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研究生:裴俊英
研究生(外文):Bui Tuan Anh
論文名稱:Structural Analyses of Flybar/Flybarless Rotor Head Systems of RC Helicopter
論文名稱(外文):Structural Analyses of Flybar/Flybarless Rotor Head Systems of RC Helicopter
指導教授:劉乃上
指導教授(外文):Nai-Shang Liou
學位類別:碩士
校院名稱:南台科技大學
系所名稱:機械工程系
學門:工程學門
學類:機械工程學類
論文種類:學術論文
論文出版年:102
畢業學年度:101
語文別:中文
論文頁數:67
中文關鍵詞:直升飛機子系統陀螺儀關鍵字主旋翼
外文關鍵詞:FlybarFlybarless Rotor Head SystemFinite element
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如今,無人駕駛的無線電遙控直升機(RC helicopter)不僅用於娛樂用途,在許多領域它也作為一個有用的飛行器,如航拍、治安、觀察或檢查。對滾動和升降轉動控制主要有兩種類型:第一種類型是通過平衡翼機制和斜盤移動,平衡翼系統改變主葉片的槳距角。此外,由於平衡翼穩定的運動傳遞到主葉片安裝,通過改變主旋翼槳葉的槳距角,它會自動幫助穩定了的直升機。第二類是無平衡翼系統控制滾動和平衡而沒有平衡翼。兩個陀螺儀傳感器在這個系統中作為一個虛擬的平衡翼的作用。因為伺服電機和主葉片之間直接連接,無平衡翼系統具有更快的響應速度,但放置在斜盤的壓力也遠遠超過平衡翼系統。因此,爲了處理反應力和應力分佈需要在這些系統上建立一個優化模型。在這項研究中,實驗和數值模擬的方法被用來研究的力學響應450中型電動集體間距直升機的有/無平衡翼。被用來調查平衡翼,無平衡翼系統的應力分佈的有限元分析。關鍵部件進行了詳細分析,通過使用子模式的分析,以得到更精確的結果。為了獲得邊界和負載條件下的數值研究,本人使用實驗來收取由旋轉刀片產生的力和力矩。直升機直升機將會在被固定的狀態下進行飛行測試並從中探討其力學特性,其結果將會對有平衡翼和無平衡翼的系統進行比較,看它們之間的差異,並對各系統的優點和缺點進行研究並理解其操作方式、力學特性、應力分佈在兩個轉子系統的轉子頭組件可以提供重要的信息,在提高對RC-直升飛機主旋翼系統。
關鍵字: 平衡翼, 第二類是無平衡翼系統, 有限元素分析。 
Nowadays, radio-controlled unmanned helicopter (RC helicopter) is not only used for entertainment purpose, it also serving as a useful aerial vehicle in many areas such as aerial photography, policing, observation or inspection. There are two main types for roll and elevator controls: first type is the flybar system which changing the pitch angles of main blades via flybar mechanism and the moving of swashplate. In addition, since the flybar stabilization movement is transmitted to the main blade mounts, it automatically help stabilizes the helicopter by changing the pitch angles of the main rotor blades. The second type is flybarless system which controls the roll and does stabilization without flybar. The two gyro sensors play a virtual flybar role in this system. Because of directly connect between servo motor and main blade, the flybarless system has a faster response but the stress placed on swashplate is also much more than on the flybar system. Therefore, it is necessary to take care of the reaction forces and stress distribution on those systems to build an optimal model. In this study, experimental and numerical methods were used to investigate the mechanical response of 450 sized electric collective pitch helicopters with/without flybar. The finite element analyses were used to investigate stress distribution on flybar and flybarless system. In order to get boundary and loading conditions for the numerical study, experiments were performed to acquire the force and moments generated by the rotary blades. The force response of helicopter was monitored during the operation of helicopters mounted on the test frame. The results of both flybar and flybarless systems were compared to see the differences between them, and the advantages and disadvantages of each system were investigated. Understanding the manner of operating, the forces response, stress distributions on the components of rotor head of the two rotor systems can provide important information in improving the RC-helicopter main rotor system.
Keywords: Flybar, Flybarless Rotor Head System, Finite element. 
ABSTRACT i
摘要 ii
ACKNOWLEDGEMENT iii
TABLE OF CONTENTS iv
LIST OF FIGURES vi
LIST OF TABLES ix
CHAPTER 1: INTRODUCTION ix
1.1. RC Helicopter 1
1.2. Research objective: 10
1.3. Research scope and limit of study 10
CHAPTER 2: FINITE ELEMENT MODEL 11
2.1. Finite element method 11
2.2. Finite element model 11
CHAPTER 3: EXPERIMENTAL METHODS 23
3.1. Experiment setup 23
3.2. Investigation method: 27
CHAPTER 4: FINITE ELEMENT ANALYSIS 30
4.1. Prescribed conditions 30
4.2. Analysis procedure 30
4.3. Elevator mode 31
4.4. Aileron mode 33
4.5. Tilt mode 35
4.6. Apply moment mode 37
CHAPTER 5: RESULTS AND DISCUSSION 38
5.1. Elevator mode 38
5.2. Aileron mode (turn right) 45
5.3. Tilt mode 52
5.4. Applying moment mode 59
CHAPTER 6: CONCLUSION 64
5.1. Conclusion 64
5.2. Future works 65
REFERENCES 66
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