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Monopropellant
Category of engines.



Subtopics

Hustler APU Aerojet isopropylnitrate monopropellant rocket engine. B-58. Development begun 1953. APU for the Hustler 'controlled bomb pod', which was really a long range air to surface strategic missile

D-7 Kosberg isopropyl nitrate monopropellant rocket engine. Missile by Toropov. Out of Production. Intended for air-air missile by I I Toropov. Uncooled thrust chamber. Sea level thrust 11.8 kN.

DOK-10 Isayev monopropellant rocket engine. In Production. Pressure-fed monopropellant engine. Thermal decomposition of hydrazine by an iridium-based catalyst, which heated to increase stability. 40,000 ignitions

DOK-50 Isayev monopropellant rocket engine. In Production. Pressure-fed monopropellant engine. Thermal decomposition of hydrazine by an iridium-based catalyst, which heated to increase stability. 40,000 ignitions

DOT-25 Isayev monopropellant rocket engine. In Production. Pressure-fed monopropellant engine. Thermal decomposition of hydrazine by a wire catalyst, which is electrically heated to 620 K. 60,000 ignitions

DOT-5 Isayev monopropellant rocket engine. In Production. Pressure-fed monopropellant engine. Thermal decomposition of hydrazine by a wire catalyst, which is electrically heated to 620 K. 550,000 ignitions

D-1 engine Kosberg isopropyl nitrate monopropellant rocket engine. Developed 1955-56. Second thrust level at 50%. Explosion of D-1 on test bench in 1956 forced stop of work with mono-propellant OT-152. Sea level thrust 39 kN.

MR-111 Redmond hydrazine monopropellant rocket engine. Attitude control, Intelsat 5, ERBS, ACTS, Radarsat, MMAS 4000, 5000, and. 7000, Wind/Polar Landsat, and Mars Observer. In Production. First flight 1980.

MR-502 Redmond hydrazine monopropellant rocket engine. Communications satellite N-S stationkeeping, MMAS 5000. In Production. First flight 1991.

MR-103 Redmond hydrazine monopropellant rocket engine. Attitude control thruster for Voyager, GPS, Intelsat 5, MMAS 3000, 4000,. 5000, and 7000, Mars Observer, ACTS, and Magellan. In Production. First flight 1974.

MR-104 Redmond hydrazine monopropellant rocket engine. Attitude control and velocity corrections, Voyager, Magellan, DMSP, Tiros N, Landsat. In Production. First flight 1977.

MR-106 Redmond hydrazine monopropellant rocket engine. 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.

MR-107 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.

MR-508 Redmond hydrazine monopropellant rocket engine. Communications satellite N-S stationkeeping, MMAS 7000. In Production. First flight 1993.

MRE-15/OMV TRW hydrazine monopropellant rocket engine. In Production. Mono-propellant Hydrazine Thrusters.

MR-50 Redmond hydrazine monopropellant rocket engine. Attitude control for SMS, Viking, Meteosat, GOES, Voyager, GPS, Intelsat 5,. Scatha, MMAS 5000, Delta Star, Magellan, Wind/Polar. In Production. First flight 1974.

REA 10 Marquardt hydrazine monopropellant rocket engine. In Production.

REA 17-12 Marquardt hydrazine monopropellant rocket engine. In Production.

REA 22-2 Marquardt hydrazine monopropellant rocket engine. In Production.

REA 39-2 Marquardt hydrazine monopropellant rocket engine. In Production.

REA 20-4 Marquardt hydrazine monopropellant rocket engine. In Production.

REA 22-5 Marquardt hydrazine monopropellant rocket engine. In Production.

REA 16 Marquardt hydrazine monopropellant rocket engine. In Production.

REA 17-6 Marquardt hydrazine monopropellant rocket engine. In Production.

REA 22-16 Marquardt hydrazine monopropellant rocket engine. In Production.

REA 22-17 Marquardt hydrazine monopropellant rocket engine. In Production.

RM-01 Null

XCNLT-1500 Aerojet isopropylnitrate monopropellant rocket engine for Lark missile. Development begun March 1945. Turborocket; turbine-pump fed monopropellant, single uncooled thrust chamber. Development unsuccessful, all work terminated.



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