This page no longer updated from 31 October 2001. Latest version can be found at MR-508 LPHA

Other Designations: Low Power Hydrazine Arcjet. Designer: Rocket Research. Application: Communications satellite N-S stationkeeping, MMAS 7000. Propellants: Hydrazine Thrust(vac): 0 kgf. Thrust(vac): 0.00 kN. Isp: 502 sec. Burn time: 234,000 sec. Mass Engine: 1 kg. Diameter: 0.1 m. Length: 0.2 m. Chambers: 1. Chamber Pressure: 4.70 bar. Area Ratio: 100.00. Country: USA. Status: In Production.

First Flight: Telstar 4 (December 1993). qualified autumn 1991. Flown: 6 (28 produced) planned to end-1995. Dry Mass: 1338 gm. Length: 24.4 cm. Max Diameter: 9.27 cm. Mounting Method: bolted four places. Propellant: hydrazine at 0.068-0.077 gm/sec over Shell 405 catalyst and 1.8 kW. electric arc. Feed Method: GN2 or Ghe at 14.9-20.4 atm through Wright Components 9 W dual seat. solenoid valve. Thrust: 0.20-0.23 N. Isp: 502 sec vacuum. Time to Full Thrust: N/A. Expansion Ratio: 100:1. Nozzle Length: 0.879 cm. Nozzle Cooling Method: radiative. Combustion Chamber Pressure: 4.1-4.7 atm. Combustion Chamber Temperature: 800 Celsius. Combustion Chamber Cooling Method: radiative. Duty Cycle: 5 minutes minimum to 65 hr maximum. Itotal: 654 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 .