在渦輪螺旋槳引擎的應用上，擁有較高的推進效率以降低油耗的優點，因此，在短程飛行過程當中，不需要太大的推力，並且擁有其一定的速度與方便性，隨著無人飛機的發展越加興盛渦輪螺旋槳為一具有發展潛能的引擎。
在飛機飛行時，隨著高度變化，會影響環境的空氣密度與溫度，因而影響引擎的操作條件，此篇文獻在於探討其各層面的變化對飛機引擎的影響，除了引擎本身的壓縮器會因流量變化而導致湧振(Surge)或失速(Stall)，葉輪的材料耐熱限度外，亦對飛行性能的表現作搭配，以期完成一引擎控制邏輯，能將之使用於我國未來航太工業之發展。
引擎之控制邏輯須使引擎在提供足夠的能量時，並確保引擎的各操作條件不會使超越極限值，以免發生引擎失效或損毀的情況，此文獻以探討各層面的影響為基礎，自行發展了一最小油量控制邏輯。

In the applications of a turboprop, it has a good propulsion efficiency to reduce the fuel cost. Therefore, it is a proper choice for a short-range flight that doesn’t need large thrust to fly at a fast speed. With the growing interest in unmanned aerial vehicles (UAVs), the turboprop is also a potential engine in this field.
During a flight, the ambient condition of the air density and temperature vary with changes in altitude and further affect both flight and engine performance. This study focused on any aspect that alternating the engine performance, in addition to compressor surge or stall due to the alternating flow rate, or the temperature limit of the turbine blade, a combination of the flight performance has been investigated.
The control logic of the engine is required to provide sufficient power and prevent the operating point from exceeding any structural limit to keep the engine operating safely. This study based on numerous aspects of the effect of the engine and developed a minimum of fuel supply control logic.

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