臺灣博碩士論文加值系統

　　雖然近年來有相關文獻在致動器與感測器的配置問題上，但較少研究建立在複材機翼結構模式上，且大多是處理成對感測器與致動器共同置於同一位置上的問題，較少文獻提及分開任意的擺放情形。
　　本文以之前所建立的複材機翼(Hwu and Gai,2003)為模型，在考慮前三個模態下，以振幅及輸入電壓構成之二次形式為目標函數，用最佳化的方法找出感測器與致動器的最佳配置。在致動器與感測器的材料選擇上採用壓電材料，並黏附在機翼上下表面，在控制器設計上採用最佳控制理論求得迴授增益，並選用Kalman filter作為本系統的估測器，最後利用MATLAB 撰寫最佳化程式，並分別針對不同個數選擇下找出最佳位置。

　　Although some investigations about optimal placements of sensors and actuators can be found, it’s rare seen the research concering the composite wing structures. Besides, it is often hard to see separated placements cases compared with collocated cases.
　　The purpose of this paper is to find the optimal placement of actuators and sensors for composite wing structures. In optimization problem,a quadratic function related to the vibration amplitude and control input is defined as the objective function which will be minimized to find the optimal placements.
　　In vibration control, the first three natural vibration modes are considered. Piezoelectric materials are selected as actuators and sensors which are bonded on the upper and lower wing surfaces.
　　Using Linear Quadratic Gaussian (LQG) algorithm to be the controller design and chosing Kalman estimator as state observer for this system, a feedback control system is designed and implemented.
　　Finally, in optimal placement analysis, the numerical simulations are done by the software MATLAB and the optimal locations are presented for different cases.

致謝
摘要
英文摘要

目錄..................................................... i
表目錄................................................... iii
圖目錄................................................... iv
符號說明................................................. v

第一章 緒論.......................................... 1
1.1 前言............................................. 1
1.2 文獻回顧......................................... 2

第二章 複材機翼結構與受力振動之理論模式.............. 3
2.1 複材機翼結構模擬................................. 3
2.1.1基本假設與結構模擬.......................... 3
2.1.2運動方程式與邊界條件........................ 4
2.1.3忽略翼展方向作用力的簡化模型................ 6
2.2 受力振動分析..................................... 6

第三章 壓電材料與結構之狀態方程式.................... 8
3.1 壓電材料簡介..................................... 8
3.2 壓電致動器....................................... 9
3.3 壓電感測器....................................... 13
3.4 機翼結構之狀態方程式............................. 13

第四章 最佳配置設計.................................. 15
4.1 控制器設計....................................... 15
4.1.1迴授控制器設計.............................. 16
4.1.2卡門估測器(Kalman estimator)................ 17
4.2 目標函數值計算................................... 17
4.3 最佳化設計流程................................... 20

第五章 結論與建議.................................... 23
5.1 感測器與致動器之最佳配置......................... 23
5.1.1數值積分與Lyapunov equation的比較........... 24
5.1.2最佳化與未最佳化的比較...................... 24
5.1.3各種配置之討論.............................. 24
5.2 頻譜分析......................................... 26

第六章 結論與建議..................................... 27
6.1 結論.............................................. 27
6.2 未來工作與建議.................................... 27

參考文獻.................................................. 29
附表...................................................... 32
附圖...................................................... 38
自述
著作權聲明

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