顺轨拦截模式剩余飞行时间估计方法

doi:10.7527/S1000-6893.2015.0107

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顺轨拦截模式剩余飞行时间估计方法

李辕¹, 闫梁², 赵继广³, 陈景鹏²

1. 装备学院研究生院, 北京 101416;
2. 装备学院航天装备系, 北京 101416;
3. 装备学院科研部, 北京 101416

收稿日期:2014-05-04 修回日期:2015-04-20 出版日期:2015-09-15 发布日期:2015-05-12
通讯作者: 闫梁男, 博士, 工程师。主要研究方向: 航天任务分析与设计。 Tel: 010-66364196 E-mail: yanliangbj@163.com E-mail:yanliangbj@163.com
作者简介:李辕男, 博士研究生。主要研究方向: 航天任务分析与设计。 Tel: 010-66364196 E-mail: Bartholomew_lee@hotmail.com;赵继广男, 博士, 教授, 博士生导师。主要研究方向: 航天装备总体。 Tel: 010-66364366 E-mail: haofangshi@163.com
基金资助:
国家"863"计划

Method of time-to-go estimation for head-pursuit interception mode

LI Yuan¹, YAN Liang², ZHAO Jiguang³, CHEN Jingpeng²

1. Department of Postgraduate, Academy of Equipment, Beijing 101416, China;
2. Department of Spaceflight Equipment, Academy of Equipment, Beijing 101416, China;
3. Department of Scientific Research, Academy of Equipment, Beijing 101416, China

Received:2014-05-04 Revised:2015-04-20 Online:2015-09-15 Published:2015-05-12
Supported by:
National High-tech Research and Development Program of China

摘要/Abstract

摘要：

匹配顺轨和逆轨拦截模式的估计方法是精确计算剩余飞行时间(TGO)的必要条件,适用于逆轨拦截模式的TGO估计方法并不适于顺轨拦截模式。为此,针对顺轨拦截模式,分别提出了拦截机动/非机动目标的TGO估计方法。通过对线性制导方程的变形求解出了拦截弹的飞行弧长,并根据预测的碰撞点位置求得了TGO估计的解析式。该求解方法通用性强,适用于弹道成型制导律的TGO估计。以负比例(RPN)和扩展RPN(ARPN)为制导框架,与经典方法进行对比,所提出的TGO估计方法精确度高,能够有效提高导弹的制导性能。

关键词: 导弹, 目标跟踪, 制导律, 剩余飞行时间估计, 顺轨拦截, 机动目标

Abstract:

The estimation method suiting head-on and head-pursuit interception mode is the necessary condition of accurate time-to-go (TGO) calculation, and the method of TGO estimation is appropriate for head-on engagement but not for head-pursuit engagement. Therefore, the methods of TGO estimation for the interception of nonmaneuvering and maneuvering targets are proposed in head-pursuit interception mode. Through transforming the linear guidance equation, the flight arc of interceptor is solved; according to the predicted position of impact point, the analytic expressions of TGO estimation are obtained. The idea of TGO method has wide versatility and can be used in TGO estimation of trajectory shaping guidance. Simulations are carried out with classical method for verifying its validity based on retro-proportional-navigation (RPN) and augment RPN (ARPN). Compared with the classical method, it is demonstrated that the proposed TGO estimation method has high accuracy and is able to improve the guidance performance effectively for missile.

Key words: missiles, target tracking, guidance law, time-to-go estimation, head-pursuit interception, maneuvering targets

中图分类号:

李辕, 闫梁, 赵继广, 陈景鹏. 顺轨拦截模式剩余飞行时间估计方法[J]. 航空学报, 2015, 36(9): 3082-3091.

LI Yuan, YAN Liang, ZHAO Jiguang, CHEN Jingpeng. Method of time-to-go estimation for head-pursuit interception mode[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2015, 36(9): 3082-3091.

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E-mail：hkxb@buaa.edu.cn

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顺轨拦截模式剩余飞行时间估计方法

Method of time-to-go estimation for head-pursuit interception mode

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