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  • 學位論文

翼展10公分之拍翼式微飛行器研製

Fabrication of Flapping Micro Aerial Vehicles with 10 Centimeter Wingspan

指導教授 : 楊龍杰

摘要


本研究以10公分翼展之微飛行器為設計之目標,材料選用質量輕、強度強的鋁合金作為基座材料,並搭配本實驗室自行開發之塑膠連桿與齒輪,組成10公分翼展微飛行器之傳動機構。機翼骨架為質輕之碳纖維棒帶動聚對苯二甲酸乙二醇酯(PET)翼膜,鋰電池為動力之來源,構成全機重約4克之拍翼式飛行器。 本研究主要針對10公分拍翼機之翼膜,於不同攻角與不同拍撲頻率下氣動力之探討,經由風洞實驗,發現本研究之拍翼式微飛行器之升力與其全機重接近,但其淨推力值卻會出現負值。本研究亦針對尾翼之外型進行最佳化設計,利用田口直交表進行歸納,並得知尾翼裝置角、厚度、翼展與弦長之最佳值。分析結果發現,於裝置角0°、厚度1.8 mm、翼展15 cm與弦長22 mm時具有最佳之升推力值。與無尾翼時相較,推力值有著大幅提升。並且藉由風洞可視化實驗發現,加裝尾翼後可以有效引導拍翼時所產生之渦流,由此可看出加裝最佳化尾翼後為何淨推力值上升之原因。 本實驗最後將此拍翼式微飛行器進行實際飛行測試,其飛行時間約為11秒,飛行範圍約為直徑3公尺。

並列摘要


This research is to fabricate a flapping micro aerial vehicle (MAV) with 10 cm wingspan. The aluminum alloy with light weight and strong intensity is selected to manufacture the motor base, which is combined a plastic linkage and gear to form a wingspan of 10 centimeters of transmission system. The PET wing membrane is driven by the skeleton of the light carbon fiber rods and the power source is supplied by lithium battery. Finally, we make up a MAV which is only 4 grams in weight and 10 cm in width. Additionally, the PET films are tested by a series of aerodynamic experiments. The results show that the lift forces are sufficient to the MAV. However, the net thrust force would be a negative value. The design of tail shape is also optimized in this work. The optimization is done by Taguchi orthogonal table including the tail angle, thickness, chord length and wingspan. It is found that the best value of the aerodynamic force is the device with angle 0°, 1.8 mm thickness, 15 cm wingspan and 22 mm chord length. Then compared with non-tail, the thrust force has increased dramatically. Flow visualization by wind tunnel shows that the installed tailcan effectively guide the shedding vortex, that influences the net thrust of the MAV. Finally, we have some flying tests. The endurance of the MAV is about 11 seconds, and the flight range of about 3 meters in diameter.

並列關鍵字

Micro Aerial Vehicles PET tail

參考文獻


[34] 高敏維,“微拍翼機可撓翼之氣動特性實驗”,碩士論文,機械與機電工程學系,淡江大學,2008年。
[1] 何仁揚,「拍撲式微飛行器之製作及其現地升力之量測研究」,碩士論文,機械與機電工程學系,淡江大學,2005年。
[3] 徐振貴,「拍翼式微飛行器之設計、製造與測試整合」,博士論文,機械與機電工程學系,淡江大學,2008年。
[6] W. Shyy, M. Berg, and D. Ljungqvist, “Flapping and flexible wings for biological and micro air vehicles,” Progress in Aerospace Sciences, Vol. 35, pp. 455-505, 1999.
[7] U. M. Norberg, Vertebrate Flight: Mechanics, Physiology, Morphology, Ecology and Evolution, New York: Springer, 1990.

被引用紀錄


柯皓翔(2016)。結合音圈馬達之拍翼機構輕量化〔碩士論文,淡江大學〕。華藝線上圖書館。https://doi.org/10.6846/TKU.2016.01054
李錫軍(2016)。三維拍翼流場模擬之初探〔碩士論文,淡江大學〕。華藝線上圖書館。https://doi.org/10.6846/TKU.2016.00255
林侑廷(2016)。利用公克級機載航電元件之半自主拍翼飛控〔碩士論文,淡江大學〕。華藝線上圖書館。https://doi.org/10.6846/TKU.2016.00209
陳建瑋(2015)。多拍翼編隊飛行節能之地面初測〔碩士論文,淡江大學〕。華藝線上圖書館。https://doi.org/10.6846/TKU.2015.01111
洪堃銓(2014)。仿蜂鳥懸停機構套件之設計與製造〔碩士論文,淡江大學〕。華藝線上圖書館。https://doi.org/10.6846/TKU.2014.01134

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