飛彈從發射到命中目標之間的控制動作極為複雜，大致可分為將狀態回授的導航、擬定目標追跡策略的導引以及實踐其追跡的飛行控制。而飛行控制中必須考量到飛彈系統內部複雜的未知項，其造成難以精準地實踐追跡。本論文針對飛彈的非線性系統，提出新的姿態適應控制器，其係將氣動力矩係數以及環境造成的外擾整合在未知函數中，再以函數近似估測之，並配合Lyapunov穩定法則來確保追蹤誤差的漸近收斂性，藉此改善傳統適應控制無法處理快速時變未知項的問題，同時也解除過往強健控制需已知未知邊界之限制。此外，本文也整理現有以適應方法估測外擾邊界之強健控制法的缺點。最後，本文透過電腦模擬來驗證本文所提控制器的可行性。

The control actions of the missile from launching to intercepting the target are extremely complicated, which can be roughly divided into the navigation that feedbacks the state, the guidance that generates the target tracking strategy, and the flight control that implements its tracking strategy. The actual flight control must consider the complex unknown parameters inside the missile system, which makes it difficult to track the desired trajectory accurately. This thesis proposes a new attitude adaptive controller for the nonlinear missile dynamics, which lumps the aerodynamic moment coefficients and the external disturbances caused by the environment into an unknown function and then an update strategy is developed to give good estimation. The Lyapunov method is used to prove the convergence of the asymptotical stability of the tracking error and the boundedness of the internal signals. Finally, this thesis uses computer simulation to verify the feasibility of the proposed controller.

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