由於在飛彈控制系統中的致動器與感測器在遭受到惡意攻擊信號時顯得相當的脆弱，所以我們對於飛彈導航的控制的信賴度有著更高的期望。因此，在飛彈控制的過程中，飛彈的致動器和感測器忍受惡意攻擊信號的能力顯得相當重要。在本篇研究中，一個新穎的建模方式被提出，並且能夠有效地描述致動器與感測器的攻擊信號。為了避免惡意攻擊的破壞，惡意攻擊信號被藏在飛彈系統的增廣狀態向量當中。此外，也非常希望能發展出一個有效且基於觀測器的控制方法來使戰術飛彈有更好的飛行表現。在本篇研究，我們使用無窮H強健控制方法來處理這個基於觀測器且能忍受攻擊信號的導航控制設計問題。為了解決這個問題，我們需要去解一個非常複雜的且非線性的Hamilton-Jacobi不等式。然而，目前並沒有一個很有效率的方式來解這個不等式。因此，我們利用T-S模糊控制方式來簡化這個隨機飛彈系統在致動器和感測器遭受到惡意攻擊下的強健導航控制的設計過程。接下來利用我們提出的間接的方法將這個優化無窮H強健模糊、基於觀測器且能忍受惡意攻擊的飛彈導航控制設計問題傳換成去解一個線性矩陣不等式的問題—限制優化問題—也稱作特徵值問題。這個特徵值問題可以利用凸優化的技術來有效率的解決。隨機飛彈導航系統在遭受到惡意的致動器和感測器的攻擊信號且有外部干擾的模擬例子被提出來說明設計過程和驗證所提出的方法。

Due to the high vulnerability of actuator and sensor in the missile control system to the malicious attack signals, higher requirements of reliability for the missile guidance control have put forward. Therefore, the capability of attack tolerance under malicious actuator and sensor attacks during the missile guidance control process becomes an important issue. In this study, a novel smoothed dynamic model is introduced to efficiently describe the actuator and sensor attack signals on missile guidance system. To avoid the corruption of malicious attack signals on actuator and sensor, the attack signals are embedded in the augmented state vector of missile system. In addition, it is very desirable to develop an effective observer-based control law to improve guidance performance for tactical missiles. To treat the H_∞ observer-based attack-tolerant guidance control design problem of missile system under actuator and sensor malicious attack, we need to solve a very complicated nonlinear Hamilton-Jacobi inequality (HJI). However, there still exists no good method to solve HJI for H_∞ observer-based missile guidance control problem. Thus, a T-S fuzzy observer-based fault-tolerant missile control design is proposed to simplify the design procedure of robust guidance control for stochastic missile system under actuator and sensor attacks. By using the proposed indirect method, the optimal H_∞ fuzzy observer-based attack-tolerant missile guidance control design problem is transformed into a linear matrix inequalities (LMIs)- constrained optimization problem, i.e., a so-called eigenvalue problem (EVP). The EVP can be solved very efficiently using the convex optimization techniques. Simulation example of stochastic missile guidance system under malicious actuator and sensor attack as well as external disturbance is given to illustrate the design procedures and validate the performance of the proposed method.

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