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Damage Tolerance Analysis for Repaired Composite Stringer Panels

Conference paper
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Part of the Lecture Notes in Electrical Engineering book series (LNEE, volume 549)

Abstract

In this paper, the damage tolerance of repaired composite panels with an M style stringer was analysed through a finite element model. Firstly, an interface unit is introduced to make connection relationship between the panel and stringer. The strength and damage tolerance are analysed by using nonlinear finite element method (FEM). Then the panel laminates with internal presupposition damage are analysed. The damage tolerance is determined under four-point bending load by simulation. Then the failure laminated panel was repaired by patching method. Finally, the structure strength and damage tolerance of the repaired panel with stringer was analysed. The research results can provide some theoretical support for the repair of aircraft composite materials in the future.

Keywords

Aircraft composites Damage tolerance Repair 

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Copyright information

© Springer Nature Singapore Pte Ltd. 2019

Authors and Affiliations

  1. 1.School of Aeronautics & AstronauticsShanghai Jiao Tong UniversityShanghaiChina

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