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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

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.
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Optimal Guidance Law to Maximize Terminal Velocity for Missiles with Impact Angle Constraint
Chao Ming1, Ruisheng Sun1and Chuanjie Sun2
(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)
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
Clc Number:V11 TJ765.3