AIAA飛機模式之迴授控制及模擬

Abstract

本論文是針對 AIAA 文獻中所提供的六自由度飛行動態系統,進行模擬環 境的建立及控制器的設計.第一部份是以 SIMULINK/MATLAB 及 MATRIXx/ System-Build兩種軟體,建立一個適合分析.設計及驗証的模擬環境.第二 部份則是利用兩種不同迴授法設計控制器,以達到飛機等高加速的設計目 標.首先是利用伺服輸出迴授方式,以內迴路狀態迴授及外迴路輸出迴授作 為控制器結構,並以最佳化程序來計算參數值;另一方法則是以LQR 理論設 計狀態迴授,且運用增益預定法來調整迴授值經由模擬,結果顯示兩者均能 符合性能要求 The purpose of the thesis is to develop a simulation environment and methods for the design of flight control systems for AIAA supersonic aircraft model. The simulation environment is implemented using SIMULINK/MATLAB and MATRIXx/ System-Build. The objective of control is to maintain a straight-and-level acceleration flight. Two approaches are used. The first one designs controllers of a specified structure with linear output feedback techniques. The control gains are obtained through optimization. The second is based on LQR method, and the control system is gain scheduled with dynamic pressure. Six-degree-of-freedom simulations are used to verify design results. Both methods give satisfatory results.