空空导弹敏捷转弯的分段线性滑模控制设计  

Piecewise linear sliding mode control design for agile turn of air-to-air missile

作　　者：霍鑫[1] 彭继平[1] 马克茂[1] 张金鹏[2,3] 

机构地区：[1]哈尔滨工业大学控制与仿真中心,黑龙江哈尔滨150080 [2]中国空空导弹研究院,河南洛阳471009 [3]航空制导武器航空科技重点实验室,河南洛阳471009

出　　处：《系统工程与电子技术》2017年第10期2278-2284,共7页Systems Engineering and Electronics

基　　金：国家自然科学基金(61203191;61174001;61104193);航空科学基金(20140177006)资助课题

摘　　要：研究了空空导弹越肩发射敏捷转弯的复合执行机构姿态控制问题。针对一个直接侧向力装置安装在弹体尾部的导弹建立俯仰通道运动的数学模型,引入非光滑Lipschitz连续滑模控制,并利用非光滑分析的方法给出了分段线性滑模面的稳定性证明,然后采用气动舵控制作为等效控制,直接力控制作为切换控制的思想设计滑模控制律。数值仿真结果验证了分段线性滑模控制能改善常规线性滑模控制的性能,使得指令跟踪误差减小,复合控制效率提高。The problem of autopilot design during agile turn phase of over-the-shoulder launch is investigated, for air-to-air missile with blended actuators. A four-order dynamics is established for a missile under both low angle of attack condition and high angle of attack condition. Sliding mode control based on non-smooth Lipschitz continuous surface is introduced, and the stability proof of piecewise linear sliding mode is presented by u- sing non-smooth analysis. Elevator control and lateral force control are designed separately based on the idea of equivalent control and switch control. The numerical simulation results verify that compared with regular linear sliding mode control, piecewise linear sliding mode control has good performance in improving dynamic and reducing error, and is especially efficient for blended control

关 键 词：空空导弹 敏捷转弯 复合控制 非光滑分析 分段线性滑模控制 

分 类 号：TJ765[兵器科学与技术—武器系统与运用工程]