無人駕駛飛機產業未來將朝向開發安全、低噪音、高效率動力技術的方向發展以維持運輸業的持續成長。電動馬達與內燃機相比具有許多優點，例如低噪音、高扭矩、高效能和低維護成本等優勢。 因此在可見的未來，全電動或混合動力的無人機在市場上將逐漸盛行起來。
本篇論文研究的內容主要是將飛機性能分析方法、螺旋槳性能分析方法及馬達性能分析方法整合在一起，經過一些測試和驗證發展出一套可以對長滯空電動螺旋槳飛機動力匹配最佳化問題進行物理模型分析的程序。
其中飛機性能分析部分採用二維與三維外流場分析程式執行飛機最省能無動力飛行之高度、空速及最省能無動力飛行之阻力分析。對於螺旋槳的性能分析，則以自行撰寫的葉片元素法程式進行螺旋槳性能分析。在最省能飛行高度、空速及推力需求條件下執行螺旋槳節距性能分析以瞭解螺旋槳的性能表現和效率趨勢。對於直流馬達性能分析則以自行撰寫的穩態氣動力負載直流馬達模型程式進行電動螺旋槳模擬。模擬結果可使吾人瞭解馬達的響應狀態和電路中耗能情況，並且進行馬達螺旋槳動力匹配。最後進行馬達Kv 值變況分析和最省能動力飛行空速變況分析獲得最佳動力與其性能表現。
本篇論文所採用的飛機外流場分析程式為開放空間的公用程式XFLR5，此程式已被公認為可靠準確的分析工具。另外本研究自行撰寫的葉片元素法程式及穩態氣動負載直流馬達模型程式，在執行分析前有先執行範例分析或特定分析並與實驗數據比較以驗證程式的準確性，驗證結果令人滿意後再來進行研究分析。本研究所提出之動力匹配優化分析所使用的所有模型皆為物理模型有別於現有大部分的優化方法所使用的模型採用大量統計學的經驗模型。吾人希望本研究之成果有機會在未來無人駕駛飛機產業的發展應用上作出微薄的貢獻。

The unmanned aircraft industry is developing much safer, lower noise and more efficient power technologies to sustain the transportation industry. Electric motors have many advantages over internal combustion engines. Some of these advantages include lower noise, higher torque, higher energy efficiency and lower maintenance costs. For this reason, hybrid electric powered drones are gradually becoming popular.
The main objective of this dissertation is to develop a set of procedures by integrating aircraft performance, propeller performance and motor performance analysis program to optimize the dynamic matching of long endurance electric propeller aircraft. The aircraft performance analysis uses the 2D-3D fast external flow field program to analyze the most energy-saving flight condition and its thrust requirement data. Additionally, the performance analysis of the propeller was carried out by a self-written blade element program. Under the most energy-saving flight altitude, airspeed and thrust demand conditions, the variable propeller pitch was analyzed to obtain the best performance pitch angle. For DC motor performance, the electric propeller simulation was performed with a self-written steady-state aerodynamic load DC motor simulation program.
An analytical tool, XFLR5, that has been recognized as a reliable and accurate program was used to analyze the external flow field of the aircraft. Results of theblade element method and the self-contained steady-state aerodynamic load DC motor model program written in this study which also performs specific analysis of subsystem are compared with the experimental data to verify the satisfactory and the usefulness of the program. Finally, the DC motor velocity coefficient Kv and airplane flight speed, Vc, were chosen to proceed the conjugate direction optimum searching analysis to search the optimum performance of the whole airplane system.
The analysis tool using full physical models proposed in this thesis is different from that of the most current empirical models. It is hoped that this study has an opportunity to make effective contributions to the design and application of various types of electric thrust vehicles.

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