Aircraft fuselage frame made of laminated composite materials and including reinforcement curved zones of varying value of radius of curvature

摘要

A structural frame for a fuselage of an aircraft. The frame is formed from a composite material profile comprising curved zones (7) that interconnect together zones to be joined of the frame, having respective orientations. Each of the curved zones (7) of the frame is geometrically defined by at least one radius of curvature. The value of the radius of curvature (R2), geometrically defining a curved zone (7) of the frame varies as a function of the curvilinear abscissa of each points on the inside periphery of the inside flange from any point of the curved zone relative to a given reference point (P1).