MR-106
Engine · USA
Original archive entry. The text, images and links below are kept as they were written.
Credit: Aerojet Redmond
Redmond hydrazine monopropellant rocket engine. Spacecraft and upper stage attitude control and velocity corrections, PAM A/S,. Radarsat, GPS Block 2R, HAS/Peace Courage, Titan Centaur, Atlas Centaur. 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.
Engine: 0.48 kg (1.05 lb). Chamber Pressure: 10.90 bar. Area Ratio: 61. Thrust to Weight Ratio: 5.71.
Related
- Family
- Monopropellant
- Country
- USA
- Launch Vehicles
- Atlas E/SGS-2
- Stages
- Centaur D/E
- Agency
- Redmond