Patent ID: 8740150
Filing Date: 2014-06-03
Classification: B64C

Abstract:
1. A connection of an aerofoil to a fuselage airframe of an aircraft comprising a plurality of coupling members, in each case at least two z-coupling members which extend substantially parallel to a vertical axis of the aircraft and in each case at least two xz-coupling members being arranged in a region of two longitudinal edges of a fuselage airframe recess, wherein the spaces between the xz-coupling members and the z-coupling members are different and the xz-coupling members each comprising an xz-fuselage airframe bearing arranged on the fuselage airframe and an xz-aerofoil bearing attached to the aerofoil which are articulated to one another by two xz-straps which are inclined with respect to a longitudinal axis of the aircraft, wherein both longitudinal axes of the two xz-straps extend in an opposite inclination and with inclinations of different sizes with respect to a horizontal to compensate differing force effects, wherein the xz-straps of at least one xz-coupling member are configured such that, in the event of a crash, an energy-absorbing compression of the xz-straps occurs, as a result of which a side face of the xz-fuselage airframe bearing and a side face of the xz-aerofoil bearing are brought into direct mechanical contact, wherein the side faces are each provided with teeth which, in the event of a crash, mesh at least in a plurality of teeth, and wherein the xz-straps of the xz-coupling member comprise at least one of an elongate oval shape, a statically light configuration or have at least one weakened zone to allow a defined deformation of the xz-strap in the event of the aircraft crashing, so that impact energy is transferred by the xz-coupling member.