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 本研究依據美軍軍規MIL-A-008862A之內容要求，研析戰機起落架(Landing Gear)設計負載分析流程(負載計算公式)與理論方法，其中包括以下9種不同操作情況下所產生之負載，分別為Landing下的Spin Up、Spring Back、Symmetrical Landing、Drift Landing以及Ground Operation下Static Reaction、Braking、Turning、Pivoting及Taxiing 藉由本研究的負載分析方法研析，將可應用於起落架結構設計負載及疲勞設計負載譜之分析，對起落架結構設計強度(Strength)及疲勞(Fatigue)需求提供必要之數值依據。
 The purpose of this study according to the content requirements of the US military regulations MIL-A-008862A, the design load analysis process (load calculation formula) and theoretical methods of the landing gear of the fighter plane are studied and analyzed.　　There are two main aspects to this topic : Landing and the Ground Operation ,including the following loads generated under 9 different operating conditions: Landing, Spin Up, Spring Back, Symmetrical Landing, Drift Landing, Static Reaction, Braking, Turning, Pivoting, Taxiing.　　Based on the analysis of the load analysis method in this study, it can be applied to the analysis of the landing gear structure design load and fatigue design load spectrum, and provide the necessary numerical basis for the landing gear structure design strength and fatigue requirements.
 摘要 IAbstract II誌謝 III目錄 IV圖目錄 VI表目錄 VII第一章　緒論 11-1 研究背景與動機 11-2 研究目的 21-3 研究方法與步驟 21-4 研究架構 2第二章Landing狀況下分析計算公式 32-1 Sping up 42-2 Spring Back 72-3 Symmetrical Landing 82-4 Drift Landing 9第三章Ground Operation狀況下分析計算公式 103-1 Static Reaction 103-2 Braking 123-3 Turning 133-4 Pivoting 173-5 Taxiing 17第四章結論 20參考文獻 21附錄 軍規MIL-A-008862A 23圖目錄圖 2-1 Spin-Up Reactions 5圖 2-2 起落架動態負載因子圖 6圖 2-3 Spring-Back Reactions 8圖 3-1起落架輪子相對位置示意圖 19 表目錄表 2-1　SYMMETRICAL LANDING ATTITUDES 8表 3-1　MAIN LANDING GEAR DESIGN ULTIMATE LOADS….22表 3-2 NOSE LANDING GEAR DESIGN ULTIMATE LOADS…23
 [1]MIL-A-008862A,“Airplance Strength and Rigidity, Landplane, Landing and Ground Handing Loads”.[2]https://www.faasafety.gov/gslac/ALC/course_content.aspx?cID=34&sID=167&preview=true[3]Snorri Gudmundsson,(2014),“General Aviation Aircraft Design”, Butterworth-Heinemann Publisher, United Kingdom, Chap, 13.[4]SKYBRARY https://www.skybrary.aero/index.php/Category:Aircraft[5]Aerospaceweb.orghttp://www.aerospaceweb.org/question/design/q0289.shtml[6]Sonny T. Chai and William H. Mason＂Landing Gear Integration in Aircraft Conceptual Design＂1997[7]W. Flugge and C. W. Coate, (1954), “ The Influence of Wheel Spin-up on Landing Gear Impact ” , NACA Technical Note 3217.[8]J.Roskam, (1986), Airplane Design, Part IV: Layout Design of Landing Gear and Systems, Roskam Aviation, Ottwa, Kansas.[9]Y. B. Chang, T. Y. Lin, J. R. Wang & C. C. Chen, “Flight loads test of the indigenous defensive fighter,” Journal of Aircraft, vol. 31, pp. 7, 1994.[10]J. S. Morrel, “Flight load investigation of model FG-1 airplane empennage-calibration loading and flight tests,” Rep. TED No. NAM 2447, pt. II, NAES, Philadelphia Navy Yard, Bur. Aero, vol. 7, pp. 8, 1994.[11]N. S. Currey, (1988), Aircraft Landing Gear Design: Principles and Practices, AIAA Education Series, Washington, DC.[12]Dynamic Loads Analysis of Landing-Gear Systems for UAV (2000 year sep month) Wan-Nien Chen.[13]Sidney A. Batterson, (1959), “ Investigation of The Maximum Spin- Up Coefficients of Friction Obtained during Tests of A Landing Gear Having A Static-Load Rating of 20,000 Pounds ”, NASA Memo 12-20-58L.[14]W. Krason, J. Malachowski, ” Dynamics analysis of the main landing gear in 3d model ”, Journal of KONES Powertrain and Transport, Vol. 14, No. 3, 2007, pp. 305-310.[15]E. A. Ossa, “Failure analysis of civil aircraft landing gear”, Engineering Failure Analysis, Vol. 13, 2006, pp. 1177-1183.
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