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姿态控制是自旋稳定卫星控制的基本任务之一,其控制方法有多种,本文主要针对等倾角法进行研究。首先介绍等倾角法姿态控制的基本原理,然后详细地给出姿态控制前需确定的理论执行角、实际执行次数和时延等控制量的具体计算方法,最后进行了姿态机动仿真控制。仿真结果表明,控制量的计算结果准确,控制过程的预测结果与实际控制过程一致。此方法已在多颗自旋卫星发射中得到应用和验证。
Attitude control is one of the basic tasks of spin-stable satellite control, and there are many control methods. In this paper, we mainly study the isocline approach. Firstly, the basic principle of isometric attitude control is introduced. Then, the calculation methods of the control amount, such as the theoretical execution angle, the actual execution times and the delay before the attitude control, are given in detail. Finally, the attitude maneuver simulation is carried out. The simulation results show that the calculation result of control quantity is accurate and the prediction result of control process is consistent with the actual control process. This method has been applied and verified in multi-spin satellite launches.