The T-joint structure is a typical stiffened skin - fuselage frame joint and an important component in the integral design of composite material. Delamination of the interface between skin and frame is a typical failure mode of T-joint. Z-pin can significantly improve the interface performance between skin and frame. In this paper, the damage process and failure mode of z-pinned joint of the T-joints are studied through simulation and experiment. First, pull-out strength experiments are performed to determine the failure modes of z-pinned joint of the T-joints. The influence of clamping span on the pull-out load is also studied in the T-joint experiments. Our results show that z-pin can significantly improve the ultimate pull-out load and connection efficiency of composite T-joint. The improvement effect became more obvious with the decrease of clamping span. Second, the bilinear cohesive behavior and nonlinear spring elements are introduced to simulate T-joints the delamination of interface and the effects of z-pin under the pull-out load. Simulation results are in good agreement with the experiments, which verifies the reliability of the interface damage simulation of cohesive behavior contact and the z-pin simulation of nonlinear spring element. Our simulations and experiments reveal similar damage failure modes together.
Research on Typical Joint Technology of Composite Stiffened Skin-Fuselage Frame
Lect. Notes Electrical Eng.
Proceedings of the 5th China Aeronautical Science and Technology Conference ; Kapitel : 21 ; 197-208
2021-11-02
12 pages
Aufsatz/Kapitel (Buch)
Elektronische Ressource
Englisch
Research on Typical Joint Technology of Composite Stiffened Skin-Fuselage Frame
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