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Damage Tolerance Analysis for Repaired Composite Stringer Panels

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Proceedings of International Conference on Aerospace System Science and Engineering 2018 (ICASSE 2018)

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

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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.

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Authors and Affiliations

  1. School of Aeronautics & Astronautics, Shanghai Jiao Tong University, Shanghai, China

    Lin Ma & Yin Yu

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  1. Lin Ma
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  2. Yin Yu
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Corresponding author

Correspondence to Yin Yu .

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Editors and Affiliations

  1. School of Aeronautics and Astronautics, Shanghai Jiao Tong University, Shanghai, China

    Zhongliang Jing

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Ma, L., Yu, Y. (2019). Damage Tolerance Analysis for Repaired Composite Stringer Panels. In: Jing, Z. (eds) Proceedings of International Conference on Aerospace System Science and Engineering 2018. ICASSE 2018. Lecture Notes in Electrical Engineering, vol 549. Springer, Singapore. https://doi.org/10.1007/978-981-13-6061-9_6

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  • DOI: https://doi.org/10.1007/978-981-13-6061-9_6

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  • Publisher Name: Springer, Singapore

  • Print ISBN: 978-981-13-6060-2

  • Online ISBN: 978-981-13-6061-9

  • eBook Packages: EngineeringEngineering (R0)

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