Racemization control method for under-actuated satellite

Abstract

The invention discloses a racemization control method for an under-actuated satellite. The method comprises the following steps of: (1) determining an initial self-rotating shaft position of the under-actuated satellite by the adoption of an attitude sensor, and determining a direction and an amount of racemization control according to a position of a target self-rotating shaft; (2) determining geometric relationship between an injection control moment and a racemization control direction produced by each injection control engine, and selecting the injection control engine with the largest amount of the injection control moment in the racemization control direction as a racemization control engine; and (3) in a preliminary stage of racemization, adopting an integer multiple self-rotating period fully spraying method, in a final phase of racemization, adopting a symmetrical point spraying method, using the racemization control engine to carry out racemization control, after primary racemization is finished, enabling a planet to be naturally damped for a period of time, and then carrying out the next racemization control until a self-rotating shaft of a satellite reaches a target self-rotating shaft. According to the method, the operation of a racemization control strategy is simple and convenient, and nutation produced by racemization control can be reduced at the same time.

Description

technical field [0001] The invention relates to a satellite attitude control method. Background technique [0002] Derotation control is generally used for spin-stabilized satellites. Many satellites use spin-stabilized methods to stabilize attitude, and their spin axis is perpendicular to the orbital plane. When a constant disturbing torque acts, its spin axis drifts at a constant velocity instead of accelerating. Spin stabilization is an attitude stabilization method that uses the fixed axis of the satellite when it rotates around the spin axis to keep the spin axis in the inertial space without external torque. When there is an external force, the angular momentum of the spin satellite The direction of the vector will precess at a certain angular velocity. When the instantaneous rotation axis does not coincide with the spin axis, the spinning satellite will nutate. In order to maintain the fixed axis of the spin axis, it is necessary to consume the energy of the satellit...

AI Technical Summary

Problems solved by technology

[0004] In the process of satellite derotation control, if the satellite jet control belongs to under-driven control, if the method of full-drive derotation control is still used, the control purpose cannot be achieved, and even the safety of the satellite is enda...

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