A Terminal Multi-constraint Optimal Guidance Law for Missile

doi:10.3969/j.issn.1000-1093.2016.06.023

Abstract

Abstract: A new optimal guidance law is presented to satisfy the terminal constraints for the precise strike and efficient damage to ground target. The proportional-navigation constraint, impact angle and acceleration constraints are used to achieve the terminal acceleration command convergence through the guidance-order adjustment. The simulation results show that the optimal guidance law can meet the terminal constraints, and the command performance and the attack effect are improved as well.

Key words: control and navigation technology of aerocraft, multiple constraints for penetrating, optimal guidance law, close-form solution, guidance characteristics

CLC Number:

TJ765.3

LI Qiang， LU Bao-gang， WANG Xiao-hui， WANG Yong-hai， ZHUANG Ling. A Terminal Multi-constraint Optimal Guidance Law for Missile[J]. Acta Armamentarii, 2016, 37(6): 1131-1137.

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