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公开(公告)号：US10029426B2
公开(公告)日：2018-07-24
申请号：US14809784
申请日：2015-07-27
Applicant: Airbus Operations GmbH
Inventor： Mathias Jessrang
Abstract: A device for the manufacture of a fiber-reinforced thermoplastic composite module from a multiplicity of module components, which are continuously moved in the feed direction and are connected together section-by-section. The device includes a tool mold configured and arranged to be continuously traversed in the feed direction for purposes of positioning module components relative to one another. A pressure application head is configured and arranged to be traversed in the feed direction and in the counter-direction for purposes of connecting the module components. The pressure application head is configured and arranged to move at the same speed and in the same direction as the continuously moving tool mold, and then in an opposite direction, in order to connect to each section of the fiber reinforced thermoplastic composite during reciprocal movement.
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公开(公告)号：US10059066B2
公开(公告)日：2018-08-28
申请号：US14463086
申请日：2014-08-19
Applicant: Airbus Operations GmbH
Inventor： Ichwan Zuardy , Karim Grase , Mathias Jessrang , Martin Roehrig
IPC: B29C70/34 , B29C70/44 , B29C33/34 , B29D99/00 , C08J5/04 , B29K105/04 , B29K105/08 , B29K105/00 , B29L31/30
CPC classification number: B29C70/345 , B29C33/34 , B29C70/443 , B29D99/0021 , B29K2105/04 , B29K2105/0872 , B29K2105/256 , B29L2031/3082 , C08J5/04 , C08J2300/00
Abstract: A method of producing a composite panel member, especially a composite panel member having a foam core sandwich structure for an airframe of an aircraft or spacecraft, including: providing at least one fiber reinforcement layer in a panel molding tool; moving or transferring the molding tool to an infusion station that is pre-heated to an infusion temperature and infusing the fiber reinforcement layer in the molding tool with a polymer resin; moving or transferring the molding tool to a curing station that is pre-heated to a curing temperature and curing the at least one resin-infused fiber reinforcement layer in the molding tool to form a composite panel member; and moving or transferring the molding tool to a cooling station that is provided at a cooling temperature and cooling the composite panel member in the molding tool.
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Patent Agency Ranking
3.发明申请公开(公告)号：US20150328829A1
公开(公告)日：2015-11-19
申请号：US14809784
申请日：2015-07-27
Applicant: Airbus Operations GmbH
Inventor： Mathias Jessrang
CPC classification number: B29C70/386 , B29C43/06 , B29C65/18 , B29C65/32 , B29C66/0242 , B29C66/0342 , B29C66/112 , B29C66/131 , B29C66/301 , B29C66/3452 , B29C66/532 , B29C66/61 , B29C66/721 , B29C66/7212 , B29C66/7392 , B29C66/73921 , B29C66/81422 , B29C66/81423 , B29C66/81431 , B29C66/8242 , B29C66/83541 , B29C66/8432 , B29L2031/003 , B29L2031/3082 , Y10T156/10 , B29K2307/04
Abstract: A device for the manufacture of a fiber-reinforced thermoplastic composite module from a multiplicity of module components, which are continuously moved in the feed direction and are connected together section-by-section. The device includes a tool mold configured and arranged to be continuously traversed in the feed direction for purposes of positioning module components relative to one another. A pressure application head is configured and arranged to be traversed in the feed direction and in the counter-direction for purposes of connecting the module components. The pressure application head is configured and arranged to move at the same speed and in the same direction as the continuously moving tool mold, and then in an opposite direction, in order to connect to each section of the fiber reinforced thermoplastic composite during reciprocal movement.
Abstract translation: 一种用于从多个模块部件制造纤维增强热塑性复合材料模块的装置，它们沿进给方向连续移动并且逐段连接。 该装置包括工具模具，其被配置和布置成在进给方向上连续地横移，以便于相对于彼此定位模块部件。 为了连接模块部件，压力施加头构造和布置成沿进给方向和相对方向横移。 压力施加头构造和布置成以与连续移动的工具模具相同的速度和相同的方向移动，然后在相反的方向上移动，以便在往复运动期间连接到纤维增强热塑性复合材料的每个部分。
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4.发明授权公开(公告)号：US09834298B2
公开(公告)日：2017-12-05
申请号：US14491251
申请日：2014-09-19
Applicant: Airbus Operations GmbH
Inventor： M. Ichwan Zuardy , Karim Grase , Carsten Rowedder , Claas De Jong , Markus Mueller , Mathias Jessrang
IPC: B64C1/10
CPC classification number: B64C1/10
Abstract: A pressure bulkhead of an aircraft with a fuselage shell and a pressure bulkhead disposed therein preferably in the rear region for forming a fuselage-internal pressure region, which pressure bulkhead is attached on the edge in the interior of the fuselage shell, wherein the pressure bulkhead has a lenticular cross-section and a sandwich construction that comprises a foam core sandwiched between two opposing exterior shells.
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公开(公告)号：US20150080499A1
公开(公告)日：2015-03-19
申请号：US14463086
申请日：2014-08-19
Applicant: Airbus Operations GmbH
Inventor： Ichwan Zuardy , Karim Grase , Mathias Jessrang , Martin Roehrig
CPC classification number: B29C70/345 , B29C33/34 , B29C70/443 , B29D99/0021 , B29K2105/04 , B29K2105/0872 , B29K2105/256 , B29L2031/3082 , C08J5/04 , C08J2300/00
Abstract: A method of producing a composite panel member, especially a composite panel member having a foam core sandwich structure for an airframe of an aircraft or spacecraft, including: providing at least one fiber reinforcement layer in a panel molding tool; moving or transferring the molding tool to an infusion station that is pre-heated to an infusion temperature and infusing the fiber reinforcement layer in the molding tool with a polymer resin; moving or transferring the molding tool to a curing station that is pre-heated to a curing temperature and curing the at least one resin-infused fiber reinforcement layer in the molding tool to form a composite panel member; and moving or transferring the molding tool to a cooling station that is provided at a cooling temperature and cooling the composite panel member in the molding tool.
Abstract translation: 一种制造复合面板构件的方法，特别是具有用于飞机或航天器的机身的泡沫芯夹层结构的复合面板构件，包括：在面板模制工具中提供至少一个纤维增强层; 将模具移动或转移到预热到输注温度的浸渍站，并用聚合物树脂将模制工具中的纤维增强层注入; 将模具移动或转移到预加热到固化温度的固化站，并固化模制工具中的至少一个注入树脂的纤维增强层以形成复合板构件; 以及将成型工具移动或转移到设置在冷却温度下的冷却站，并且在模制工具中冷却复合面板构件。
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6.发明申请FIBER COMPOSITE COMPONENT WITH AN ELECTRICALLY CONDUCTIVE FIBER MATERIAL FOR REINFORCEMENT AS WELL AS A DEVICE FOR ITS MANUFACTURE 审中-公开具有电导电纤维材料的纤维复合组件，作为其制造设备的加固公开(公告)号：US20160075102A1
公开(公告)日：2016-03-17
申请号：US14851028
申请日：2015-09-11
Applicant: Airbus Operations GmbH
Inventor： Mathias Jessrang , Johannes Rehbein
CPC classification number: B32B5/26 , B32B5/022 , B32B5/024 , B32B5/026 , B32B2260/021 , B32B2260/023 , B32B2260/046 , B32B2262/106 , B32B2305/076 , B32B2307/202 , B32B2605/18 , D04H1/46 , D04H11/08
Abstract: A fiber composite component as a structural component of an aircraft, encompasses a mat-shaped, electrically conductive fiber material embedded in several layers into a synthetic resin matrix, wherein individual fibers protrude as free fiber ends from the flat plane of the mat-shaped fiber material, so as to establish an electrical bridge connection between adjacent layers of the fiber material through an interspersed synthetic resin layer. A device for manufacturing such a fiber material is also described.
Abstract translation: 作为飞行器的结构部件的纤维复合材料成分包含嵌入合成树脂基体中的几层的垫状的导电性纤维材料，其中各纤维从垫状纤维的平面伸出为自由纤维端 材料，以通过散布的合成树脂层在纤维材料的相邻层之间建立电桥连接。 还描述了用于制造这种纤维材料的装置。
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7.发明申请PRESSURE FUSELAGE OF AN AIRCRAFT WITH A FUSELAGE SHELL AND A PRESSURE BULKHEAD DISPOSED THEREIN 有权具有熔断壳的飞机的压力熔断器和其中的压力容器公开(公告)号：US20150008285A1
公开(公告)日：2015-01-08
申请号：US14491251
申请日：2014-09-19
Applicant: AIRBUS OPERATIONS GMBH
Inventor： M. Ichwan Zuardy , Karim Grase , Carsten Rowedder , Claas DeJong , Markus Mueller , Mathias Jessrang
IPC: B64C1/10
CPC classification number: B64C1/10
Abstract: A pressure bulkhead of an aircraft with a fuselage shell and a pressure bulkhead disposed therein preferably in the rear region for forming a fuselage-internal pressure region, which pressure bulkhead is attached on the edge in the interior of the fuselage shell, wherein the pressure bulkhead has a lenticular cross-section and a sandwich construction that comprises a foam core sandwiched between two opposing exterior shells.
Abstract translation: 具有机身壳体和压力舱壁的飞机的压力舱壁优选地设置在后部区域中，用于形成机身内部压力区域，该压力舱壁附接在机身壳体内部的边缘上，其中压力舱壁 具有透镜状横截面和夹层结构，其包括夹在两个相对的外壳之间的泡沫芯。
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