This page no longer updated from 31 October 2001. Latest version can be found at MR-104

Designer: Rocket Research. Application: Attitude control and velocity corrections, Voyager, Magellan, DMSP, Tiros N, Landsat. Used on spacecraft: Voyager, Magellan, DMSP Block 4A, Tiros N, Landsat 1, 2, 3. Propellants: Hydrazine Thrust(vac): 45 kgf. Isp: 239 sec. Mass Engine: 2 kg. Diameter: 0.2 m. Length: 0.5 m. Chambers: 1. Chamber Pressure: 19.00 bar. Area Ratio: 53.00. Country: USA. Status: In Production.

First Flown: Voyager (August 1977). Flown: 48 (97 produced) planned to end-1995. Dry Mass: 1860 gm. Length: 46.0 cm. Max Diameter: 15.2 cm. Mounting Method: bolted three places. Propellant: hydrazine at 91-290 gm/sec (Shell 405/LCH-202 catalytic decomposition). Feed Method: GN2 or GHe at 6.8-28.6 atm through Wright Components 30 W single seat solenoid valve. Thrust: 205-572 N (445 nominal). Isp: 228-239 sec vacuum. Time to Full Thrust (millisec): 50 to 90% PC. Expansion Ratio: 53:1 (diameter 15.2 cm). Nozzle Length: 17.8 cm. Nozzle Cooling Method: radiative. Combustion Chamber Pressure: 3.8-19.0 atm. Combustion Chamber Temperature: 800 Celsius. Combustion Chamber Cooling Method: radiative. Duty Cycle: 0.022-2000 sec single firing. 2654 cumulative. 1742 pulses. Itotal: 693.9 kNs.

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Last update 12 March 2001.
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