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Chen, X.M., Zhang, A.Y., Chai, Y.N., Liu, H.W., Wang, L.L. and Yu, F. (2017) Investigation of Repair Technique for Aircraft Composite Wing Panel with Discrete-Source Damage. Journal of Mechanical Strength, 39, 551-556.

has been cited by the following article:

• TITLE: Numerical and Experimental Study on Stiffened Composite Panel Repaired by Bolted Joints under Compressive Load

  AUTHORS: Jifeng Xu, Yuanpei Lan, Xingming Zhang, Kui Du

  KEYWORDS: Stiffened Composite Panel, Bolted Joints Repair, Compression Performance, 3D Finite Element Model

  JOURNAL NAME: Journal of Applied Mathematics and Physics, Vol.6 No.8, August 31, 2018

  ABSTRACT: Numerical and experimental study was conducted to investigate the failure mode and strength performance of stiffened composite panel repaired by bolted joints under compressive load, and the results were then compared with those from virgin stiffened composite panel without any damage. A finite element analysis model was established for repaired and virgin stiffened composite panels under compressive load, the 3D Hashin criteria was applied to identify the composite structure failure, and the secondary stress criteria was adopted to identify the adhesive failure between the base laminate and the stiffener. The failure modes of repaired stiffened composite panels were stiffened composite panels breaking off along the bolt joints. The experimental results were consistent with the finite element analysis results, indicating the reliability of the finite element analysis model.