Affiliations: Faculty of Aeronautics and Astronautics, Maslak,
Istanbul Technical University, Istanbul, Turkey | Aerospace Engineering Department, Turkish Air Force
Academy, Yesilyurt, Istanbul, Turkey
Note: [] Corresponding author: Halit S. Turkmen, Faculty of Aeronautics
and Astronautics, Istanbul Technical University, Maslak, Istanbul 34469,
Turkey. Tel.: +90 212 2853196; Fax: +90 212 2853139; E-mail:
[email protected]
Abstract: In this study, the geometrically nonlinear dynamic behaviour of
simply supported tapered laminated composite plates subjected to the air blast
loading is investigated numerically. In-plane stiffness, inertia and the
geometric nonlinearity effects are considered in the formulation of the
problem. The equations of motion for the tapered laminated plate are derived by
the use of the virtual work principle. Approximate solution functions are
assumed for the space domain and substituted into the equations of motion.
Then, the Galerkin method is used to obtain the nonlinear algebraic
differential equations in the time domain. The resulting equations are solved
by using the finite difference approximation over the time. The effects of the
taper ratio, the stacking sequence and the fiber orientation angle on the
dynamic response are investigated. The displacement-time and strain-time
histories are obtained on certain points in the tapered direction. The results
obtained by using the present method are compared with the ones obtained by
using a commercial finite element software ANSYS. The results are found to be
in an agreement. The method presented here is able to determine the nonlinear
dynamic response of simply supported tapered laminated plates to the air blast
loading accurately.
Keywords: Tapered plate, blast loading, laminated composite plate, large deflection, nonlinear analysis, finite element method
