四軸飛行器為近年來極具發展潛力的新興電子產品，不止在軍事偵察與商用拍攝具有貢獻，在農事、消防救災、包裹輸送、地質偵查與科學研究等方面也具有相當大的潛力。藉由輕巧便利、能夠進行垂直起降、滯空懸停與在不同地形穿越等優點，迅速成為各界新寵。但在巨大開發潛能下，四軸飛行器仍有載重能力不足、續航力較短的缺點，若能藉改善電能應用效率與增大單一馬達提供升力，能使四軸飛行器發展不再受到侷限，具有更廣泛的新興應用潛力。
螺旋槳效率曲線以不同進動比下的利用效率表示。對固定俯仰角螺旋槳而言，由於製造時角度已固定，其效率曲線只有一條，而可調俯仰角螺旋槳則因俯仰角可調整，能依據不同俯仰角輸入得到一系列效率曲線，增大了螺旋槳效率應用可調性；目前螺旋槳飛機廣泛應用的恆速螺旋槳系統，即利用可調俯仰角螺旋槳原理使引擎燃油效率大為增加。本研究主旨為建立可同時控制多片葉片俯仰角的四軸飛行器葉片俯仰角變換控制機構，增加單一馬達能提供的升力，同時藉控制俯仰角變換使四軸飛行器電能應用效率更好，增加滯空飛行時間。
本研究設計並製造的俯仰角變換控制機構可依加裝的葉片數目進行快速調整，共測試分別裝配2、3與4片螺旋槳葉片的機構，驗證其在轉速6000rpm下的使用安全性，並找出造成機構使用缺陷的可能原因分析。同時發現在靜態流場下，葉片俯仰角變換精確度誤差的發生原因有1.在不同轉速旋轉，2.葉片俯仰角變換方向(葉片受力大小不同)，3.裝配不同數目葉片等三變數；而機構採用PLA材料印製，質輕不失強度，對機體負擔小。此葉片俯仰角變換控制機構經實驗證明可在螺旋槳高速動態轉動下確實變換多片葉片的俯仰角，達成攻角變換與提升單位馬達提供升力的目的。

Quadcopter is an emerging electronic product with great potential in recent years. It not only contributes to military reconnaissance and commercial application, but also can play an important role in agriculture, remote area parcel transportation, geological exploration and scientific research. However, under its huge potential, the quadcopter still has the disadvantages of low load capacity and low endurance. Therefore, if power utilization efficiency can be improved and the lift provided by a single motor can be increased, the future of quadcopter can be no longer limited.
The propeller efficiency theory shows that the propeller efficiency curve can be expressed as a function of advance ratio and blade angle. For fixed-pitch propellers, since the pitch angle is fixed at manufacturing process, there is only one efficiency curve. But variable pitch propellers can have several propeller efficiency curves according to different pitch angle inputs, which increases the adjustability of the propeller efficiency application.
Constant-speed propeller system which widely used in propeller aircraft is based on the variable pitch propellers to greatly increase the fuel efficiency of the engine. The main purpose of this study is establishing a pitch angle control mechanism for quadcopter to increase the adjustable possibilities of propellers.
The pitch angle control mechanism designed in this study can be quickly adjusted according to the number of installed blades, and it can control several blades’ pitch angle at the same time. We tested the mechanism of assembling 2, 3 and 4 propeller blades respectively, verifying the safety of the use below 6000 rpm, and have found out the possible causes of the defects in the mechanism. The tested experiment proved that the pitch angle control mechanism is suitable for medium size quadcopter, but still need some control algorithm design to have the same benefits in Constant-speed propeller system which widely used in propeller aircraft.

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