本論文目的是討論非線性動態反算(Nonlinear Dynamic Inverse, NDI)於高攻角飛行控制的應用，主要工作為高攻角和飛行控制律的設計，因此需要處理大範圍的操作點。當戰機進入高攻角時，由於氣流的分離，主要氣動力操作面的性能都急遽下降，因此翼面的控制力會大幅降低，造成飛行器的操縱性能下降。針對後失速的特點，本論文建立了多軸向量噴嘴，推力可進行上下與左右偏轉，並結合氣動力及向量推力進行控制。非線性動態反算為控制系統設計者提供了直接的方法，推導非線性系統的控制律，將非線性系統轉成等義的線性系統，並利用此方式進行角速度迴路與姿態迴路之控制器設計。本論文增加了向量噴嘴控制面，並採用控制配置來分配氣動力與向量噴嘴控制面的選擇。最後驗證不同的飛行操作模式，其結果皆顯示，透過NDI控制可以證明在大範圍攻角飛行下仍具有良好的控制能力。

The purpose of this thesis is to discuss the application of Nonlinear Dynamic Inverse (NDI) in high-angle flight control. The main work is around high angle of attack (A.O.A) and the design of flight control law, so it is necessary to deal with a wide range of operating points. When entering a A.O.A, the performance of the control surfaces is drastically reduced due to the separation of the airflow, so the control of the airfoil is greatly reduced, resulting in a decrease in the maneuverability of the aircraft. The NDI provides a direct method for the control system designers to derive the control law of the nonlinear system, convert the nonlinear system into an equivalent linear system, and use this method to design the controller of the angular velocity loop and the attitude loop. This thesis adds the thrust vectoring and uses a control allocation to assign the choice of aerodynamic and vector nozzle control surfaces. Finally, different flight operation modes are verified. The results show that the NDI control can prove that it has good control ability under a wide range of angles of attack.

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