确定卫星可达范围的优化方法

Optimization of the reachable domain of a satellite

为设计空间合作目标任务中各卫星间的安全距离,研究在初始椭圆轨道上施加一次脉冲后卫星的可达范围。考虑脉冲幅值较小,因此卫星的可达范围有界。针对脉冲位于轨道面内的情况,令脉冲的幅值固定而施加位置和方向均任意,推导了生成轨道的运行规律,提出了确定卫星可达范围的优化法,该方法能够直接给出边界点的真近点角。通过与拟合法的结果进行对比表明,对于初始轨道偏心率不同的情况,采用优化法均能够实现确定卫星可达范围的目的。

The safe distance between satellites in cooperative missions depends on the reachable domain of a satellite for a single thrust impulse applied at the initial elliptic orbit. The reachable domain is bounded assuming that all the generated trajectories are ellipses due to the low impulse. Trajectories are given for a coplanar impulse with fixed magnitude and arbitrary direction applied at any point on the initial orbit. An optimization method is used to determine the boundary of the reachable domain, through which the true anomaly of the points composing the boundary is given. In contrast to the fitting method, the optimization method is valid for various initial elliptical orbits with different eccentricities to determine the boundary of the reachable domain.