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。

公开(公告)号：US10730243B2

公开(公告)日：2020-08-04

申请号：US15603010

申请日：2017-05-23

Applicant: Airbus Operations GmbH

Inventor： Joachim Piepenbrock ,  Alexander Engels ,  Gregor Graßl ,  Karsten Gensicke ,  Klaus Apel

IPC: B29C65/78 ,  B29C65/00 ,  B25J13/08 ,  B25J15/00 ,  B25J15/06 ,  B29C65/48 ,  B25J15/02 ,  B29C31/00 ,  B64F5/10 ,  B29C65/56 ,  F16B11/00 ,  B29K307/04 ,  B29K309/08

Abstract: A system for handling a first component includes: a main-device and a module-device, the module-device having a pressing section arranged to form an outer surface of the module-device, the module-device configured to releasably receive the first component, such that a connection section of the first component is attachable to the pressing section of the module-device. The module-device is releasably connected to a second component, wherein the main-device includes a grabbing unit adapted for releasably connecting the module-device, such that the pressing section is arranged to form a first outer surface section of the main-device, and wherein the main-device includes a connector for connecting to a handling-unit for arranging the main-device at the second component, such that the connection section of the first component, if attached to the pressing section of the module-device, is at least indirectly attachable to a front surface of the second component.

公开(公告)号：US20180155012A1

公开(公告)日：2018-06-07

申请号：US15814928

申请日：2017-11-16

Applicant: Airbus Operations GmbH

Inventor： Thomas Hoffmeister ,  Joachim Piepenbrock ,  Alexander Engels

IPC: B64C21/10 ,  F16B33/00 ,  B05D3/12 ,  B05D5/02

CPC classification number: B64C21/10 ,  B05D3/12 ,  B05D5/02 ,  B05D7/5483 ,  B29C37/005 ,  B29C73/02 ,  B29C73/04 ,  B64C1/00 ,  B64C2001/0072 ,  C09K3/1012 ,  F16B33/004

Abstract: A method for producing a smooth aerodynamic surface of an aircraft component is depicted and described. The method includes: provision of an aircraft component with an aerodynamic surface, which has an uneven section, introduction of a liquid or viscous, uncured sealing compound into the uneven section, introduction of a solid, precured sealing body into the uneven section in such a way that the sealing body presses into the sealing compound until the sealing compound at least partially surrounds the sealing body, curing of the sealing compound.

公开(公告)号：US09511337B2

公开(公告)日：2016-12-06

申请号：US14730588

申请日：2015-06-04

Applicant: Airbus Operations GmbH

Inventor： Alexander Engels ,  Tassilo Witte

IPC: C08J11/04 ,  B01J6/00 ,  B29B17/02 ,  C01B31/02 ,  C03C3/04 ,  C08J11/12 ,  B29B17/00 ,  B29K105/06 ,  B29B17/04 ,  B29K77/00 ,  B29L9/00 ,  B29L31/00

CPC classification number: B01J6/008 ,  B29B17/02 ,  B29B17/04 ,  B29B2017/0496 ,  B29K2077/10 ,  B29K2105/06 ,  B29L2009/00 ,  B29L2031/772 ,  C01B32/05 ,  C03C3/04 ,  C08J11/12 ,  C08J2377/10 ,  Y02W30/622 ,  Y02W30/625

Abstract: Disclosed is a method and an apparatus for extracting a long fiber, and in particular an endless fiber, embedded in a resin matrix forming a wound composite part, wherein the fiber is extracted as one single part by unwinding after a pyrolisis treatment for a decomposition of the matrix.

Abstract translation: 公开了一种用于提取长纤维，特别是环状纤维的方法和装置，其包含在形成缠绕的复合部件的树脂基体中，其中纤维在用于分解的热解法处理之后通过放卷来提取为单一部分 矩阵。

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.