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中文摘要：
针对拦截卫星和目标航天器都可以采用幅值受限连续推力进行轨道机动时的卫星末端拦截控制问题,由于对抗双方都会采用对自己有利的控制策略来实现追击和逃逸,因此将该问题可以看作追踪逃逸问题.由于两卫星距离较近,因此将非线性拦截逃逸相对动力学简化为CW方程.根据拦截任务终止要求引入零控脱靶矢量将动力学方程降阶,采用拦截脱靶量和燃料消耗作为二次最优目标函数,推导了卫星轨道次优控制策略.仿真表明该控制方法可以在目标卫星具有机动逃逸能力时仍能成功将其拦截.
英文摘要：
In the satellite interception control strategies,both the interceptor and target could perform orbital maneuver with limited magnitude continuous thrust.Basically,this problem was regarded as a pursuit-evasion game since satellites in both sides would try their best to catch or escape.Assumption that the two player were close such that the nonlinear interception dynamics could be reduced to the CW equations.Zero effort miss was introduced to simplify the system.The controller was constructed by adding the interception miss and the fuel consumption to the optimal objective.Simulation was conducted to analyze the advantage and weakness of proposed control strategy.
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