DAMAGE TOLERANCE EXPERIMENT AND ANALYSIS OF STIFFENED FUSELAGE PANEL WITH LONGITUDINAL CRACK: Fid-Bau Portal

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DAMAGE TOLERANCE EXPERIMENT AND ANALYSIS OF STIFFENED FUSELAGE PANEL WITH LONGITUDINAL CRACK

CHEN An / WEI YuLong / LIAO JiangHai / DONG DengKe

Results from an experimental and analytical study of a curved stiffened aluminum panel subjected to combined internal pressure and axial tension loads are presented. The behaviors of the crack propagation and characteristics of the residual strength for fuselage panel are investigated. Stress intensity factors associated with different crack lengths are analyzed by using ANSYS software,and the crack propagation cycles are predicted. The residual strength curves are calculated based on the linear elastic fracture mechanics by comparison of experimental results. Analysis results agree well with the test results. Both results can provide the bases for the damage tolerance design and assessment of fuselage structure.

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DAMAGE TOLERANCE EXPERIMENT AND ANALYSIS OF STIFFENED FUSELAGE PANEL WITH LONGITUDINAL CRACK

CHEN An / WEI YuLong / LIAO JiangHai / DONG DengKe

Results from an experimental and analytical study of a curved stiffened aluminum panel subjected to combined internal pressure and axial tension loads are presented. The behaviors of the crack propagation and characteristics of the residual strength for fuselage panel are investigated. Stress intensity factors associated with different crack lengths are analyzed by using ANSYS software,and the crack propagation cycles are predicted. The residual strength curves are calculated based on the linear elastic fracture mechanics by comparison of experimental results. Analysis results agree well with the test results. Both results can provide the bases for the damage tolerance design and assessment of fuselage structure.

DAMAGE TOLERANCE EXPERIMENT AND ANALYSIS OF STIFFENED FUSELAGE PANEL WITH LONGITUDINAL CRACK

CHEN An / WEI YuLong / LIAO JiangHai / DONG DengKe

Results from an experimental and analytical study of a curved stiffened aluminum panel subjected to combined internal pressure and axial tension loads are presented. The behaviors of the crack propagation and characteristics of the residual strength for fuselage panel are investigated. Stress intensity factors associated with different crack lengths are analyzed by using ANSYS software,and the crack propagation cycles are predicted. The residual strength curves are calculated based on the linear elastic fracture mechanics by comparison of experimental results. Analysis results agree well with the test results. Both results can provide the bases for the damage tolerance design and assessment of fuselage structure.

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Title:

DAMAGE TOLERANCE EXPERIMENT AND ANALYSIS OF STIFFENED FUSELAGE PANEL WITH LONGITUDINAL CRACK

Contributors:

CHEN An (author) / WEI YuLong (author) / LIAO JiangHai (author) / DONG DengKe (author)

Published in:

Jixie qiangdu, Vol 39, Pp 1463-1467 (2017)

Publication date:

2017

ISSN:

Type of media:

Article (Journal)

Type of material:

Electronic Resource

Language:

Unknown

Keywords:

Fuselage panel , Longitudinal crack , Damage tolerance experiment , Crack propagation , Residual strength , Stress intensify factor , 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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