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对于外部扰动力矩模型近似已知的一类卫星,可以充分发挥斜装飞轮的优势使姿态控制系统的性能指标大幅度提高。文献[1]讨论了斜装飞轮相对能控度问题,本文在此基础上引入了相对能控度椭球和相对能控度向量等概念;指出在任何外部扰动力矩作用下相对能控度的值都可以用星本体坐标系中一个能控度椭球上的一点到原点的距离的平方表示;介绍了能控度椭球的性质,结合飞轮最小动量存储能力的要求,为姿态控制系统执行机构安装方式的选择提供了一种理论依据和直观的几何解说。
For a class of satellites whose known external perturbation moment model is approximately known, the advantages of inclined flywheel can be fully utilized to greatly improve the performance of attitude control system. In [1], the relative controllability of inclined flywheel is discussed. Based on this, concepts such as relative energy control ellipsoid and relative energy control vector are introduced. It is pointed out that the relative controllability of inclined flywheel under any external disturbance torque Can be expressed as the square of the distance from one point on the ellipsoid to the origin in the star body coordinate system. The properties of the controllable ellipsoid are introduced, and the attitude control system is executed according to the requirement of the minimum momentum storage capacity of the flywheel The choice of mechanism installation provides a theoretical basis and an intuitive geometric explanation.