Elasticity approach for delamination buckling of composite beam plates

Haozhong Gu, Aditi Chattopadhyay

Research output: Contribution to journalArticle

17 Citations (Scopus)

Abstract

An elasticiry-theory-based approach is developed for delamination buckling of simply supported composite laminates whose behavior is referred to as cylindrical bending. The approach ensures an accurate description of the transverse shear and the transverse normal effects in delamination buckling of composite plates. The uniform prebuckling stress assumption, which is comparable to the membrane assumption used in plate theories, is made for deriving the elasticity-theory-based buckling equations. The closed-form expressions for the displacements and stresses are derived, and the nonlinear eigenvalue equations that are used to solve for critical loads are presented. The results obtained from the elasticity solution are compared with the critical loads furnished by the existing classical laminate theory and a previously developed higher-order shear deformation theory. The solution provides a means of accurate assessment of existing plate theories used in delamination buckling problems.

Original languageEnglish (US)
Pages (from-to)1529-1534
Number of pages6
JournalAIAA Journal
Volume36
Issue number8
StatePublished - Aug 1998

Fingerprint

Delamination
Buckling
Elasticity
Composite materials
Laminates
Loads (forces)
Shear deformation
Membranes

ASJC Scopus subject areas

  • Aerospace Engineering

Cite this

Elasticity approach for delamination buckling of composite beam plates. / Gu, Haozhong; Chattopadhyay, Aditi.

In: AIAA Journal, Vol. 36, No. 8, 08.1998, p. 1529-1534.

Research output: Contribution to journalArticle

@article{294fee78c8b849ec83f80de134a488c7,
title = "Elasticity approach for delamination buckling of composite beam plates",
abstract = "An elasticiry-theory-based approach is developed for delamination buckling of simply supported composite laminates whose behavior is referred to as cylindrical bending. The approach ensures an accurate description of the transverse shear and the transverse normal effects in delamination buckling of composite plates. The uniform prebuckling stress assumption, which is comparable to the membrane assumption used in plate theories, is made for deriving the elasticity-theory-based buckling equations. The closed-form expressions for the displacements and stresses are derived, and the nonlinear eigenvalue equations that are used to solve for critical loads are presented. The results obtained from the elasticity solution are compared with the critical loads furnished by the existing classical laminate theory and a previously developed higher-order shear deformation theory. The solution provides a means of accurate assessment of existing plate theories used in delamination buckling problems.",
author = "Haozhong Gu and Aditi Chattopadhyay",
year = "1998",
month = "8",
language = "English (US)",
volume = "36",
pages = "1529--1534",
journal = "AIAA Journal",
issn = "0001-1452",
publisher = "American Institute of Aeronautics and Astronautics Inc. (AIAA)",
number = "8",

}

TY - JOUR

T1 - Elasticity approach for delamination buckling of composite beam plates

AU - Gu, Haozhong

AU - Chattopadhyay, Aditi

PY - 1998/8

Y1 - 1998/8

N2 - An elasticiry-theory-based approach is developed for delamination buckling of simply supported composite laminates whose behavior is referred to as cylindrical bending. The approach ensures an accurate description of the transverse shear and the transverse normal effects in delamination buckling of composite plates. The uniform prebuckling stress assumption, which is comparable to the membrane assumption used in plate theories, is made for deriving the elasticity-theory-based buckling equations. The closed-form expressions for the displacements and stresses are derived, and the nonlinear eigenvalue equations that are used to solve for critical loads are presented. The results obtained from the elasticity solution are compared with the critical loads furnished by the existing classical laminate theory and a previously developed higher-order shear deformation theory. The solution provides a means of accurate assessment of existing plate theories used in delamination buckling problems.

AB - An elasticiry-theory-based approach is developed for delamination buckling of simply supported composite laminates whose behavior is referred to as cylindrical bending. The approach ensures an accurate description of the transverse shear and the transverse normal effects in delamination buckling of composite plates. The uniform prebuckling stress assumption, which is comparable to the membrane assumption used in plate theories, is made for deriving the elasticity-theory-based buckling equations. The closed-form expressions for the displacements and stresses are derived, and the nonlinear eigenvalue equations that are used to solve for critical loads are presented. The results obtained from the elasticity solution are compared with the critical loads furnished by the existing classical laminate theory and a previously developed higher-order shear deformation theory. The solution provides a means of accurate assessment of existing plate theories used in delamination buckling problems.

UR - http://www.scopus.com/inward/record.url?scp=0006168206&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=0006168206&partnerID=8YFLogxK

M3 - Article

AN - SCOPUS:0006168206

VL - 36

SP - 1529

EP - 1534

JO - AIAA Journal

JF - AIAA Journal

SN - 0001-1452

IS - 8

ER -