基于偏置比例导引的落角约束滑模制导律

doi:10.12305/j.issn.1001-506X.2021.05.17

系统工程与电子技术 ›› 2021, Vol. 43 ›› Issue (5): 1295-1302.doi: 10.12305/j.issn.1001-506X.2021.05.17

基于偏置比例导引的落角约束滑模制导律

王晓海^1,*(), 孟秀云¹(), 周峰²(), 邱文杰²()

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

收稿日期:2020-07-23 出版日期:2021-05-01 发布日期:2021-04-27
通讯作者: 王晓海 E-mail:wxhumi@163.com;mengxy@bit.edu.cn;flair2000@163.com;qwjonmxg@163.com
作者简介:王晓海(1996—), 男, 硕士研究生, 主要研究方向为飞行器制导与控制、飞行器航迹规划。E-mail: wxhumi@163.com|孟秀云(1963—), 女, 教授, 博士, 主要研究方向为飞行器导航制导与控制、系统仿真。E-mail: mengxy@bit.edu.cn|周峰(1980—), 男, 高级工程师, 博士, 主要研究方向为系统建模与仿真技术研究。E-mail: flair2000@163.com|邱文杰(1989—), 男, 工程师, 博士, 主要研究方向为弹道优化、飞行器制导控制与仿真。E-mail: qwjonmxg@163.com

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

Xiaohai WANG^1,*(), Xiuyun MENG¹(), Feng ZHOU²(), Wenjie QIU²()

1. School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, China
2. Beijing Aerospace Automatic Control Research Institute, Beijing 100039, China

Received:2020-07-23 Online:2021-05-01 Published:2021-04-27
Contact: Xiaohai WANG E-mail:wxhumi@163.com;mengxy@bit.edu.cn;flair2000@163.com;qwjonmxg@163.com

摘要/Abstract

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。

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

Abstract:

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.

Key words: bias proportional navigation, sliding mode variable structure, impact angle constraint, extended states observer (ESO), maneuvering target

中图分类号:

TJ765

王晓海, 孟秀云, 周峰, 邱文杰. 基于偏置比例导引的落角约束滑模制导律[J]. 系统工程与电子技术, 2021, 43(5): 1295-1302.

Xiaohai WANG, Xiuyun MENG, Feng ZHOU, Wenjie QIU. Sliding mode guidance law with impact angle constraint based on bias proportional navigation[J]. Systems Engineering and Electronics, 2021, 43(5): 1295-1302.

图/表 8

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场景	制导律
场景	制导律1	制导律2	本文制导律
场景1	-59.87	-60.00	-60.01
场景2	-59.94	-50.75	-59.92
场景3	-69.76	-64.47	-69.29
场景4	-59.91	-63.67	-60.16

场景	制导律
场景	制导律1	制导律2	本文制导律
场景1	0.030	0.000	0.012
场景2	0.015	0.001	0.008
场景3	0.008	0.069	0.042
场景4	0.027	0.081	0.046

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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

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