Nonlinear stability analysis of sandwich wide panels - Part I: buckling behavior

[+] Author and Article Information
Zhangxian Yuan

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

Dr. George Kardomateas

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

1Corresponding author.

ASME 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 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 pre-buckling state and buckling mode shape, which are commonly presumed in literature. In addition, edge effects, which are also commonly neglected are included. The pre-buckling state is determined via a nonlinear static analysis. Solving an eigen-value problem yields the critical load and the corresponding eigen-vector 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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