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Research Papers

Nonlinear Stability Analysis of Sandwich Wide Panels—Part II: Postbuckling Response

[+] 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), 081007 (Jun 01, 2018) (9 pages) Paper No: JAM-18-1110; doi: 10.1115/1.4039954 History: Received February 21, 2018; Revised April 05, 2018

The nonlinear post-buckling response of sandwich panels based on the extended high-order sandwich panel theory (EHSAPT) is presented. The model includes the transverse compressibility, the axial rigidity, and the shear effect of the core. Both faces and core are considered undergoing large displacements with moderate rotations. Based on the nonlinear weak form governing equations, the post-buckling response is obtained by the arc-length continuation method together with the branch switching technique. Also, the post-buckling response with imperfections is studied. The numerical examples discuss the post-buckling response corresponding to global buckling and wrinkling. It is found that due to the interaction between faces and core, localized effects may be easily initiated by imperfections after the sandwich structure has buckled globally. Furthermore, this could destabilize the post-buckling response. The post-buckling response verifies the critical load and buckling mode given by the buckling analysis in part I. The axial rigidity of the core, although it is very small compared to that of the faces, has a significant effect on the post-buckling response.

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References

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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

Equilibrium path of a = 300 mm sandwich panel: (a) wt versus load P at middle (x=a/2) and (b) ut versus load P at left edge (x = 0)

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Fig. 3

Variations of transverse displacement at various axial compressive loads (a = 300 mm sandwich panel with uniform distributed load imperfection): (a) top face wt and (b) bottom face wb

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Fig. 4

Variations of transverse displacement at various axial compressive loads (a = 300 mm sandwich panel with uniform distributed load imperfection and concentrated load imperfection): (a) top face wt and (b) bottom face wb

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Fig. 5

Equilibrium path of a = 300 mm sandwich panel with E1c=1.0×10−5 MPa, wt versus load P at middle (x=a/2)

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Fig. 6

Variations of transverse displacement at various axial compressive loads (a = 300 mm sandwich panel with uniform distributed load imperfection and E1c=1.0×10−5 MPa): (a) top face wt and (b) bottom face wb

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Fig. 7

Equilibrium path of a = 150 mm sandwich panel: (a) wt versus load P at x=a/30 and (b) ut versus load P at left edge (x = 0)

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Fig. 8

Variations of transverse displacement at various axial compressive loads of a = 150 mm sandwich panel of the right part of first branch: (a) top face, wt and (b) bottom face, wb

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Fig. 9

Variations of transverse displacement at various axial compressive loads a = 150 mm sandwich panel of the right part of second branch: (a) top face, wt and (b) bottom face, wb

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