公开(公告)号：US09902483B2

公开(公告)日：2018-02-27

申请号：US14469146

申请日：2014-08-26

Applicant: Airbus Operations GmbH

Inventor： Pierre C. Zahlen ,  Johannes Born ,  Lars Meyer ,  Gregor Baumbach ,  Claus Hanske ,  Jens Prowe ,  Johan Oentoro ,  M. Ichwan Zuardy ,  Wouter Brok ,  Martin Metten

IPC: B32B3/24 ,  B32B3/26 ,  B32B5/18 ,  B32B5/24 ,  B32B5/26 ,  B32B5/28 ,  B32B7/04 ,  B60J1/00 ,  B64C1/14 ,  B29C70/02 ,  B32B3/08 ,  B32B37/16 ,  B32B37/30 ,  B32B37/12 ,  B32B38/04 ,  B29C70/30 ,  B29L7/00 ,  B32B3/02 ,  B29C70/54 ,  B29L9/00 ,  B29L31/30 ,  B29L31/00 ,  B64C1/12 ,  B64C1/00

CPC classification number: B64C1/1484 ,  B29C70/023 ,  B29C70/026 ,  B29C70/30 ,  B29C70/545 ,  B29C2793/0018 ,  B29C2793/0081 ,  B29L2007/002 ,  B29L2009/00 ,  B29L2031/005 ,  B29L2031/30 ,  B29L2031/3082 ,  B32B3/02 ,  B32B3/08 ,  B32B3/263 ,  B32B3/266 ,  B32B5/18 ,  B32B5/245 ,  B32B5/26 ,  B32B5/28 ,  B32B7/04 ,  B32B37/16 ,  B32B37/30 ,  B32B38/04 ,  B32B2250/03 ,  B32B2250/24 ,  B32B2250/40 ,  B32B2250/44 ,  B32B2260/00 ,  B32B2266/08 ,  B32B2305/022 ,  B32B2305/07 ,  B32B2605/00 ,  B32B2605/006 ,  B32B2605/18 ,  B60J1/00 ,  B60J1/004 ,  B60J1/006 ,  B64C1/12 ,  B64C1/14 ,  B64C1/1492 ,  B64C2001/0072 ,  Y02T50/43 ,  Y10T29/49163 ,  Y10T29/49165 ,  Y10T428/12667 ,  Y10T428/239 ,  Y10T428/24322 ,  Y10T428/24521 ,  Y10T428/25 ,  Y10T428/256 ,  Y10T428/257 ,  Y10T428/26 ,  Y10T428/2982

Abstract: The present disclosure pertains to a window panel for a body structure of a vehicle, especially an airframe of an aircraft or spacecraft, including a first skin which extends over a first side of the panel to form an outer skin of the vehicle body structure; a second skin which extends over a second side of the panel to form an inner skin of the vehicle body structure; and a core, especially a foam core, located between and covered by the first and second skins in a sandwich structure. The window panel includes at least one window aperture formed through the first layer, the core, and the second layer. The core may be confined to or extends over a limited extent, region or part of the panel. Thus, the first skin and/or the second skin may extend over or cover a greater area of the panel than the core.

公开(公告)号：US09682523B2

公开(公告)日：2017-06-20

申请号：US14522776

申请日：2014-10-24

Applicant: Airbus Operations GmbH

Inventor： Alexander Engels ,  Pierre Zahlen ,  Lars Meyer

IPC: B65G7/08 ,  B29D99/00

CPC classification number: B29D99/0014

Abstract: A system for producing a fiber-reinforced composite module, such as a panel module, having an integrated stiffening structure for an aircraft or spacecraft includes a form core assembly station for assembling a plurality of form cores covered with reinforcing fiber layers to constitute at least one stiffening element of the integrated stiffening structure, a form core placement station which receives assembled form cores from the assembly station for placing or depositing the assembled form cores in or on a molding tool, and a turning station for rotating or inverting the assembled form cores. The turning station is configured to convey or transport the assembled form cores from the assembly station to the placement station. The turning station defines a path which is configured to rotate or invert the assembled form cores as they are conveyed or moved to the placement station.

公开(公告)号：US20150064389A1

公开(公告)日：2015-03-05

申请号：US14469146

申请日：2014-08-26

Applicant: AIRBUS OPERATIONS GMBH

Inventor： Pierre C. Zahlen ,  Johannes Born ,  Lars Meyer ,  Gregor Baumbach ,  Claus Hanske ,  Jens Prowe ,  Johan Oentoro ,  M. Ichwan Zuardy ,  Wouter Brok ,  Martin Metten

IPC: B64C1/14 ,  B32B37/16 ,  B32B5/18 ,  B32B3/26 ,  B32B7/04 ,  E06B3/263 ,  B32B37/30

CPC classification number: B64C1/1484 ,  B29C70/023 ,  B29C70/026 ,  B29C70/30 ,  B29C70/545 ,  B29C2793/0018 ,  B29C2793/0081 ,  B29L2007/002 ,  B29L2009/00 ,  B29L2031/005 ,  B29L2031/30 ,  B29L2031/3082 ,  B32B3/02 ,  B32B3/08 ,  B32B3/263 ,  B32B3/266 ,  B32B5/18 ,  B32B5/245 ,  B32B5/26 ,  B32B5/28 ,  B32B7/04 ,  B32B37/16 ,  B32B37/30 ,  B32B38/04 ,  B32B2250/03 ,  B32B2250/24 ,  B32B2250/40 ,  B32B2250/44 ,  B32B2260/00 ,  B32B2266/08 ,  B32B2305/022 ,  B32B2305/07 ,  B32B2605/00 ,  B32B2605/006 ,  B32B2605/18 ,  B60J1/00 ,  B60J1/004 ,  B60J1/006 ,  B64C1/12 ,  B64C1/14 ,  B64C1/1492 ,  B64C2001/0072 ,  Y02T50/43 ,  Y10T29/49163 ,  Y10T29/49165 ,  Y10T428/12667 ,  Y10T428/239 ,  Y10T428/24322 ,  Y10T428/24521 ,  Y10T428/25 ,  Y10T428/256 ,  Y10T428/257 ,  Y10T428/26 ,  Y10T428/2982

Abstract: The present disclosure pertains to a window panel for a body structure of a vehicle, especially an airframe of an aircraft or spacecraft, including a first skin which extends over a first side of the panel to form an outer skin of the vehicle body structure; a second skin which extends over a second side of the panel to form an inner skin of the vehicle body structure; and a core, especially a foam core, located between and covered by the first and second skins in a sandwich structure. The window panel includes at least one window aperture formed through the first layer, the core, and the second layer. The core may be confined to or extends over a limited extent, region or part of the panel. Thus, the first skin and/or the second skin may extend over or cover a greater area of the panel than the core.

Abstract translation: 本公开涉及一种用于车辆的车体结构的窗板，特别是飞机或航天器的机身，包括在面板的第一侧上延伸以形成车身结构的外皮的第一皮肤; 第二皮肤，其在所述面板的第二侧上延伸以形成所述车身结构的内表皮; 以及位于三明治结构中的第一和第二表层之间并覆盖的核心，特别是泡沫芯。 窗口面板包括通过第一层，芯部和第二层形成的至少一个窗孔。 芯可以限制在或限制在面板的有限程度，区域或部分上。 因此，第一皮肤和/或第二皮肤可以延伸超过或覆盖面板的比芯的更大的面积。

公开(公告)号：US20150118001A1

公开(公告)日：2015-04-30

申请号：US14522776

申请日：2014-10-24

Applicant: Airbus Operations GmbH

Inventor： Alexander Engels ,  Pierre Zahlen ,  Lars Meyer

IPC: B65G47/248

CPC classification number: B29D99/0014

Abstract: A system for producing a fibre-reinforced composite module, such as a panel module, having an integrated stiffening structure for an aircraft or spacecraft includes a form core assembly station for assembling a plurality of form cores covered with reinforcing fibre layers to constitute at least one stiffening element of the integrated stiffening structure, a form core placement station which receives assembled form cores from the assembly station for placing or depositing the assembled form cores in or on a moulding tool, and a turning station for rotating or inverting the assembled form cores. The turning station is configured to convey or transport the assembled form cores from the assembly station to the placement station. The turning station defines a path which is configured to rotate or invert the assembled form cores as they are conveyed or moved to the placement station.

Abstract translation: 一种用于制造具有用于飞行器或航天器的集成加强结构的诸如面板模块的纤维增强复合模块的系统包括：形成芯组合站，用于组装覆盖有增强纤维层的多个模芯，以构成至少一个 集成加强结构的加强元件，形成铁芯放置台，其从组装工位接收组装成型的芯，用于将组装的成形芯放置在模制工具中或模具上，以及用于旋转或反转组装的芯的转台。 转台被构造成将组装好的成形芯从组装站传送或运输到放置台。 车削站定义了一个路径，该路径被配置为在组装好的成形铁芯被输送或移动到放置台时旋转或倒转。