Progressive Failure Analysis of Composite/Aluminum Riveted Joints Subjected to Pull-Through Loading

Abstract Out-of-plane mechanical properties of the riveted joints restrict performance wing box assembly airplane. It is necessary to investigate pull-through composite/metal in order guide riveting design and ensure safety assembly. The progressive failure mechanism composite/aluminum joint subjected loading was investigated by experiments finite element method. A damage model based on Hashin-type criteria zero-thickness cohesive zone method developed VUMAT subroutine, which validated both open-hole tensile test three-point bending test. Predicted load-displacement response, modes propagation were analysed compared with results tests. There are 4 obvious characteristic stages curve that model: first load take-up stage, second stage stage. Relative error stiffness, peak between 8.1%, − 3.3% 10.6%, respectively. found specimen mainly broken rivet-penetration fracture delamination plies composite laminate. And material within scope rivet head more dangerous serious damages than other regions, especially for 90° plies. This study proposes a numerical prediction reveals hybrid loading.