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 Please use this identifier to cite or link to this item: http://ir.lib.ncu.edu.tw/handle/987654321/72372

 Title: 縱向飛行姿態自適應控制 Authors: 涂凱翊;Tu,Kai-Yi Contributors: 機械工程學系在職專班 Keywords: 飛行控制;自適應性控制;模型參考;非線性;flight control;adaptive control;model reference;nonlinear Date: 2016-07-28 Issue Date: 2016-10-13 14:50:53 (UTC+8) Publisher: 國立中央大學 Abstract: 本研究以飛行姿態中縱向運動控制為例，運用自適應性控制中模型參考自適性控制方法(Model Reference Adaptive Control,MRAC)，及Matlab Simulink所構建之模型，進行自適應性控制器的設計及分析，探討非線性模型架構與控制器、自適應律、參考模型及誤差增益之間的影響。透過改良後的MRAC方式，獲得控制器的自適應律後，依據系統模型及參考模型之間的誤差，推算出整個非線性控制系統控制器輸出，進而使系統輸出趨近於參考模型。根據模擬結果，藉由改良MRAC獲得之控制器，系統最後輸出情況，並不受非線性模型本身內部參數變化的影響，而受參考模型及誤差增益的影響。研究結果顯示，在可獲得系統輸出及參考輸出的情況下，即可設計出該系統之控制律及控制器，而無需該系統非線性複雜的數學模型，或是精確的各項物理參數。;In this study, take the longitudinal motion flight attitude control for example, using model reference adaptive control that method of adaptive control of model reference adaptive control, and constructed of Simulink model, to design and analysis of adaptive controllers, and to explore the influence of nonlinear model structure and controller, adaptive law reference model and error gain.After using the improved MRAC method, a controller adaptive law, based on the error model and the reference model among the entire nonlinear control systems calculate the controller output, thereby enabling the system output close to the reference model. According to the simulation results, obtained by the controller improved MRAC, the final output of the system, the nonlinear model itself is not affected by changes in internal parameters, and influenced by the reference model and gain error. The results show that, in the case of system output and the reference output available, you can design a control law and control of the system without the system of nonlinear complex mathematical model, or an exact parameters of the physical. Appears in Collections: [Executive Master of Mechanical Engineering] Electronic Thesis & Dissertation

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