近地共面轨道上两飞行器在径向连续小推力下的追逃界栅

针对近地共面轨道上两飞行器在轨追逃对策问题,以轨道根数为状态变量,在双方均为径向连续可变小推力的假设条件下,研究定性微分对策方法中考虑推力性能的界栅存在条件.在此条件下推导出可变推力的最优控制量,以及以偏心率和幅角为状态变量的界栅表达式.仿真实例在给定捕获半径的条件下,给出了偏心率的界栅曲线,并表明当对策结束时,逃逸器位于追踪器的正上方或正下方.

Pursuit-evasion barrier of two spacecrafts under minute continuous radial thrust in coplanar orbit

The pursuit-evasion game of two coplanar near-earth orbiters is investigated based on orbital element equations. Under the assumption of radial, minute, continuous and variable thrust for both spacecrafts, the condition of barrier existence is established, which takes into account of thrust index. The optimum control parameter of the variable thrust is deduced based on the condition of the existence of the barrier, together with the expressions of the barriers in terms of eccentricity and argument. In numerical examples, the barrier curves of the eccentricity are obtained under given capture radius and it is shown that at the end of the game, the evader is right above or below the pursuer.