非线性动态逆在大攻角导弹控制系统设计中的应用

Nonlinear Dynamic Inversion Applied to Design of.Control System for High Angle of Attack Missile

导弹在大攻角飞行时,非线性及耦合严重,本文对推力矢量控制的空空导弹的控制系统进行了研究。根据导弹状态变化快慢不同,在奇异摄动理论的基础上,采用非线性动态逆设计了导弹的控制系统,并对导弹大攻角有侧滑飞行进行了仿真,结果表明文中设计的控制系统可以很好地控制导弹作机动飞行。

Nonlinear and couple are severe when missile flight at high angle of attack.Control system of air-to air missile with thrust vectored is discussed.The state variables of missile are different according to its time scale. Nonlinear dynamic inversion is adopted to design the control system based on singularity perturbed theory.Simulation of missile flight at high angle of attack with sideslip angle has been done,and the results show that the control system finely maneuvers the missile.