Primary to secondary buckling transition and stability of composite plates using a higher order theory

Adrian G. Radu; Aditi Chattopadhyay

doi:10.2514/6.2001-1531

Primary to secondary buckling transition and stability of composite plates using a higher order theory

Adrian G. Radu, Aditi Chattopadhyay

Engineering, Ira A. Fulton Schools of (IAFSE)

Research output: Contribution to conference › Paper › peer-review

Abstract

A variationaly consistent mathematical model based on the refined higher order theory is used to develop a finite element procedure for analyzing the dynamic instability under biaxial buckling loads of rectangular composite plates. Laminates with various thicknesses and stacking sequence under various biaxial loads and boundary conditions are considered. The natural frequencies and mode shapes as well as the buckling loads and deformed shapes are computed for different values of transverse compressive load and the shift between the primary and secondary buckling modes is analyzed. The second order approximation of the instability regions corresponding to the first two natural frequencies are determined and the effects of static transverse and longitudinal compressive loads are investigated.

Original language	English (US)
DOIs	https://doi.org/10.2514/6.2001-1531
State	Published - Jan 1 2001
Event	19th AIAA Applied Aerodynamics Conference 2001 - Anaheim, CA, United States Duration: Jun 11 2001 → Jun 14 2001

Other

Other	19th AIAA Applied Aerodynamics Conference 2001
Country/Territory	United States
City	Anaheim, CA
Period	6/11/01 → 6/14/01

ASJC Scopus subject areas

Mechanical Engineering
Aerospace Engineering

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10.2514/6.2001-1531

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abstract = "A variationaly consistent mathematical model based on the refined higher order theory is used to develop a finite element procedure for analyzing the dynamic instability under biaxial buckling loads of rectangular composite plates. Laminates with various thicknesses and stacking sequence under various biaxial loads and boundary conditions are considered. The natural frequencies and mode shapes as well as the buckling loads and deformed shapes are computed for different values of transverse compressive load and the shift between the primary and secondary buckling modes is analyzed. The second order approximation of the instability regions corresponding to the first two natural frequencies are determined and the effects of static transverse and longitudinal compressive loads are investigated.",

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

year = "2001",

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doi = "10.2514/6.2001-1531",

language = "English (US)",

note = "19th AIAA Applied Aerodynamics Conference 2001 ; Conference date: 11-06-2001 Through 14-06-2001",

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T1 - Primary to secondary buckling transition and stability of composite plates using a higher order theory

AU - Radu, Adrian G.

AU - Chattopadhyay, Aditi

PY - 2001/1/1

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N2 - A variationaly consistent mathematical model based on the refined higher order theory is used to develop a finite element procedure for analyzing the dynamic instability under biaxial buckling loads of rectangular composite plates. Laminates with various thicknesses and stacking sequence under various biaxial loads and boundary conditions are considered. The natural frequencies and mode shapes as well as the buckling loads and deformed shapes are computed for different values of transverse compressive load and the shift between the primary and secondary buckling modes is analyzed. The second order approximation of the instability regions corresponding to the first two natural frequencies are determined and the effects of static transverse and longitudinal compressive loads are investigated.

AB - A variationaly consistent mathematical model based on the refined higher order theory is used to develop a finite element procedure for analyzing the dynamic instability under biaxial buckling loads of rectangular composite plates. Laminates with various thicknesses and stacking sequence under various biaxial loads and boundary conditions are considered. The natural frequencies and mode shapes as well as the buckling loads and deformed shapes are computed for different values of transverse compressive load and the shift between the primary and secondary buckling modes is analyzed. The second order approximation of the instability regions corresponding to the first two natural frequencies are determined and the effects of static transverse and longitudinal compressive loads are investigated.

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M3 - Paper

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T2 - 19th AIAA Applied Aerodynamics Conference 2001

Y2 - 11 June 2001 through 14 June 2001

ER -

Primary to secondary buckling transition and stability of composite plates using a higher order theory

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