This page no longer updated from 31 October 2001. Latest version can be found at MR-502 IMPEHT

Other Designations: Improved Electrothermal Hydrazine Thruster. Designer: Rocket Research. Application: Communications satellite N-S stationkeeping, MMAS 5000. Propellants: Hydrazine Thrust(vac): 0 kgf. Thrust(vac): 0.00 kN. Isp: 304 sec. Burn time: 7,200 sec. Mass Engine: 1 kg. Diameter: 0.1 m. Length: 0.2 m. Chambers: 1. Chamber Pressure: 6.50 bar. Area Ratio: 100.00. Country: USA. Status: In Production.

First Flown: Astra 1B (March 1991). Flown: 16 (32 produced) planned to end-1995. Dry Mass: 848 gm. Length: 19.4 cm. Max Diameter: 8.84 cm. Mounting Method: bolted four places. Propellant: hydrazine at 0.119-0.167 gm/sec over Shell 405 catalyst and 610-839.6. W electric heater. Feed Method: GN2 or Ghe at 21.8-23.8 atm through Wright Components 9 W dual seat. solenoid valve. Thrust: 0.36-0.50 N. Isp: 280-304 sec vacuum. Expansion Ratio: 100:1. Nozzle Length: 0.879 cm. Nozzle Cooling Method: radiative. Combustion Chamber Pressure: 3.4-6.5 atm. Combustion Chamber Temperature: 800 Celsius. Combustion Chamber Cooling Method: radiative. Duty Cycle: 300 sec minimum to 2 hr maximum. 430,000 pulses. Itotal: 525 kNs.

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Last update 12 March 2001.
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