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PRIVATE ENTERPRISE ON THE MOON 		Rocket Engine Specifications
Section 4.3.9.1.
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Rocket Research Company Rocket Engines

Credits for providing information to Jim Glass
Boeing North American and Jane's Space

  • Rocket Research Company

    Rocket Research Company

    Rocket Research Company
    11441 Willows Road NE,
    P.O. Box 97009
    Redmond, Washington
    98073-9709
    Tel: (206) 885-5000
    Fax: (206) 882-5804

    Control Thrusters

    MR - 50

    Applications attitude control for SMS, Viking, Metosat, GOES, Voyager, GPS, Intelsat 5, Scatha, MMAS 5000, Delta Star, Magellan, Wind/Polar
    First Flown SMS metsat (May 1974)
    Flown 680 (744 produced) planned to end-1994
    Dry Mass(gm) 680
    Length(cm) 18.3
    Max Diameter(cm) 6.6
    Mounting Method bolted three places
    Propellant hydrazine at 4.67 - 17.33 gm/sec (Shell 405 catalytic decomposition)
    Feed Method G-dinitrogen or Ghe at 4.8 - 32.7 atm, through 29 W solenoid dual seat valve
    Thrust 9.79 - 38.7 N (22.2 nominal)
    Isp 215 - 228 sec vacuum
    Time to Full Thrust (millisec) 150 to 90% PC
    Nozzle Area Ratio 40:1
    Nozzle Length 3.95 cm
    Nozzle Cooling Method radiative
    Combustion Chamber Pressure 2.9 - 11.3 atm
    Combustion Chamber Temp. 800 Celsius
    Combustion Chamber Cooling Method radiative
    Duty Cycle(sec) 0.020 min to 5400 max; 471,000 pulses
    It 459.4 kNs

    MR - 103

    Applications attitude control thruster for Voyager, GPS, Intelsat 5, MMAS 3000, 4000, 5000, and 7000, Mars Observer, ACTS, and Magellan
    First Flown ATS 6 commssat( May 1974 )
    Flown 1014 (1744 produced) planned to end-1997
    Dry Mass 332 gm
    Length 14.7 cm
    Max Diameter 3.43 cm
    Mounting Method bolted three places
    Propellant hydrazine at 0.091-0.499 gm/sec (Shell 405 catalytic decomposition)
    Feed Method GN2 at 4.8-28.6 atm through 9 W solenoid dual seat valve
    Thrust 0.19-1.12 (0.89 nominal)
    Isp 206-227 sec vacuum
    Time to Full Thrust (millisec) 150 to 90%
    Nozzle Area Ratio 100:1
    Nozzle Length 0.98 cm
    Nozzle Cooling Method radiative
    Combustion Chamber Pressure 4.35-23.9 atm
    Combustion Chamber Temperature 800 Celsius
    Combustion Chamber Cooling Method radiative
    Duty Cycle 0.008 sec minimum to unlimited maximum burn; 750,000 pulses
    Itotal 158.46 kNs

    MR - 104

    Applications attitude control and (V corrections, Voyager, Magellan, DMSP, Tiros N, Landsat
    First Flown Voyager (August 1977)
    Flown 48 (97 produced) planned to end-1995
    Dry Mass 1860 gm
    Length 46.0 cm
    Max Diameter 15.2 cm
    Mounting Method bolted three places
    Propellant hydrazine at 91-290 gm/sec (Shell 405/LCH-202 catalytic decomposition)
    Feed Method GN2 or GHe at 6.8-28.6 atm through Wright Components 30 W single seat solenoid valve
    Thrust 205-572 N (445 nominal)
    Isp 228-239 sec vacuum
    Time to Full Thrust (millisec) 50 to 90% PC
    Expansion Ratio 53:1 (diameter 15.2 cm)
    Nozzle Length 17.8 cm
    Nozzle Cooling Method radiative
    Combustion Chamber Pressure 3.8-19.0 atm
    Combustion Chamber Temperature 800 Celsius
    Combustion Chamber Cooling Method radiative
    Duty Cycle0.022-2000 sec single firing; 2654 cumulative; 1742 pulses
    Itotal693.9 kNs

    MR - 106

    Applicationsspacecraft and upper stage attitude control and (V corrections, PAM A/S, Radarsat, GPS Block 2R, HAS/Peace Courage, Titan Cenataur, Atlas Cenataur
    First FlownHAS/Peace Courage
    Flown204 (2359 produced) planned to end-1997
    Dry Mass476 gm
    Length17.8 cm
    Max Diameter6.4 cm
    Mounting Methodbolted three places
    Propellanthydrazine at 4.08-11.79 gm/sec (LCH 227/202 catalytic decomposition)
    Feed MethodGN2 or Ghe at 6.8-30.6 atm through Wright Components 27 W solenoid valve
    Thrust8.9-26.7 N (26.7 nominal)
    Isp218-232 sec vacuum
    Time to Full Thrust (millisec)200 to 90% PC
    Expansion Ratio61:1
    Nozzle Length4.72 cm
    Nozzle Cooling Methodradiative
    Combustion Chamber Pressure6.12-10.8
    Combustion Chamber Temperature800 Celsius
    Combustion Chamber Cooling Methodradiative
    Duty Cycle0.016 sec minimum to 2000 maximum; 12,397 pulses
    Itotal167 kNs

    MR - 107

    Applicationsspacecraft 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
    First FlownHAS/Peace Courage
    Flown321 (1871 produced) planned to end-1997
    Dry Mass885 gm
    Length21.8 cm
    Max Diameter6.6 cm
    Mounting Methodbolted in three places
    Propellanthydrazine at 24-113 gm/sec (LCH 207/LCH 202 catalytic decomposition)
    Feed MethodGN2 or Ghe at 6.8-34 atm through 50 W solenoid valve
    Thrust51.2-257.9 N (178 nominal)
    Isp217-236 sec vacuum
    Time to Full Thrust (millisec)200 to 90% PC
    Expansion Ratio21:1
    Nozzle Length4.72 cm
    Nozzle Cooling Methodradiative
    Combustion Chamber Pressure1.9-9.5 atm
    Combustion Chamber Temperature800 Celsius
    Combustion Chamber Cooling Methodradiative
    Duty Cycle0.016 sec minimum to 2137 maximum; 7005 pulses
    Itotal332.3 kNs

    MR - 111

    Applicationsattitude control, Intelsat 5, ERBS, ACTS, Radarsat, MMAS 4000, 5000, and 7000, Wind/Polar Landsat, and Mars Observer
    First FlownIntelsat 5 (December 1980)
    Flown348 (499 produced) planned to end-1995
    Dry Mass345 gm
    Length16.7 cm
    Max Diameter35.6 cm
    Mounting Methodbolted three places
    Propellanthydrazine at 0.19-2.4 gm/sec (Shell 405 catalytic decomposition)
    Feed MethodGN2 or He at 4.08-27.2 atm through Wright Components 9 W dual seat solenoid valve
    Thrust0.44-5.34 N (2.2-4.4 nominal)
    Isp213-229 sec vacuum
    Time to Full (millisec)150 to 90% PC
    Expansion Ratio200:1
    Nozzle Length2.18 cm
    Nozzle Cooling Methodradiative
    Combustion Chamber Pressure3.1-13.9 atm
    Combustion Chamber Temperature800 Celsius
    Combustion Chamber Cooling Methodradiative
    Duty Cycle0.020 sec minimum to 15 hr maximum; 420,000 pulses
    Itotal260.21 kNs

    MR - 502 Improved Electrothermal Hydrazine Thruster (IMPEHT)

    Applicationscommunications satellite N-S stationkeeping, MMAS 5000
    First FlownAstra 1B (March 1991)
    Flown16 (32 produced) planned to end-1995
    Dry Mass848 gm
    Length19.4 cm
    Max Diameter8.84 cm
    Mounting Methodbolted four places
    Propellanthydrazine at 0.119-0.167 gm/sec over Shell 405 catalyst and 610-839.6 W electric heater
    Feed MethodGN2 or Ghe at 21.8-23.8 atm through Wright Components 9 W dual seat solenoid valve
    Thrust0.36-0.50 N
    Isp280-304 sec vacuum
    Expansion Ratio100:1
    Nozzle Length0.879 cm
    Nozzle Cooling Methodradiative
    Combustion Chamber Pressure3.4-6.5 atm
    Combustion Chamber Temperature800 Celsius
    Combustion Chamber Cooling Methodradiative
    Duty Cycle300 sec minimum to 2 hr maximum; 430,000 pulses
    Itotal525 kNs

    MR - 508 Low Power Hydrazine Arcjet

    Applicationscommunications satellite N-S stationkeeping, MMAS 7000
    First FlightTelstar 4 (December 1993); qualified autumn 1991
    Flown6 (28 produced) planned to end-1995
    Dry Mass1338 gm
    Length24.4 cm
    Max Diameter9.27 cm
    Mounting Methodbolted four places
    Propellanthydrazine at 0.068-0.077 gm/sec over Shell 405 catalyst and 1.8 kW electric arc
    Feed MethodGN2 or Ghe at 14.9-20.4 atm through Wright Components 9 W dual seat solenoid valve
    Thrust0.20-0.23 N
    Isp502 sec vacuum
    Time to Full Thrust N/A
    Expansion Ratio100:1
    Nozzle Length0.879 cm
    Nozzle Cooling Methodradiative
    Combustion Chamber Pressure4.1-4.7 atm
    Combustion Chamber Temperature800 Celsius
    Combustion Chamber Cooling Methodradiative
    Duty Cycle5 minutes minimum to 65 hr maximum
    Itotal654 kNs

    Rocket Engine Specifications
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