INVESTIGATION OF THE STRENGTH BEHAVIOUR OF A FUSELAGE STRUCTURE PLACED IN A LINEARLY EXPANDING WING WITH CIRCULAR ENDS IN CROSS-SECTION

Abstract

In this study, a structurally different drop wing geometry was modelled and its mechanical behaviour was investigated with computer aided analysis software within the finite element method. The tip of the drop wing geometry consists of one large and the other small circles. There were linear line profiles between them. In order to prevent collapse in the wing geometry modelled with the plate structure, a profile in the rigid body structure was created and its effect was investigated. The effect of the wing length and the plate thickness covering the wing was examined and shown in the results. It was defined as the profile material for the steel blade and for the standard features. In the static examinations carried out under the pressure loading applied on the wing, it was determined that the vertical deformation caused by the wing length was not linear, and the stresses that occur with the increasing wing plate thickness form a decreasing function. The stresses that occur in the inside of the wing support were intense in the support area, but also in the bending areas.