Abstract
The dynamic behaviour of a composite wing structure is studied. By computing strain-energy, kinetic energy and work of external loads, and by using Minimum Principles, differential matrix equations of the structure are written, where displacements play the role of degrees of freedom. By dividing the wing into a certain number of spanwise elements, two different methods can be used: FEM, (where descriptive functions for every element are given), and CEM (continuous elements) where the equations of the structure are solved for each element, and then continuity conditions are imposed. Several numerical examples complete the work; CEM and FEM are compared, and the influence of several parameters, in particular anisotropy, is considered.
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