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A reaction control system (RCS) is a spacecraft system that uses thrusters to provide attitude control and translation. Alternatively, reaction wheels can be used for attitude control. Use of diverted engine thrust to provide stable attitude control of a short-or-vertical takeoff and landing aircraft below conventional winged flight speeds ...
The R-4D is a small hypergolic rocket engine, originally designed by Marquardt Corporation for use as a reaction control system thruster on vehicles of the Apollo crewed Moon landing program. Aerojet Rocketdyne manufactures and markets modern versions of the R-4D.
The forward fairing measured 1 foot 11 inches (58 cm) long and housed the reaction control system (RCS) computer, power distribution block, ECS controller, separation controller, and components for the high-gain antenna, and included eight EPS radiators and the umbilical connection arm containing the main electrical and plumbing connections to ...
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 ...
Ullage is often a secondary function of the reaction control system such as on the Apollo Lunar Module (LM). In his book Lost Moon, Jim Lovell recounted a description of a course-correction burn of the LEM's main descent engine to re-enter a free return trajectory to Earth during the successful recovery of the Apollo 13 capsule:
The second passive system orients the satellite along Earth's magnetic field thanks to a magnet. [7] These purely passive attitude control systems have limited pointing accuracy, because the spacecraft will oscillate around energy minima. This drawback is overcome by adding damper, which can be hysteretic materials or a viscous damper.
AS-201 (Also known as SA-201, Apollo 1-A, or Apollo 1 prior to the 1967 pad fire), flown February 26, 1966, was the first uncrewed test flight of an entire production Block I Apollo command and service module and the Saturn IB launch vehicle. The spacecraft consisted of the second Block I command module and the first Block I service module.
The Apollo command module reentered with the center of mass offset from the center line; this caused the capsule to assume an angled attitude through the air, providing lift that could be used for directional control. Reaction control system thrusters were used to steer the capsule by rotating the lift vector.