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Research Papers

Nonlinear Stability Analysis of Sandwich Wide Panels—Part I: Buckling Behavior

[+] Author and Article Information
Zhangxian Yuan

School of Aerospace Engineering,
Georgia Institute of Technology,
Atlanta, GA 30332-0150

George A. Kardomateas

Professor
School of Aerospace Engineering,
Georgia Institute of Technology,
Atlanta, GA 30332-0150

Contributed by the Applied Mechanics Division of ASME for publication in the JOURNAL OF APPLIED MECHANICS. Manuscript received February 21, 2018; final manuscript received April 5, 2018; published online June 1, 2018. Editor: Yonggang Huang.

J. Appl. Mech 85(8), 081006 (Jun 01, 2018) (11 pages) Paper No: JAM-18-1109; doi: 10.1115/1.4039953 History: Received February 21, 2018; Revised April 05, 2018

This is a series of two papers in which the nonlinear stability behavior of sandwich panels is investigated. This part presents the buckling behavior and focuses on the critical load and the buckling mode. The buckling analysis is based on the extended high-order sandwich panel theory (EHSAPT) which takes transverse compressibility and axial rigidity of the core into account. It allows for the interaction between the faces and the core. The geometric nonlinearity, i.e., large displacement with moderate rotation, is considered in both faces and core. The weak form governing equations are derived based on the EHSAPT-based element. Detailed formulations and analysis procedures are provided. It presents a general approach for arbitrary buckling type without decoupling it into isolated global buckling and wrinkling. There are no additional assumptions made about the prebuckling state and buckling mode shape, which are commonly presumed in the literature. In addition, edge effects which are also commonly neglected are included. The prebuckling state is determined via a nonlinear static analysis. Solving an eigenvalue problem yields the critical load and the corresponding eigenvector gives the buckling mode. Sandwich panels with different lengths are studied as examples. Both global buckling and wrinkling are observed. It shows that the axial rigidity of the core has a pronounced effect on both the critical load and the buckling mode.

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Figures

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Fig. 1

Definition of the geometry, loads, and coordinate system of the sandwich panel

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Fig. 2

Transverse displacement in the prebuckling state of a = 300 mm sandwich panel subjected to equal axial compressive loads Nt=Nb=P/2 with P = 9000 N: (a) E1c=52.0 MPa and (b) E1c=52.0×10−5 MPa

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Fig. 3

First buckling mode of a = 300 mm sandwich panel: (a) EHSAPT, E1c=52.0 MPa, (b) EHSAPT, E1c=52.0×10−5 MPa, and (c) ADINA

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Fig. 4

Second buckling mode of a = 300 mm sandwich panel: (a) EHSAPT, E1c=52.0 MPa and (b) ADINA

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Fig. 5

Third buckling mode of a = 300 mm sandwich panel: (a) EHSAPT, E1c=52.0 MPa and (b) ADINA

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Fig. 6

Buckling modes of a = 600 mm sandwich panel: (a) mode 1, (b) mode 2, (c) mode 3, and (d) mode 4

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Fig. 7

Buckling modes of a = 150 mm sandwich panel: (a) mode 1 and (b) mode 2

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Fig. 8

Buckling modes of a = 600 mm sandwich panel with E1c=52.0×10−5 MPa: (a) mode 1 and (b) mode 2

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Fig. 9

Transverse displacement in the prebuckling state of a = 300 mm sandwich panel subjected to unequal axial compressive loads Nt=0.3P, Nb=0.7P with P = 6600 N

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Fig. 10

Buckling modes of a = 300 mm symmetrical sandwich panel subjected to unequal axial compressive loads Nt=0.3P, Nb=0.7P: (a) mode 1 and (b) mode 2

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Fig. 11

Buckling modes of a = 300 mm unsymmetrical sandwich panel (ft = 1 mm, fb=0.5 mm) subjected to equal axial compressive loads: (a) mode 1 and (b) mode 2

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