采用层削法测试了7050-T7451高强度铝合金航空板材的残余应力，对比了不同标准测试方法的差异，研究了不同厚度板材残余应力的分布规律。结果表明：试样两端有沉孔和无沉孔对残余应力的测试结果无明显影响；在板材不同宽度位置取样测得的残余应力无显著差异；厚度为20 mm及76 mm板材纵向试样的表层为压缩应力区，次表层为拉伸应力区，心部为无应力或低应力区；厚度为165 mm板材纵向试样从表层到心部分别为拉伸应力区、压缩应力区、拉伸应力区、低拉伸应力区。

The residual stress of 7050-T7451 high strength aluminum alloy aerospace plate was tested by removing layer method. The difference of different standard test methods was compared, and the distribution law of residual stress of plates with different thickness were studied. The results show that the presence or absence of sink holes at both ends of the sample had no significant effect on the residual stress test results. There was no significant difference in residual stress measured by sampling at different width positions of the plate. The surface layer of the longitudinal specimens with thickness of 20 mm and 76 mm was the compressive stress zone, the subsurface layer was the tensile stress zone, and the center was the stress free or low stress zone. From the surface to the center, the longitudinal specimen of 165 mm thick plate was divided into tensile stress zone, compressive stress zone, tensile stress zone and low tensile stress zone.