基于滑模控制理论的导弹自动驾驶仪的设计

Missile Autopilot Design Based on Sliding Mode Control Theory

基于变结构自适应控制理论 ,提出一种新的 STT导弹自动驾驶仪三通道独立设计方法。该方法在设计过程中保留了通道间的全部耦合因素 ,通过构造滑模面和最优值原理配置转换系统零动态的极点 ,从而提高了系统的稳定性 ,增强了系统的适应性和鲁棒性。运用所提出的方法 ,本文设计了某型导弹的自动驾驶仪 ,并在考虑了舵机系统 ,加速度计等各种非理想因素的情况下 。

A tracking control technique is applied to autopilot d es ign of a tail-controlled STT missile system with coupling among channels. To av oid instability problem associated with unstable internal-dynamics, the output -tracking problem is replaced by state-tracking, then sliding mode control can be applied to this non-minimum phase system. This method can apply the sliding mode control to non-minimum phase system, and the sliding mode surface coeffi cients are selected to stabilize the generalized internal-dynamics. The control ler is stable in presence of coupling among channels if the magnitudes of the co upling terms are confined at certain range. Additionally, the global second orde r sliding mode control is used to avoid chattering. This solution is a complete constructive algorithm. Simulation results show the validity of the proposed met hod on output tracking.