基于偏置比例导引的落角约束滑模制导律  

Sliding mode guidance law with impact angle constraint based on bias proportional navigation

作　　者：王晓海 孟秀云[1] 周峰[2] 邱文杰 WANG Xiaohai;MENG Xiuyun;ZHOU Feng;QIU Wenjie(School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, China;Beijing Aerospace Automatic Control Research Institute, Beijing 100039, China)

机构地区：[1]北京理工大学宇航学院,北京100081 [2]北京航天自动控制研究所,北京100039

出　　处：《系统工程与电子技术》2021年第5期1295-1302,共8页Systems Engineering and Electronics

摘　　要：为实现导弹以一定落角攻击装甲车辆等地面移动目标,应用变结构控制理论,推导基于偏置比例导引的落角约束滑模制导律,并基于李雅普诺夫稳定性理论设计了参数自适应的幂次趋近律。考虑目标速度难以测量的问题,引入扩张状态观测器(extended states observer,ESO)对目标速度进行估计。仿真结果表明,所设计的制导律能够以要求的落角准确打击静止目标与机动目标,且需用法向过载和命中点附近的法向过载较小,弹道后段较为平直。In order to make the missile attack ground moving targets such as armored vehicles at a certain impact angle,the variable structure control theory is applied to derive the sliding mode guidance law with impact angle constraint based on the bias proportional guidance,and parameter adaptive power reaching law is designed based on the Lyapunov stability theory.Considering the difficulty of measuring for target speed,the extended states observer(ESO)is introduced to estimate the target speed.Simulation results show that the designed guidance law can accurately hit stationary targets and maneuvering targets with required impact angle,and need less maximum required normal overload and less normal overload near the hit point,and the rear part of trajectory is relatively straight.

关 键 词：偏置比例导引律 滑模变结构 落角约束 扩张状态观测器 机动目标 

分 类 号：TJ765[兵器科学与技术—武器系统与运用工程]