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首页> 外文期刊>Journal of Aerospace Sciences and Technologies >DAMAGE TOLERANCE EVALUATION OF WING BOTTOM SKIN PANEL OF AN AIRCRAFT
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DAMAGE TOLERANCE EVALUATION OF WING BOTTOM SKIN PANEL OF AN AIRCRAFT

机译：飞机机翼底部皮肤面板的损伤容限评估

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摘要

This paper presents the details of damage tolerance evaluation of a Wing Bottom Skin Panel (WBSP) of an aircraft. Finite element analysis (FEA) of an integrally stiffened WBSP has been conducted to identify the probable location for crack initiation and the same has been confirmed by conducting experiments. Linear elastic fracture mechanics (LEFM) principles have been used for computation of stress intensity factor (SIF). Static results obtained from FEA and experiments are found to compare well. SIF has been computed for different crack lengths in mode I under intact-stiffener condition by using displacement extrapolation and strain energy release rate (SERR) techniques. SIF has also been computed for the same crack lengths under broken stiffener and unstiffened conditions. A comparison between the residual strength predicted under intact-stiffener, broken stiffener and unstiffened conditions clearly indicates the efficacy of the stiffener in arresting the crack propagation.
机译：本文介绍了飞机机翼底部蒙皮面板（WBSP）的损伤承受能力评估的详细信息。已经对整体加强的WBSP进行了有限元分析（FEA），以识别裂纹萌生的可能位置，并且已经通过实验证实了这一点。线性弹性断裂力学（LEFM）原理已用于计算应力强度因子（SIF）。发现从FEA和实验获得的静态结果可以很好地进行比较。通过使用位移外推法和应变能释放率（SERR）技术，在完整加劲肋条件下，在模式I下针对不同裂纹长度计算了SIF。在断裂的加劲肋和未加劲的条件下，对于相同的裂纹长度也已计算出SIF。在完整加劲肋，断裂的加劲肋和未加劲的条件下预测的残余强度之间的比较清楚地表明了加劲肋在阻止裂纹扩展方面的功效。

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