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Research Papers

Dynamic Instability of Laminated-Composite and Sandwich Plates Using a New Inverse Trigonometric Zigzag Theory

[+] Author and Article Information
Rosalin Sahoo

Department of Aerospace Engineering,
Indian Institute of Technology Kharagpur,
Kharagpur 721302, India
e-mail: sahoorosalin7@gmail.com

B. N. Singh

Professor
Department of Aerospace Engineering,
Indian Institute of Technology Kharagpur,
Kharagpur 721302, India
e-mail: bnsingh@aero.iitkgp.ernet.in

1Corresponding author.

Contributed by the Technical Committee on Vibration and Sound of ASME for publication in the JOURNAL OF VIBRATION AND ACOUSTICS. Manuscript received July 3, 2014; final manuscript received May 7, 2015; published online July 9, 2015. Assoc. Editor: Mohammed Daqaq.

J. Vib. Acoust 137(6), 061001 (Dec 01, 2015) (12 pages) Paper No: VIB-14-1239; doi: 10.1115/1.4030716 History: Received July 03, 2014; Revised May 07, 2015; Online July 09, 2015

A structure with periodic dynamic load may lead to dynamic instability due to parametric resonance. In the present work, the dynamic stability analysis of laminated composite and sandwich plate due to in-plane periodic loads is studied based on recently developed inverse trigonometric zigzag theory (ITZZT). Transverse shear stress continuity at layer interfaces along with traction-free boundary conditions on the plate surfaces is satisfied by the model obviating the need of shear correction factor. An efficient C0 continuous, eight noded isoparametric element with seven field variable is employed for the dynamic stability analysis of laminated composite and sandwich plates. The boundaries of instability regions are determined using Bolotin's approach and the first instability zone is presented either in the nondimensional load amplitude–excitation frequency plane or load amplitude–load frequency plane. The influences of various parameters such as degrees of orthotropy, span-thickness ratios, boundary conditions, static load factors, and thickness ratios on the dynamic instability regions (DIRs) are studied by solving a number of problems. The evaluated results are validated with the available results in the literature based on different deformation theories. The efficiency of the present model is ascertained by the improved accuracy of predicted results at the cost of less computational involvement.

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References

Figures

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Fig. 1

Schematic diagram of a laminate

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Fig. 2

General lamination scheme and displacement configuration

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Fig. 3

Eight noded isoparametric serendipity element

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Fig. 10

Effect of span-thickness ratio on principal instability region of a simply supported unsymmetric sandwich plate [0/90/C/0/90] for (α = 0.2) with (hc/hf = 10)

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Fig. 11

Effect of boundary conditions on principal instability region of a symmetric sandwich plate [0/90/C/90/0] for (α = 0.2) with (a/h = 10)

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Fig. 4

Instability region of a simply supported isotropic plate considering (α=0.0) with (a/h=100)

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Fig. 5

Comparison of DIR of a simply supported laminated composite plate [0/90/90/0] for (α=0.0) with (a/h=25)

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Fig. 6

Effect of modular ratio on principal instability region of a simply supported laminated composite plate [0/90/90/0] for (α = 0.0) with (a/h = 25)

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Fig. 7

Effect of boundary conditions on principal instability region of a laminated composite plate [0/90/90/0] for (α = 0.2) with (a/h = 25)

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Fig. 8

Effect of static load factor on principal instability region of a simply supported unsymmetric sandwich plate [0/90/C/0/90] for (a/h = 10)

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Fig. 9

Effect of thickness ratio on principal instability region of a simply supported unsymmetric sandwich plate [0/90/C/0/90] for (α = 0.2) with (a/h = 10)

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