Zobrazeno 1 - 10
of 49
pro vyhledávání: '"Chai, Yanan"'
Akademický článek
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Publikováno v:
Journal of Aeronautical Materials, Vol 42, Iss 6, Pp 88-96 (2022)
In order to study the effect of opening size and layering ratio on the compression performance, the compression experiments of composite laminates with three opening sizes and ply were carried out. The strains near the opening area were measured by r
Externí odkaz:
https://doaj.org/article/f697e53275b440f1a1ba04292ec6fafd
Publikováno v:
Jixie qiangdu, Pp 1490-1497 (2022)
Debonding between flange and skin is the dominate failure mode of stiffened composite panels which are widely used in modern aircraft. The influence of internal cladding layer in hat stringer on the onset of debonding is investigated experimentally a
Externí odkaz:
https://doaj.org/article/6e31dce033a6415ca8d6cd63983af5b2
Autor:
Chai, Yanan1 (AUTHOR) yananchai@nwafu.edu.cn, Hong, Weijin1 (AUTHOR), Liu, Hang1 (AUTHOR), Shi, Xia1 (AUTHOR), Liu, Yanfei1 (AUTHOR), Liu, Zhande1 (AUTHOR) dezhanliu@nwafu.edu.cn
Publikováno v:
International Journal of Molecular Sciences. May2023, Vol. 24 Issue 10, p8876. 13p.
Autor:
Chen, Xiangming, Sun, Xiasheng, Chen, Puhui, Wang, Binwen, Gu, Jiefei, Wang, Wenzhi, Chai, Yanan, Zhao, Yueran
Publikováno v:
In Composite Structures 15 January 2021 256
Publikováno v:
In Composite Structures 1 June 2020 241
Publikováno v:
Jixie qiangdu, Vol 42, Pp 716-722 (2020)
Composite stiffened panels always have defects at the bonding surface in preparation,which accelerates the debonding of the interface between skin and stringer,greatly affects the bearing capacity of the structure. The model of stiffened panel with p
Externí odkaz:
https://doaj.org/article/d55d763839594ea3a24e9b2bf2e28be8
Publikováno v:
Jixie qiangdu, Vol 41, Pp 1473-1479 (2019)
A six-point bending test that characterized the failure of the stiffener-skin interface of a stiffened composite panel at the post-buckling stage is studied. A FEM model for a stiffened panel subjected to compression and a six-point bending test mode
Externí odkaz:
https://doaj.org/article/fc8eb872834c4e0f83e0cad5ee8d687f
Publikováno v:
Jixie qiangdu, Vol 40, Pp 1090-1096 (2018)
as multi-spar composite box has been used for many airplanes,in order to assure structure security,it is necessary to study the mechanical properties of multi-spar composite box. Aiming at the buckling and postbuckling problems,buckling behavior and
Externí odkaz:
https://doaj.org/article/c5a76c2c7b5546bab0455ca1bafad0cc
Akademický článek
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