隨著現代戰機對於作戰性能(如：高機動性、靈活性、匿蹤能力)的要求提高，控制配置(Control Allocation)是多控制面戰鬥機不可或缺的設計方法，不具備多控制面的第四代戰機已無法滿足需求。第五代戰機大多採用多控制面布局，除了氣動力控制面的個數增加外，還增加了推進系統的向量噴嘴，大大地增加了控制面的個數，但也超出了飛行員的操縱能力。本論文根據控制配置的觀念，將控制系統拆分為控制律與分配律，其中控制律選用非線性動態反算(NDI)，且獨立設計分配律。本論文引入線性規劃法於分配律設計中，並建立出一套分配律自動切換的管理方案，根據不同的飛行任務切換不同的分配律模式。最後透過六自由度模擬驗證管理方案的優缺點，並比較線性規劃法與其他配置法的差異。

With the increasing requirements of modern fighters for combat performance (such as high maneuverability, flexibility, and stealth ability), Control Allocation is an indispensable design method for multi-control surface fighters. Fourth-generation fighters can no longer meet the demand. Most of the fifth-generation fighters adopt a multi-control surface layout. In addition to the increase in the number of aerodynamic control surfaces, the vector nozzles of the propulsion system are also increased, which greatly increases the number of control surfaces, but also exceeds the pilot's ability to control. According to the concept of control configuration, this dissertation divides the control system into control law and distributive law. The control law adopts nonlinear dynamic inverse calculation (NDI), and the distributive law is designed independently. In this paper, the linear programming method is introduced into the design of the distribution law, and a set of management scheme of automatic switching of the distribution law is established, and different distribution law modes are switched according to different flight tasks. Finally, the advantages and disadvantages of the management scheme are verified by 6-DOF simulation, and the differences between the linear programming method and other configuration methods are compared.

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