eprintid: 4113
rev_number: 8
eprint_status: archive
userid: 354
dir: disk0/00/00/41/13
datestamp: 2020-12-04 08:24:31
lastmod: 2020-12-04 08:24:31
status_changed: 2020-12-04 08:24:31
type: article
metadata_visibility: show
creators_name: Pham, Minh Vuong
creators_name: Nguyen, Dinh Duc
creators_id: ducnd@vnu.edu.vn
title: Nonlinear buckling and post-buckling behavior of shear deformable sandwich toroidal shell segments with functionally graded core subjected to axial compression and thermal loads
ispublished: pub
subjects: isi
divisions: CET_uet
abstract: This paper presents an analytical investigation on buckling and post-buckling of shear deformable sandwich toroidal shell segments with functionally graded core and homogeneous face sheets. The effective material properties of core layer are graded in the thickness direction according to a simple power law distribution in terms of volume fraction index. The shells are surrounded by an elastic foundation and subjected to axial compressive or thermal loads. Reddy's third-order shear deformation shell theory (TSDT) is used to established formulations. A new solution using Galerkin method for solving a governing system of four-partial differential equations is carried out to obtain closed-form expressions of buckling stresses and post-buckling curves. Two cases of bowed-out and bowed-in sandwich toroidal shells are considered. Effects of material, geometric parameters and elastic foundation on stability behavior of the shells is analyzed in detail. The difference between bucking stresses basing on TSDT and those basing on classical shell theory (CST) is also clearly shown in this study.
date: 2020-11
date_type: published
publisher: Elsevier
official_url: https://doi.org/10.1016/j.ast.2020.106084
full_text_status: public
publication: Aerospace Science and Technology
volume: 106
number: 106084
refereed: TRUE
issn: 1270-9638
citation:   Pham, Minh Vuong and Nguyen, Dinh Duc  (2020) Nonlinear buckling and post-buckling behavior of shear deformable sandwich toroidal shell segments with functionally graded core subjected to axial compression and thermal loads.  Aerospace Science and Technology, 106  (106084).    ISSN 1270-9638     
document_url: https://eprints.uet.vnu.edu.vn/eprints/id/eprint/4113/1/pii/S1270963820307665