拦截卫星轨道优化和控制方法研究

发布时间：2018-06-30 22:17

本文选题：改进布谷鸟算法 + 微分对策　；参考：《哈尔滨工业大学》2015年硕士论文

【摘要】：当前空间技术发展迅速,并在国民的经济,生活和军事中扮演着重要角色,空间攻防技术的研究对国家空间资源的保护具有重要意义。本文对空间拦截中的一种重要方式,反卫星拦截的轨道优化和控制进行了研究,主要内容包括以下几点:针对精确动力学远程多脉冲拦截问题,建立了含有多种摄动项的拦截动力学方程,首先忽略摄动项,采用可行解迭代方法,将拦截末端约束和交会角约束包含在目标函数中,得到了含有约束处理项的燃料优化问题。对布谷鸟算法进行改进,利用该算法搜索得到该优化问题的全局解初值。再使用非线性规划算法优化的到燃料最优时的脉冲矢量。通过仿真验证了修改的布谷鸟算法的有效性。针对J2项摄动作用下拦截卫星和目标都采用连续小推力机动时的双边最优控制问题,建立含有J2项摄动时大地坐标系下空间飞行器的动力学方程,基于哈密顿函数得到了微分对策鞍点解时两星的最优控制输出。将双边最优控制问题转化为两点边值问题。针对该情况下两点边值的多解性和初值难以获取问题,采用启发式算法和非线性规划算法混合求解的方法获得精确解。对于控制角受限的情况,从二维平面拦截入手,得到了两星的最优推力角,并在三维情况中,利用几何方法得到了此时鞍点解对应的控制策略。仿真说明了该方法可以解决该类问题。在拦截末段我方卫星和目标同时机动时的追踪逃逸问题中,基于虚拟轨道给出了末端拦截的轨道方程。采用微分对策理论研究了拦截逃逸过程中双边最优的控制策略。对于无限时间拦截逃逸问题,将问题转化为代数黎卡提方程的求解,给出了两星控制输出不受幅值限制时的最优反馈控制和受到幅值限制时的次优控制策略。而针对有限时间控制问题,研究得到推力幅值限制时的次优反馈控制律。根据零控脱靶量导数与两星的控制输出的关系,得到最优反馈控制律,给出了拦截卫星减少燃料消耗时的反馈策略,仿真分析了上述方法的优缺点。在零控脱靶量的基础上,研究了多星合作时拦截卫星多目标函数反馈控制策略和单一目标合作时的反馈控制策略。对于拦截防御场景,在考虑防御卫星作用时间较短的情况下,构造包含防御卫星和目标卫星零控脱靶量的目标函数,利用极值条件得到反馈控制策略。通过分析防御卫星的攻击时间,利用几何方法,得到了拦截卫星对防御卫星躲避的同时进行目标追踪的最优控制方法。仿真分析了合作拦截的可靠性,快速性和防御卫星存在时拦截卫星反馈控制策略的优越性。
[Abstract]:At present, space technology develops rapidly and plays an important role in the national economy, life and military affairs. The research of space attack and defense technology is of great significance to the protection of national space resources. In this paper, an important way of space interception, orbit optimization and control of anti-satellite interception, is studied. The main contents are as follows: aiming at the problem of precise dynamics long-range multi-pulse interception, In this paper, the interception dynamics equation with various perturbation terms is established. Firstly, the perturbation term is ignored, and the intercept terminal constraint and intersection angle constraint are included in the objective function by using the feasible solution iteration method, and the fuel optimization problem with constraint processing term is obtained. The Cuckoo algorithm is improved and the initial global solution of the optimization problem is obtained by searching the algorithm. Then the nonlinear programming algorithm is used to optimize the pulse vector when the fuel is optimal. The validity of the modified Cuckoo algorithm is verified by simulation. Aiming at the bilateral optimal control problem of intercepting satellites and targets under the action of J2 perturbation, the dynamic equations of space vehicles in geodetic coordinate system with J2 perturbation are established. Based on Hamiltonian function, the optimal control output of two stars for saddle point solution of differential game is obtained. The two-sided optimal control problem is transformed into a two-point boundary value problem. In view of the multi-solution of two-point boundary value and the difficulty of obtaining initial value, the exact solution is obtained by combining heuristic algorithm and nonlinear programming algorithm. In the case of restricted control angle, the optimal thrust angle of two stars is obtained from two-dimensional plane interception, and the corresponding control strategy of saddle point solution is obtained by using geometric method in three-dimensional case. Simulation shows that this method can solve this kind of problem. In the problem of tracking and escaping during simultaneous maneuvering of our satellite and target at the end of interception, the orbit equation of terminal interception is given based on virtual orbit. In this paper, the differential game theory is used to study the bilateral optimal control strategy in the process of interception and escape. For the problem of infinite time interception and escape, the problem is transformed into the solution of algebraic Riccati equation, and the optimal feedback control and the suboptimal control strategy are given for the two-star control output without amplitude restriction. For the finite time control problem, the suboptimal feedback control law is obtained for the thrust amplitude limitation. According to the relation between the derivative of zero control miss distance and the control output of two stars, the optimal feedback control law is obtained, and the feedback strategy for intercepting satellite to reduce fuel consumption is given. The advantages and disadvantages of the above methods are analyzed by simulation. Based on the zero-control miss distance, the multi-objective function feedback control strategy and the feedback control strategy for multi-target cooperative interceptor satellite are studied. Considering the short time of defense satellites, the objective function including the zero control miss distance of defense satellite and target satellite is constructed, and the feedback control strategy is obtained by using extremum condition. By analyzing the attack time of the defense satellite and using the geometric method, the optimal control method for the interception satellite to evade the defense satellite and to track the target at the same time is obtained. The reliability, rapidity and superiority of feedback control strategy of cooperative interception are analyzed by simulation.
【学位授予单位】：哈尔滨工业大学
【学位级别】：硕士
【学位授予年份】：2015
【分类号】：V412.41;V448.2

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