航空铝合金7050-T7451毛坯初始残余应力测试

The Measurement of Original Residual Stress in Aircraft Aluminum Alloy

为提高裂纹柔度法测试铝合金预拉伸板材毛坯初始残余应力的测试效率和测试精度,从应变采集精度和柔度函数计算效率等方面展开研究,采用基于ABAQUS有限元软件Load Case功能对柔度函数的算法进行了优化。对铝合金预拉伸板7050-T7451的毛坯初始残余应力进行了测试,建立了裂纹柔度法残余应力高效、高精度测量的测试规程,给出了突发状况应对机制。结果表明:柔度函数的计算效率得到显著提升,获得了该板材轧制方向和横向方向的残余应力均呈明显"M型曲线"的分布规律。

In order to improve the measuring accuracy and efficiency, the crack compliance method was adopted to measure the original residual stresses in the pre-stretched aluminum alloy plates, the accuracy of the measured strain and the computational efficiency＇of the compliance functions were discussed. The ＂Load Case＂ of ABAQUS software was applied to optimize the calculation method of compliance function. Then, the original residual stresses in the pre-stretehed aluminum alloy plate 7050-T7451 were measured. The high efficiency, high precision measurement procedures of residual stress and emergency response mechanism were established based on the crack compliance method. The calculated results show the computational efficiency was improved obviously; ＂M type curves＂ of residual stresses were obtained for the rolling and the transverse directions.