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公开(公告)号：US09471046B2
公开(公告)日：2016-10-18
申请号：US13947475
申请日：2013-07-22
Applicant: AIRBUS OPERATIONS GMBH
Inventor： Stephan Tertel , Markus Longeru , Patrick Steinmueller , Dirk Elbracht , Chris Degen
CPC classification number: G05B13/04 , B29C33/3835 , B29C70/54 , G06F17/5009 , G06F17/5095 , G06F2217/41 , G06F2217/80 , G06Q50/04 , Y02P90/30
Abstract: A method for producing a part is provided, the method including the following: a first step of a computer-aided simulation for a plurality of cross-sections of the part based on a 3D cross-sectional model and obtaining a first result, which represents shrinkage of the part basically caused by thermal and/or chemical reactions; a second step of a further computer-aided simulation for the plurality of cross-sections of the part based on a 2D shell model and obtaining a second result, which represents shrinkage of the part basically caused by thermal and/or chemical reactions; determining a scale factor for the second result in such a way that the second result corresponds to the first result; determining scale factors for any cross-sections which are between two adjacent cross-sections from the plurality of cross-sections, by interpolation; predicting a distortion of the part; and producing the part based on the predicted distortion of the part.
Abstract translation: 提供了一种制造零件的方法，所述方法包括以下步骤：基于3D横截面模型对所述零件的多个横截面进行计算机辅助模拟的第一步骤，并获得第一结果，其代表 部分收缩基本上由热和/或化学反应引起; 基于2D壳模型对所述部分的多个横截面进行另外的计算机辅助模拟的第二步骤，并获得表示基本上由热和/或化学反应引起的部分收缩的第二结果; 以所述第二结果对应于所述第一结果的方式确定所述第二结果的比例因子; 通过内插确定来自多个横截面的两个相邻横截面之间的任何横截面的比例因子; 预测零件的扭曲; 并基于预测的零件变形产生零件。
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公开(公告)号：US20180155013A1
公开(公告)日：2018-06-07
申请号：US15819560
申请日：2017-11-21
Applicant: Airbus Operations GmbH
Inventor： Dirk Elbracht , Bruno Stefes
Abstract: An aircraft airflow modification device, comprising: at least one resiliently deformable base member; and at least one resiliently deformable flap member that extends from the resiliently deformable base member. Deformation of the resiliently deformable base member from a first state to a second state results in corresponding deformation of the resiliently deformable flap member from a first state to a second state.
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公开(公告)号：US10427795B2
公开(公告)日：2019-10-01
申请号：US14674320
申请日：2015-03-31
Applicant: AIRBUS OPERATIONS GMBH
Inventor： Jens Telgkamp , Dirk Elbracht , Wolfgang Eilken , Bruno Stefes , Christian Bartels
Abstract: Inter alia, an apparatus including a ramp, the ramp configured to enable variation of a cross section of a ram air passage of the apparatus. The ramp includes a first rigid member, a second rigid member and a flexible member coupled to the first rigid member and the second rigid member. The ramp is movably mounted at two ends. Moreover, a method of varying the cross section of the ram air passage of such an apparatus by moving the ramp of the apparatus is disclosed. Further, an arrangement including such an apparatus and a ram air channel communicating with the ram air passage is disclosed.
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公开(公告)号：US20160280354A1
公开(公告)日：2016-09-29
申请号：US15019506
申请日：2016-02-09
Applicant: Airbus Operations GmbH
Inventor： Matthias Hegenbart , Torsten Noebel , Liu Wang , Michael Sauer , Memis Tiryaki , Dirk Elbracht
CPC classification number: B64C1/1461 , A47B97/04 , E05F5/02 , E05F5/025 , E05F5/06 , E05Y2900/502 , E05Y2900/531 , F16B1/00 , Y10T16/61
Abstract: A door stop element for an aircraft door has a body which is formed at least approximately L-shaped, and which has at least one contact area on the outer side of one of the legs for fixed contact on the aircraft fuselage, and a stop surface on the inner side of the other leg for the aircraft door. The body has a cavity, on the inner side of which adjacent to the stop surface a rib is provided, which extends through the stop surface symmetrically on both sides of the longitudinal median plane that extends perpendicular to the stop surface.
Abstract translation: 用于飞机门的门挡元件具有形成为至少大致L形的主体，并且在其中一个腿的外侧上具有用于固定接触在飞机机身上的至少一个接触区域，以及止动表面 在飞机门的另一条腿的内侧。 主体具有空腔，其内侧与止动表面相邻，设有肋，该纵向中心平面的垂直于止动表面延伸的纵向中间平面的两侧对称延伸。
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公开(公告)号：US11969955B2
公开(公告)日：2024-04-30
申请号：US17514783
申请日：2021-10-29
Applicant: Airbus Operations GmbH
Inventor： Johannes Born , Dirk Elbracht , Konstantin Schubert
CPC classification number: B29C70/30 , B29C70/24 , B29C70/382 , B33Y80/00 , B29K2101/12 , B29L2031/3082
Abstract: A component made of a fiber-reinforced plastic, having a first surface portion, a second surface portion and a transition portion, which is enclosed by the first surface portion and the second surface portion, wherein surface tangents to the first surface portion and the second surface portion are not parallel, at least in regions adjacent to the transition portion. The transition portion has a curvature adjoining the adjacent surface portions in a tangentially constant manner, wherein an arrangement of at least two layers made of a fiber-reinforced plastic extends from the first surface portion, over the transition portion, onto the second surface portion, and fibers at least of one of the layers run with an unchanging orientation on the first surface portion and the second surface portion and, on the transition portion, run in a laterally offset, inflected or curved manner along the running direction.
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Patent Agency Ranking
公开(公告)号：US11548213B2
公开(公告)日：2023-01-10
申请号：US16829534
申请日：2020-03-25
Applicant: Airbus Operations GmbH
Inventor： Claus Fastert , Dirk Elbracht , Johannes Born , Konstantin Schubert
IPC: B29C64/118 , B29C64/321 , B29C64/255 , B33Y10/00 , B33Y30/00
Abstract: A method of using solid profile rods instead of the usual filament coils for additive manufacturing methods such as 3D printing for industrial applications such as aircraft manufacturing, and to enable a more rapid production of fiber-composite components. The additive manufacturing device, or the 3D printer which generates the component layer by layer, respectively, comprises a material magazine in which a plurality of profile rods are stored. The profile rods are pre-tailored and are adapted to the component layer by layer. The profile rods, when printing, are successively retrieved from the material magazine and, by way of an infeed installation, guided to the nozzle of the additive manufacturing installation and subsequently applied to the printing bed so as to form the component layer by layer.
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公开(公告)号：US20170129586A1
公开(公告)日：2017-05-11
申请号：US15346166
申请日：2016-11-08
Applicant: Airbus Operations GmbH
Inventor： Dirk Elbracht , Cord Haack
CPC classification number: B64C1/1461 , B29C64/00 , B29L2031/3082 , B33Y10/00 , B33Y80/00 , B64C1/12 , B64C1/14
Abstract: An aircraft fuselage structure comprising a skin element having an inner surface, a support structure connected to the inner surface for supporting the skin element, and a door opening provided in the skin element, wherein the support structure comprises an upper longitudinal element, a lower longitudinal element, a first circumferential element and a second circumferential element provided at the door opening. The object to provide an aircraft fuselage structure, wherein the support structure around the door opening is optimized for a minimum weight, is achieved in that the support structure comprises a first upper angled element extending from an upper first corner to an upper center point, and a second upper angled element extending from an upper second corner to the upper center point, such that the upper longitudinal element, the first upper angled element, and the second upper angled element together form a central upper triangle.
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公开(公告)号：US10737771B2
公开(公告)日：2020-08-11
申请号：US15819560
申请日：2017-11-21
Applicant: Airbus Operations GmbH
Inventor： Dirk Elbracht , Bruno Stefes
Abstract: An aircraft airflow modification device, comprising: at least one resiliently deformable base member; and at least one resiliently deformable flap member that extends from the resiliently deformable base member. Deformation of the resiliently deformable base member from a first state to a second state results in corresponding deformation of the resiliently deformable flap member from a first state to a second state.
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公开(公告)号：US10450048B2
公开(公告)日：2019-10-22
申请号：US15346166
申请日：2016-11-08
Applicant: Airbus Operations GmbH
Inventor： Dirk Elbracht , Cord Haack
Abstract: An aircraft fuselage structure comprising a skin element having an inner surface, a support structure connected to the inner surface for supporting the skin element, and a door opening provided in the skin element, wherein the support structure comprises an upper longitudinal element, a lower longitudinal element, a first circumferential element and a second circumferential element provided at the door opening. The object to provide an aircraft fuselage structure, wherein the support structure around the door opening is optimized for a minimum weight, is achieved in that the support structure comprises a first upper angled element extending from an upper first corner to an upper center point, and a second upper angled element extending from an upper second corner to the upper center point, such that the upper longitudinal element, the first upper angled element, and the second upper angled element together form a central upper triangle.
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公开(公告)号：US09745045B2
公开(公告)日：2017-08-29
申请号：US15019506
申请日：2016-02-09
Applicant: Airbus Operations GmbH
Inventor： Matthias Hegenbart , Torsten Noebel , Liu Wang , Michael Sauer , Memis Tiryaki , Dirk Elbracht
CPC classification number: B64C1/1461 , A47B97/04 , E05F5/02 , E05F5/025 , E05F5/06 , E05Y2900/502 , E05Y2900/531 , F16B1/00 , Y10T16/61
Abstract: A door stop element for an aircraft door has a body which is formed at least approximately L-shaped, and which has at least one contact area on the outer side of one of the legs for fixed contact on the aircraft fuselage, and a stop surface on the inner side of the other leg for the aircraft door. The body has a cavity, on the inner side of which adjacent to the stop surface a rib is provided, which extends through the stop surface symmetrically on both sides of the longitudinal median plane that extends perpendicular to the stop surface.
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