現代戰機為了達到更高效能的飛行效率，其首要條件為更改飛行器基礎設計，使得飛行器重心後移，並且放寬其靜穩定的程度，使得飛行器之基本空氣動力學建立於一個不穩定的狀況下，因此飛控電腦變成為了相當重要的一環，飛控系統將使得現代戰機在低速或者是高攻角的狀態下進行穩定的飛行，也可以避免飛行員之操作指令超出飛行器之飛行包絡線，最重要的是在戰機進行戰鬥時若是損壞了某部分的致動器還可以保持飛行器之穩定。
對於人類而言飛行的領域是如此的未知並且充滿不確定性，因此對於戰鬥機而言在飛行的過程中其系統強健性則是相當必須的一環，因此本文將使用順滑模式控制器與非線性動態反算與增量式非線性動態反算進行搭配，並且將在系統中加入不確定性進而比較外擾對於其兩種不同控制的影響。
而其中本文將選用X-31向量推力試驗機 之空氣動力學模型進行控制，並且使用MATLAB SIMULINK進行模擬，最後將加入致動面失效所產生之影響，並且改變控制策略，避免其所產生的影響抑或是系統之發散。

The aim of this thesis is to control the X-31(Rockewll-MBB X-31) experiment aircraft which has high flight performance and super-maneuverable experimental aircraft. By applying the method that combines Non-linear Dynamic Inversion (NDI) and Incremental Non-linear Dynamic Inversion (INDI) with Sliding Mode Control (SMC), a robust nonlinear controller can be set up for super-maneuverable aircraft. To realize this approach, the aerodynamic and dynamic model is calculated and simulated by MATLAB SIMULINK.
For the morden fighter The robustness is essential to the aircraft system. Therefore,it is the SMC that is chosen to be the way enhancing the robustness of the system. In this thesis a disturbance added to the X-31 model will be discussed by two different method. First, the robustness of NDI and INDI is compared with a nonlinear disturbance. The control surface failure will be discussed in at last. By reconstructing the control strategy the impact of control surface failure can be completely eliminated.

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