带落角约束的空地导弹滑模末制导律研究

Sliding Mode Terminal Guidance Law for Air to Ground Missile with Impact Angle Constraint

在空地导弹末制导的过程中,为了提高空地导弹的命中精度,追求最佳的打击效果。设计了一种以零化弹-目视线角速率,及终端视线角与期望视线角之差为切换面的带落角约束的空地导弹滑模末制导律。针对空地导弹滑模末制导律的抖振问题,应用径向基函数(RBF)神经网络自适应调整符号项增益的方法来削弱抖振。仿真结果表明该滑模末制导律能够以期望的落角命中目标,且具有良好的制导精度。

In order to improve the shoot accuracy and pursue the optimal efficiency of the Air to ground missile in the terminal guidance process. A sliding mode variable structure terminal guidance law for air to ground missile with impact angle constraint is designed by zeroing the missile target line-of-sight angular rate and the difference between the terminal line-of-sight angle and the anticipant line-of-sight an- gle. For the chattering problem of the sliding mode variable structure terminal guidance law for air to ground missile, a method based on the radical basis function （RBF） neural network to adjust the parame- ters of the sign term is applied to weaken the chattering. The simulation results show that the sliding mode terminal guidance law can hit the target with anticipant impact angle and has fine guidance precision.