系統識別號 | U0002-0608201911305600 |
---|---|
DOI | 10.6846/TKU.2019.00157 |
論文名稱(中文) | 提高拍翼升力之單向閥門製作 |
論文名稱(英文) | Fabrication of Check Valves on Flapping Wings for Lift Enhancement |
第三語言論文名稱 | |
校院名稱 | 淡江大學 |
系所名稱(中文) | 機械與機電工程學系碩士班 |
系所名稱(英文) | Department of Mechanical and Electro-Mechanical Engineering |
外國學位學校名稱 | |
外國學位學院名稱 | |
外國學位研究所名稱 | |
學年度 | 107 |
學期 | 2 |
出版年 | 108 |
研究生(中文) | 王偉丞 |
研究生(英文) | Wei-Chen Wang |
學號 | 606370053 |
學位類別 | 碩士 |
語言別 | 英文 |
第二語言別 | |
口試日期 | 2019-06-21 |
論文頁數 | 81頁 |
口試委員 |
指導教授
-
楊龍杰(ljyang@mail.tku.edu.tw)
委員 - 胡毓忠 委員 - 羅元隆 |
關鍵字(中) |
單向閥門 自然頻率 PET翼模設計 |
關鍵字(英) |
Check Valves Natural frequency Wing design |
第三語言關鍵字 | |
學科別分類 | |
中文摘要 |
本篇論文提供一個新型的翼膜設計概念,即針對舊式的PET翼膜安裝單向閥門(check valve),使其在拍翼機進行拍翼的過程中,藉由單向閥門於拍翼上行程時開啟閥門,而下行程時關閉閥門的開合控制降低翼膜所需承受的空氣阻力,而達到提升拍翼升力的目的。文章中也會提及各式的加工技巧以及軟體操作概念輔助,進行諸如機構設計以及結構、自然頻率分析等,所使用的軟體包括Solidworks和ANSYS,其中Solidworks主要輔助機構以及單向閥門結構設計,而ANSYS軟體則是用於單向閥門在拍翼運動中之自然頻率模擬量測,藉由頻率響應之計算與分析來確保閥門的設計在翼膜上運作之實用性以及可靠性,本論文最終所設計之單向閥門,經過自然頻率分析所得到之結果為17.86Hz,以低通濾波的概念來說明,其成功達到所期望之高於拍翼頻率(14Hz)的範圍,從而認定此單向閥門之設計是可行的。此外本論文也提及到運用傳統加工的方式如切割機的運作,輔助製作單向閥門。 風洞實驗在本篇論文中的主要目的是比較翼膜在有無安裝單向閥門間之升力差異,以便做進一步的單向閥門設計與校正。本研究最終目的為研發出能夠藉由降低拍翼阻力來達到提升平均拍翼升力之單向閥門,並以20cm翼展之「金探子」PET拍翼膜為例,在加裝半徑7.43mm之三樑式單向閥門後,在3.7V電壓,傾斜角30度,自由流速3.0m/s下,輸出平均升力25.5gf,高於無安裝單向閥門拍翼平均升力86%。 |
英文摘要 |
This thesis provides the new concept, which is related to the wing membrane where some check valves were attached on the wing membrane, which acts as an actuator. The opening and closing of check valves will help in reducing the air resistance of the wing during the upstroke, which can improve in the overall lift during the flapping. This article also demonstrates the various processing technique and software processing like mechanism design, flow field analysis, and more. The software which made in use was Solidworks and ANSYS where Solidworks was used primarily for design and development of various structure like check valve structure design, and more and ANSYS was used for the analysis of natural frequency on the wing membrane during to flapping process in order to facilitate the availability of check valves design on the wing membrane. The result of natural frequency comes to 17.86Hz, which is in anticipation of the range that higher than flapping frequency (14Hz) by frequency response analysis. As the conception of low-pass filter, it is easy to quantify the effect of check valves on flapping. In this study, it also mentions the traditional processing methods like the operation of cutting machine-auxiliary production of check valve. The wind tunnel experiment was conducted where the comparison was made with and without the check valves. Furthermore, wing design calibration has also been conducted. The final objective for this experiment was to develop a check valve that can increase the overall lift by reducing the wind resistance during the upstroke. For the current study, Evans mechanism was used with 20cm wingspan of PET as the wing membrane the check valve with three beams of radius 7.43mm was used which get active during the downstroke. At 3.7V with 30 inclined angle at 30(m/s) wind velocity the average output of lift was 25.5(gf) which is 86% higher than the valve less model. |
第三語言摘要 | |
論文目次 |
CONTENT Chapter 1 Introduction 1 1-1 Research background 1 1-2 Literature review 2 Chapter 2 Motivation and Procedure of Design 7 2-1 The production of NACA wing model 7 2-2 The final result of NACA wing made by parylene coating 9 Chapter 3 Check Valve Design for Flapping Wings 12 3-1 Conception design of check valve wing 12 3-2 The evolution of check valves 16 3-2-1 A new design of check valve with 3 beams 18 3-2-2 A derivation of specification for check valves 29 3-3 Calculation of check valve efficiency 21 3-4 Natural frequency simulation of check valves 24 3-5 Wind tunnel experiment of a flapping wing with check valves 26 3-6 Improvement of check valves in new dimension 30 3-7 Wind tunnel experiment of check valves in dimension 32 Chapter 4 Results and Discussion 35 4-1 Observation on check valve by high-speed camera 35 4-2 Flight testing of FWMAV with check valves 36 Chapter 5 Conclusion and Future Work 40 REFERENCES 43 APPENDIX A 48 APPENDIX B 54 APPENDIX C 62 APPENDIX D 66 Publication List 81 LIST OF FIGURES Figure 1.1 (a)Initiator, (b)Eagle II 4 Figure 1.2 Golden Snitch 5 Figure 1.3 FWMAV with voice coil motor 6 Figure 2.1 3D Printer LPD Plus technology 8 Figure 2.2 Parameter of aerofoil 11 Figure 3.1 The function of check valve in flapping motion 13 Figure 3.2 The check valve made by cutting machine 14 Figure 3.3 The first type of check valve design by AutoCAD 14 Figure 3.4 The second type of check valve design by AutoCAD 14 Figure 3.5 The process of making wing with check valve 15 Figure 3.6 The wing with check valve before doing HCL melting 16 Figure 3.7 The production of wing with 30 check valves 16 Figure 3.8 The fluid field simulation from COMSOL software 17 Figure 3.9 The proper arrangement of hole on the wing surface 18 Figure 3.10 Illustration of check valve 20 Figure 3.11 The dimension of check valve in new design 20 Figure 3.12 The check valve made by cutting machine 21 Figure 3.13 The FWMAV fix with check valve 21 Figure 3.14 The Bode plot of frequency 23 Figure 3.15 The check valve made by cutting machine 25 Figure 3.16 The stress distribution on check valves 26 Figure 3.17 The 6-Component load cell of wind tunnel 27 Figure 3.18 Wind tunnel in Tamkang University 27 Figure 3.19 The experiment data of lift force testing with original wing 29 Figure 3.20 The weight comparison 30 Figure 3.21 The dimensions of new check valve in 7.43mm radius 31 Figure 3.22 The substance of check valve in new design 31 Figure 3.23 The arrangement of new check valve 32 Figure 3.24 The data of lift force testing in new check valve 33 Figure 3.25 The graph of lift coefficient vs. Reynolds number in different voltage 34 Figure 4.1 The motion of check valves in flapping sequence 36 Figure 4.2 Weight distribution . 38 Figure 5.1 Flight testing 42 Figure A.1 The NACA wing mode design by SolidWork software 48 Figure A.2 PDMS liquid pouring in NACA wing mode 48 Figure A.3 The PDMS film release from silicon wafer 49 Figure A.4 The NACA0012 wing model made by PDMS 49 Figure A.5 The prototype of NACA wing design 50 Figure A.6 NACA wing making layer-by-layer in AutoCad software 50 Figure A.7 Coating layer arrangement on the PET wing surface 51 Figure A.8 The PET wing was wrapped by aluminium foil 51 Figure A.9 The Graphtec cutting plotter CE5000-60 52 Figure A.10 The MEMS process of wing with check valves 52 Figure A.11 The LH 300- parylene coating machine 53 Figure A.12 The staples were removed by HCL etching 53 Figure A.13 Evans mechanism in new design 56 Figure A.14 Stress contour of modified Evans mechanism 57 Figure A.15 Displacement plot of modified Evans mechanism 57 Figure A.16 Polycarbonate mechanism assembly 58 Figure A.17 Visijet SL Flex mechanism assembly 59 Figure A.18 Visijet M2R-Wt mechanism assembly 59 Figure A.19 Low speed sub sonic wind tunnel in Vel Tech University, India 61 Figure A.20 Test section of wind tunnel in Vel Tech University, India 61 Figure A.21 The raw data of lift force 62 Figure A.22 The raw data of lift force 63 Figure A.23 Flapping lift (frequency domain) of FWMAV with check valves . 63 Figure A.24 Lift signal (time domain) from FWMAV with check valves 63 Figure A.25 Lift force with inclined angle 20°, 3.0V, wind speed 1.5-3.0 from (a)-(d) 66 Figure A.26 Lift force with inclined angle 20°, 3.4V, wind speed 1.5-3.0 from (a)-(d)67 Figure A.27 Lift force with inclined angle 20°, 3.7V, wind speed 1.5-3.0 from (a)-(d)68 Figure A.28 Lift force with inclined angle 30°, 3.0V, wind speed 1.5-3.0 from (a)-(d) 69 Figure A.29 Lift force with inclined angle 30°, 3.4V, wind speed 1.5-3.0 from (a)-(d)70 Figure A.30 Lift force with inclined angle 30°, 3.7V, wind speed 1.5-3.0 from (a)-(d) 71 Figure A.31 Lift force with inclined angle 50°, 3.0V, wind speed 0.5-1.0 from (a)-(c)72 Figure A.32 Lift force with inclined angle 50°, 3.4V, wind speed 0.5-1.0 from (a)-(c) 73 Figure A.33 Lift force with inclined angle 50°, 3.7V, wind speed 0.5-1.0 from (a)-(c) 74 Figure A.34 Lift force with inclined angle 60°, 3.0V, wind speed 0.5-1.0 from (a)-(c) 75 Figure A.35 Lift force with inclined angle 60°, 3.4V, wind speed 0.5-1.0 from (a)-(c) 76 Figure A.36 Lift force with inclined angle 60°, 3.7V, wind speed 0.5-1.0 from (a)-(c) 77 Figure A.37 Lift force with inclined angle 70°, 3.0V, wind speed 0.5-1.0 from (a)-(c)78 Figure A.38 Lift force with inclined angle 70°, 3.4V, wind speed 0.5-1.0 from (a)-(c) 79 Figure A.39 Lift force with inclined angle 70°, 3.7V, wind speed 0.5-1.0 from (a)-(c) 80 LIST OF TABLE Table 3.1 Material selection for check valve 25 Table 4.1 Weight distribution 37 Table 4.2 The specification and pixel of high speed camera 38 Table 4.3 The comparison with check valve in different types and normal wing ....... 39 Table A.1 Evans mechanism assembly 55 Table A.2 The material property of Evans mechanism under 3D printing 60 |
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