【作者】 王国梁；

【导师】 郑建华；

【作者基本信息】 中国科学院研究生院（空间科学与应用研究中心） ， 飞行器设计， 2010， 硕士

【摘要】 随着战争格局的变化,空间拦截越来越受到各国的重视。拦截过程燃料消耗的多少很大程度上决定了拦截任务是否能够圆满完成,因此拦截轨道的优化和控制具有重要的意义。本文重点研究了空间拦截轨道优化和初始段、末端控制以及悬停问题,并开发了相应的设计软件。对于空间拦截轨道优化,采用非线性规划方法进行优化和用主矢量法进行优化。利用非线性规划方法研究了多脉冲最优拦截问题。考虑地球扁率J2摄动影响,建立普遍适用的空间拦截数学模型。在此基础上建立了用于求解多脉冲最优拦截的非线性规划模型,并对双脉冲、三脉冲固定时间拦截轨道进行优化,得到了最优速度增量的大小、方向和作用时间,最后对单脉冲、双脉冲和三脉冲在不同时间的优化结果进行了比较,验证了此方法的有效性。利用主矢量原理判断在固定时间内近距离脉冲拦截轨道速度增量是否最优,并对非最优情况提出了优化策略。根据轨道动力学理论,建立了近距离空间拦截轨道的数学模型。根据主矢量理论给出了判断冲量拦截是否最优的理论依据,并给出了优化方法。对不同时间的空间拦截速度增量进行仿真比较分析,提出了速度增量最优的拦截策略。对于空间拦截控制,利用微分修正法进行初始控制。在之前建立的普遍适用的空间拦截数学模型的基础上,基于状态转移矩阵不断迭代求解得出初始拦截所需的速度增量的大小和方向。采用这种控制方法能够补偿轨道摄动对拦截脱靶量的影响,并通过仿真验证了此方法的有效性。利用准滑模控制进行末端控制,针对空间拦截的非线性模型,考虑到发动机的实际工作特性,基于准滑模控制思想,设计了一种易于工程实现又可精度可控的控制律,克服了滑模控制的抖振问题,并对扰动有较强的鲁棒性。对圆轨道悬停问题进行了研究。给出了卫星悬停的轨道动力学模型,不考虑地球扁率J2摄动影响,通过在一段时间内对轨道实施连续有限推力控制,使得卫星运行在新的轨道上,实现对目标卫星的悬停。通过数学仿真,验证了在一段时间内对目标卫星实现悬停的可行性。更多还原

【Abstract】 As the war situation changed, more and more country pay attention to space interception. Whether the interception mission successfully completed is depended on the amount of fuel consumption in the interception process, thus orbit optimization and control is of great significance. This paper focuses on orbit optimization, initial control, terminal control and hovering, based on above corresponding software was developed.Nonlinear programming and primer vector theory was used for orbit optimization. Optimal multiple-impulse interception was studied by nonlinear programming, considering the J2 perturbation. Based on normal Interception model, the nonlinear programming model was set up. Using this method,the times , magnitudes and directions of three-impulse Interception with time constraint were obtained. Finally, optimal results were compared for one-impulse interception, two-impulse interception and three-impulse interception with different time constrain. The simulation results show that the initial control is rational and efficient. Whether the fuel consumption was optimal in time-fixed interception was mainly studied by primer vector theory. Based on orbit dynamic theory,the close interception model was set up. According to primer vector theory, whether the interception optimal and how to optimize was given. Finally, a great lot of simulations were done to investigate the fuel consumption with different time and impulses restraint.Initial control for space Interception was studied by differential correction method. Based on the mathematical model and the state transition matrix for orbit Interception, the magnitude and direction of velocity were attained. The miss distance caused by the effects of perturbation was compensated in this initial control. The simulation results show that the initial control is rational and efficient. Terminal control for space Interception was studied by quasi-sliding mode control. For the nonlinear models of the space interception and characteristics of the engines terminal guidance laws were proposed based on quasi-sliding mode control theory. The guidance law is easy to be realized in engineering. Numerical simulation is carried out with available and satisfactory results.Circular orbit of satellite hovering over space target was studied. Dynamics analysis of hovering orbit was presented, not considering J2 perpetual. By implementing a continuous pulse thrust control, the satellite was kept in a period of time on a new hovering orbit other than Kepler orbit. Finally, numerical simulation shows that it was feasible to hover over space targets in a period of time.更多还原