Xiao Shan, Huang Mingxuan, Xu Zhonghai, Yang Yusong, Du Shanyi
National Key Laboratory of Science and Technology on Advanced Composites in Special Environments, Harbin Institute of Technology, Harbin 150080, China.
Shenyang Aircraft Design and Research Institute, Shenyang 110135, China.
Polymers (Basel). 2024 Oct 17;16(20):2918. doi: 10.3390/polym16202918.
Composite materials are widely used in aircraft due to the urgent need for high-quality structures in aerospace engineering. In order to verify the effectiveness of complex bolt repairs on composite structures, compression tests have been performed on three types (intact, damaged, and repaired) of composite plate specimens, and finite element simulation results of these three types' specimens were obtained. The experimental results show that for damaged composite laminates, the strength recovery after bolt repair can reach an impressive 107%, and the delamination propagation caused by over-buckling deformation is considered to be the main cause of failure, which also suggests that although bolt repair can improve the strength of the specimens, it has a limited ability to inhibit delamination propagation. The simulation results of the finite element model in this paper are in good agreement with the actual experimental results, and the maximum error does not exceed 7.9%. In conclusion, this paper verifies the suitability of the proposed repair scheme in engineering applications and the correctness of the modeling method for repaired composite laminates.
由于航空航天工程对高质量结构的迫切需求，复合材料在飞机上得到了广泛应用。为了验证复合结构复杂螺栓修复的有效性，对三种类型（完整、受损和修复）的复合板试件进行了压缩试验，并获得了这三种类型试件的有限元模拟结果。实验结果表明，对于受损的复合材料层压板，螺栓修复后的强度恢复率可达107%，超屈曲变形引起的分层扩展被认为是失效的主要原因，这也表明虽然螺栓修复可以提高试件的强度，但抑制分层扩展的能力有限。本文有限元模型的模拟结果与实际实验结果吻合良好，最大误差不超过7.9%。总之，本文验证了所提出的修复方案在工程应用中的适用性以及修复后复合材料层压板建模方法的正确性。
