電動飛行翼無人機的設計、製作與試飛

本論文介紹了台灣無人機產業的現況，並記錄了電動飛行翼無人機的設計、製作、與試飛過程。依據無人機的性能需求：失速速率、最大飛行速率、巡航高度、絕對飛行升限、及轉彎半徑與速率等，求得滿足上述性能需求的機翼負載(Wing loading)及功率負載(Power loading)配對。再根據飛行時間及酬載質量的需求估算無人機的質量，接著計算翼面積及功率需求。由功率需求尋找合適的馬達，根據翼面積選擇適當的翼剖面、進行氣動力設計、及穩定性設計。根據完成的設計以複合材料製作，無人機拆分成三大區塊：機身段、及左右機翼，以CNC開模並以碳纖維環氧樹酯貼附。載具空重6公斤，動力採用AXi 4130/20 kv305電動無刷馬達，飛控系統用Pixhawk，全機質量8.62公斤。飛行試飛包含兩階段，第一階段為遙控飛行觀察飛機飛行狀況，第二階段透過Pixhawk遙控飛行，利用內建陀螺儀、加速儀記錄飛行姿態等，待日後分析飛機的動態特性。由於實際製作的飛機質量大於較原先設計，本文也討論了實際製作完成的無人機對性能需求的影響。

關鍵字

無人機；飛行翼；無人機設計；無人機製作；無人機試飛

並列摘要

This paper presents the design, manufacturing, and flight testing of an electrically powered experimental flying wing unmanned aerial vehicle (UAV). The design process starts with defining the performance requirements including stall speed, maximal speed, cruise altitude, absolute ceiling, and turn radius and speed. The wing loading and the associated power loading are obtained based on the defined performance requirements. The wing area, UAV mass, and power requirement are determined from the endurance and payload requirements. Power requirement supports the determination for motor sizing. Aerodynamics and stability designs are accomplished based on the selected airfoil and the obtained wing area. After the completion of the design, the UAV is made of composite material. The flying wing UAV is equipped with AXi 4130/20 kv305 brushless motor and Pixhawk flight control board. The total mass of the UAV is 8.6 Kg. Flight tests were conducted to evaluate the performance and dynamic characteristics of the produced flying wing UAV and to demonstrate the success of the design.