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    Title: 玻璃纖維複合材料使用於輕型飛機起落架之疲勞模擬分析
    Other Titles: Fatigue analysis of light aircraft fiber glass composite landing gear
    Authors: 黃婉庭;Huang, Wan-Ting
    Contributors: 淡江大學航空太空工程學系碩士班
    陳步偉;Chen, Pu-Woei
    Keywords: 輕航機;起落架;複合材料;疲勞;light aircraft;Landing Gear;composites;Fatigue
    Date: 2013
    Issue Date: 2014-01-23 14:42:54 (UTC+8)
    Abstract: 隨著油價高居不下,為因應現今油價問題,使用高強度比之複合材料來降低營運成本為目前航空業之市場趨勢。另外,飛機之延壽計畫也是航空業者為降低營運成本所積極進行之計畫。但由於航空器隨使用年限的增加,因疲勞問題所造成之機構故障頻率也大幅增加。因此,探討飛機之疲勞壽命分析顯得更為重要。
    本研究主要利用有限元素軟體建立輕型航空運動載具之起落架疲勞模擬平台,並對起落架之不同材料與不同外形進行靜態與動態(疲勞)模擬分析。材料主要選用鋁合金6061-T6與玻璃纖維強化複合材料。起落架外型則以板狀起落架與圓管狀起落架進行分析。負載重量根據Zenith公司CH701最大起飛重量450kg為主要負載。
    由本研究結果可得:複合材料之重量相對於鋁合金大幅減少45%。另外,於相同外形之板狀起落架,其複合材料之應力值相對鋁合金減少21%;而複合材料之應變量則相對鋁合金增加78%。又於相同外形之圓管狀起落架,其複合材料之應力值相對鋁合金增加35%;而複合材料之應變量則相對鋁合金增加76%。於疲勞模擬方面,複合材料與鋁合金起落架於450kg負載時,其疲勞壽命皆高達108cycle。由結果顯示,此兩種材料皆滿足一般輕型航空運動載具所設計之安全壽期,且皆無發生破壞。
    另外,為探究彈性係數、剪力模數與應力比對材料之影響。本研究於靜態分析時,亦分析彈性係數與剪力模數對材料之影響。其結果顯示:剪力模數相對彈性係數對材料之變形量有較大之影響。而於動態分析時,亦分析應力比對材料之影響。其結果顯示:材料之疲勞壽命值隨著應力比之減少而增加;而當材料於往復式循環負載時,其疲勞壽命值則隨著振幅值增加而減少。
    With the hard price of oil, it has been a trend using the composite materials of high ratio of the aircraft in order to reduce the cost of the aviation industry. As time goes, fatigue failure would also increase the probability of accidents. Therefore, it is important to discuss the analysis of the fatigue life.
    The purpose of this study is to use ANSYS Workbench to simulate the fatigue of the Light Sport Aircraft landing gear and analyze the fatigue life in different materials and different shapes. Aluminum alloy 6061-T6 and M9.6 Hexcel Glass Composite in shapes of leaf and tube are both used in this study. The load is considered the maximum of landing weight 450 kg, which is designed from CH701 according to Zenith.
    From the results of this study shows that the using composite material relative to the aluminum alloy cause 45% reduction significantly in weight. Static analysis for the leaf of the same shape shows that using composite material reduce stress to 21% and increase strain up to 78% related to aluminum alloy. On the other hand, in the analysis of the same tube shape, the composite material have huge progress in stress and strain by 35% and 76% respectively in comparison of aluminum alloy. From the results of fatigue analysis, , the fatigue life both reach to 108 cycle when loading for 450kg and are without any damage in materials of whether composite or aluminum alloy landing gear.
    In addition, the study also research that what do Elastic coefficient and the shear modulus have impact on materials in static analysis. The result shows that shear modulus have the larger effect on the deformation. Nevertheless, in the dynamic analysis, the result of stress analysis shows that the materials fatigue life value decreases with increasing stress ratio. Contrarily, when in the reversed cycle, the value of the fatigue life increases with the amplitude value decreases.
    Appears in Collections:[航空太空工程學系暨研究所] 學位論文

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