基于微分几何方法的大迎角导弹解耦控制

Decoupled Control for a High Angle of Attack Missile Based on Differential Geometry Method

导弹在大迎角飞行时,非线性及耦合严重,而且大迎角本身引起的非线性和耦合也必须加以考虑。采用微分几何方法,通过在控制系统中人为地加入耦合信息,以抵消弹体运动的交叉耦合,设计大迎角导弹解耦控制系统。并对结果进行了仿真验证,证实所设计的控制系统可以很好地控制导弹的大迎角飞行。

The phenomena of nonlinearity and cross-coupling are serious when a missile flights at high angles of attack. At this time, the nonlinearity and coupling caused by high angle of attack itself for the missile must be considered. In this paper, the differential geometry adopted through appended coupling information so that it may eliminate the cross-coupling of the missile. Thus the decoupling control system of missile flight at high angles of attack is designed. At last, the simulation test is done. The simulation results show that the control system can finely maneuver the missile flight at high angles of attack.