公开(公告)号：US10384759B2

公开(公告)日：2019-08-20

申请号：US15361292

申请日：2016-11-25

Applicant: Airbus Operations GmbH

Inventor： Ichwan Zuardy ,  Thomas Hoffmeister ,  Axel Siegfried Herrmann ,  Markus Müller

IPC: B64C1/10 ,  B64C1/06

Abstract: A pressure bulkhead for an aircraft fuselage having a skin element, with a first surface and a second surface, a circumferential edge and a center axis, and a reinforcement assembly, which has radially disposed reinforcement elements extending along the first surface radially between an outer end at the edge of the skin element and an inner end, which faces the center axis, wherein, in a cross section, which extends radially along the center axis, each of the radially disposed reinforcement elements defines first and second contour lines, each extending from the outer end of the radially disposed reinforcement elements to the inner end thereof, and the reinforcement assembly resting with the first contour lines thereof on the first surface of the skin element. A pressure bulkhead for an aircraft fuselage can efficiently absorb occurring pressure loads.

公开(公告)号：US10301003B2

公开(公告)日：2019-05-28

申请号：US15141203

申请日：2016-04-28

Applicant: Airbus Operations GmbH

Inventor： Paul J Jörn ,  Markus Müller

IPC: B29C65/00 ,  B29C65/56 ,  B29C65/60 ,  B64C1/06 ,  B64F5/10 ,  B64C1/00 ,  B29K301/00 ,  B29K305/00 ,  B29K307/04 ,  B29K309/02

Abstract: This pertains to a method for connecting fiber-reinforced structural components. In a first step of the method, a first fiber-reinforced structural component and a second fiber-reinforced structural component are supplied. In another step, the first fiber-reinforced structural component and the second fiber-reinforced structural component are heated by means of a heating device. A penetration through the first fiber-reinforced structural component and the second fiber-reinforced structural component is produced in another step by means of a fastening device. In another step, the first fiber-reinforced structural component is connected to the second fiber-reinforced structural component by means of the fastening device. This furthermore pertains to a structural aircraft element.

公开(公告)号：US20170137107A1

公开(公告)日：2017-05-18

申请号：US15361292

申请日：2016-11-25

Applicant: Airbus Operations GmbH

Inventor： Ichwan Zuardy ,  Thomas Hoffmeister ,  Axel Siegfried Herrmann ,  Markus Müller

IPC: B64C1/10 ,  B64C1/06

CPC classification number: B64C1/10 ,  B64C1/064

Abstract: A pressure bulkhead for an aircraft fuselage having a skin element, with a first surface and a second surface, a circumferential edge and a center axis, and a reinforcement assembly, which has radially disposed reinforcement elements extending along the first surface radially between an outer end at the edge of the skin element and an inner end, which faces the center axis, wherein, in a cross section, which extends radially along the center axis, each of the radially disposed reinforcement elements defines first and second contour lines, each extending from the outer end of the radially disposed reinforcement elements to the inner end thereof, and the reinforcement assembly resting with the first contour lines thereof on the first surface of the skin element. A pressure bulkhead for an aircraft fuselage can efficiently absorb occurring pressure loads.

公开(公告)号：US20160340018A1

公开(公告)日：2016-11-24

申请号：US15159010

申请日：2016-05-19

Applicant: Airbus Operations GmbH

Inventor： Paul Jörn ,  Markus Müller

IPC: B64C1/10 ,  B32B5/18 ,  B32B3/12

CPC classification number: B64C1/10 ,  B32B3/12 ,  B32B5/18 ,  B32B2605/18

Abstract: Described and illustrated is a pressure bulkhead for an aircraft fuselage, comprising a sandwich structure defining a central axis and extending between a circumferential border area which is configured for being mounted to a fuselage shell, wherein the sandwich structure comprises an inner face sheet extending perpendicularly with respect to the central axis, an outer face sheet opposite the inner face sheet, extending perpendicularly with respect to the central axis, and a core assembly sandwiched between the inner face sheet and the outer face sheet, wherein the inner face sheet, when viewed in a radial cross section along the central axis, has an even shape. The object of the present disclosure, to provide a pressure bulkhead for an aircraft fuselage, wherein the required weight is reduced, is achieved in that the outer face sheet, when viewed in the radial cross section along the central axis, has a convex shape, wherein the distance between the outer face sheet and the inner face sheet increases tangent continuously from the border area to the central axis.

Abstract translation: 描述和示出的是用于飞行器机身的压力舱壁，其包括限定中心轴线并且在构造成安装到机身壳体的周向边界区域之间延伸的夹层结构，其中夹层结构包括垂直于 相对于中心轴线的相对于内表面片相对于中心轴线垂直延伸的外表面片和夹在内表面片和外面片之间的芯组件，其中，当从内表面片 沿着中心轴的径向横截面具有均匀的形状。 本发明的目的是提供一种用于飞机机身的压力舱壁，其中所需重量减小，其中当沿着中心轴线的径向横截面观察时，外表面片具有凸形， 其中，所述外表面片和所述内面片之间的距离从所述边界区域连续地增加到所述中心轴线。

公开(公告)号：US10259557B2

公开(公告)日：2019-04-16

申请号：US15159010

申请日：2016-05-19

Applicant: Airbus Operations GmbH

Inventor： Paul Jörn ,  Markus Müller

IPC: B64C1/10 ,  B32B3/12 ,  B32B5/18

Abstract: Described and illustrated is a pressure bulkhead for an aircraft fuselage, comprising a sandwich structure defining a central axis and extending between a circumferential border area which is configured for being mounted to a fuselage shell, wherein the sandwich structure comprises an inner face sheet extending perpendicularly with respect to the central axis, an outer face sheet opposite the inner face sheet, extending perpendicularly with respect to the central axis, and a core assembly sandwiched between the inner face sheet and the outer face sheet, wherein the inner face sheet, when viewed in a radial cross section along the central axis, has an even shape. The object of the present disclosure, to provide a pressure bulkhead for an aircraft fuselage, wherein the required weight is reduced, is achieved in that the outer face sheet, when viewed in the radial cross section along the central axis, has a convex shape, wherein the distance between the outer face sheet and the inner face sheet increases tangent continuously from the border area to the central axis.

公开(公告)号：US20160001869A1

公开(公告)日：2016-01-07

申请号：US14747707

申请日：2015-06-23

Applicant: Airbus Operations GmbH

Inventor： Paul Jörn ,  Pierre Zahlen ,  Markus Müller ,  Ichwan Zuardy ,  Claus Hanske

IPC: B64C1/12 ,  B64C1/06

CPC classification number: B64C1/12 ,  B64C1/064 ,  B64C1/068

Abstract: An aircraft structural component having a skin element, including an inner surface, a multitude of transverse stiffening elements, which lie against the inner surface of the skin element, and a multitude of longitudinal stiffening elements, perpendicular to the transverse stiffening elements against the inner surface of the skin element, wherein between a first and a second transverse stiffening element and also between a first and a second longitudinal stiffening element, a first skin section is defined. An aircraft structural component is provided with the quantity of the longitudinal stiffening elements reduced. A first applied reinforcement includes a core layer having a contour line running along the circumference of the skin element, the first applied reinforcement including a face sheet surrounding the core layer on the side thereof which faces away from the skin element, which face sheet is connected to the skin element along the core layer contour line.

Abstract translation: 一种具有皮肤元件的飞机结构部件，包括内表面，多个横向加强元件，其位于皮肤元件的内表面上，以及多个纵向加强元件，其垂直于横向加强元件抵靠内表面 的皮肤元件，其中在第一和第二横向加强元件之间以及在第一和第二纵向加强元件之间，限定第一皮肤部分。 飞机结构部件具有减少的纵向加强元件的数量。 第一施加的加强件包括具有沿着皮肤元件的圆周延伸的轮廓线的芯层，第一施加的加强件包括围绕其侧面的芯层的面板，其面向远离皮肤元件，该面板被连接 沿着核心层轮廓线到皮肤元素。

公开(公告)号：US11618544B2

公开(公告)日：2023-04-04

申请号：US16199886

申请日：2018-11-26

Applicant: Airbus Operations GmbH

Inventor： Peter Linde ,  Markus Müller ,  Markus Feiler

IPC: B64C1/06 ,  B64C1/12 ,  B64F5/10 ,  B29D99/00 ,  B29C70/08 ,  B29K71/00 ,  B64C1/00 ,  B29L31/30

Abstract: A method for producing a structural section of a vehicle comprises the steps of providing multiple separate skin panels of a fiber-reinforced plastic having an inner side, an outer side and a border running peripherally around the respective skin panel; arranging at least one stiffening component of a fiber-reinforced plastic on each skin panel, on the respective inner side; integrally connecting the respective at least one stiffening component to the skin panels concerned to form a structural component; arranging at least two structural components on a carrier, so that at least regions of the borders of the structural components concerned are in surface-area contact; and integrally connecting the regions of the borders that are in surface-area contact to one another.

公开(公告)号：US10377461B2

公开(公告)日：2019-08-13

申请号：US14747707

申请日：2015-06-23

Applicant: Airbus Operations GmbH

Inventor： Paul Jörn ,  Pierre Zahlen ,  Markus Müller ,  Ichwan Zuardy ,  Claus Hanske

IPC: B64C1/12 ,  B64C1/06

Abstract: An aircraft structural component having a skin element, including an inner surface, a multitude of transverse stiffening elements, which lie against the inner surface of the skin element, and a multitude of longitudinal stiffening elements, perpendicular to the transverse stiffening elements against the inner surface of the skin element, wherein between a first and a second transverse stiffening element and also between a first and a second longitudinal stiffening element, a first skin section is defined. An aircraft structural component is provided with the quantity of the longitudinal stiffening elements reduced. A first applied reinforcement includes a core layer having a contour line running along the circumference of the skin element, the first applied reinforcement including a face sheet surrounding the core layer on the side thereof which faces away from the skin element, which face sheet is connected to the skin element along the core layer contour line.

公开(公告)号：US10350821B2

公开(公告)日：2019-07-16

申请号：US14947753

申请日：2015-11-20

Applicant: Airbus Operations GmbH

Inventor： Markus Müller ,  Heike Klinger

IPC: B29C67/00 ,  B29C64/106 ,  B29C70/70 ,  B33Y80/00 ,  B33Y10/00 ,  B33Y30/00 ,  B29C64/112

Abstract: A method, system and dispensing head for manufacturing a three-dimensional object by additive manufacturing. The three-dimensional object includes a three-dimensional component. The method provides a substrate and forming layers there-on, each layer formed in a pattern corresponding to a three-dimensional component being manufactured and each layer formed by dispensing a curable material from a nozzle of a dispensing head and subsequently curing the curable material. The three-dimensional object comprises the combination of the substrate and the three-dimensional component, wherein the substrate has a non-planar surface portion and the three-dimensional component is formed on the non-planar surface portion such that it is fixedly secured to the substrate. During forming of the layers and/or between forming of two adjacent layers a relative movement between the substrate and the dispensing head is effected such that in a substrate coordinate system the dispensing head moves along a non-linear path over the non-planar surface portion.

公开(公告)号：US20160340017A1

公开(公告)日：2016-11-24

申请号：US15158994

申请日：2016-05-19

Applicant: Airbus Operations GmbH

Inventor： Paul Jörn ,  Markus Müller

IPC: B64C1/10 ,  B32B3/12 ,  B32B5/18

CPC classification number: B64C1/10

Abstract: A pressure bulkhead for an aircraft fuselage including a sandwich structure defining a central axis and extending between a circumferential border area, the sandwich structure including an inner face sheet and an outer face sheet extending transverse to the central axis, and a core assembly sandwiched between the inner face sheet and the outer face sheet. The pressure bulkhead can receive pressure loads and can be used as a structural bearing element for receiving loads introduced by other structural parts. The inner face sheet and/or the outer face sheet has a corrugated shape. The distance between the outer face sheet and the inner face sheet increases and subsequently decreases from the border area to a central area about the central axis, forming a thickened area where the distance between the outer face sheet and the inner face sheet has a peak.

Abstract translation: 一种用于飞行器机身的压力舱壁，包括限定中心轴线并且在周向边界区域之间延伸的夹层结构，所述夹层结构包括内表面片和横向于中心轴线延伸的外表面片，以及夹在 内表面片和外面片。 压力舱壁可承受压力负荷，可用作结构轴承元件，用于承受由其他结构部件引入的载荷。 内面片和/或外面片具有波纹形状。 外表面片与内面片之间的距离随着边界区域向中心轴线的中心区域的增加而逐渐减小，形成外面片与内面片之间的距离为峰值的增厚区域。