Encyclopedia Astronautica
Redmond


American manufacturer of rocket engines. Redmond, USA.

The original Rocket Research Corporation had development and test facilities at Moses Lake. Redmond's expertise covered a variety of spacecraft propulsion systems:monopropellant hydrazine thrusters, bipropellant engines, and electric propulsion systems including power processing units. The Redmond Rocket Center was acquired by General Dynamics' Space Propulsion and Fire Suppression business. In October 2002 Aerojet acquired the business from General Dynamics.

AKA: Rocket Research; General Dynamics; Aerojet.

More... - Chronology...


Associated Countries
Associated Engines
  • Aerojet 50kW Redmond electric/xenon rocket engine. Effort 2001-2003 developed a 50 kW Hall thruster in parallel to NASA's in-house development of the NASA-457M thruster. More...
  • BPT-2000 Redmond electric/xenon rocket engine. 120 mN. In Production. Hall effect thruster. Nominal power input 2200 W at 350 V. Isp=1765s. More...
  • BPT-4000 Redmond electric/xenon rocket engine. 270 mN. In Production. Hall effect thruster. Nominal power input 4500 W at 350 V. Isp=1950s. More...
  • BPT-600k Redmond electric/xenon rocket engine. 0.030 kN. In Development, 2005-2006. Isp=1800s. Began as 1995 contract for 600kWe Hall thruster electric propulsion system designed for future interplanetary manned spacecraft. More...
  • ESEX Arcjet Redmond electric/ammonia rocket engine. 2 N. In Production. Isp=800s. Electric Propulsion Space Experiment) program begun 1989 under the then Air Force Astronautics Lab. Flew once in 1999 on board the ARGOS satellite. More...
  • HiPAT Redmond N2O4/MMH rocket engine. 0.445 kN. In Production. High performance liquid apogee thruster. Isp=323s. More...
  • MR-107 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. More...
  • MR-111 Redmond hydrazine monopropellant rocket engine. 4.4 N. Attitude control, Intelsat 5, ERBS, ACTS, Radarsat, MMAS 4000, 5000, and. 7000, Wind/Polar Landsat, and Mars Observer. In Production. Isp=229s. First flight 1980. More...
  • MR-120 Redmond Hydrazine rocket engine. 0.090 kN. Small ICBM. In Production. Developed as an attitude control thruster for the small ICBM. Isp=229s. More...
  • MR-104 Redmond hydrazine monopropellant rocket engine. 0.441 kN. Attitude control and velocity corrections, Voyager, Magellan, DMSP, Tiros N, Landsat. In Production. Isp=239s. First flight 1977. More...
  • MR-106 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. More...
  • MR-103 Redmond hydrazine monopropellant rocket engine. 1.12 N. Attitude control thruster for Voyager, GPS, Intelsat 5, MMAS 3000, 4000,. 5000, and 7000, Mars Observer, ACTS, and Magellan. In Production. Isp=227s. First flight 1974. More...
  • MR-50 Redmond hydrazine monopropellant rocket engine. 0.022 kN. Attitude control for SMS, Viking, Metosat, GOES, Voyager, GPS, Intelsat 5,. Scatha, MMAS 5000, Delta Star, Magellan, Wind/Polar. In Production. Isp=228s. First flight 1974. More...
  • MR-501B Redmond Hydrazine rocket engine. 369 mN. BSAT-2 communications satellite. In Production. Electrothermal hydrazine thruster (EHT). 493 W input power at 24 V DC. Isp=303s. More...
  • MR-502 Redmond hydrazine monopropellant rocket engine. 500 mN. Communications satellite N-S stationkeeping, MMAS 5000. In Production. Isp=304s. First flight 1991. More...
  • MR-508 Redmond hydrazine monopropellant rocket engine. 230 mN. Communications satellite N-S stationkeeping, MMAS 7000. In Production. Isp=502s. First flight 1993. More...
  • MR-509 Redmond Hydrazine rocket engine. 254 mN. In Production. Low-power arcjet system. Input power 1800 W at 65 V DC. Isp=502s. More...
  • MR-510 Redmond Hydrazine rocket engine. 254 mN. In Production. Arcjet system. Isp=600s. More...
  • MR-512 Redmond Hydrazine rocket engine. 254 mN. In Production. Low-voltage bus arcjet system. Input power 1780 W at 35 V DC. Isp=502s. More...
  • MRM-106 Redmond Hydrazine rocket engine. 0.027 kN. In Production. Steady-state thrust 9 N. Isp=231s. More...
  • MRM-122 Redmond Hydrazine rocket engine. 0.142 kN. In Production. Steady-state thrust 51 N. Isp=228s. More...
  • MRM-103 Redmond Hydrazine rocket engine. 0.22 N. In Production. Steady-state thrust 0.22 N. Isp=224s. More...
  • PRS-101 Redmond electric/teflon rocket engine. 1.24 mN. In Production. Pulsed plasma thruster system. Completely solid state propulsion. Up to 100 W input power at 28 V DC, thrust to power ratio 12.4 microN/W. Isp=1350s. More...
  • R-40B Redmond N2O4/MMH rocket engine. 4 kN. In Production. Isp=293s. More...
  • R-42 Redmond N2O4/MMH rocket engine. 0.890 kN. In Production. Isp=303s. More...

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