INTERNAL CLADDING LAYER INFLUENCE ON THE DEBONDING OF HAT-STRINGER STIFFENED COMPOSITE PANELS UNDER AXIAL COMPRESSION (MT): Fid-Bau Portal

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INTERNAL CLADDING LAYER INFLUENCE ON THE DEBONDING OF HAT-STRINGER STIFFENED COMPOSITE PANELS UNDER AXIAL COMPRESSION (MT)

YUAN Fei / LIU Fu / CHAI YaNan / CHEN XiangMing / LIN GuoWei / LI XinXiang

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 and numerically. Cohesive elements are used to simulate the adhesive layer between skin and flange and Hashin’s failure criterion is adopted to determine damage initiation of composite layers in the numerical simulations. The process of damage initiation, propagation and failure of the stiffened composite panels was simulated in detail. A good agreement between tests and numerical prediction was observed.

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INTERNAL CLADDING LAYER INFLUENCE ON THE DEBONDING OF HAT-STRINGER STIFFENED COMPOSITE PANELS UNDER AXIAL COMPRESSION (MT)

YUAN Fei / LIU Fu / CHAI YaNan / CHEN XiangMing / LIN GuoWei / LI XinXiang

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 and numerically. Cohesive elements are used to simulate the adhesive layer between skin and flange and Hashin’s failure criterion is adopted to determine damage initiation of composite layers in the numerical simulations. The process of damage initiation, propagation and failure of the stiffened composite panels was simulated in detail. A good agreement between tests and numerical prediction was observed.

INTERNAL CLADDING LAYER INFLUENCE ON THE DEBONDING OF HAT-STRINGER STIFFENED COMPOSITE PANELS UNDER AXIAL COMPRESSION (MT)

YUAN Fei / LIU Fu / CHAI YaNan / CHEN XiangMing / LIN GuoWei / LI XinXiang

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 and numerically. Cohesive elements are used to simulate the adhesive layer between skin and flange and Hashin’s failure criterion is adopted to determine damage initiation of composite layers in the numerical simulations. The process of damage initiation, propagation and failure of the stiffened composite panels was simulated in detail. A good agreement between tests and numerical prediction was observed.

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Title:

INTERNAL CLADDING LAYER INFLUENCE ON THE DEBONDING OF HAT-STRINGER STIFFENED COMPOSITE PANELS UNDER AXIAL COMPRESSION (MT)

Contributors:

YUAN Fei (author) / LIU Fu (author) / CHAI YaNan (author) / CHEN XiangMing (author) / LIN GuoWei (author) / LI XinXiang (author)

Published in:

Jixie qiangdu, Pp 1490-1497 (2022)

Publication date:

2022

ISSN:

Type of media:

Article (Journal)

Type of material:

Electronic Resource

Language:

Unknown

Keywords:

Mechanical engineering and machinery , TJ1-1570 , Materials of engineering and construction. Mechanics of materials , TA401-492

Metadata by DOAJ is licensed under CC BY-SA 1.0

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