Abstract: In this paper, the hole-edge stress and damage of open-hole CFRP laminate plate were studied by means of analytical calculation and tensile test. Based on the complex variable function method and the Tsai-Hill failure criterion, the principal stress distribution and the first damage load coefficient of each layer of the laminate plate are calculated. In order to determine the in-plane tensile properties of the plate and verify the analytical results, tensile tests on the plate were carried out based on the ASTM D5766-07 test standard. The results show that 0 degree and ±45 degrees layers are the main bearing layers when the open-hole laminate plate is subjected to the tensile load along the long axis direction, and the maximum value of the principal stress, σ₁, occurs in the range of 65 to 115 degrees and 245 to 295 degrees along the center of the hole, the minimum first damage load coefficient of each layer is within the range of 65 to 115 degrees and the damage load coefficient of 45 and -45 degrees is the smallest. When the load reaches the initial damage load, the internal damage and the parameter degradation begin to occur. After the tensile test, the damage of the laminate plate is mainly based on the matrix cracking and the fiber fracture, the damage region is within the range of 61 to 90 degrees and 241 to 270 degrees around the hole, the results of the test are in agreement with the analytical results.

Key words: analytical calculation, tensile test, damage analysis, hole-edge stress