现代防御技术2017，Vol.45Issue(6)：66-73,158,9.DOI:10.3969/j.issn.1009-086x.2017.06.012
带落角约束有限时间收敛滑模制导律
Finite Time Convergent Sliding Mode Guidance Law with Impact Angle Constraint
摘要
Abstract
A finitetime convergent sliding mode guidance law with terminal impact angle constraint is presented using the finite time convergence control theory.It is rigorously proved that the states of the guidance system converge to a sliding mode in finite time.The line of sight (LOS) angular rate also converges to zero in finite time and the flightpath angle will meet the terminal impact angle requirement.The guidance law is extended to the case of dynamic delay of autopilot,considering the dynamics of the missile autopilot as a firstorder lag.Simulation results show that the guidance law is effective.关键词
反坦克导弹/滑模制导律/落角约束/有限时间收敛/自动驾驶仪/变开关系数法Key words
antitank missile/sliding mode guidance law/impact angle constraint/finite time convergence/autopilot/variable switching coefficient method分类
军事科技引用本文复制引用
李鹏程..带落角约束有限时间收敛滑模制导律[J].现代防御技术,2017,45(6):66-73,158,9.
