MR-107

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MR-107

Part of MR-100 engine series

MR-107B
Credit: Aerojet Redmond

Redmond hydrazine monopropellant rocket engine. Spacecraft and upper stage attitude control and dV corrections, Delta 2, Titan 2, PAM D, SICBM, HAS/Peace Courage, Atlas roll control module, STEP, Pegasus. First flight 1990.

Number: 61 . Thrust: 257 N (57 lbf). Unfuelled mass: 0.89 kg (1.95 lb). Specific impulse: 236 s. Burn time: 1,200 s. Height: 2.18 m (7.15 ft). Diameter: 0.0660 m (0.2160 ft).

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.

Engine: 0.89 kg (1.95 lb). Chamber Pressure: 21.00 bar. Thrust to Weight Ratio: 29.37.

Family: Monopropellant. Country: USA. Spacecraft: Mars Reconnaissance Orbiter. Launch Vehicles: Pegasus. Stages: Pegasus-4, OAM. Agency: Redmond.

Photo Gallery

MR-107J
Credit: Aerojet Redmond

MR-107K
Credit: Aerojet Redmond

MR-107L
Credit: Aerojet Redmond

MR-107M
Credit: Aerojet Redmond

MR-107N
Credit: Aerojet Redmond

MR-107P
Credit: Aerojet Redmond

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