Abstract: The invention concerns a shell segment for the purpose of manufacturing a fuselage cell section for a fuselage cell of an aeroplane, with at least one skin field and with a multiplicity of longitudinal stiffeners arranged thereon, in particular stringers, and also at least one transverse stiffening element running transverse to the longitudinal stiffeners, in particular at least one frame. In that the connection of the at least one transverse stiffening element to the at least one skin field is undertaken with at least one connecting bracket wherein the at least one connecting bracket has at least one corrugation, the supporting brackets for purposes of absorbing tilting moments of the frames, in forms of embodiment of shell segments of prior known art, can be omitted. By this means a considerable weight reduction is possible with, at the same time, a reduced production effort.

Abstract: The invention relates to a device for the production of an angle for connecting a fuselage cell skin to an annular former and/or a stringer inside a fuselage cell structure of an aircraft, the angle taking place by the one-step deformation of an initially planar blank along at least three fold lines in a uniaxial compression molding device. A mounting frame with hinges is arranged in the compression molding device, the blank to be deformed being accommodated along the edges preferably by means of a plurality of peripherally arranged springs. A deformation of the blank into an auto-stabilized angle is possible in one step while simultaneously ensuring interlaminar slide. Due to the constructively conditioned auto-stabilization of the angle, additional components which increase the weight and the assembly effort (so-called “stabilos”) in the connection region between fuselage cell skin, stringers and annular formers inside a fuselage structure of an aircraft are unnecessary.

Abstract: The invention concerns a shell segment for the purpose of manufacturing a fuselage cell section for a fuselage cell of an aeroplane, with at least one skin field and with a multiplicity of longitudinal stiffeners arranged thereon, in particular stringers, and also at least one transverse stiffening element running transverse to the longitudinal stiffeners, in particular at least one frame. In that the connection of the at least one transverse stiffening element to the at least one skin field is undertaken with at least one connecting bracket wherein the at least one connecting bracket has at least one corrugation, the supporting brackets for purposes of absorbing tilting moments of the frames, in forms of embodiment of shell segments of prior known art, can be omitted. By this means a considerable weight reduction is possible with, at the same time, a reduced production effort.

Abstract: The invention relates to a method for producing a component for connecting a fuselage cell skin to an annular rib of an aircraft, wherein the component is formed by bending of a flat blank along at last two edge lines and wherein the blank is formed by a CFRP. According to the invention the interlaminar sliding of the fiber layers is largely completed in a first forming step, while in a second forming step a consolidation of the component takes place by the use of pressure from the press on all sides by means of an upper tool and a lower tool. This enables complex components with at least two edge lines to be produced, which edge lines run at angles of approximately, preferably at angles of 309° to 90°, to each other, and which edge lines also lie in at least two different planes.

Abstract: The invention relates to a method for producing a component for connecting a fuselage cell skin to an annular rib of an aircraft, wherein the component is formed by bending of a flat blank along at last two edge lines and wherein the blank is formed by a CFRP. According to the invention the interlaminar sliding of the fibre layers is largely completed in a first forming step, whilst in a second forming step a consolidation of the component takes place by the use of pressure from the press on all sides by means of an upper tool and a lower tool. This enables complex components with at least two edge lines to be produced, which edge lines run at angles of approximately, preferably at angles of 309° to 90°, to each other, and which edge lines also lie in at least two different planes.