Analysis of Composite Plate Subjected to Impact Load

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Analysis of Composite Plate Subjected to Impact Load
(Part I: Analytical Solution)
Abstract
Composite laminated plates are found in many types of structural and aeronautical
weight sensitive applications, such as, ships, automobiles. This work includes developing
the equations of motion of composite laminated plates to obtain deformations and stresses
under impact loading.
The Hertzian impact law is modeled to describe the contact force between the
projectile and the laminated plates. Analytical solution using (Navier solution) and theories
(First Order Shear Deformation Theory „FSDT‟ and Higher Order Shear Deformation
Theory „HOST 5‟) is presented. The results show the parametric effect of number of layers,
lamination angle, and orthotropy ratio on the behavior of the laminated plates.
CONCLUSIONS
Many conclusions can be drawn from the present work which can be summarized, as follows:
1) Increase in volume fraction causes increasing modules of elasticity and decreases passion ratio of
composite materials.
2) The increasing volume fraction causes decreasing in maximum deflection of (mat, randam1
{450kg/m3}, and randam2 {300kg/m3}) composite materials.
3) The randam2 composite beam gives minimum deflection compared with mat and randam1
composite materials.
4) The heating of top surface of the beam causes decreasing in maximum deflection. While when
the bottom surface of the beam is heating, the maximum deflection is increases.
5) The cooling of top surface of the beam causes increasing in maximum deflection. While when
the bottom surface of the beam is cooling, the maximum deflection is decreases.
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