A Buckling Analysis Method for Composite Panels in Multiweb Box Structures Based on Elastic Boundaries

ZHAO Bei; XIONG Sijun; CHEN Liang; WANG Chengbo; LI Rui

doi:10.21656/1000-0887.440283

Volume 45 Issue 9

Sep. 2024

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Article Navigation > Applied Mathematics and Mechanics > 2024 > 45(9): 1182-1199

ZHAO Bei, XIONG Sijun, CHEN Liang, WANG Chengbo, LI Rui. A Buckling Analysis Method for Composite Panels in Multiweb Box Structures Based on Elastic Boundaries[J]. Applied Mathematics and Mechanics, 2024, 45(9): 1182-1199. doi: 10.21656/1000-0887.440283

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A Buckling Analysis Method for Composite Panels in Multiweb Box Structures Based on Elastic Boundaries

doi: 10.21656/1000-0887.440283

ZHAO Bei^{1, 2
,},
XIONG Sijun^{1, 3
,},
CHEN Liang^{3, 4
,},
WANG Chengbo^{3, 4
,},
LI Rui^{1, 4
,
,}

1.
State Key Laboratory of Structural Analysis, Optimization and CAE Software for Industrial Equipment, Department of Engineering Mechanics, Dalian University of Technology, Dalian, Liaoning 116024, P.R.China
2.
Department of Strength, AVIC Chengdu Aircraft Design and Research Institute, Chengdu 610091, P.R.China
3.
Department of Strength, AVIC Shenyang Aircraft Design and Research Institute, Shenyang 110035, P.R.China
4.
Key Laboratory of Digital Twin for Aircraft Structural Strength, Liaoning Province, Shenyang 110035, P.R.China

Received Date: 2023-09-20
Rev Recd Date: 2024-05-27
Publish Date: 2024-09-01

Abstract

Abstract

The multiweb box structures in the wings are paid special attention in aircrafts' structural design. The multiweb box is mainly composed of skins and stiffeners. The skins are approximately divided into many rectangular panels by stiffeners. During the service of an aircraft, the wing majorly bears bending, torsion, and bending-torsion coupling loads, etc., so the panels in box structures are susceptible to instability. In traditional buckling analysis of composite panels, the boundary conditions were typically simplified as either clamped or simply supported boundaries, with significant deviations from experimental results. On the other hand, comprehensive simulations with the finite element method are generally inefficient. Aimed at the above issues, a rapid buckling analysis method combining the unit cell model with the differential quadrature method for composite panels was proposed. Firstly, the unit cell model was established to calculate the stiffness coefficients of elastic boundaries of rectangular panels. The governing equations were then solved with the differential quadrature method to obtain the buckling loads on the panels. Finally, the buckling loads on composite panels in different types of box structures were calculated and compared to the results obtained with the finite element method to verify the accuracy of the presented buckling analysis method.
- composite panel,
- elastic boundary,
- buckling,
- differential quadrature method

(Contributed by LI Rui, M.AMM Editorial Board)

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References(29)

References

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