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研究生：	詹詠超 Chan, Yung-Chao
論文名稱：	高展弦比翼地效應機驗證與穩定性分析 Performance Validation and Stability Analysis of High Aspect Ratio Wing in Ground Effect (WIG) Aircraft
指導教授：	蕭樂群 Shiau, Le-Chun
共同指導教授:	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：	2013
畢業學年度：	101
語文別：	英文
論文頁數：	129
中文關鍵詞：	地面效應、升阻比、縱向穩定性
外文關鍵詞：	lift-drag ratio, longitudinal stability, WIG aircraft
相關次數：	點閱：115 下載：6
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現今是講求低能源消耗、高經濟效益和節能的世代，且為因應中短程距離的航空運輸，因此本論文期望發展一架具備高升阻比、低能源消耗、附載能力大與快速運輸等能力的地面效應機。本文設計一台新的無人機，包含了飛機的結構設計和氣動力學分析。這台PIS-1地面效應機有著高展弦比的機翼，不同於一般無人機和以往的設計。利用PIS-1進行模擬分析以及飛行測試，進而驗證地面效應的效益。因此本論文在設計上主要掌握幾個重點：升阻比、力矩係數與縱向穩定性。
當地面效應機飛行在地效區時，載具的縱向穩定性會相較於在空中飛行時來的差。在機翼的部分，選了幾種可能適合地面效應機的翼型做分析比較。此PIS-1飛機對縱向運動是很敏感的。本論文使用SolidWorks建立實體原型、ANSYS/Fluent以及XFLR模擬現實情況的邊界條件做設定進行流場的分析，進而找尋出最佳的巡航高度，以達到低油耗的目的。同時利用實體載具進行飛行測試、收集相關數據，以便對照數值模擬的結果做驗證，希望能將此研究的數據應用在往後可載人的大型地面效應機上。

In this low energy consumption, highly economic efficiency and energy-saving society, the main purpose of the wing in ground effect (WIG) aircraft that possessed the higher lift-drag ratio, lower energy cost, higher payload and rapid transport has been developed in response to the short-medium transportation. To design a new unmanned aerial vehicle (UAV) in WIG includes the aircraft structure design and the aerodynamics analysis. This design of WIG aircraft named “PIS-1” with high aspect ratio is different than the conventional UAV and previous design. The simulation and flight tests of this aircraft verify the performance of ground effect. Several critical criteria in this thesis are as following: lift-drag ratio, coefficient of moment and longitudinal stability.
When WIG aircraft flies in ground effect section, its longitudinal stability will weaker than flies in the air. Several airfoils will be analyzed in order to find a suitable one for the WIG aircraft. This PIS-1 aircraft is sensitive to the longitudinal motion. It uses not only the SolidWorks to build the prototype of the aircraft, but also using the ANSYS/Fluent and XFLR to simulate the fluid field around it. Simultaneously, remote control prototype model will have flying tests to compare with numerical simulation in order to achieve the main purpose of this study.

ABSTRACT i
摘要 ii
ACKNOWLEDGMENTS iv
LIST OF TABLES viii
LIST OF FIGURES ix
Chapter I 1
Introduction 1
1.1 Motivation 1
1.2 Main idea 2
1.3 Literature Survey 3
1.4 Organization of Thesis 6
Chapter II 8
Technical Survey on WIG	8
2.1 WIG Craft Development 8
2.1.1 The Development of Russian Ekranoplan 9
2.1.2 Sea Monster 15
2.1.3 Orlyonok 16
2.1.4 Lun 18
2.1.5 The Second Evolution of WIG craft 19
2.2 Ground Effect 23
2.3 WIG (Wing in Ground Effect) Aircraft 29
2.3.1 Types of WIG Aircraft 29
2.3.2 Ram Wing and Ekranoplan 30
2.3.3 Lippish 34
2.3.4 Tandem 37
Chapter III 39
WIG Aircraft Design Methodology 39
3.1 Mathematical Calculation 39
3.1.1 Preliminary Design 39
3.1.2 The Main Aerodynamic Parameters 41
3.1.3 Aerodynamic principles and Formula 49
3.2 Numerical Methods 55
3.2.1 Preliminary Design Model 55
3.2.2 ANSYS/Fluent Analysis 61
Chapter IV 67
System Design and Simulation 67
4.1 XFLR Simulation 67
4.1.1 3D Model 67
4.1.2 XFoil Stability Analysis 68
4.1.3 XFoil Aerodynamic Analysis 72
4.2 Production Process 84
4.2.1 Materials and Tools 84
4.2.2 Production Details 87
4.2.3 Assembly and Testing 95
Chapter V 98
Test and Verification 98
5.1 Test and Modification 98
I.   Water Sailing Stability 98
II.  Center of Gravity Test 102
III. Floating Test 106
IV.  Flight Test 108
V.   Steady Flight Test 115
VI.  Low-Altitude Test 122
Chapter VI 125
Conclusion and Prospect 125
6.1 Conclusion 125
6.2 Prospect 126
References 127
                                    

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校內：2015-08-07公開
校外：2018-08-07公開

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