Please submit manuscripts in either of the following two submission systems

    ScholarOne Manuscripts

  • ScholarOne

    • 勤云稿件系统

  • 登录

Search by Issue

  • 2024 Vol.31
  • 2023 Vol.30
  • 2022 Vol.29
  • 2021 Vol.28
  • 2020 Vol.27
  • 2019 Vol.26
  • 2018 Vol.25
  • 2017 Vol.24
  • 2016 vol.23
  • 2015 vol.22
  • 2014 vol.21
  • 2013 vol.20
  • 2012 vol.19
  • 2011 vol.18
  • 2010 vol.17
  • 2009 vol.16
  • No.1
  • No.2

Search by Keywords

  • Search by Title
  • Search by Keywords
  • Search by Abstract
  • Search by Author's Chinese Name
  • Search by Author's English Name
  • Search by Fund

News & AnnouncementMORE

Supervised by Ministry of Industry and Information Technology of The People's Republic of China Sponsored by Harbin Institute of Technology Editor-in-chief Yu Zhou ISSNISSN 1005-9113 CNCN 23-1378/T

期刊网站二维码
微信公众号二维码
Related citation:Chao Ming,Ruisheng Sun.Optimal Guidance Law to Maximize Terminal Velocity for Missiles with Impact Angle Constraint[J].Journal of Harbin Institute Of Technology(New Series),2016,23(2):72-78.DOI:10.11916/j.issn.1005-9113.2016.02.011.
【Print】   【HTML】   【PDF download】   【View/Add Comment】  【Download reader】  【 Close 】
←Previous|Next→ Back Issue    Advanced Search
This paper has been: browsed 2976times   downloaded 2506times 本文二维码信息
码上扫一扫！
Shared by: Wechat More
Font:larger+|default|smaller-
Optimal Guidance Law to Maximize Terminal Velocity for Missiles with Impact Angle Constraint
Author NameAffiliation
Chao Ming School of Energy and Power Engineering, Nanjing University of Science and Technology, Nanjing 210094, China 
Ruisheng Sun School of Energy and Power Engineering, Nanjing University of Science and Technology, Nanjing 210094, China 
Abstract:
In this paper, an optimal guidance law for missiles with impact angle and miss distance constraints is proposed to achieve the maximal terminal velocity. The normal acceleration command that includes the time-varying coefficients is introduced to satisfy the desired impact angle as well as zero miss distance according to the geometric relation and relative motion parameters between missile and target. The problem is formulated as an optimal control problem by defining the angle of velocity error and flight-path angle as state variables and maximizing a performance index of the terminal velocity. The analytical form of the proposed guidance law is obtained as the solution of the optimal control problem combining optimal control theory and numerical value computation method. Nonlinear simulations of various situations demonstrate the performance and feasibility of the proposed optimal guidance law.
Key words:  optimal guidance law  maximum terminal velocity  missiles  impact angle and miss distance constraints  analytical form
DOI：10.11916/j.issn.1005-9113.2016.02.011
Clc Number:V11 TJ765.3
Fund:

LINKS

Copyright © The Editorial Department of Journal of Harbin Institute of Technology
Address: 92 West Dazhi Street, Nan Gang District, Harbin, Heilongjiang Province, China Postcode: 150001
(C)2015 JOURNAL OF HIT ALL RIGHTS RESERVED. ICP. 0000423255