The invention relates to a satellite angular momentum unloading method using a rotating mechanism, and belongs to the technical field of spacecraft attitude control. The technical problem that an existing method is not applicable if the attitude of a satellite is required to face the ground during on-orbit work is solved. The method comprises the following steps of: calculating rotational inertia change caused by an angle of a satellite rotating mechanism; calculating the influence of the satellite attitude and the inertia matrix on the gravity gradient moment; unloading the angular momentum by using the product of inertia; and planning the angle of the rotating mechanism. According to the satellite angular momentum unloading method utilizing the rotating mechanism, the characteristic that the gravity gradient moment can be generated by utilizing the inertia product in a satellite rotational inertia matrix is utilized for solving the satellite angular momentum unloading problem. According to the current angular momentum of the satellite, calculating an expected inertia product in a satellite rotational inertia matrix; and an expected angle of rotation maneuvering is calculated, so that unloading of the angular momentum is completed.
本发明涉及一种利用转动机构的卫星角动量卸载方法,属于航天器姿态控制技术领域。本发明解决了若卫星在轨工作中要求姿态对地,则现有方法不适用的技术问题。本发明的方法包括以下步骤:计算卫星转动机构角度引起的转动惯量变化;计算卫星姿态和惯量矩阵对重力梯度力矩的影响;利用惯性积对角动量进行卸载;以及转动机构角度规划。本发明的利用转动机构的卫星角动量卸载方法,针对卫星角动量卸载问题,利用卫星转动惯量矩阵中的惯性积能够产生的重力梯度力矩的特性。根据卫星当前角动量,计算卫星转动惯量矩阵中期望的惯性积。进而计算得到转动机动的期望角度,从而完成对角动量的卸载。
Satellite angular momentum unloading method using rotating mechanism
一种利用转动机构的卫星角动量卸载方法
2023-11-14
Patent
Electronic Resource
Chinese
IPC: | B64G Raumfahrt , COSMONAUTICS |
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