Investigation of field coupling into a carbon fiber aircraft fuselage with the method of moments

In this paper the field coupling into a fuselage model consisting of carbon fiber composite with apertures is analyzed by means of the Method of Moments. A set of two boundary integral equations, involving two current layers, is applied for accurate treatment of aperture coupling. The considered anisotropic shell is investigated by two approaches, where the modeling is accomplished using boundary impedances and a multilayer technique, respectively. The applicability of these techniques is studied and validated by reference computations on generic test objects. It turns out that the results gained by the proposed techniques are in very good agreement with results of the finite element method.