公开(公告)号：WO2015015152A1

公开(公告)日：2015-02-05

申请号：PCT/GB2014/052008

申请日：2014-07-02

Applicant: AIRBUS OPERATIONS LIMITED

Inventor： PRICE, Jonathan ,  MEAKIN, Alastair ,  EDEN, James ,  KORYA, Chetan ,  WILLIAMS, Stephen ,  BURLEIGH, Christopher ,  BAKER, Peter

IPC: B64C3/26

CPC classification number: B64C3/187 ,  B64C3/182 ,  B64C3/26

Abstract: An aircraft structure extending from a root to a tip, the root being adapted to be joined to an aircraft fuselage. The structure has a cover with an aerodynamic outer surface and an inner surface, a plurality of stiffeners, and a plurality of ribs. The ribs include an inboard rib and a plurality of further ribs between the inboard rib and the tip. Each of the stiffeners has a stiffener flange joined to the inner surface of the cover and a stiffener web extending away from the stiffener flange. One of the further ribs has a rib web and a plurality of rib feet, each rib foot including a first rib foot flange joined to the web of a respective one of the stiffeners, a second rib foot flange joined to the inner surface of the cover or to the flange of the respective one of the stiffeners, and a rib foot web joined to the rib web. The joint between the first rib foot flange and the stiffener flange provides an efficient path for transmitting load from the cover into the rib web. Typically each first rib foot flange is joined to the stiffener web by a joint which can transmit load in shear from the stiffener web to the first rib foot flange.

Abstract translation: 从根部延伸到尖端的飞行器结构，该根部适于与飞行器机身连接。 该结构具有具有空气动力学外表面和内表面，多个加强件和多个肋的盖。 所述肋包括内侧肋和所述内侧肋与所述尖端之间的多个另外的肋。 每个加强件具有连接到盖的内表面的加强件凸缘和远离加强件凸缘延伸的加强筋。 其中一个肋条具有肋腹板和多个肋脚，每个肋脚包括连接到相应一个加强筋的腹板的第一肋脚法兰，连接到罩的内表面的第二肋脚法兰 或相应的一个加强件的凸缘，以及连接到肋腹板的肋脚腹板。 第一肋脚法兰和加强筋法兰之间的接合提供了有效的路径，用于将载荷从盖传递到肋腹板中。 通常，每个第一肋脚凸缘通过接头连接到加强筋腹板，所述接头可将来自加强筋的剪切载荷传递到第一肋脚凸缘。

公开(公告)号：WO2010010382A2

公开(公告)日：2010-01-28

申请号：PCT/GB2009/050889

申请日：2009-07-20

Applicant: AIRBUS OPERATIONS LIMITED ,  WILLIAMS, Stephen

Inventor： WILLIAMS, Stephen

IPC: B64C3/18 ,  B64F5/00

CPC classification number: B64C3/187 ,  B64F5/10 ,  Y10T29/49622

Abstract: A method of stiffening a rib during the assembly of an aircraft wing is described. A stiffener panel is attached to a face of the rib. The rib is aligned with one or more wing components with the stiffener panel attached. An assembly operation such as drilling is performed with the rib aligned and the stiffener panel attached. The stiffener panel is removed from the rib after the assembly operation. The stiffener panel has a resilient external sealing ring which is mounted on a face of the panel and forms an external perimeter of a vacuum cavity; and at least one resilient internal sealing ring which is mounted on the panel within the perimeter defined by the external sealing ring and forms an internal perimeter of the vacuum cavity. The stiffener can be attached to the rib by a vacuum clamping force, the vacuum being sealed by the external and internal sealing rings. The internal sealing ring(s) seal any holes which are present in the rib. The stiffener can support the rib during alignment to give it the required flatness.

Abstract translation: 描述了在飞行器机翼的组装期间加强肋的方法。 加强板连接到肋的表面。 肋与一个或多个机翼部件对准，加强板连接在一起。 执行诸如钻孔的组装操作，其中所述肋对准并且加强板连接。 在组装操作后，加强板被从肋上取下。 加强板具有弹性的外部密封环，其安装在面板的表面上并形成真空腔的外周; 以及至少一个弹性内部密封环，其在由外部密封环限定的周边内安装在面板上并形成真空腔的内部周边。 加强件可以通过真空夹紧力连接到肋上，真空由外部和内部密封环密封。 内密封环密封肋中存在的任何孔。 加强件可以在对准期间支撑肋条，使其成为所需的平整度。