基于等倾角进动的自旋卫星姿态控制方法  

Attitude Control Method for Spin-Stabilized Satellites Based on Equiangular Precession

作　　者：王恒[1] 郭力兵[1] 李永刚[1] 胡上成[1] 

机构地区：[1]中国卫星海上测控部

出　　处：《飞行器测控学报》2012年第4期20-24,共5页Journal of Spacecraft TT&C Technology

摘　　要：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 an essential task in control of a spin-stabilized satellite and there are many methods for attitude control. This paper focuses on equiangular precession method. First, the basic principle of equiangular pre- cession method is introduced. Then, calculation processes are given for attitude control quantities including thcoreti cal execution angle, execution times and time delay. Finally, attitude maneuver process is simulated. The simulation result shows that the computed result of attitude control quantity is correct and the forecast result of the control process is consistent with that of the actual control process. The method has been used in launch of several spin-sta- bilized satellites.

关 键 词：自旋稳定卫星 姿态控制 等倾角进动 理论执行角 执行次数 

分 类 号：V556.8[航空宇航科学与技术—人机与环境工程]