Study on Damage Tolerance of Composite Laminates with Hole or Crack

Wu Wen Yao; Ping Zhou; Sheng Li Hou; Ming Wu Tu

doi:10.4028/www.scientific.net/AMR.1037.16

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HomeAdvanced Materials ResearchAdvanced Materials Research Vol. 1037Study on Damage Tolerance of Composite Laminates...

Study on Damage Tolerance of Composite Laminates with Hole or Crack

Abstract:

By means of computation and analysis of damage tolerance of composite laminates with hole or crack, the conclusion is brought forth that crack on laminates can’t be cut into hole to improve the residual strength; otherwise the damage will become more serious. The method and conclusion can be reference and basis for battle damage repair of airplane composite component.

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Periodical:

Advanced Materials Research (Volume 1037)

Pages:

16-19

DOI:

https://doi.org/10.4028/www.scientific.net/AMR.1037.16

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Online since:

October 2014

Authors:

Wu Wen Yao*, Ping Zhou, Sheng Li Hou, Ming Wu Tu

Keywords:

Battle Damage Repair, Composite, Damage Tolerance

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* - Corresponding Author

References

[1] Yao Wuwen, Zhou Ping, Cai Kailong and Wang Dongfeng. Study on Damage Repair Technology for Composite component of New Aircraft. The 4th Yough Science Forum, pp.527-532, Aviation Industry Press (2010).

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[2] Yao Wuwen, Lu Yang. Airplane Battle Damage Analysis and Assessment. Beijing: PLA Press, (2006).

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[3] China Aviation Academy. Durability and Damage Tolerance Design Guide for Composite Structures of Airplane. Beijing: Aviation Industry Press, (1995).

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