This page no longer updated from 31 October 2001. Latest version can be found at MR-111

Designer: Rocket Research. Application: Attitude control, Intelsat 5, ERBS, ACTS, Radarsat, MMAS 4000, 5000, and. 7000, Wind/Polar Landsat, and Mars Observer. Propellants: Hydrazine Thrust(vac): 0 kgf. Isp: 229 sec. Burn time: 54,000 sec. Mass Engine: 0 kg. Diameter: 0.4 m. Length: 0.2 m. Chambers: 1. Chamber Pressure: 13.90 bar. Area Ratio: 200.00. Country: USA. Status: In Production.

First Flown: Intelsat 5 (December 1980). Flown: 348 (499 produced) planned to end-1995. Dry Mass: 345 gm. Length: 16.7 cm. Max Diameter: 35.6 cm. Mounting Method: bolted three places. Propellant: hydrazine at 0.19-2.4 gm/sec (Shell 405 catalytic decomposition). Feed Method: GN2 or He at 4.08-27.2 atm through Wright Components 9 W dual seat. solenoid valve. Thrust: 0.44-5.34 N (2.2-4.4 nominal). Isp: 213-229 sec vacuum. Time to Full (millisec). 150 to 90% PC. Expansion Ratio: 200:1. Nozzle Length: 2.18 cm. Nozzle Cooling Method: radiative. Combustion Chamber Pressure: 3.1-13.9 atm. Combustion Chamber Temperature: 800 Celsius. Combustion Chamber Cooling Method: radiative. Duty Cycle: 0.020 sec minimum to 15 hr maximum. 420,000 pulses. Itotal: 260.21 kNs.

Back to Index
Last update 12 March 2001.
Definitions of Technical Terms.
Contact Mark Wade with any corrections or comments.
Conditions for use of drawings, pictures, or other materials from this site..
© Mark Wade, 2001 .