非最小相位导弹自动驾驶仪设计

对于尾控型导弹，过载输出与舵偏转之间为非最小相位特性，这使得反馈线性化和滑模控制等非线性控制算法不能应用于控制器设计。将输出跟踪问题转化为状态跟踪，这样，可以应用滑模控制设计过载控制自动驾驶仪，通过构造合适的滑模输出，可得到稳定的零动态。此外，采用全局二阶滑模控制可削弱抖振现象。仿真结果表明，本设计具有良好的输出跟踪性能和鲁棒性。

Non-Minimum Phase Missile Autopilot Design

The dynamics between the control fin deflection and missile overload output in tail-controlled missiles has non-minimum phase characteristics. The non-minimum phase nature of a plant restricts application of the powerful nonlinear control techniques such as feedback linearization control and sliding mode control. The output-tracking problem is replaced by the states tracking problem, hence, sliding modes control can be adopted to design autopilot. Valid sliding modes output that gives the system stable zero dynamics is constructed. The global second order sliding mode control approach is applied to avoid chattering phenomenon. The solution is a complete constructive algorithm. The simulation results show excellent load output-tracking performance and robustness.