自旋弹道导弹动力学与控制

Dynamic and Control of Spinning Ballistic Missile

弹道导弹主动段自旋飞行是一种新的构想,旨在对抗激光武器拦截,实现主动段突防。导弹自旋飞行引起的运动耦合、控制耦合及其它效应可能导致弹体失稳,实现较强耦合作用下弹道导弹自旋飞行姿态稳定控制是亟待解决的问题。文中建立了自旋弹道导弹的动力学和控制频域模型,分析了几种主要耦合作用对系统的影响,将系统开环传递矩阵分解为动力学耦合和控制耦合两部分,结合古典和现代频域方法进行了姿态控制系统设计研究,采用根轨迹方法分析了运动耦合对自旋弹道导弹性能的影响,用动态预补偿技术实现姿态解耦控制。仿真结果表明,方法有效改善了低滚速较强耦合条件下自旋弹道导弹姿态控制性能。

Spin flight of Ballistic Missile in boost phase is a new idea in order to penetrate laser＇ s interception. Spinning missiles may be unstable due to dynamic and control coupling, It is a crucial question to stabilize missiles under stronger interactions. Dynamic and control frequency nodel of spinning ballistic missile were developed for the analysis of several interactions. Based on the separation of dynamic model and control model, design of attitude control system was studide by classic and modem frequency theory. Root locus was used to analyze the affections of motion interactions. Dynamic pseudodiagonalisation was used for uncoupling control. Simulation indicates that the performance of attitude control under low spinning rate and stronger interactions is improved effectively.