Optimal Design of Guidance Law for Missile Launch with Large Off-Axis Angle
The guidance law of air-to-air missile with large off-axis launch angle is studied in this paper.The BTT control mode is applied to missile cruise in the turning stage.The mechanism and requirements of fast turning of missile are briefly analyzed,and the optimal lift surface for fast turning is studied and the missile roll control command is determined.The dynamic model of missile is established in turning phase,and the control command of angle of attack is designed by using the relation of residual turning angle.The rotation coordinate system is proposed to optimize the roll control command,solve the problem of command jump and achieve the minimum roll deviation control in the turning process.The projection of the best nor-mal vector of lift surface is used to determine the control logic of the command of angle of attack and realize matching with the minimum roll deviation control commands.In the end,the correctness and effectiveness of design method are verified by digitalized simulation of typical scenes.
Air-to-air missileLaunch at large off-axis angleGuidance law designFast turn
万方数据
维普
