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Short/Small Crack Model Development for Aircraft Structural Life Assessment

机译:飞机结构寿命评估的短/小裂纹模型开发

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This paper presents the testing and modeling results from an NRC project on short/small ① crack model development for aircraft structures.Fatigue tests were conducted for 7075-T73 hand forging aluminium material using precracked compact tension (C(T)) and naturally cracked single edge-notch tension (SENT) coupons,under various stress ratios.The adjusted compliance ratio (ACR) method was used for the C(T) coupon tests aiming to quantify remote closure due to plasticity and forging-induced residual stresses.For the SENT coupons,three-dimensional StressCheck finite element (FE) models were developed to accurately calculate the stress intensity factors of surface and corner cracks.Both C(T) and SENT test data were combined to develop short-long fatigue crack growth rate models.These models were then used in crack growth life analyses for coupon and component cases,taken from transport aircraft under spectrum loadings.It was shown that the newly developed models resulted in more accurate fatigue life estimations.
机译:本文介绍了NRC飞机结构的短/小①裂纹模型开发项目的测试和建模结果。使用预裂纹压紧力(C(T))和自然裂纹单杆对7075-T73手工锻造铝材料进行了疲劳测试在各种应力​​比下的边缘缺口拉力(SENT)试件.C(T)试件测试使用调整后的柔度比(ACR)方法,目的是量化由于塑性和锻造引起的残余应力而导致的远程闭合。试件,建立了三维StressCheck有限元(FE)模型以精确计算表面和拐角裂纹的应力强度因子,并结合C(T)和SENT测试数据建立了短时疲劳裂纹扩展率模型。然后将模型用于频谱载荷下从运输机上获取的试样和零件盒的裂纹扩展寿命分析。结果表明,新开发的模型可以更精确地计算出疲劳寿命估计。

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