Research Papers

Efficient Hybrid Finite Element Method for Flutter Prediction of Functionally Graded Cylindrical Shells

[+] Author and Article Information
Farhad Sabri

Postdoctoral Fellow
Department of Mechanical and
Industrial Engineering,
University of Toronto,
Toronto M5S 3G8, Canada
e-mail: sabri@mie.utoronto.ca

Aouni A. Lakis

Applied Mechanics Section,
Department of Mechanical Engineering,
Ecole Polytechnique de Montreal,
Montreal H3T 1J4, Canada
e-mail: aouni.lakis@polymtl.ca

1Corresponding author.

Contributed by the Design Engineering Division of ASME for publication in the JOURNAL OF VIBRATION AND ACOUSTICS. Manuscript received December 2, 2010; final manuscript received July 15, 2013; published online September 27, 2013. Assoc. Editor: Bogdan Epureanu.

J. Vib. Acoust 136(1), 011002 (Sep 27, 2013) (6 pages) Paper No: VIB-10-1286; doi: 10.1115/1.4025397 History: Received December 02, 2010; Revised July 15, 2013

In this work, a hybrid finite element formulation is presented to predict the flutter boundaries of circular cylindrical shells made of functionally graded (FG) materials. The development is based on a combination of linear Sanders thin shell theory and the classic finite element method. Material properties are temperature dependent and graded in the shell thickness direction according to a simple power law distribution in terms of volume fractions of constituents. The temperature field is assumed to be uniform over the shell surface and along the shell thickness. First-order piston theory is applied to account for supersonic aerodynamic pressure. The effects of temperature rise and shell internal pressure on the flutter boundaries of a FG circular cylindrical shell for different values of power law index are investigated. The present study shows efficient and reliable results that can be applied to aeroelastic design and analysis of shells of revolution in aerospace vehicles.

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Grahic Jump Location
Fig. 2

Shell element geometry

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Fig. 1

Variation of the ceramic volume fraction

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Fig. 5

Flutter boundaries for pressurized FG cylindrical shells

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Fig. 3

(a) Real part, (b) imaginary part of eigenvalue versus freestream static pressure, n = 25; ceramic rich N = 0

Grahic Jump Location
Fig. 4

(a) Real part, (b) imaginary part of eigenvalue versus freestream static pressure, n = 25; N = 3




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