eprintid: 2820
rev_number: 8
eprint_status: archive
userid: 354
dir: disk0/00/00/28/20
datestamp: 2017-12-20 04:25:14
lastmod: 2017-12-20 04:25:14
status_changed: 2017-12-20 04:25:14
type: article
metadata_visibility: show
creators_name: Nguyen, Dinh Duc
creators_name: Kim, Seung-Eock
creators_name: Ngo, Duc Tuan
creators_name: Tran, Phuong
creators_id: ducnd@vnu.edu.vn
title: New approach to study nonlinear dynamic response and vibration of sandwich composite cylindrical panels with auxetic honeycomb core layer
ispublished: pub
subjects: Mechanics
subjects: isi
divisions: fac_fema
abstract: The main goal of this study is using analytical solution to investigate the nonlinear dynamic response and
vibration of sandwich auxetic composite cylindrical panels. The sandwich composite panels have three
layers in which the top and bottom outer skins are isotropic aluminum materials, the central auxetic
core layer – honeycomb structures with negative Poisson’s ratio using the same aluminum material. The
panels are resting on elastic foundations and subjected to mechanical, blast and damping loads. Based
on Reddy’s first order shear deformation theory (FSDT) with the geometrical nonlinear in von Karman
and using the Airy stress functions method, Galerkin method and fourth-order Runge–Kutta method,
the resulting equations are solved to obtain expressions for nonlinear motion equations. The effects
of geometrical parameters, material properties, elastic Winkler and Pasternak foundations, mechanical,
blast and damping loads on the nonlinear dynamic response and the natural frequencies of sandwich
composite cylindrical panels are studied.
date: 2017
date_type: published
publisher: Elsevier
full_text_status: public
publication: Aerospace Science and Technology
volume: 70
pagerange: 396-404
refereed: TRUE
issn: 1270-9638
related_url_url: https://doi.org/10.1016/j.ast.2017.08.023
citation:   Nguyen, Dinh Duc and Kim, Seung-Eock and Ngo, Duc Tuan and Tran, Phuong  (2017) New approach to study nonlinear dynamic response and vibration of sandwich composite cylindrical panels with auxetic honeycomb core layer.  Aerospace Science and Technology, 70 .   pp. 396-404.  ISSN 1270-9638     
document_url: https://eprints.uet.vnu.edu.vn/eprints/id/eprint/2820/1/1-s2.0-S1270963817308842-main.pdf