Under-flap stiffener for aircraft

摘要

An assembly of longitudinal structural stiffeners for an aircraft including, in a front portion of the fuselage, a windscreen that is slightly recessed relative to the airplane nose, and a fuselage portion extending in alignment with the airplane nose up to the base of the windscreen. The stiffeners include a bending-resistance main plane and are arranged under the flap and connected to the fuselage along a force transfer line. For one or more of the 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 predetermined by the local normal to the fuselage surface and the longitudinal axis of the airplane. A method is also provided for calculating the shape of the stiffeners.

主权项

1. An assembly comprising:
a fuselage surface; and a plurality of longitudinal structural stiffeners, the stiffeners comprising a main plane of bending resistance substantially perpendicular to the fuselage surface, being positioned below a portion of the fuselage surface and secured to the fuselage surface along a force transfer line; wherein, for plural of the stiffeners, the main plane of bending resistance of the stiffener substantially coincides, in at least a certain number of points Pi of its surface force transfer line, with the plane XPiNi defined by the local normal Ni to the surface and an already known impact axis XPi, wherein the stiffeners have an “I”-type cross-section comprising a core and two struts at extremities of the core and perpendicular to the core, and wherein the core forms the main plane of bending resistance.