R-4D
An RCS quad containing four R-4D thrusters, as used on the Apollo Service Module
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| Country of origin | United States |
|---|---|
| Manufacturer |
Kaiser Marquardt Aerojet Rocketdyne |
| Application | Reaction control system |
| Liquid-fuel engine | |
| Propellant | NTO / MMH |
| Cycle | pressure-fed |
| Performance | |
| Thrust (vac.) | 440 N (100 lbf) |
| Thrust-to-weight ratio | 13.74 |
| Chamber pressure | 6.84 |
| Isp (SL) | 312s |
| Used in | |
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Orion (spacecraft) H-II Transfer Vehicle Space Shuttle Apollo (spacecraft) Cassini (spacecraft) |
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The R-4D is a small hypergolic rocket engine, originally designed by Marquardt Corporation for use as a reaction control thruster on vehicles of the Apollo moon program. Today, Aerojet Rocketdyne manufactures and markets modern versions of the R-4D.
Developed as an attitude control thruster for the Apollo Command/Service Module and Lunar Module in 1960s, each unit for the modules employed four quadruple clusters (pods). It was first flown on AS-201 in February 1966. Approximately 800 were produced during the Apollo program.
Sixteen R-4Ds were mounted on the exterior of each lunar module in four quadruple clusters and sixteen on each service module. Because both the lunar module and service module were jettisoned during the Apollo missions, no flown examples exist.
Post-Apollo, modernized versions of the R-4D have been used in a variety of spacecraft, including the U.S. Navy's Leasat, Insat 1, Intelsat 6, and Italsat. It has also been used on Japan's H-II Transfer Vehicle and the European Automated Transfer Vehicle, both of which deliver cargo to the International Space Station.
R-4D was one of the first liquid-fueled rocket thruster engines to cool itself using its own fuel as coolant. Some fuel was injected longitudinally down the combustion chamber, where it formed a cooling film. The thruster's design has changed several times since its introduction. The original R-4D's combustion chamber was formed from an alloy of molybdenum, coated in a layer of disilicide. Later versions switched to a niobium alloy, for its greater ductility. Beginning with the R-4D-14, the design was changed again to use an iridium-lined rhenium combustion chamber, which provided greater resistance to high-temperature oxidization and promoted mixing of partially reacted gasses.
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