Dynamic instability of composite laminates using a higher order theory

Aditi Chattopadhyay; Adrian G. Radu

doi:10.1016/S0045-7949(00)00005-5

Dynamic instability of composite laminates using a higher order theory

Aditi Chattopadhyay, Adrian G. Radu

Mechanical and Aerospace Engineering

Research output: Contribution to journal › Article › peer-review

93 Scopus citations

Abstract

A higher order shear deformation theory is used to investigate the instability associated with composite plates subject to dynamic loads. Both transverse shear and rotary inertia effects are taken into account. The procedure is implemented using the finite element approach. The natural frequencies and the critical buckling load are computed and compared with the results based on the classical laminate plate theory and the first-order shear deformation theory. The first two instability regions are determined for various loading conditions using both first- and second-order approximations. These results are also compared with the other approaches. Significant deviations are observed for thick plates due to the presence of shear deformation.

Original language	English (US)
Pages (from-to)	453-460
Number of pages	8
Journal	Computers and Structures
Volume	77
Issue number	5
DOIs	https://doi.org/10.1016/S0045-7949(00)00005-5
State	Published - Jul 21 2000

ASJC Scopus subject areas

Civil and Structural Engineering
Modeling and Simulation
General Materials Science
Mechanical Engineering
Computer Science Applications

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10.1016/S0045-7949(00)00005-5

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title = "Dynamic instability of composite laminates using a higher order theory",

abstract = "A higher order shear deformation theory is used to investigate the instability associated with composite plates subject to dynamic loads. Both transverse shear and rotary inertia effects are taken into account. The procedure is implemented using the finite element approach. The natural frequencies and the critical buckling load are computed and compared with the results based on the classical laminate plate theory and the first-order shear deformation theory. The first two instability regions are determined for various loading conditions using both first- and second-order approximations. These results are also compared with the other approaches. Significant deviations are observed for thick plates due to the presence of shear deformation.",

author = "Aditi Chattopadhyay and Radu, {Adrian G.}",

note = "Funding Information: The support of the present research by the US Army Research Office, Grant # DAAH04-94-G-0157, Technical Monitor, Dr. Gary Anderson is acknowledged. The authors are also thankful to Dr. Haozhong Gu and to Dan Dragomir-Daescu, the Arizona State University, for their valuable comments during the research.",

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AU - Chattopadhyay, Aditi

AU - Radu, Adrian G.

N1 - Funding Information: The support of the present research by the US Army Research Office, Grant # DAAH04-94-G-0157, Technical Monitor, Dr. Gary Anderson is acknowledged. The authors are also thankful to Dr. Haozhong Gu and to Dan Dragomir-Daescu, the Arizona State University, for their valuable comments during the research.

PY - 2000/7/21

Y1 - 2000/7/21

N2 - A higher order shear deformation theory is used to investigate the instability associated with composite plates subject to dynamic loads. Both transverse shear and rotary inertia effects are taken into account. The procedure is implemented using the finite element approach. The natural frequencies and the critical buckling load are computed and compared with the results based on the classical laminate plate theory and the first-order shear deformation theory. The first two instability regions are determined for various loading conditions using both first- and second-order approximations. These results are also compared with the other approaches. Significant deviations are observed for thick plates due to the presence of shear deformation.

AB - A higher order shear deformation theory is used to investigate the instability associated with composite plates subject to dynamic loads. Both transverse shear and rotary inertia effects are taken into account. The procedure is implemented using the finite element approach. The natural frequencies and the critical buckling load are computed and compared with the results based on the classical laminate plate theory and the first-order shear deformation theory. The first two instability regions are determined for various loading conditions using both first- and second-order approximations. These results are also compared with the other approaches. Significant deviations are observed for thick plates due to the presence of shear deformation.

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Dynamic instability of composite laminates using a higher order theory

Abstract

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