Integral Aircraft Wing Panels with Penetration Cracks: The Influence of Structural Parameters on the Stress Intensity Factor
Source abstract
Abstract
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.
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Research context
OpenAlex topics: Fatigue and fracture mechanics · Numerical methods in engineering · Mechanical Behavior of Composites
SciVX discovery tags are terminology-based. OpenAlex topics are source-provided classifications.
Affiliations
College of Mechanical and Electrical Engineering, Central South University, Changsha 410083, China
Light Alloy Research Institute, Central South University, Changsha 410083, China
State Key Laboratory of High Performance Complex Manufacturing, Central South University, Changsha 410083, China
Avic The First Aircraft Institute, Xi’an 710000, China
School of Astronautics, Northwestern Polytechnical University, Xi’an 710072, China
Funding
National Natural Science Foundation of China
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