Lateral Compressive Behavior of Scarf Repaired Honeycomb Sandwich Panels
LIU Sui1, GUAN Zhidong1, GUO Xia1, YAN Dongxiu2, LIU Weiping2, KONG Jiaoyue2
1. School of Aeronautic Science and Engineering, Beihang University, Beijing 100191, China;2. Composite Center of Shanghai Aircraft Manufacturing CO. Ltd., Commercial Aircraft Corporation of China, Ltd., Shanghai 200436, China
Abstract：Three different repair methods were adopted in the paper to restore the mechanical performance of composite honeycomb sandwich panels with different initial damages, and an experimental study was conducted to compare the edgewise compressive capacities of repaired specimens. Test results demonstrate that all these repair methods can recover the edgewise compressive strength of specimens effectively, and the strength recoveries are all above 79% of the intact panel level. The panel with the smallest initial damage has the highest strength recovery. Besides, unsymmetrical repair structures should be adopted cautiously to avoid the mechanical performance degradation induced by the additional bending moment. Based on test results, a finite element model was adopted to investigate the edgewise compressive behavior of repaired specimen. The calculated stiffness, ultimate load and failure model are in good agreement with test results. The numerical model provides an efficient repair design method on composite honeycomb sandwich panels.