攔截飛彈複合控制系統設計

Abstract

本論文提出一攔截飛彈的混合控制器，使用尾翼控制為主要控制器，側推力控制為輔助控制器的混合控制系統架構，改善僅用純尾翼控制的攔截效果。本論文之尾翼控制器以傳統的相位領先與比例積分控制器控制達到暫態與穩態的性能要求，但純尾翼控制有角度上的限制與非最小相位零點的問題無法滿足快速反應的需求，因此部分攔截飛彈如愛國者三型，加入了側推力致動器，提升攔截能力。側推力控制器採用非線性的順滑模態理論。在模擬中，使用純尾翼控制與混合控制器來模擬在飛彈具有航向誤差，以及目標飛彈具加速度等兩種情況的攔截表現，模擬結果可發現混合控制能夠有較快速的反應，且較具強韌性，可有效降低攔截的誤失距離。

This thesis proposes a blended controller consisting of the tail fins controller and lateral thruster controller for interceptor. Using the blended controller, the performance of interceptors will be better, compared with using tail fins controller. The tail fins controller is designed with a classical phase-lead and proportional-integral controller to achieve the requirements of transient and steady-state performance. Due to the limitations for degree of the tail and non-minimum phase dynamics, the speed of response may not meet the requirements of interception. So, some interceptors, such as PAC-3, combines lateral thrust actuators to increase the ability of interception. The lateral thrust controller is nonlinear and designed with sliding mode control theory. In simulation, the performance of interception using the tail fins controller and blended controller are compared when heading error exists and target has acceleration. The simulation results show that the blended controller has higher speed of response, and is more robust, which can reduce the miss distance effectively.