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Crack linkup and residual strength of aircraft structure containing multiple site damage.

机译:包含多个部位损坏的飞机结构的裂纹连接和残余强度。

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An experimental and numerical study was completed to evaluate the characteristics of the T*ϵ integral fracture criterion and to explore the possibility of using it to predict crack linkup and residual strength of aircraft structures containing MSD. The study included five different crack configurations, ranging from one to five cracks, for studying the basic characteristics of the T*ϵ integral in the single crack environment as well as in the multiple cracks environment with interactions between cracks.; Moiré interferometry was used to determine the orthogonal displacement fields surrounding stably growing cracks and a procedure was developed to evaluate T*ϵ directly from the displacement data. Elastic-plastic finite element analyses of the fracture specimens were evaluated by inputting the measured moiré displacement data along the width, 10 to 25mm away from the crackline, of the specimens.; Overall, the experimentally and the FE determined T*ϵ values were in excellent agreement with each other. Both experimentally and FE evaluated T*ϵ showed that T*ϵ is contour size dependent. However, for a constant integral contour size, T* ϵ is constant during steady state crack growth. Cracks on all five specimen configurations exhibited crack growth at similar T*ϵ values. Thus T*ϵ integral is a local fracture parameter and that it is independent of the specimen geometry or crack configurations.; Crack growth simulation based on the T*ϵ criterion to predict crack linkup and residual strengths correlated very well with test results. On the average, the predicted maximum loads were within 3% of the test results.; The CTOA criterion is a local fracture parameter and the angle is constant during steady state crack growth, similar to the T*ϵ integral. However, during the initial stage of crack growth where crack tunneling and shear lip formation exist, the measured CTOA was larger than the steady state CTOA and are scattered. For problems where fracture occurs immediately within crack growth, the CTOA criterion may not be very reliable since the CTOA criterion is usually assumed constant through out the fracture process.; The plastic zone criterion was also used to predict the crack linkup and residual strength. It was shown that the criterion worked well for some cases but poorly for others.
机译:完成了一项实验和数值研究,以评估T * ϵ 整体断裂准则的特性,并探索使用该准则预测含MSD的飞机结构的裂纹连接和残余强度的可能性。该研究包括五种不同的裂纹形态,范围从一到五个裂纹,以研究单裂纹环境以及多裂纹环境中T * ϵ 积分之间的相互作用的基本特征。裂缝。利用莫尔干涉法确定围绕稳定生长的裂纹的正交位移场,并开发了一种直接从位移数据评估T * ϵ 的程序。通过沿沿距裂纹线10至25mm的宽度输入测得的莫尔位移数据来评估断裂试样的弹塑性有限元分析。总体而言,通过实验和FE确定的T * ϵ 值彼此之间非常吻合。通过实验和有限元评估,T * ϵ 均显示T * ϵ 与轮廓尺寸有关。但是,对于恒定的整体轮廓尺寸,在稳态裂纹扩展过程中T * ϵ 是恒定的。所有五个试样构型上的裂纹在相似的T *和ε处均表现出裂纹扩展。 值。因此,T * ϵ 积分是一个局部断裂参数,它与试样的几何形状或裂纹形态无关。基于T * ϵ 准则的裂纹扩展模拟来预测裂纹连接和残余强度与测试结果非常相关。平均而言,预计的最大负载在测试结果的3%以内。 CTOA准则是局部裂缝参数,在稳态裂纹扩展过程中角度恒定,类似于T * ϵ 积分。然而,在存在裂纹隧道和剪切唇形成的裂纹扩展的初始阶段,测得的CTOA大于稳态CTOA并散布。对于裂纹在裂纹扩展范围内立即发生的问题,由于通常认为CTOA准则在整个断裂过程中都是恒定的,因此CTOA准则可能不是很可靠。塑性区准则还用于预测裂纹连接和残余强度。结果表明,该标准在某些情况下适用,但在另一些情况下效果较差。

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