航天器碰撞规避单脉冲切向控制最优策略

Optimal Control Strategy of Spacecraft Tangential Collision Avoidance with Single Pulse

针对在轨航天器采用切向单脉冲喷气规避空间碰撞风险的最优控制策略问题,推导了小偏心率轨道卫星切向控制后的轨道相对原轨道的相对运动方程,分析了空间接近几何关系,给出了满足空间接近距离和交垂线方向距离约束情况下不同控制时刻对应的最小控制量的计算方法和函数曲线,证明了控制量与控制效果的单调关系并讨论了控制时刻对控制效果的敏感性。只要综合测站跟踪情况、卫星工作情况、燃料节省等多种约束确定了控制时刻,即可通过上述控制时刻和控制量函数曲线确定最小的切向控制方向和控制量大小。

Aiming at the problem of optimal control strategy for spacecraft on orbit by using tangential monopulse jet to avoid space collision risk,a method is proposed.Firstly,a relative motion equation of the satellite with small eccentricity orbit after tangential control related to the original orbit is derived.Then,the spatial proximity geometric relationship is analyzed.There are distance constraints both from the perpendicular direction and space proximity,under which the calculation method of the minimum control quantity corresponding to control time is developed and the function curves at different control time are drawn.Besides,the monotone function relationship between control quantity and control effect is proven,and the sensitivity of the control time to the control effect is discussed.As long as the control time is obtained by integrating multiple constraints such as station tracking,satellite conditions and fuel saving,the minimum tangential control quantity and the control direction can be determined through the above control time and control function curve.