拦截空中飞行目标导航导引律优化设计仿真  

The Optimizing Simulation of Navigation Guidance Law to the Intercept Airflight Target

作　　者：程明阳[1] 马建伟[2] 李磊[2] CHENG Ming - yang MA Jian - wei LI Lei(China Airborne Missile Academy, Luoyang Henan 471000, China Institute of Information Engineering,Henan University of Science and Technology, Luoyang Henan 471023, China)

机构地区：[1]中国空空导弹研究院,河南洛阳471000 [2]河南科技大学,河南洛阳471023

出　　处：《计算机仿真》2017年第4期86-89,94,共5页Computer Simulation

基　　金：航空科学基金(20130142004);国家自然科学基金(61203047)资助项目

摘　　要：针对导弹末制导律设计过程中要求系统全局收敛的问题,基于局部稳定性理论设计了一种局部滑模变结构三维导引律。在设计过程中,先对局部稳定性理论进行了数学描述,上述理论通过对系统变量进行分析,将系统分解为两个子系统来设计。然后在只考虑视线角速率变化的情况下,假设目标机动加速度未知,结合滑模变结构控制设计控制律,提高了系统的鲁棒性。考虑到滑模开关项抖动对系统稳定性的影响,又采用自适应控制对结果进行估计,从而减小了脱靶量。仿真结果验证了上述方法的有效性。For the problems of the global convergence in designing terminal guidance of missile, a local convergence variable structure guidance law is proposed based on the local convergence theory. During the design process, the local stability theory was described at first. The system variables were analyzed with this method, and system was decomposed into two subsystems. Then under the condition of considering the change of angular speed of line - of - sight only, in case of unknown target maneuvering acceleration, combined with variable structure control designed controller, the robustness of the system was improved. Take into account the effects of sliding mode switch on system stability, adaptive control was used to estimate the results, and reduce the miss distance. The simulation results show the validity of this method.

关 键 词：局部收敛 滑模变结构 自适应控制 脱靶量 

分 类 号：TJ765.43[兵器科学与技术—武器系统与运用工程]