UNDER-FLAP STIFFENER FOR AIRCRAFT

摘要

The invention relates to an assembly of longitudinal structural stiffeners for an aircraft comprising, in the front portion of the fuselage, a windscreen that is slightly recessed relative to the airplane nose, a fuselage portion (flap) extending in alignment with the airplane nose up to the base of the windscreen, said stiffeners being of the kind that comprise a bending-resistance main plane and being arranged under the flap and connected to the fuselage along a force transfer line, characterised in that for one or more of said stiffeners, the bending resistance main plane substantially coincides, at at least a certain number of points of the fuselage force transfer line, with the plane XNi predetermined by the local normal Ni to the fuselage surface and the longitudinal axis X of the airplane. The invention also relates to a method for calculating the shape of the stiffeners.