基于纯比例导引的拦截碰撞角约束制导策略

黎克波; 廖选平; 梁彦刚; 李超勇; 陈磊

doi:10.7527/S1000-6893.2020.24277

航空学报 >

2020 , Vol. 41 >Issue S2: 724277 - 724277

DOI: https://doi.org/10.7527/S1000-6893.2020.24277

基于纯比例导引的拦截碰撞角约束制导策略

黎克波 ,
廖选平 ,
梁彦刚 ,
李超勇 ,
陈磊

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1. 国防科技大学空天科学学院, 长沙 410073;
2. 浙江大学电气工程学院, 杭州 310027;
3. 军事科学院国防科技创新研究院, 北京 100071

收稿日期: 2020-04-20

修回日期: 2020-05-15

网络出版日期: 2020-06-04

基金资助

国家自然科学基金（61690210，61690213）；湖南省自然科学基金（2019JJ50736）

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Guidance strategy with impact angle constraints based on pure proportional navigation

LI Kebo ,
LIAO Xuanping ,
LIANG Yan'gang ,
LI Chaoyong ,
CHEN Lei

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1. College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China;
2. College of Electrical Engineering, Zhejiang University, Hangzhou 310027, China;
3. National Innovation Institute of Defense Technology, Academy of Military Sciences, Beijing 100071, China

Received date: 2020-04-20

Revised date: 2020-05-15

Online published: 2020-06-04

Supported by

National Natural Science Foundation of China (61690210,61690213); Natural Science Foundation of Hunan Province(2019JJ50736)

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摘要

拦截碰撞角约束制导是当前导弹制导研究的关键问题之一。首先基于理想比例导引（IPN）律拦截非机动目标的解析解，推导了纯比例导引律（PPN）拦截固定目标的解析解，得到了弹目相对距离、制导指令加速度和导弹前置角的显示表达式，并进一步得到了拦截碰撞角与弹目相对运动状态和比例导引系数之间的解析表达式。其次，基于该解析表达式，提出了基于PPN的拦截碰撞角约束制导策略（PPNIACG），并探讨了在铅垂面内进行落角约束打击和水平面内进行拦截碰撞角约束打击的2种实现方式。最后，以弹道成型制导律（TSG）和最优碰撞角约束制导律（OIACG）为参考，通过数值仿真算例，对PPNIAC的拦截性能进行了对比分析，验证了所提出制导策略的有效性和正确性。

关键词： 导弹制导; 纯比例导引律; 拦截碰撞角约束; 固定目标; 解析解

本文引用格式

黎克波 , 廖选平 , 梁彦刚 , 李超勇 , 陈磊 . 基于纯比例导引的拦截碰撞角约束制导策略[J]. 航空学报, 2020 , 41(S2) : 724277 -724277 . DOI: 10.7527/S1000-6893.2020.24277

Abstract

Guidance law design with impact angle constraints is one of the key research problems in the missile guidance community. In this paper, the analytical solution of the Pure Proportional Navigation (PPN) guidance law against stationary targets is deduced based on that of the Ideal Proportional Navigation (IPN) guidance law against non-maneuvering targets. The analytical expressions of the relative range, the commanded acceleration, and the missile lead angle are obtained, followed by an introduction of the relationship among the final impact angle, the relative states, and the navigation gain of the PPN. Based on this relationship, the Guidance strategy with Impact Angle Constraints based on the PPN (PPNIACG) is proposed with two applications of this guidance strategy, i.e., interceptions with impact angle constraints in the vertical and horizontal planes, discussed. After that, taking the Trajectory Shaping Guidance (TSG) and the Optimal Impact Angle Control Guidance (OIACG) as reference, we demonstrate the interception performance of the PPNIACG through numerical simulation examples, revealing the effectiveness and robustness of the proposed PPNIACG for guiding missiles to hit the target with impact angle constraints.

Key words： missile guidance; pure proportional navigation; impact angle constraints; stationary targets; analytical solutions

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