火力与指挥控制2026，Vol.51Issue(7)：33-40,8.DOI:10.3969/j.issn.1002-0640.2026.07.006
面向高超声速目标的攻击角约束预设性能制导律
Prescribed Performance Guidance Law with Impact Angle Constraint for Hypersonic Targets
摘要
Abstract
To address the requirement of head-on interception against hypersonic vehicles,this paper proposes a sliding mode guidance law with an impact angle constraint based on prescribed performance control.First,sliding mode control is combined with prescribed performance control.By introducing an appointed-time prescribed performance function,the tracking error is ensured to converge to a preset accuracy within the appointed time and predefined performance bounds.Then,an appointed-time reaching law is adopted to ensure the sliding manifold converges to zero in a fixed appointed time.Finally,an extended state observer is employed to estimate unknown target maneuver information,ensuring that the estimation error converges within the prescribed time.Simulation results verify the effectiveness and superiority of the proposed guidance law.关键词
高超声速飞行器/逆轨拦截/攻击角度约束/指定时间预设性能控制/滑模控制Key words
hypersonic vehicle/head-on interception/impact angle constraint/appointed-time prescribed performance control/sliding mode control分类
军事科技引用本文复制引用
付主木,夏明佶,王志凯,高颂,陶发展..面向高超声速目标的攻击角约束预设性能制导律[J].火力与指挥控制,2026,51(7):33-40,8.基金项目
航空科学基金(20220001042002,20240001042001) （20220001042002,20240001042001）
河南省科技攻关项目(242102221025) （242102221025）
河南省高等学校重点科研基金资助项目(24B590001) （24B590001）
