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Meccanica
Erschienen in: Meccanica 4/2016

14.07.2015

Aerothermoelastic analysis of lattice sandwich composite panels in supersonic airflow

verfasst von: Zhi-Guang Song, Feng-Ming Li

Erschienen in: Meccanica | Ausgabe 4/2016

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Abstract

This paper is devoted to investigate the aerothermoelastic properties of the composite sandwich panels with two- and three-dimensional lattice cores in supersonic airflow. Both the top and bottom face sheets of the sandwich panels are composite laminated panels. The two- and three-dimensional lattice cores are composed of triangular grids and pyramidal trusses, respectively. The first-order shear deformation theory is used in the structural modeling. The equivalent thermal expansion coefficients of the triangular grid are obtained by the physical and geometric relations of the deformed core only under the temperature change. The equation of motion of the structural system is formulated using the Hamilton’s principle. The supersonic piston theory is used to evaluate the aerodynamic pressure. The aerothermoelastic properties of the lattice sandwich panels are analyzed by the frequency-domain method. The influences of parameters of the lattice core on the aeroelastic stability of the sandwich panel are investigated. The aerothermoelastic properties of the sandwich composite panels with two- and three-dimensional lattice cores are compared. Some useful results are obtained from the present study.
Vorheriger Artikel Multivariable optimal control of an industrial nonlinear boiler–turbine unit
Nächster Artikel A novel stochastic-spectral finite element method for analysis of elastodynamic problems in the time domain

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Metadaten
Titel
Aerothermoelastic analysis of lattice sandwich composite panels in supersonic airflow
verfasst von
Zhi-Guang Song
Feng-Ming Li
Publikationsdatum
14.07.2015
Verlag
Springer Netherlands
Erschienen in
Meccanica / Ausgabe 4/2016
Print ISSN: 0025-6455
Elektronische ISSN: 1572-9648
DOI
https://doi.org/10.1007/s11012-015-0240-y

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