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研究生： 林田龍平
Hayashida, Ryuhei
論文名稱： 雙駕駛伺服系統超輕飛機之設計與實做
Servo System Design for Dual Pilot Ultra Light Aircraft
指導教授： 林清一
Lin, Chin E.
學位類別： 碩士
Master
系所名稱： 工學院 - 民航研究所
Institute of Civil Aviation
論文出版年： 2014
畢業學年度： 102
語文別： 英文
論文頁數： 47
中文關鍵詞： 無人飛行載具 、超輕飛機 、電動推桿操控系統
外文關鍵詞： Unmanned Aerial Vehicle, Ultra-Light Aircraft, Electric Lever Drive System
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    • 無人飛行載具的研究與應用越來越廣泛，多數無人機的設計無法執行高酬載任務。研發大型無人載具需龐大經費，然而從超輕飛機轉換為無人飛機操作，可以解決酬載及經費的問題。本論文提供一種解決方法，使超輕飛機在各種任務能有廣泛的應用。利用電動推桿並保留傳統操控桿的方式，使超輕飛機可以自由切換成為手動駕駛或線傳操控，未來將導入自動飛行系統。本研究基於電腦輔助設計，透過前述的想法，製造修改並整合機構，建立雙系統超輕飛機。本文最後以操控面之地面測試來驗證此套控制系統的可行性及超輕雙系統載具的操作性能。

    Unmanned Aerial Vehicles (UAVs) have been widely studied and used. But most UAVs are not capable to carry on high payload missions. Development of large UAVs demands high investment. However, conversion from ultra-light aircraft (ULA) into large UAV can economically solve the cost problem. This thesis proposes a large UAV solution using ULA for high mission requirements. Using electrically driven lever by reserving the original control sticks, the ULA can be switched for manual or fly-by-wire mode and then transition into autopilot mode. Based on computer aid design to realize the proposed idea, a complete flight mechanics is manufactured and integrated into a dual mode ULA for UAV. This thesis verifies the dual mode operation on ground tests for its feasibility and controllability unmanned ultra-light aircraft (UUL).

    Abstract I 摘　要 II 致　謝 III Contents IV List of Tables VI List of Figures VII Chapter 1 Introduction 1 1.1 Motivation 1 1.2 Main Idea 2 1.3 Literature Survey 3 1.4 Scope 4 1.5 Thesis Outline 6 Chapter 2 Fundamental Analysis of Ultra-Light Aircraft 7 2.1 Introduction of Eipper Quicksilver Ultra-light 7 2.2 Eipper Quicksilver Ultra-Light Aircraft configuration 12 2.2.1 Elevator Mechanism 13 2.2.2 Ailerons Mechanism 15 2.2.3 Rudder and Nose Wheel Mechanism 17 2.3 Summary of Configuration 18 Chapter 3 Mechanism Design of Dual Pilot Ultra-Light 19 3.1 Design Consideration 19 3.2 Ball Screw 19 3.3 Solenoid 20 3.4 Rotary Encoder 21 3.5 Frame Design 23 3.6 Joystick 27 3.7 STM32F103 28 3.8 Control Board Design 30 3.9 Program Design 32 Chapter 4 Dual Pilot Ultra-Light System Integration 35 4.1 Platform 35 4.2 Elevator 36 4.3 Ailerons 37 4.4 Rudder and Nose Wheel 38 4.5 Summary of Assembly 39 Chapter 5 Experiments 40 5.1 Aileron Motion Test 40 5.2 Elevator Motion Test 41 5.3 Rudder Motion Test 43 Chapter 6 Conclusion and Prospect 45 6.1 Conclusion 45 6.2 Prospect 45 References 46

    [1] T. Y. Lu, “Design and Verification for Unmanned Ultra-light Aircraft System” Master Thesis, Department of Aeronautics and Astronautics, NCKU, 2012.
    [2] H. Y. Chen, “Hydraulic Control System Design for Unmanned Ultra-Light (UUL)” Master Thesis, Department of Aeronautics and Astronautics, NCKU, 2013.
    [3] C. E. Lin, Y. H. Lai, Y. C. Huang, C. C. Li, C. C. Nien, “System Design Approach for Experimental UAV”, Journal of Aeronautics, Astronautics and Aviation, Series A, Vol. 45 No. 1, March 2013, pp. 25-36.
    [4] Eipper Aircraft Sport 2S Datasheet, Quicksilver Mfg.®, California, U.S.A., June 2014. Available on web: http://www.quicksilveraircraft.com/, available in April 2014.
    [5] Ballscrews Technical Information, HIWIN Technologies Corp, Taichung, Taiwan, May 2014. Available on web: http://www.hiwin.tw/, available in April 2014.
    [6] C. E. Lin, T. Y. Lu,H. Y. Chen, Y. H. Lai, “System Reengineering in Mechanism Design and Implementation for Unmanned Ultra-Light (Part I)”, Journal of Aeronautics, Astronautics and Aviation, Series A, Vol. 46, 2014, pp. 124-131. DOI: 10.6125/14-0311-786.
    [7] C. E. Lin, H. Y. Chen, T. Y. Lu, Y. C. Huang, “System Reengineering in Flight Control Verification for Unmanned Ultra-Light (Part II)”, Journal of Aeronautics, Astronautics and Aviation, Series A, Vol. 46, 2014, pp. 132-141. DOI: 10.6125/14-0311-787.

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