Encyclopedia Astronautica
MR-106



mr106e.jpg
MR-106E
Credit: Aerojet Redmond
Redmond hydrazine monopropellant rocket engine. 0.027 kN. 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. Isp=232s.

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.

Application: Spacecraft and upper stage attitude control and velocity corrections, PAM A/S,. Radarsat, GPS Block 2R, HAS/Peace Courage, Titan Centaur, Atlas Centaur..

Characteristics

Engine: 0.48 kg (1.05 lb). Chamber Pressure: 10.90 bar. Area Ratio: 61. Thrust to Weight Ratio: 5.71.

Status: In Production.
Unfuelled mass: 0.48 kg (1.05 lb).
Height: 0.18 m (0.58 ft).
Diameter: 0.0640 m (0.2090 ft).
Thrust: 27 N (6 lbf).
Specific impulse: 232 s.

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Associated Countries
See also
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
  • Centaur D/E Lox/LH2 propellant rocket stage. Loaded/empty mass 16,258/2,631 kg. Thrust 131.22 kN. Vacuum specific impulse 444 seconds. More...
  • PAM-S Solid propellant rocket stage. Loaded/empty mass 2,182/220 kg. Thrust 66.60 kN. Vacuum specific impulse 288 seconds. More...

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