A method for de-rotating control of a rotating body of a satellite and a corresponding de-rotating device

Abstract

The invention relates to a method for de-rotating control of a rotating body of a satellite, wherein the satellite has a rotating body, a balancing wheel and a reaction wheel, and the rotation axis ofthe balancing wheel is parallel to the rotation axis of the rotating body. The method comprises the steps of rotating the balancing wheel and the reaction wheel; obtaining the excess angular momentumabsorbed by the reaction wheel after the three-axis attitude of the satellite is stabilized; and adjusting the rotational speed of the balance wheel according to the excess angular momentum so as toperform de-rotating control on the rotating body. The invention also relates to a de-rotating device. The invention can realize the combined de-rotating control of the balance wheel and the reaction wheel, thereby basically eliminating the significant disturbance of the residual angular momentum and moment to the attitude of the satellite platform caused by the inertia uncertainty of the rotatingbody on the satellite, and improving the performance of the satellite attitude control system.

Description

technical field [0001] The present invention generally relates to the field of attitude control of spacecraft, and in particular, relates to a method for derotation control of a rotating body of a satellite. Furthermore, the invention also relates to a derotation device for a rotating body of a satellite. Background technique [0002] With the rapid development of modern satellite technology, spaceborne equipment, especially reconnaissance and detection application equipment, has more and more requirements for satellite rotation mechanisms, and higher and higher requirements for satellite attitude accuracy. [0003] When the rotating body on the star rotates, it generates angular momentum in the direction of the rotation axis and reverse interference torque, which acts on the satellite platform and interferes with the attitude of the satellite; by configuring the balance wheel on the star for derotation, according to the designed derotation control strategy, the balance whee...

AI Technical Summary

Problems solved by technology

[0005] However, due to the existence of installation errors, measurement errors, model errors and other factors, there are always residual moments and residual angular momentum

The residual angular momentum makes the star bias in a certain direction, reducing the lateral maneuverability of the satellite; at the same time, the additional disturbance torque aggravates the satellite attitude fluctuation, and the attitude control accuracy decreases; the reaction wheel controls the satellite attitude on the one hand, and absorbs the residual angle of the star on the other Momentum makes the center speed of the reaction wheel deviate from the nominal speed, which may cause the angular momentum unloading module on the star to work frequently for a long time, and further reduce the attitude control performance

[0006] For satellites with a rotating body with large inertia and uncertain inertia of the rotating body, the traditional balance wheel derotation control, the method of reaction wheel controlling residual torque and absorbing angular momentum will reduce the accuracy of the satellite platform and deteriorate the dynamic response characteristics. control performance, a new solution is needed

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