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研究生： 賴亞咸
Lai, Ya-Hsien
論文名稱： 任務型無人飛行載具之設計與驗證
Design and Verification for Mission UAV
指導教授： 林清一
Lin, Chin E.
學位類別： 碩士
Master
系所名稱： 工學院 - 航空太空工程學系
Department of Aeronautics & Astronautics
論文出版年： 2011
畢業學年度： 99
語文別： 英文
論文頁數： 118
中文關鍵詞： 無人飛機設計 、高升力裝置
外文關鍵詞： UAV design, high lift device
相關次數： 點閱：72  下載：9 
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    • 無人飛機的研究與應用越來越廣泛，針對任務需求所設計製作的Cardinal UAV 是以低飛行空速以及高載重需求來規劃。本研究詳細記載Cardinal UAV 的設計發展與基本測試，以適用於民間防災救災任務。Cardinal UAV是翼展3.6米、配有一具157cc雙缸引擎的雙尾管無人飛機， 有一個可以容納96公升的大容量機身，結構油箱的設計增加載油量以及大範圍的飛行速度來增加它的可用性。本文中詳細的敘述Cardinal UAV的研發過程，從概念到完整設計、加工製作與測試驗證，完成高酬載任務的可用系統。

    Research and applications related to Unmanned Aerial Vehicles (UAVs) had been increasing broader and broader in present days. Due to specific mission requirements, Cardinal series UAV was designed to apply to the disaster rescue and surveillance demands at low airspeed and high payload. This UAV has 3.6 meter wingspan, 157 cc engine and with twin booms tail. The special characteristics of this UAV are 96 liters large fuselage space, structural fuel tank and relatively large operation airspeed range for its practicality.
    This study well proposes a documentation of the Cardinal UAV from initial concepts to complete designs then to the manufacture of the UAV and last the verification and test. Finally a useable UAV system will be finished for the high payload mission.

    Chapter 1 1 1.1 Background Literature survey 1 1.2 Introduction to Manned aircrafts and UAVs 2 1.2.1 Manned Aircraft 2 1.2.2 Unmanned Aerial Vehicles: 4 1.3 UAVs advantages to manned aircrafts 5 1.3.1 Dull roles 6 1.3.2 Dirty Roles 6 1.3.3 Dangerous Roles 7 1.3.4 Covert Roles 7 1.3.5 Research Roles 8 1.3.6 Environmentally Critical Roles 8 1.4 Aerodynamic categories for UAVs 9 1.4.1 Tailplanes 9 1.4.2 Twin fins 10 1.4.3 V-tail 10 1.5 Design of Cardinal Series UAV 10 1.6 Thesis overview 12 Chapter 2 14 2.1 The Cardinal UAV 14 2.1.1 Configuration design concept 14 2.1.2 Preliminary CAD design of Cardinal series UAV 22 2.1.3 Mold design and UAV construction 53 2.2 Control system for high lift device 59 2.2.1 Active high lift system concept 60 2.2.2 Microchip 61 2.3 Perspective difficulties 66 2.3.1 UAV 67 2.3.2 Control 68 Chapter 3 69 3.1 UAV Structural test 69 3.1.1 Wing structural loading test 69 3.1.2 Fuel consumption test 70 3.2 UAV performance test 70 3.1.1 Stage 1 72 3.1.2 Stage 2 73 3.1.3 Stage 3 74 3.2 High lift device control method 74 Chapter 4 76 4.1 Design 76 4.1.1 The fabricated structure design 76 4.1.2 Assembly 81 4.1.3 Difference from CAD design 86 4.2 Structural test result 88 4.2.1 Wing structural loading test 88 4.2.2 Fuel consumption test 89 4.3 Data comparison and Discussion 90 4.3.1 Simulation parameter 90 4.3.2 Real flight data 92 4.3.3 Special Characteristic 105 4.3.4 Simulation and test flight comparison 109 Chapter 5 112 5.1 Concluding remarks 112 5.2 Perspectives 115 Reference 117

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