本論文建立起落架模型並搭配飛行控制律，使戰機得以執行短場起降功能。吾人利用起落架的座標判斷輪胎是否觸地，當起落架接收到輪胎觸地訊號時，系統會藉由彈簧阻尼避震器計算出跑道給予的正向力及輪胎的摩擦力。最後將正向力與摩擦力輸入F-16模型中，模擬戰機在起飛及降落後於跑道上的滑行動作。
戰機在執行短場起飛時，需要降低仰轉速度；而執行短場降落時，需要降低著陸速度，使滑行距離縮短。而傳統戰機在未加裝向量噴嘴的情況下，無法彌補戰機因為速度太小導致升力不足的狀況。為了解決此問題，吾人透過加裝向量噴嘴，提供額外的力與力矩，補足戰機不足的升力，使戰機具備執行短場起降的能力。透過模擬比較，戰機在加裝向量噴嘴後，起飛滑行距離縮短37%，而降落滑行距離則約減少了62%。

In this paper, the landing gear model is established and matched with the flight control law, so that the fighter can perform short-field take-off and landing functions. We use the coordinates of the landing gear to determine whether the tire touches the ground. When the landing gear receives the tire touchdown signal, the system uses the spring damping shock absorber to calculate the forward force given by the runway and the friction force of the tire. Finally, the forward force and friction force are input into the F-16 model to simulate the taxiing action of the fighter plane on the runway after take-off and landing.
When performing a short-field takeoff, a fighter needs to reduce its rotation speed; when performing a short-field landing, it needs to reduce the landing speed to shorten the takeoff and landing distance. In the case of traditional fighters without vectoring nozzles, they cannot make up for the insufficient lift of the fighters due to low speed. In order to solve this problem, we installed vector nozzles to provide additional force and torque to make up for the lack of lift of the fighters, So that the fighter has the ability to perform short-field takeoff and landing. Through simulation comparison, after the fighter plane is equipped with vector nozzles, the take-off taxi distance reduce 37%, while the landing taxi distance approximately reduce 62%.

[1] D. Ikaza, "Thrust Vectoring Nozzle for Military Aircraft Engines, Industria de Turbo Propulsores," in Industria de Turbo Propulsores, SA, 2000.
[2] F. Capone, M.L. Mason and L. Leavitt, An Experimental Investigation of Thrust Vectoring Two-Dimensional Convergent-Divergent Nozzles Installed in a Twin-Engine Fighter Model at High Angles of Attack, NASA TM-4155, 1990.
[3] Philippe Costes, Investigation of Thrust Vectoring and Post-stall Capability in Air Combat, AIAA-88-4160, Aug. 1988.
[4] Peter Huber and Patricia Seamount, X-31 high angle of attack control system performance, Materials Science,1994.
[5] David Canter and Allen Groves, X-31 Post-Stall Envelope Expansion and Tactical Utility Testing, Fourth NASA High Alpha Conference, NASA CP- 10143, July 1994.
[6] H. Chen, Effectiveness of Thrust Vectoring Control for Longitudinal Trim of a Blended Wing Body Aircraft, Delft University of Technology, 2015.
[7] Vinayagam A K and Nandan K Sinha,Optimal Aircraft Take-off with Thrust Vectoring, Aeronautical Journal, Oct. 2013.
[8] Jean-Jacques E. Slotine and Weiping Li, Applied Nonlinear Control (3rd ed.), Prentice-Hall, 1991.
[9] Dale Enns, Dan Bugajski, Russ Hendrick and Gunter Stein, "Dynamic inversion: An evolving methodology for flight control design," Int. J. Contr., vol. 59, no. 1, pp. 71-91, 1994.
[10] S. Antony Snell, Dale F. Enns and William L. Garrard, Nonlinear Inversion Flight Control for a Supermaneuverable Aircraft, AIAA J. of Guidance Control and Dynamics, vol. 15, no. 4, pp. 976-984, 1992.
[11] Jeffrey J. Harris, "F-35 Flight Control Law Design, Development and Verification," AIAA AVIATION Forum, 25-29 June 2018.
[12] C. de Visser, J. Mulder and Q. Chu, "Global Nonlinear Aerodynamic Model Identification with Multivariate Splines," AIAA Atmospheric Flight Mechanics Conference, 10-13 August 2009.
[13] Thomas Grohs, Balazs Fischer, Olaf Heinzinger and Oliver Brieger, "X-31 VECTOR Control Law Design for ESTOL to the Ground," AIAA Guidance, Navigation, and Control Conference and Exhibit, 11-14 Aug. 2003.
[14] Scott C. Asbury and Francis J. Capone, Multiaxis Thrust-Vectoring Characteristics of a Model Representative of the F-18 High-Alpha Research Vehicle at Angles of Attack from 0° to 70°, NASA TP-3531, December 1995.
[15] 許莉玲,“下一代戰機起降距離需求分析,”新新季刊第四十七卷第一期,2019.
[16] Charles E. Bentz and John R. Zeller, "Integrated Propulsion Control System Program," in SAE Transaction, 1973.
[17] 張舜淵, “高攻角戰機之非線性動態反算控制律設計,”碩士論文,國立成功大學航空太空工程學系, 2019.
[18] 邱宥瑋, “應用飛行推進整合控制於戰機短場降落,”碩士論文,國立成功大學航空太空工程學系, 2020.
[19] S. N. Singh, M.L. Steinberg and A. B. Page, Nonlinear adaptive and sliding mode flight path control of F/A-18 model, IEEE Trans. Aerosp. Electron. Syst., vol. 39, no. 4, pp. 1250-1262, Oct. 2003.
[20] H. Beh, B. Fischer and R. van den Bunt, "High Angle of Attack Approach and Landing Control Law Design for the X-31A," 40th AIAA Aerospace Sciences Meeting and Exhibit, 14-17 Jan 2002.
[21] John S. Orme and Gilyard, G. Glennd, "Preliminary Supersonic Flight Test Evaluation of Performance Seeking Control, "AIAA-93-1821, June 1993.
[22] Zhaohui Chen, Tim Smith, Paul Stewart and Jill Stewart, "Integrated flight/thrust vectoring control for jet-powered unmanned aerial vehicles with ACHEON propulsion," Institution of Mechanical Engineers Part G Journal of Aerospace Engineering, Apr. 2014.
[23] Michael V. Cook, Flight Dynamics Principles:A Linear Systems Approach to Aircraft Stability and Control Third Edition, Butterworth-Heinemann,2012.
[24] L. T. Nguyen, M. E. Ogburn, W. P. Gilbert, K. Kibler, P. W. Brown, P. Deal, "Simulator Study of StallPost-Stall Characteristics of a Fighter Airplane with Relaxed Longitudinal Static Stability," NASA Technical Paper 1538, Dec. 1979.
[25] Carl Banks, "A DISSCUSSION OF METHODS OF REAL-TIME AIRPLANE FLIGHT SIMULATION," The Pennsylvania State University Graduate School College of Engineering,2004.
[26] Max Baarspul, "A Review of Flight Simulition Techniques," Progress in the Aerospace Sciences, Vol. 27, No. 1, pp. 1-120, 1990.
[27] Frank W. Burcham and Edward A. Haering, "Highly Inegrated Digital Engine Control System on an F-15 Airplane," AIAA-84-1259, June 1984.
[28] MIL-F-8785C Military Specification Flying Quality of Piloted Airplanes, IHS, 1980.
[29] Lochheed Martin Corporation, Flight Manual USAF/ EPAF Series Aircraft F-16A/B, 1995.
[30] Fan Ran, Fang Yuanyuan, Han Yu, Xue Caijun and Wang Enzhen, " Landing dynamic simulation of aircraft landing gear with multi struts," Nanjing University of Aeronautics and Astronautics, Nanjing, 210016, China, 2014.
[31] 楊憲東, “自動駕駛與飛行管理系統,” 於 自動飛行控制原理與實務, 國立成功大學航空太空工程學系, 2002.
[32] 林可心,岑國平,李樂,劉鋼, “飛機起飛著陸性能仿真與分析,” 空軍工程大學學報,Vol.13, No.4, Aug.2019.
[33] 袁東, “飛機起落架數學模型建立與仿真研究,” 碩士論文,西北工業大學, 2001.
[34] 薛宏濤,王克波,“基於起降性能模型的軍用飛機起降規劃與計算,”計算機工程與設計,2011.
[35] Joshua A. Harris, "Nonlinear Adaptive Dynamic Inversion Control for Variable Stability Small Unmanned Aircraft Systems," Master's thesis, Texas A & M University,Dec 2017.
[36] H. J. Tol, C. C. de Visser, E. van Kampen and Q. P. Chu, "Nonlinear Multivariate Spline-Based Control Allocation for High-Performance Aircraft," AIAA Journal of Guidance, Control, and Dynamics, Nov.-Dec. 2014.
[37] Steven P. Wurth and Mark S. Smith, "F-35 Propulsion System Integration, Development, and Verification," AIAA AVIATION Forum, 25-29 June 2018.
[38] Kenneth Bordignon and John Bessolo, "Control Allocation For The X-35B," AIAA 2002-6020, 5-7 November 2002.
[39] Gregory P. Walker, James W. Fuller and Steven P. Wurth, "F-35B Integrated Flight-Propulsion Control Development," AIAA Aviation, 12-14 Aug 2013.
[40] Christopher Miller, "Nonlinear Dynamic Inversion Baseline Control Law:Architecture and Performance Predictions," AIAA Guidance,Navigation, and Control Coference, 2011.
[41] 範平燦(2017),“改變海戰史的垂直起降技術，F35從這裡起飛”,2017年4月17號,取自https://kknews.cc/military/39622y8.html
[42] “英國曾經的輝煌，世界最早的垂直起降戰機，堪稱一代傳奇”,2月11號,取自http://www.ifuun.com/a20172111128659/
[43] "F-18 HARV in flight",2009.12.09,from https://www.dvidshub.net/image/728187/f-18-harv-flight
[44] “美國X-31驗證機“,取自https://www.newton.com.tw/wiki/%E7%BE%8E%E5%9C%8BX-31%E9%A9%97%E8%AD%89%E6%A9%9F/10408558