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MR-508
Part of MR-500 engine series Family
Redmond hydrazine monopropellant rocket engine. Communications satellite N-S stationkeeping, MMAS 7000. In Production. First flight 1993.

AKA: Low Power Hydrazine Arcjet. Status: In Production. Thrust: 0.23 N (0.05 lbf). Unfuelled mass: 1.34 kg (2.95 lb). Specific impulse: 502 s. Burn time: 234,000 s. Height: 0.24 m (0.80 ft). Diameter: 0.0927 m (0.3041 ft).

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.

Engine: 1.34 kg (2.95 lb). Chamber Pressure: 4.80 bar. Area Ratio: 100. Thrust to Weight Ratio: .01.



Family: Monopropellant. Country: USA. Agency: Redmond.

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