Integral Aircraft Wing Panels with Penetration Cracks: The Influence of Structural Parameters on the Stress Intensity Factor

The finite element model of integral wing panels with central penetration cracks under bending load was established, and the crack propagation process of the aircraft panel was simulated. The stress intensity factor (SIF) of the crack tip during crack propagation under varying conditions of crack le...

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Bibliographic Details
Published inApplied sciences Vol. 10; no. 12; p. 4142
Main Authors Hai, Gong, Bin, Yi, Yunxin, Wu, Zhiqi, Liao, Yaoqiong, Liu, Fei, Du
Format Journal Article
LanguageEnglish
Published Basel MDPI AG 01.06.2020
Subjects
Aircraft
Airplanes
Analysis
Computer simulation
Crack initiation
Crack propagation
Crack tips
Finite element analysis
integral aircraft wing panel
Mechanical properties
Parameters
Regression analysis
Sheet-metal
Simulation
Stress concentration
stress intensity factor
Stress intensity factors
Stress propagation
Structural dynamics
Wing panels
Wings
Wings (aircraft)
China
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Summary:The finite element model of integral wing panels with central penetration cracks under bending load was established, and the crack propagation process of the aircraft panel was simulated. The stress intensity factor (SIF) of the crack tip during crack propagation under varying conditions of crack length and panel structural parameters was determined. The effects of the panel structure parameters and crack size on the crack tip SIF were obtained. The regression analysis of the finite simulation element results has been performed and a regression model of SIF at the crack tip of the integral panel has been established, the determination coefficient of the regression model is 0.955.
ISSN:2076-3417
2076-3417
DOI:10.3390/app10124142