本論文的研究目的是應用飛行與推進系統整合控制(Integrated Flight/Propulsion Control, IFPC)於戰機短場降落。吾人透過速度向量追蹤控制迴路的疊代邏輯，計算出內迴路飛行控制所需的輸入命令以及當下的推力命令，並輸入到推進系統模型，藉此達到飛行與推進系統整合。接著，設計位置向量追蹤控制迴路，使F-16戰機可以在慣性座標上做精確的路徑追蹤。
當執行短場降落時，需要降低著陸速度使滑行距離縮短，而此時一般未加裝向量噴嘴的傳統戰機會因為速度不足而導致升力不夠的情況。為了解決此現象，吾人透過加裝向量噴嘴，利用推進系統提供額外的力與力矩，使戰機在升力不足的情況下，仍能達到平衡。經過兩種模擬的比較，結果顯示，戰機在加入向量推力後可以執行短場降落，使降落速度有效減少16.7%。

The purpose of the thesis is to discuss the application of Integrated Flight/Propulsion Control in aircraft short-field landing. Through the Speed Vector Tracking Control integrate the flight system and propulsion system, we can calculate the input commands required by the inner loop and input the thrust command to the propulsion system. Then, we design a Position Tracking Control Loop so that the F-16 can accurately track the path on the inertial frame.
When performing the short-field Landing, it need to reduce the landing airspeed to shorten the landing distance. At this time, the traditional aircraft which isn’t equipped with vector nozzle will be unstable due to insufficient lift. To solve this problem, we install a vector nozzle let the propulsion system provide additional force and moment, so that the fighter can still maintain balance in the case of insufficient speed. After comparing the two simulations, the results show that adding the vector nozzle can make the aircraft perform the short-field Landing and let the touchdown speed efficiently reduce 16.7%.

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