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    Modular System For Installing Modules On A Fuselage Structure Of A Vehicle
    42.
    发明申请
    Modular System For Installing Modules On A Fuselage Structure Of A Vehicle 审中-公开

    公开(公告)号：US20190193872A1

    公开(公告)日：2019-06-27

    申请号：US16205504

    申请日：2018-11-30

    Applicant: Airbus Operations GmbH

    Inventor： Hermann Benthien ,  Martin Metten ,  Florian Müller ,  Michael Telkamp ,  Marcus Hinrichs ,  Tancredi Tincani ,  Ralph Schmitt

    IPC: B64F5/10 ,  B64C1/06

    CPC classification number: B64F5/10 ,  B64C1/069

    Abstract: A system for installing modules on a fuselage structure has modules with holders arranged thereon for fastening on a fuselage structure, assembly stands, which can be moved on a floor level, and a flexible connecting element, extending via all the modules and coupling them together. Each assembly stand has a base for supporting the stand on the floor level and a holding device, designed to support the module. The assembly stands, the modules and the at least one connecting element are designed to form a chain of assembly stands, such that two successive groups of assembly stands enclose a pivot point at which the mutually facing modules have a larger spacing relative to one another than the modules within the respective groups. The connecting element allows the pivoting of the groups relative to one another at the pivot point through an angle of at least 90°.

    JOINT DEVICE AND GUIDE ARRANGEMENT
    44.
    发明申请
    JOINT DEVICE AND GUIDE ARRANGEMENT 审中-公开

    公开(公告)号：US20170292551A1

    公开(公告)日：2017-10-12

    申请号：US15473342

    申请日：2017-03-29

    Applicant: Airbus Operations GmbH

    Inventor： Hermann Benthien ,  Andreas Poppe

    IPC: F16B9/00 ,  B64C1/06 ,  B64D11/02 ,  F16B21/08

    Abstract: A joint device rotatably connecting a functional component to a fixing structure includes a bearing shell having a first guide body with a curved first guide face, and a second guide body with a second guide face. The bearing shell connects to either the functional component or the fixing structure. An inner body having a connection portion and a guide portion is arranged between the first and second guide faces. The connection portion connects to the other of the functional component or the fixing structure. The guide portion is movably guided on the first and second guide faces about a first rotational axis defined by the curved first guide face. The connection portion or the bearing shell connects to the fixing structure by a pin. A second rotational axis extending transversely to the first rotational axis is defined by a pin central axis and/or the first guide face curvature.

    Locally reinforced aircraft structural component
    47.
    发明授权
    Locally reinforced aircraft structural component 有权
    当地强化飞机结构部件

    公开(公告)号：US09386825B2

    公开(公告)日：2016-07-12

    申请号：US14312211

    申请日：2014-06-23

    Applicant: Airbus Operations GmbH

    Inventor： Hermann Benthien ,  Axel Soeffker

    IPC: B64C1/18 ,  A44B18/00

    CPC classification number: A44B18/0069 ,  B64C1/18 ,  Y10T24/2767 ,  Y10T29/49622

    Abstract: An aircraft structural component comprising a panel element made of a fiber reinforced composite material and provided with an opening extending fully through the panel element. A reinforcing element made of a fiber reinforced composite material has an opening extending through the reinforcing element from a first surface to a second surface of the reinforcing element. The opening extending through the reinforcing element is aligned with the opening extending through the panel element. A bushing extends through the opening provided in the panel element and the opening provided in the reinforcing element and is adapted to receive an attachment device for attaching a load to the aircraft structural component. A connecting element connects the reinforcing element to the panel element in a region of the panel element adjacent to the opening extending through the panel element by means of a hook and loop connection.

    Abstract translation: 一种飞机结构部件，包括由纤维增强复合材料制成的面板元件，并且具有完全延伸穿过所述面板元件的开口。 由纤维增强复合材料制成的增强元件具有从加强元件的第一表面延伸穿过加强元件的第二表面的开口。 穿过加强元件的开口与延伸穿过面板元件的开口对齐。 衬套延伸穿过设置在面板元件中的开口和设置在加强元件中的开口，并且适于接收用于将负载附接到飞机结构部件的附接装置。 连接元件通过钩环连接将加强元件连接到面板元件的与通过屏元件延伸的开口相邻的区域中。

    HOLDER FOR CONNECTING A MODULE TO A COMPONENT OF AN AIRCRAFT OR SPACECRAFT, ARRANGEMENT, AIRCRAFT OR SPACECRAFT, AND METHOD
    48.
    发明申请
    HOLDER FOR CONNECTING A MODULE TO A COMPONENT OF AN AIRCRAFT OR SPACECRAFT, ARRANGEMENT, AIRCRAFT OR SPACECRAFT, AND METHOD 审中-公开
    将模块连接到飞机或飞机组件，安装，飞机或机架和方法的持有人

    公开(公告)号：US20150252824A1

    公开(公告)日：2015-09-10

    申请号：US14636507

    申请日：2015-03-03

    Applicant: Airbus Operations GmbH

    Inventor： Hermann Benthien ,  Matthias Hegenbart ,  Sheriff Shehata

    IPC: F16B2/02 ,  F16M11/22 ,  F16B11/00

    CPC classification number: F16B2/02 ,  B64C1/406 ,  F16B2/12 ,  F16B11/006 ,  F16B11/008 ,  F16M11/22 ,  Y02T50/46 ,  Y10T156/10

    Abstract: A holder for connecting a module to a component of an aircraft or spacecraft includes a first holder portion having a first adhesive face and a second holder portion having a second adhesive face. The first and second holder portions are movable relative to one another in an initial state of the holder such that a portion of the component can be received between the holder portions so as to glue the holder portions to the component by means of an adhesive layer in each case. The holder has two or more guided parts which are movable relative to one another by means of mutually cooperating guide faces in the initial state of the holder. The guide faces are suitably formed for being glued together using an adhesive. The holder can be used to counter peeling stress of an adhesive connection of the holder in the region of the first and/or second adhesive face.

    Abstract translation: 用于将模块连接到飞机或航天器的部件的保持器包括具有第一粘合面的第一保持器部分和具有第二粘合面的第二保持器部分。 第一和第二保持器部分可以在保持器的初始状态下相对于彼此移动，使得部件的一部分可以容纳在保持器部分之间，以便通过粘合剂层将保持器部分粘合到部件上 每个案例。 保持器具有两个或更多个引导部件，它们在保持器的初始状态下可通过相互配合的引导面相对于彼此移动。 引导面适当地形成用于使用粘合剂胶合在一起。 保持器可以用于抵抗在第一和/或第二粘合面的区域中保持器的粘合连接的剥离应力。

    Fastening apparatus for fastening a furnishing component to an attachment structure of an aircraft cabin
    49.
    发明授权
    Fastening apparatus for fastening a furnishing component to an attachment structure of an aircraft cabin 有权

    公开(公告)号：US12195181B2

    公开(公告)日：2025-01-14

    申请号：US18159779

    申请日：2023-01-26

    Applicant: Airbus Operations GmbH

    Inventor： Matthias Hegenbart ,  Hermann Benthien

    IPC: F16B5/12 ,  B64D11/00

    Abstract: An apparatus for fastening a component to an aircraft cabin attachment structure, the attachment structure having a fastening tube with a longitudinal axis. The apparatus has an internally bored sleeve rotatably positionable on the fastening tube and an external thread. A holding body connects to the component and has two spaced-apart limbs and a bearing surface enclosed by the limbs, and on which, an internal thread configured to the sleeve external thread, is arranged. A device fixes the holding body to the threaded sleeve and the fastening tube, the external and internal threads being non-self-locking. When the holding body internal thread presses against the threaded sleeve external thread, the threaded sleeve rotates until the external and internal threads align. The fixing device connects the threaded sleeve to the holding body in a rotationally fixed manner and fixes the holding body transversely with respect to the longitudinal axis.

    Vortex generator apparatus for an aircraft
    50.
    发明授权
    Vortex generator apparatus for an aircraft 有权

    公开(公告)号：US11643190B2

    公开(公告)日：2023-05-09

    申请号：US17159829

    申请日：2021-01-27

    Applicant: Airbus Operations GmbH

    Inventor： Peter Linde ,  Matthias Hegenbart ,  Hermann Benthien

    IPC: B64C23/06

    CPC classification number: B64C23/076

    Abstract: A vortex generator apparatus for an aircraft includes a surface section having a receiving recess, a vortex generator having a first edge, an opposite second edge and a vortex generator surface component extending from the first edge to the second edge, wherein the first edge is fixedly arranged in or adjacent to the receiving recess. The vortex generator surface component includes at least one electroactive polymer assembly, wherein the at least one electroactive polymer is switchable into an extended state by applying an electrical voltage and into a neutral state by removing the electrical voltage. The electroactive polymer assembly and the vortex generator surface component are configured to retract the vortex generator surface component completely into the receiving recess in the neutral state of the electroactive polymer assembly and to extend the vortex generator surface component from the receiving recess in the extended state.

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