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The Apollo Command Module had a set of twelve hypergolic thrusters for attitude control, and directional reentry control similar to Gemini. The Apollo Service Module and Lunar Module each had a set of sixteen R-4D hypergolic thrusters, grouped into external clusters of four, to provide both translation and attitude control. The clusters were ...
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, Italsat, and BulgariaSat-1. [3] It has also been used on Japan 's H-II Transfer Vehicle and the European Automated Transfer Vehicle , both of which delivered cargo to the International Space Station . [ 4 ]
RCS quad containing four R-4D thrusters, as used on the Apollo Service Module. Four clusters of four reaction control system (RCS) thrusters (known as "quads") were installed around the upper section of the SM every 90°. The sixteen-thruster arrangement provided rotation and translation control in all three
Some devices that are used or proposed for use as thrusters are: Cold gas thruster; Electrohydrodynamic thruster, using ionized air (only for use in an atmosphere) Electrodeless plasma thruster, electric propulsion using ponderomotive force; Electrostatic ion thruster, using high-voltage electrodes; Hall effect thruster, a type of ion thruster
Some LESS designs used a single engine under the center, but many used multiple engines around the edge, typically based on the Apollo reaction control system (RCS) thrusters used for attitude control on the command and service module (CSM) and lunar module (LM). These had a thrust of around 100 pounds-force (440 N) each, so putting eight ...
R-4D (MMH/NTO) – 100 lbf (exact thrust depends on variant) hypergolic thruster, originally developed by Marquardt as RCS thrusters for the Apollo SM and LM. Currently used as secondary engines on the Orion European Service Module, and as apogee motors on various satellite buses. MR103G — 0.2 lb hydrazine monopropellant thruster
The ascent propulsion system (APS) or lunar module ascent engine (LMAE) is a fixed-thrust hypergolic rocket engine developed by Bell Aerosystems for use in the Apollo Lunar Module ascent stage. It used Aerozine 50 fuel, and N 2 O 4 oxidizer.
A Mode V abort was only planned for use during the Apollo-Soyuz Test Project launch. In the event of an early S-IVB shutdown, the CSM RCS thrusters would be used to insert the entire stack (including the docking adapter) into orbit. The time window for a Mode V abort was only 1.5 seconds before nominal S-IVB cutoff.