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

A structural frame of an aircraft fuselage, said frame including curved zones interconnecting together zones to be joined;

• said zones to be joined are located at respective ends of a given curved zone, the frame being formed by a profile made of laminated composite materials comprising a core bordered at least by one inside flange facing towards an inside recess of the frame, each of the curved zones of the frame being geometrically defined by at least one radius of curvature;
• wherein said at least one radius of curvature geometrically defining at least one curved zone of the frame at least in part, is variable, having a value that varies as a function of a curvilinear abscissa of each points on an inside periphery of the inside flange facing towards the inside recess of the frame, from any point of the curved zone relative to a given reference point.