导弹复合控制系统的多目标优化设计

建立了具有气动力/直接侧向力混合控制的导弹动力学模型,采用反馈加前馈控制结构,设计了导弹复合控制系统,实现了气动力/直接侧向力的解耦控制。建立了导弹复合控制系统性能代价函数,并采用进化策略实现了复合控制系统参数的多目标优化。仿真结果表明:进化策略收敛速度快,优化以后的导弹复合控制系统具有很好的快速大机动跟踪能力,且直接力控制有效补偿了气动面控制效益低下和非最小相位系统造成的响应延迟。     

地基雷达探测方位对目标识别的影响研究

导弹防御系统的地基X波段雷达和海基X波段雷达是进行目标识别的主要传感器,它们只有在探测到目标以后才能通过记录目标的相关特性,进行目标识别。由于雷达探测的方向不同,探测到的目标散射截面也不同,因此,在导弹突防过程中,可通过调整弹头的飞行姿态,改变雷达探测方位,从而最大限度地减小目标散射截面,最终影响雷达识别目标的效果。     

弹用涡喷发动机的动态仿真研究

采用变比热容的方法及容积积累模型,建立了调节系统及发动机主要部件的动力学方程,对某弹用涡喷发动机的过渡态进行了模拟仿真。结果表明：该发动机转速特性典型,加速性好,仿真数模及程序有较好的可信度。此外,还分析了涡喷发动机的仿真特点和仿真中必须解决的关键问题。     

导弹敏捷转弯段的新型非奇异终端滑模控制

针对具有快时变性、不确定性、强非线性和系统初始状态远离平衡点等特点的敏捷导弹的直接力/气动力复合控制律设计问题,提出了一种新型非奇异终端滑模控制方法。为缩短到达平衡态的时间,设计了一种组合非奇异终端滑模面,提高了系统状态在滑模面上的收敛速度,设计了改进的变系数双幂次趋近律,提高了系统状态到达滑模面的速度,并利用扩张状态观测器实时估计系统内外扰动,消除了观测误差对系统造成的干扰,抑制了抖振。最后,证明了所提方法的有限时间收敛特性,通过仿真对比校验了所提方法的有效性。     

Optimal three-dimensional impact time guidance with seeker’s field-of-view constraint

This paper proposes a new three-dimensional optimal guidance law for impact time control with seeker’s Field-of-View (FOV) constraint to intercept a stationary target. The proposed guidance law is devised in conjunction with the concept of biased Proportional Navigation Guidance (PNG). The guidance law developed leverages a nonlinear function to ensure the boundedness of velocity lead angle to cater to the seeker’s FOV limit. It is proven that the impact time error is nullified in a finite-time under the proposed method. Additionally, the optimality of the biased command is theoretically analyzed. Numerical simulations confirm the superiority of the proposed method and validate the analytic findings.     

Distributed cooperative guidance for multiple missiles with fixed and switching communication topologies

This study investigates cooperative guidance problems for multiple missiles with fixed and switching directed communication topologies.A two-step guidance strategy is proposed to realize the simultaneous attack.In the first step,a distributed cooperative guidance law is designed using local neighboring information for multiple missiles to achieve consensus on range-to-go and leading angle.The second step begins when the consensus of multiple missiles is realized.During the second step,multiple missiles disconnect from each other and hit the target using the proportional navigation guidance law.First,based on the local neighboring communications,a sufficient condition for multiple missiles to realize simultaneous attack with a fixed communication topology is presented,where the topology is only required to have a directed spanning tree.Then,the results are extended to the case of switching communication topologies.Finally,numerical simulations are provided to validate the theoretical results.     

基于Lyapunov稳定性理论的导弹电动舵机控制算法研究

基于Lyapunov稳定性理论,提出了导弹电动舵机的一种自适应控制算法。以Lyapunov稳定性判据为前提,保证算法的稳定性。综合自适应控制算法与经典比例积分微分（PID）控制算法,给出了模型参考自适应控制（MRAC）与分离比例积分（PI）复合控制。仿真结果表明：由该控制算法可在考虑舵机铰链力矩等因素变化条件下,获得到良好的输出跟踪性能和鲁棒性。     

Ideal proportional navigation for exoatmospheric interception

Ideal proportional navigation (IPN) is a natural choice for exoatmospheric interception for its mighty capture capability and ease of implementation. The closed-form solution of two- dimensional ideal proportional navigation was conducted in previous public literature, whereas the practical interception happens in the three-dimensional space. A novel set of relative dynamic equations is adopted in this paper, which is with the advantage of decoupling relative motion in the instantaneous rotation plane of the line of sight from the rotation of this plane. The dimension-reduced IPN is constructed in this instantaneous plane, which functions as a three-dimensional guidance law. The trajectory features of dimension-reduced IPN are explored, and the capture regions of dimension-reduced IPN with limited acceleration against nonmaneuvering and maneuvering targets are analyzed by using phase plane method. It is proved that the capture capability of IPN is much stronger than true proportional navigation (TPN), no matter the target maneuvers or not. Finally, simulation results indicate that IPN is more effective than TPN in exoatmospheric interception scenarios.     

导弹系统贮存可靠性预测的数学模型

本文研究了贮存环境对导弹系统贮存可靠性的影响问题。提出了合理的数学模型。在产品的固有贮存寿命为指数分布情况下，得到了在定期检测修复条件下，产品的贮存寿命分布。并以此为依据研究了贮存寿命数据的统计方法。作为一个实例分析，本文对于导弹系统的某部件给出了实用的贮存可靠度预测模型。所用估计方法简单易行，有较强的实用性。数值结果表明预测模型有较好的预测精度     

伸缩弹翼巡航导弹气动外形优化研究

基于一种伸缩弹翼改变巡航导弹外形的概念,提出超声速巡航与亚声速盘旋相结合的飞行任务,使用Missile Datcom作为气动计算的工具,分别对固定翼、两级伸缩翼和三级伸缩翼的外形参数进行了优化,使三种不同弹翼导弹完成相同飞行任务的燃料消耗分别最小,优化方法选取遗传算法与模式搜索法相结合的混合优化策略.优化结果显示,两级、三级伸缩翼巡航导弹相对固定翼巡航导弹燃料消耗量分别减少7.8%和12%,表明伸缩弹翼有效提高了巡航导弹在整个飞行任务中的气动性能.