Impact angle constrained optimal midcourse guidance law for missiles of time-varying speed
XIONG Shao-feng
WEI Ming-ying
ZHAO Ming-yuan
XIONG Hua
Abstract：In the background of counter parallel intercepting high-speed moving target,the indirect Gauss pseudospec-tral method is employed to design an impact angle constrained optimal midcourse guidance law in this paper. Through vanishing the relative normal velocity between missile and target,the impact angle constraint is converted into the line of sight angle constraint.Considering the time-varying velocity of missile,the guidance equation with impact angle constraint is established. An analytical expression of optimal midcourse guidance law is derived based on the Minimum Principle. The Gauss pseudospectral method is used to discretize the optimal midcourse guidance law,then differential equations are turned into algebraic equations,and solving the Riccati equations is avoided.It does not need to know in advance the future velocity information of missiles and the computation load is small,which in-dicates that the proposed method has good real time property. The simulation results show that the proposed mid-course guidance law can satisfy the intersection angle constraint of counter parallel intercepting,and the acceleration command at the end of the midcourse guidance is small.
Keywords：midcourse guidance lawoptimal controlhead on interceptionimpact angle constraintGauss pseudospec-tral methodtime-varying velocity of missile
Publication Date：2018-01-01
Online Publishing Date：2025-08-15(First online date of this platform, not the publication date of the document)
Pages：10( 248-257 )