【作者】 李玉玲；

【导师】 赵琳；

【作者基本信息】 哈尔滨工程大学 ， 控制科学与工程， 2018， 硕士

【摘要】 空间技术的发展极为迅速,在现代化战争中空间平台的作用愈来愈显著。各国都在大力地研发空间技术和空间武器,以提高本国在信息化战争中的实力。本课题以空间攻防中采用反卫星拦截为背景,对拦截卫星的攻击轨道规划及控制方法展开研究。课题的研究内容主要有以几个方面:首先,针对“单-单”态势下的拦截卫星攻击轨道优化问题,以配备脉冲火箭的脉冲推力卫星和配备电推进的连续推力卫星为对象,利用遗传算法对这两种机动方式的拦截卫星攻击轨道优化问题展开研究。建立目标卫星的动态防御模型,针对拦截卫星轨道机动特点,将脉冲式推力模型转化成拦截卫星特征速度;将连续小推力模型简化为拦截卫星的推进系统在参考轨道坐标系中姿态角,设计了一种可变长实数遗传编码。将遗传算法的遗传算子和适应度函数进行优化设计,并且仿真验证遗传算法的有效性。其次,针对“多-多”态势下的拦截卫星协同攻击轨道优化问题,提出了一种基于自适应遗传算法的多星协同攻击轨道规划方法。采用拦截卫星团队预计抵达目标位置所需时间为协同变量;以攻击轨道的安全性为协同约束;以路径代价函数为协同函数。实现多拦截卫星同时击中目标,提高整体作战效能及任务成功率。并且将遗传算法的运行参数及遗传算子进行了优化设计,增强算法的自适应能力。仿真说明了该方法的能够满足拦截任务的要求。再次,针对目标机动逃逸的拦截卫星攻击轨道优化问题,提出了一种协同进化算法解决固定对抗时间下两航天器的三维空间追逃问题。根据纳什均衡思想,将复杂的双边最优规划问题转化为对纳什均衡点的搜索,使系统模型得到简化。以两航天器的相对距离作为支付函数,建立算法的适应度函数,对协同算子进行改进。分别对共面轨道和异面轨道下两航天器追逃路径进行仿真分析,同时得到追逃过程中二者控制加速度随时间的变化情况。仿真得出,当对抗双方为共面轨道时,其最优的追逃策略仍然在共面轨道上产生。最后,当采用电磁干扰等方式摧毁目标卫星通讯系统时,需使拦截卫星停靠在目标卫星附近,因此,针对持续悬停绕飞干扰轨道规划问题,对悬停轨道构型保持的控制力方程及燃耗估计进行分析,在常值推力作用下利用幂级数法对系统近似求解。在悬停距离一定的条件下,以燃耗最优为原则,利用遗传算法规划出航天器悬停的最佳位置,从而计算构型保持所需的控制力。以相对位置和相对速度为状态量,建立悬停过程中的误差状态方程,在此开环控制的基础上,利用LQR控制设计反馈控制律,实现悬停保持过程中两航天器的相对位置及相对速度的精确控制。仿真验证了本文所提出的悬停轨道控制方法具有一定的抗干扰性。更多还原

【Abstract】 The development of space technology is extremely rapid,and the role of space platform in information warfare is becoming more and more obvious.All countries are vigorously developing space technology and space weapons in order to enhance their own status in the information war.In this paper,the space attack and defense in the use of anti-satellite interception as the background,to intercept satellite attack orbit planning and control methods are studied.First of all,aiming at the orbital optimization problem of intercepting satellite attack under the "single-single" situation,this paper uses the impulsive satellite equipped with pulse rocket and continuous thrust satellite equipped with electric propulsion as the object to orbit optimization problem.The dynamic defense model of the target satellite is established.According to the characteristics of the orbital,the impulsive thrust model is transformed into the characteristic velocity of the intercepting satellite.The continuous small thrust model is simplified as the attitude angle of the propulsion system of the intercepting satellite in the reference orbit coordinate system.A variable length real number genetic code is designed.The genetic algorithm genetic algorithm and fitness function are optimized,and the feasibility of genetic algorithm is verified by simulation.Secondly,in order to solve the orbiting problem of intercepting satellite coordinated attacks in the "multi-multi" situation,a multi-star cooperative orbit planning method based on adaptive genetic algorithm is proposed.The time required for the intercepting satellite team to arrive at the target location is assumed to be a co-variable;the security of the attacking orbit is a collaborative constraint;and the path cost function is a synergistic function.Achieve multiple interception of satellites hit the target at the same time,improve the overall combat effectiveness and mission success rate.In addition,the operation parameters and genetic operators of genetic algorithm are optimized,and the adaptive ability of the algorithm is improved.Simulation shows that this method can meet the requirements of interception tasks.Thirdly,aiming at the orbit optimization problem of intercepting satellites with maneuvering escape,a co-evolutionary algorithm is proposed to solve the problem of three-dimensional space pursuit of two spacecraft with fixed confrontation time.According to Nash equilibrium,the complicated bilateral optimal programming problem can be transformed into a search for Nash equilibrium,which simplifies the system model.Taking the relative distance of two spacecraft as the payment function,the fitness function of the algorithm is established and the cooperative operator is improved.The trajectory of two spacecraft escape routes under coplanar orbits and the orbital orbits are simulated and analyzed respectively.At the same time,the changes of the two controlled accelerations over time are obtained.Simulation results show that when the two opposing sides are coplanar orbit,the optimal pursuit strategy is still generated in the coplanar orbit.Finally,when using electromagnetic interference to destroy the target satellite communication system,it is necessary to stop the intercepting satellite near the target satellite.In view of the orbit planning problem of sustained hovering orbiting interference and the control force equation and fuel consumption estimation of hovering orbit configuration,the system is approximated by the power series method under the constant thrust.Under the condition of a certain hovering distance,the optimal position of spacecraft hovering is calculated by the genetic algorithm based on the principle of optimal fuel consumption,so as to calculate the control force needed to maintain the configuration.Based on the open-loop control,the feedback control law is designed by using LQR control to realize the relative position of the two spacecraft during the hovering and accurate control of relative speed.The simulation verifies that the hovering orbit control method proposed in this paper has certain anti-interference ability.更多还原