公开(公告)号：US08800928B2

公开(公告)日：2014-08-12

申请号：US13384033

申请日：2010-07-15

Applicant: Thorsten Roming ,  Hansjörg Horneber ,  Thorsten Schröer ,  Tobias Wirtz ,  Klaus Edelmann ,  Tanja Menken (Frese)

Inventor： Thorsten Roming ,  Hansjörg Horneber ,  Thorsten Schröer ,  Tobias Wirtz ,  Klaus Edelmann ,  Tanja Menken (Frese)

IPC: B64C1/12

CPC classification number: B64C1/061 ,  B64C1/068 ,  B64C1/12

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 translation: 本发明涉及一种用于制造用于飞机的机身单元的机身单元部分的壳段，其具有布置在其上的至少一个皮肤区域和多个纵向加强件，特别是桁条，以及至少一个横向加强件 元件横向于纵向加强件，特别是至少一个框架。 由于至少一个横向加强元件与至少一个皮肤区域的连接是用至少一个连接支架进行的，其中至少一个连接支架具有至少一个波纹，所述支撑托架用于吸收倾斜力矩 可以省略以现有技术的壳段的实施例的框架。 通过这种方式，相当可观的重量减轻是可能的，同时减少了生产力。

公开(公告)号：US20120132756A1

公开(公告)日：2012-05-31

申请号：US13384033

申请日：2010-07-15

Applicant: Thorsten Roming ,  Hansjörg Horneber ,  Thorsten Schröer ,  Tobias Wirtz ,  Klaus Edelmann ,  Tanja Menken

Inventor： Thorsten Roming ,  Hansjörg Horneber ,  Thorsten Schröer ,  Tobias Wirtz ,  Klaus Edelmann ,  Tanja Menken

IPC: B64C1/06

CPC classification number: B64C1/061 ,  B64C1/068 ,  B64C1/12

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 translation: 本发明涉及一种用于制造用于飞机的机身单元的机身单元部分的壳段，其具有布置在其上的至少一个皮肤区域和多个纵向加强件，特别是桁条，以及至少一个横向加强件 元件横向于纵向加强件，特别是至少一个框架。 由于至少一个横向加强元件与至少一个皮肤区域的连接是用至少一个连接支架进行的，其中至少一个连接支架具有至少一个波纹，所述支撑托架用于吸收倾斜力矩 可以省略以现有技术的壳段的实施例的框架。 通过这种方式，相当可观的重量减轻是可能的，同时减少了生产力。