This page no longer updated from 31 October 2001. Latest version can be found at MR-107

Designer: Rocket Research. Application: Spacecraft and upper stage attitude control and (V corrections, Delta 2, Titan 2,. Commercial Titan, PAM D, Small ICBM, HAS/Peace Courage, Atlas roll control. module, STEP, Pegasus. Used on stages: Pegasus-4. Used on launch vehicles: Pegasus. Propellants: Hydrazine Thrust(vac): 26 kgf. Thrust(vac): 0.26 kN. Isp: 236 sec. Burn time: 1,200 sec. Mass Engine: 1 kg. Diameter: 0.1 m. Length: 2.2 m. Chambers: 1. Chamber Pressure: 21.00 bar. Country: USA. Status: In Production. First Flight: 1990. Last Flight: 1998. Flown: 30.

First Flown: HAS/Peace Courage. Flown: 321 (1871 produced) planned to end-1997. Dry Mass: 885 gm. Length: 21.8 cm. Max Diameter: 6.6 cm. Mounting Method: bolted in three places. Propellant: hydrazine at 24-113 gm/sec (LCH 207/LCH 202 catalytic decomposition). Feed Method: GN2 or Ghe at 6.8-34 atm through 50 W solenoid valve. Thrust: 51.2-257.9 N (178 nominal). Isp: 217-236 sec vacuum. Time to Full Thrust: (millisec). 200 to 90% PC. Expansion Ratio: 21:1. Nozzle Length: 4.72 cm. Nozzle Cooling Method: radiative. Combustion Chamber Pressure: 1.9-9.5 atm. Combustion Chamber Temperature: 800 Celsius. Combustion Chamber Cooling Method: radiative. Duty Cycle: 0.016 sec minimum to 2137 maximum. 7005 pulses. Itotal: 332.3 kNs.

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Last update 12 March 2001.
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© Mark Wade, 2001 .