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astronautix.com R-4D


Designer: Marquardt. Application: Apollo LM, Leasat, Insat, HS 393, Milstar, Intelsat 6, Italsat, Eurostar. Used on stages: IABS, Jarvis-3. Used on launch vehicles: Atlas II, Jarvis. Used on spacecraft: HS 381, HS 393, HS 601. Propellants: N2O4/MMH Thrust(vac): 49 kgf. Thrust(vac): 0.49 kN. Isp: 312 sec. Mass Engine: 4 kg. Diameter: 0.3 m. Length: 0.6 m. Chambers: 1. Chamber Pressure: 6.84 bar. Area Ratio: 164.00. Oxidizer to Fuel Ratio: 1.65. Thrust to Weight Ratio: 13.74. Country: USA. Status: In Production. First Flight: 1991. Last Flight: 1998. Flown: 20.

Developed as an attitude control thruster for the Apollo's Service and Lunar Module. Each unit for the modules employed four quadruple clusters. Approximately 800 were built. The thruster is currently employed in the R-4D-10 version of the U.S. Navy's Leasat, R-4D-11 by Insat 1 and Arabasat 1, R-4D-12 by HS-393, Milstar, Intelsat 6, Italsat, and Olympus and Eurostar.. Manufacturer: Kasier Marquardt. Application: apogee/perigee maneuvers, orbit adjust, and attitude control. First Flown: February 1966 (Apollo 201). Number Produced: about 800. Dry Mass: 3.63 kg. Length: 55.41 cm. Maximum Diameter: 27.94 cm. Mounting: fixed. Engine Cycle: pressure-fed. Propellants: hypergolic nitrogen tetroxide and MMH or hyrdazine which was pressure-fed at 0.05 kg/sec fuel and 0.091 kg/sec oxidizer at atm. Mixture Ratio: 1.65 (1.0 - 2.4 range). Thrust: 490 N vacuum standard. Isp: 312 sec vacuum standard. Expansion Ratio: 164:1. Chamber Pressure: 6.84 atm. Combustion Chamber: a single chamber/nozzle of welded coated columbium (niobium), radiatively and film-cooled, controlled by an on/off solenoid, and a multiple doublet injector with hypergolic ignition.. Burn Time: up to 1 hour continuous with a 2.67 Ns min impulse bit.Used in Jarvis-3; IABS.


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