Encyclopedia Astronautica
MR-107



mr107b.jpg
MR-107B
Credit: Aerojet Redmond
mr107j.jpg
MR-107J
Credit: Aerojet Redmond
mr107k.jpg
MR-107K
Credit: Aerojet Redmond
mr107l.jpg
MR-107L
Credit: Aerojet Redmond
mr107m.jpg
MR-107M
Credit: Aerojet Redmond
mr107n.jpg
MR-107N
Credit: Aerojet Redmond
mr107p.jpg
MR-107P
Credit: Aerojet Redmond
Redmond hydrazine monopropellant rocket engine. 0.257 kN. 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. Isp=236s. First flight 1990.

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.

Application: Spacecraft and upper stage attitude control and (V corrections, Delta 2, Titan 2,. Commercial Titan, PAM D, Small ICBM, HAS/Peace Courage, Atlas roll control. module, STEP, Pegasus..

Characteristics

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

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

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Associated Countries
Associated Spacecraft
  • Mars Reconnaissance Orbiter American Mars orbiter. One launch, 2005.08.12. Mars Reconnaissance Orbiter was the first spacecraft designed from the beginning for aerobraking to place it into the desired orbit around Mars. More...

See also
Associated Launch Vehicles
  • Pegasus American air-launched orbital launch vehicle. Privately-funded, air-launched winged light satellite launcher. More...

Associated Manufacturers and Agencies
  • Redmond American manufacturer of rocket engines. Redmond, USA. More...

Associated Propellants
  • Hydrazine Hydrazine (N2H4) found early use as a fuel, but it was quickly replaced by UDMH. It is still used as a monopropellant for satellite station-keeping motors. Hydrazine (N2H4) found early use as a fuel, but it was quickly replaced by UDMH. It is still used as a monopropellant for satellite station-keeping motors. More...

Associated Stages
  • OAM Hydrazine propellant rocket stage. Loaded/empty mass 714/360 kg. Thrust 0.88 kN. Vacuum specific impulse 222 seconds. Monopropellant final stage providing precise orbital injection. Pressure-fed, indefinite number of restarts. More...
  • Pegasus-4 Hydrazine propellant rocket stage. Loaded/empty mass 90/17 kg. Thrust 0.67 kN. Vacuum specific impulse 236 seconds. More...

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