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Reaction control systems are capable of providing small amounts of thrust in any desired direction or combination of directions. An RCS is also capable of providing torque to allow control of rotation (roll, pitch, and yaw). [2] Reaction control systems often use combinations of large and small thrusters, to allow different levels of response.
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A vernier thruster or gimbaled engine are particular cases used on launch vehicles where a secondary rocket engine or other high thrust device is used to control the attitude of the rocket, while the primary thrust engine (generally also a rocket engine) is fixed to the rocket and supplies the principal amount of thrust.
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Depending on the design of a craft's maneuvering and stability systems, it may simply be a smaller thruster complementing the main propulsion system, [1] or it may complement larger attitude control thrusters, [2] or may be a part of the reaction control system.
The original Soyuz had a separated orbital correction system from its orientation system. The latter, integrated a reaction control system called DPO and the attitude control system, called DO. The KTDU-35 had a main orbit correction engine SKD, the S5.60 and a backup orbital correction engine DKD, the S5.35.
The system was also used to push the spacecraft away from the spent second stage of the Titan II launch vehicle on first reaching orbit. The eight rotational control engines were mounted off the spacecraft's center of mass around the aft section of the Equipment Module, pointed at 90 degree positions up, down, left and right.
The definition of a closed loop control system according to the British Standards Institution is "a control system possessing monitoring feedback, the deviation signal formed as a result of this feedback being used to control the action of a final control element in such a way as to tend to reduce the deviation to zero." [2]