国防科技大学学报Issue(3)：136-141,6.DOI:10.11887/j.cn.201503022
零控脱靶量有限时间收敛制导律
Finite time convergent zero-effort miss guidance law
摘要
Abstract
A finite time convergent zero-effort miss guidance law considering the dynamics of the missile autopilot is proposed for the problems of intercepting high speed and maneuvering targets.The three-dimensional relative geometric relation between the missile and target is decoupled. A new three-dimensional zero-effort miss guidance model incorporating the dynamics of the missile autopilot is derived.Based on the adaptive sliding mode control theory and the finite time stability theory,the zero-effort miss in pitch plane and yaw plane is chosen as the sliding mode surfaces,and then the three-dimensional adaptive sliding mode guidance with finite time convergent zero-effort miss is proposed.The guidance law’ s stability and finite time convergence ability are analyzed and proved.Simulation results show that the proposed guidance law can achieve the finite time convergence of the zero-effort miss,and has better guidance precision compared with the proportional guidance law.关键词
零控脱靶量/自动驾驶仪/有限时间收敛/制导律Key words
zero-effort miss/autopilot/finite time convergence/guidance law分类
军事科技引用本文复制引用
雷虎民,张旭,董飞篧,李炯..零控脱靶量有限时间收敛制导律[J].国防科技大学学报,2015,(3):136-141,6.基金项目
航空科学基金资助项目 （）
