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Characteristic and Application of Extended Optimal Guidance Law with Multiple Constraints

  • MA Tingting 1 ,
  • DIAO Zhaoshi 2 ,
  • WEI Yuliang 1 ,
  • HE Ting 1
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  • 1 Beijing Institute of Control Engineering, Beijing 100190, China
  • 2 Navigation and Control Technology Research Institute of China Ordnance Industries, Beijing 100094, China

Received date: 2018-06-28

  Online published: 2025-05-12

Abstract

A family of extended optimal guidance laws with multiple constraints, which weighted function is the reciprocal of the power of time-to-go, are presented for the guidance problem with terminal multiple constraints.Closed-form solutions for the missile acceleration command requirements are derived using Schwarz inequality, and the dimensionless acceleration profiles due to initial position error, initial heading error, constant target maneuver and terminal impact-angle constraint, are respectively investigated in detail.Closed-form solutions for line-of-sight angle are yielded through missile-target geometry relationship and the dimensionless line-of-sight histories are analyzed..Simulation results of vertical-attack example demonstrate the validity of relative theoretical results.It is also shown by simulation that the acceleration command dramatically changes at terminal phase due to the existence of lag property in actual control systems.

Cite this article

MA Tingting , DIAO Zhaoshi , WEI Yuliang , HE Ting . Characteristic and Application of Extended Optimal Guidance Law with Multiple Constraints[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2019 , 39(6) : 37 -44 . DOI: 10.15892/j.cnki.djzdxb.2019.06.010

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