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astronautix.com MR-106


Designer: Rocket Research. Application: Spacecraft and upper stage attitude control and velocity corrections, PAM A/S,. Radarsat, GPS Block 2R, HAS/Peace Courage, Titan Centaur, Atlas Centaur. Used on stages: PAM-S, Centaur D/E. Used on spacecraft: GPS Block 2 and 2A, Radarsat. Propellants: Hydrazine Thrust(vac): 3 kgf. Thrust(vac): 0.03 kN. Isp: 232 sec. Mass Engine: 0 kg. Diameter: 0.1 m. Length: 0.2 m. Chambers: 1. Chamber Pressure: 10.80 bar. Area Ratio: 61.00. Country: USA. Status: In Production.

First Flown: HAS/Peace Courage. Flown: 204 (2359 produced) planned to end-1997. Dry Mass: 476 gm. Length: 17.8 cm. Max Diameter: 6.4 cm. Mounting Method: bolted three places. Propellant: hydrazine at 4.08-11.79 gm/sec (LCH 227/202 catalytic decomposition). Feed Method: GN2 or Ghe at 6.8-30.6 atm through Wright Components 27 W solenoid valve. Thrust: 8.9-26.7 N (26.7 nominal). Isp: 218-232 sec vacuum. Time to Full Thrust (millisec): 200 to 90% PC. Expansion Ratio: 61:1. Nozzle Length: 4.72 cm. Nozzle Cooling Method: radiative. Combustion Chamber Pressure: 6.12-10.8. Combustion Chamber Temperature: 800 Celsius. Combustion Chamber Cooling Method: radiative. Duty Cycle: 0.016 sec minimum to 2000 maximum. 12,397 pulses. Itotal: 167 kNs.


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Last update 12 March 2001.
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