臺灣博碩士論文加值系統

串聯式雙翼無人機擁有兩個機翼，與雙翼機(biplane)不同的是它並非兩個機翼以上下垂直堆疊的方式配置，而是兩機翼一前一後並相差一個翼弦長以上。串聯式雙翼無人機不只前翼能夠產生升力，後翼也能產生升力並保持無人機飛行的穩定，因此在相同的升力之下，能夠大幅縮短單機翼無人機的翼展長度，降低製造上的難度、存放無人機的空間，以及降低無人機起降時所受到空間大小的限制。由於目前對串聯式雙翼飛行器的研究上不如單翼飛行器那麼充分，進而有待進一步深入研究。
本研究所使用的無人機模型全長為6.2公尺，機翼翼弦長1公尺、翼展15公尺，全機總重約93.4公斤。在飛機飛行時，所遇到的顫振問題會對無人機造成影響，顫振是一種振福會增加的震動，由於慣性力、空氣動力、彈性力相互作用導致無人機在動態中的不穩定而產生，先對其進行模態分析，以獲得振動頻率以及振動模態。對於飛行中的無人機受力狀態，則是先將無人機進行流場分析，以巡航速度每秒12至20公尺飛行，獲得在無人機上的壓力分佈，再將結果輸入靜態結構中，進行單向流固耦合分析，模擬飛行時無人機結構所受之應力。為了近一步探討碳纖維管製作的翼樑受力狀態，將對無人機內部的部件及翼樑進行尺寸的更動，並進行流固耦合分析，以觀察改變參數對於翼樑受力狀態的影響程度，而無人機的重量也是需要注意的一點，因此在改變尺寸的同時也須注意重量的變化。

A Tandem Wing unmanned aerial vehicle (UAV) has two wings, but unlike a biplane, they are not vertically stacked on top of each other. Instead, they are arranged with one wing in front and the other behind, with a distance difference of more than one wing chord length. This configuration allows both wings to generate lift and maintain stability, making it possible to significantly reduce the wingspan of a single-wing UAV under the same lift, which reduces the manufacturing difficulty, storage space, and limitations on takeoff and landing. However, research on Tandem Wing UAVs is not as comprehensive as that on single-wing UAVs, so further investigation is required.
The UAV model used in this study is 6.2 meters long with a wing chord length of 1 meter and a wingspan of 15 meters. The total weight of the aircraft is about 93.4 kg. During aircraft flight, encountered flutter issues can have an impact on unmanned aerial vehicles. Flutter is a type of vibration that increases, resulting in instability during dynamic flight due to the interaction of inertial forces, aerodynamic forces, and elastic forces. Modal analysis is conducted initially to obtain vibration frequencies and modes.For the forces acting on the UAV during flight, a flow field analysis is performed first to obtain the pressure distribution on the UAV at cruising speeds of 12 to 20 meters per second. The results are then inputted into a static structure for one-way fluid-structure coupling analysis to simulate the stress on the UAV's structure during flight. To further investigate the stress conditions of wing beams made of carbon fiber tubes, modifications will be made to the dimensions of internal components and wing beams of the UAV. Flow-structure coupling analysis will then be conducted to observe the extent of the influence of parameter changes on the stress conditions of the wing beams. Additionally, the weight of the UAV is also a crucial consideration, so alterations in dimensions must be mindful of potential changes in weight.

摘要.................................i
Abstract............................ii
誌謝................................iv
目錄.................................v
表目錄..............................vii
圖目錄.............................viii
符號說明.............................xi
1 第一章 緒論.........................1
1.1 研究動機與目的.....................1
1.2 文獻回顧..........................1
1.3 文章架構..........................3
2 第二章 問題定義......................4
2.1 問題描述與模型.....................4
2.2 流場分析統御方程式.................5
2.3 層板理論..........................7
3 第三章 數值方法與驗證................11
3.1 流力模型分析設定與驗證.............11
3.1.1 流力模型分析設定................11
3.1.2 網格收斂性測試..................11
3.2 結構模型分析設定與驗證.............12
3.2.1 結構模型分析設定................12
3.2.2 網格數量收斂性測試..............13
3.3 流固耦合分析設定..................13
4 第四章 結果與討論...................14
4.1 全機結構受力狀態..................14
4.2 流固耦合分析......................14
4.3 全機自然振動頻率..................15
4.4 機翼參數探討......................15
4.4.1 縱樑寬度及厚度探討..............15
4.4.2 翼樑厚度探討....................16
4.4.3 翼樑碳纖維疊層角度探討...........17
4.4.4 翼肋間距........................17
4.4.5 不同風速........................18
5 第五章 結論.........................19
參考文獻..............................58

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