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Optimal Guidance Law to Maximize Terminal Velocity for Missiles with Impact Angle Constraint

Chao Ming Ruisheng Sun and Chuanjie Sun

哈尔滨工业大学学报（英文版）2016，Vol.23Issue(2)：72-78,7.

哈尔滨工业大学学报（英文版）2016，Vol.23Issue(2)：72-78,7.DOI:10.11916/j.issn.1005-9113.2016.02.011

Optimal Guidance Law to Maximize Terminal Velocity for Missiles with Impact Angle Constraint

Chao Ming ¹Ruisheng Sun ¹and Chuanjie Sun²

作者信息

1. School of Energy and Power Engineering, Nanjing University of Science and Technology, Nanjing 210094, China
2. Institute of Structural Mechanics, China Academy of Engineering Physics, Mianyang 621900,Sichuan, China
折叠

摘要

关键词

optimal guidance law/maximum terminal velocity/missiles/impact angle and miss distance constraints/analytical form

Key words

optimal guidance law/maximum terminal velocity/missiles/impact angle and miss distance constraints/analytical form

分类

航空航天

引用本文复制引用

Chao Ming,Ruisheng Sun,and Chuanjie Sun..Optimal Guidance Law to Maximize Terminal Velocity for Missiles with Impact Angle Constraint[J].哈尔滨工业大学学报（英文版）,2016,23(2):72-78,7.

基金项目

Sponsored by the National Security Academic Foundation （Grant No．11176012），and the CALT University Joint innovation Foundation （Grant No．CALT 201302）Corresponding author． E-mailsrscom＠163．com．（）

哈尔滨工业大学学报（英文版）

ISSN：1005-9113

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