). Chambers: 1. Chamber Pressure: 23.90 bar. Area Ratio: 100.00. Thrust to Weight Ratio: 0.34. Country: USA. Status: In Production. First Flight: 1974. Last Flight: 1997. 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.
