公开(公告)号：EP1122052A2

公开(公告)日：2001-08-08

申请号：EP01101296.0

申请日：2001-01-19

申请人： Ishikawajima-Harima Heavy Industries Co., Ltd.

发明人： Nakamura, Takeshi

IPC分类号： B29C65/50

CPC分类号： B29C53/828 ,  B29C31/002 ,  B29C70/32 ,  B29C70/545 ,  B29C2793/00 ,  B29C2793/009 ,  B29L2031/3082

摘要： There is disclosed a method of connecting a plurality of mandrels to one another to constitute an integral mandrel 10, forming a fabric 1 on the surface of the integral mandrel, and infiltrating the formed fabric with matrix. A plurality of products can simultaneously be manufactured, and this can remarkably reduce fiber loss and enhance productivity.

摘要翻译： 公开了一种将多个心轴彼此连接以构成整体的心轴10的方法，在整体式心轴的表面上形成织物1，并将基体上的成形织物浸透。 可以同时制造多个产品，并且可以显着降低纤维损失并提高生产率。

公开(公告)号：EP0261850A2

公开(公告)日：1988-03-30

申请号：EP87308081.6

申请日：1987-09-11

申请人： WESTLAND GROUP PLC

发明人： Barnes, Nicholas Anthony Preston Middle Cottage ,  Damon, John William ,  Duthie, Anthony Craig ,  Heseltine, Mark Julian

IPC分类号： B29C65/00 ,  B29C65/50 ,  B29C65/08

CPC分类号： B29C65/08 ,  B29C65/06 ,  B29C65/4815 ,  B29C65/5057 ,  B29C66/1122 ,  B29C66/3024 ,  B29C66/30341 ,  B29C66/43 ,  B29C66/54 ,  B29C66/71 ,  B29C66/721 ,  B29C66/7212 ,  B29C66/72141 ,  B29C66/72143 ,  B29C66/73921 ,  B29C66/80 ,  B29C66/8167 ,  B29C66/8322 ,  B29C66/847 ,  B29C66/9513 ,  B29C66/9516 ,  B29K2071/00 ,  B29K2105/06 ,  B29K2105/14 ,  B29K2105/206 ,  B29K2277/10 ,  B29K2305/00 ,  B29K2307/00 ,  B29K2307/02 ,  B29K2309/08 ,  B29L2031/3082 ,  B29L2031/3088 ,  B29K2307/04

摘要： In a method of manufacturing a fusion bonded joint between a fibre reinforced thermoplastic resin component having at least 30 per cent of its volume comprised by reinforcing fibres (high fibre loaded) and another fibre reinforced thermoplastic resin component having more or less than 30 per cent of its volume comprised by reinforcing fibres, additional thermoplastic resin is incorporated at the joint interface prior to joining by fusion bonding.
The additional thermoplastic resin is preferably consolidated in those surfaces of the high fibre loaded component which are to be joined to other components before fusion bonding takes place.
A preferred method of fusion bonding is by ultrasonic welding.
A mesh comprising metal strands extending at least across the joint may be incorporated at the interface of a joint between two components to provide increased joint strength and electrical conductivity across the joint in the case of carbon fibre reinforced components.

摘要翻译： 在制造纤维增强热塑性树脂成分的纤维增强热塑性树脂成分的方法中，所述纤维增强热塑性树脂成分的至少30％的体积由增强纤维（高纤维负载）和另外的纤维增强的热塑性树脂成分组成， 其通过增强纤维的体积，另外的热塑性树脂通过熔融接合在接合之前被结合在接合界面处。 另外的热塑性树脂优选被固结在高纤维负载的组分的那些表面中，在发生熔融粘合之前要与其它组分接合。 熔接的优选方法是通过超声波焊接。 包括至少横过接头延伸的金属丝线的网可以结合在两个部件之间的接头的界面处，以在碳纤维增强部件的情况下提供增加的接头强度和接头的电导率。

公开(公告)号：EP3372395A2

公开(公告)日：2018-09-12

申请号：EP17206550.0

申请日：2017-12-11

申请人： The Boeing Company

发明人： PHAM, Doan Dinh ,  HARLOW, William Brent

IPC分类号： B29D99/00 ,  B29C70/44 ,  B29C70/02 ,  B21D47/00 ,  B29D24/00 ,  B32B3/12 ,  B29L31/60 ,  B29C70/08 ,  B33Y80/00 ,  B33Y10/00 ,  B22F3/105

CPC分类号： B64C3/22 ,  B21D47/00 ,  B22F3/1055 ,  B29C64/10 ,  B29C64/106 ,  B29C70/023 ,  B29C70/026 ,  B29C70/086 ,  B29C70/443 ,  B29D24/005 ,  B29D99/0014 ,  B29D99/0089 ,  B29K2063/00 ,  B29K2105/06 ,  B29L2031/3082 ,  B29L2031/3085 ,  B29L2031/60 ,  B29L2031/608 ,  B32B3/12 ,  B33Y10/00 ,  B33Y80/00 ,  D06M15/55 ,  D06M2101/40

摘要： A component, including a part, comprising a honeycomb-like structure formed from at least a seamless resin-infused fiber composite material. The honeycomb-like structure includes a first plurality of honeycomb-like cells, and a second plurality of honeycomb-like cells, different than the first plurality of honeycomb-like cells.

公开(公告)号：EP2540476B1

公开(公告)日：2018-08-29

申请号：EP12173577.3

申请日：2012-06-26

申请人： Airbus Operations GmbH

发明人： Goehlich, Robert Alexander ,  Sander, Malte

IPC分类号： B29C65/06 ,  B29K105/06

CPC分类号： B29C65/0681 ,  B23K20/122 ,  B23K20/1255 ,  B23K20/128 ,  B23K2101/08 ,  B23K2101/18 ,  B23K2103/16 ,  B29C35/02 ,  B29C65/028 ,  B29C65/06 ,  B29C65/0672 ,  B29C65/086 ,  B29C65/4815 ,  B29C65/488 ,  B29C65/72 ,  B29C66/0242 ,  B29C66/0382 ,  B29C66/1142 ,  B29C66/30341 ,  B29C66/43 ,  B29C66/721 ,  B29C66/7212 ,  B29C66/72141 ,  B29C66/72143 ,  B29C66/73921 ,  B29C66/7394 ,  B29C66/836 ,  B29C66/9261 ,  B29K2101/12 ,  B29K2105/08 ,  B29K2105/256 ,  B29L2031/3082 ,  Y10T428/24479 ,  B29K2307/04 ,  B29K2309/08 ,  B29K2277/10

摘要： Disclosed is a method for producing a bonded joint between fiber-reinforced thermoplastic parts (2, 4) to be joined, in which fiber-containing plastic material (22) is mixed into the joining zone while friction stir welding the parts (2, 4) to be joined in the form of a butt joint, as well as a device for carrying out such a method and a thusly joined component.

公开(公告)号：EP3363622A2

公开(公告)日：2018-08-22

申请号：EP18160977.7

申请日：2012-01-26

申请人： The Boeing Company

发明人： KAMARAJ, Malmurugan ,  MATHESON, Donald Paul

IPC分类号： B29C70/34 ,  B29L31/00 ,  B29L31/30

CPC分类号： B64C1/00 ,  B29C70/34 ,  B29L2031/008 ,  B29L2031/3082 ,  Y02T50/43 ,  Y10T29/49616 ,  Y10T29/49622 ,  Y10T29/49801 ,  Y10T428/24008 ,  Y10T428/24174 ,  Y10T428/24182 ,  Y10T428/24785

摘要： An element comprising a composite elongate member (2302), a channel (2328), and a number of composite structures (2200). The composite elongate member has a side (2305) configured for attachment to a surface (2326) of a structure (2304). The channel is on the side and extends along a length of the composite elongate member. The number of composite structures is configured for placement in the channel and configured to attach a portion of the side of the composite elongate member to the structure. A composite structure in the number of composite structures comprises layers (2332) having different orientations selected to increase a capacity of the composite elongate member to withstand forces that pull the composite elongate member away from the structure.

公开(公告)号：EP2433783B1

公开(公告)日：2018-08-22

申请号：EP11007753.4

申请日：2011-09-23

申请人： Aumann Beelen GmbH

发明人： Düker, Martin ,  Bühlmeyer, Robert

IPC分类号： B29C70/38 ,  B29C33/26 ,  B29C70/32 ,  B29L31/30

CPC分类号： B29C70/38 ,  B29C33/26 ,  B29C70/323 ,  B29L2031/3082

公开(公告)号：EP3243640A3

公开(公告)日：2018-01-24

申请号：EP17155243.3

申请日：2017-02-08

申请人： Subaru Corporation

发明人： Takahashi, Kohei

IPC分类号： B29C70/42 ,  B29C33/42 ,  B29C70/34 ,  B29C43/02 ,  B29C33/00

CPC分类号： G01N29/2418 ,  B29C33/42 ,  B29C43/021 ,  B29C43/58 ,  B29C59/022 ,  B29C59/026 ,  B29C65/4855 ,  B29C70/34 ,  B29C70/42 ,  B29C2033/0094 ,  B29C2043/5808 ,  B29K2105/06 ,  B29K2995/0001 ,  B29L2031/3076 ,  B29L2031/3082 ,  B32B5/10 ,  B32B7/12 ,  B32B27/00 ,  B32B37/12 ,  B32B2307/10 ,  B32B2605/18 ,  B64C3/18 ,  G01N29/043 ,  Y02T50/43

摘要： According to one embodiment, a composite material molding jig (1) includes a rigid portion (2) and a convex portion (3) for forming a groove (70) for inserting an optical fiber sensor (10). The rigid portion (2) has a surface for laminating prepreg sheets (S1, S2). The convex portion (3) is formed in a surface side (2A) of the rigid portion (2). Further, according to one embodiment, a composite material molding method is a method for molding a composite material (30, 40), on which the groove (70) for inserting the optical fiber sensor (10) has been formed, by heating and curing a laminated body (20) of the prepreg sheets (S1, S2) laminated on the above-mentioned composite material molding jig (1).

摘要翻译： 根据一个实施例，复合材料模制夹具（1）包括用于形成用于插入光纤传感器（10）的凹槽（70）的刚性部分（2）和凸起部分（3）。 刚性部分（2）具有用于层压预浸渍片材（S1，S2）的表面。 凸部（3）形成在刚性部（2）的表面侧（2A）。 此外，根据一个实施例，复合材料模制方法是用于模制复合材料（30,40）的方法，通过加热和固化在其上形成用于插入光纤传感器（10）的凹槽（70） 在上述复合材料成型用夹具（1）上层叠的半固化片（S1，S2）的层叠体（20）。

公开(公告)号：EP2842728B1

公开(公告)日：2018-01-10

申请号：EP13182087.0

申请日：2013-08-28

申请人： Airbus Operations GmbH

发明人： Zuardy, Ichwan ,  Grase, Karim ,  Jeßrang, Mathias ,  Röhrig, Martin

IPC分类号： B29K105/00 ,  C08J5/04 ,  B29L31/30 ,  B29K105/08 ,  B29C70/44 ,  B29D99/00 ,  B29C33/34 ,  B29K105/04

CPC分类号： B29C70/345 ,  B29C33/34 ,  B29C70/443 ,  B29D99/0021 ,  B29K2105/04 ,  B29K2105/0872 ,  B29K2105/256 ,  B29L2031/3082 ,  C08J5/04 ,  C08J2300/00

摘要： The invention provides a method of producing a composite panel member (2), and especially a composite panel member (2) having a foam core sandwich structure for an airframe of an aircraft or spacecraft, the method comprising: providing one or more fibre reinforcement layer (L) in a panel moulding tool (3); moving or transferring the moulding tool (3) to an infusion station (S 1 ) that is pre-heated to an infusion temperature (T 1 ) and infusing the fibre reinforcement layer (L) in the moulding tool (3) with a polymer resin; moving or transferring the moulding tool (3) to a curing station (S 2 ) that is pre-heated to a curing temperature (T 2 ) and curing the resin-infused fibre reinforcement layer(s) in the moulding tool (3) to form a composite panel member (2); and moving or transferring the moulding tool (3) to a cooling station (S 3 ) that is provided at a cooling temperature (T 3 ) and cooling the composite panel member (2) in the moulding tool (3). In addition, the invention provides a corresponding system (1) for producing a composite panel member (2).

公开(公告)号：EP3261834A1

公开(公告)日：2018-01-03

申请号：EP15883635.3

申请日：2015-12-21

申请人： Sikorsky Aircraft Corporation

发明人： DEW, Nathaniel ,  DENAVIT, Paul H. ,  GARHART, Jonathan K. ,  CAWTHRA, Neil W.

IPC分类号： B32B3/12

CPC分类号： B29C73/10 ,  B29C33/0016 ,  B29C35/02 ,  B29C35/0227 ,  B29C37/0075 ,  B29C70/00 ,  B29C73/04 ,  B29C2035/0827 ,  B29C2791/001 ,  B29K2105/0872 ,  B29K2307/04 ,  B29L2031/3082

摘要： A method of repairing a composite structure or forming a component of a part is provided. The method includes releasably laying up of a first member that is curable at a first temperature at or above a constrained temperature limit of the composite structure or part, releasably laying up of a second member on the first member that is curable at a second temperature below the constrained temperature limit, curing the second member into a scaffold at the second temperature at the composite structure or part, transferring the first member and the scaffold remotely from the composite structure or part for first member curing and removing the cured first member from the scaffold for bonding of the cured first member to the composite structure or part.

公开(公告)号：EP2440451A4

公开(公告)日：2017-12-20

申请号：EP09845908

申请日：2009-06-11

申请人： SAAB AB

发明人： HALLANDER PER ,  PETERSSON MIKAEL ,  WEIDMANN BJÖRN ,  GRANKÄLL TOMMY ,  STRINDBERG GÖTE ,  NORDIN PONTUS

IPC分类号： B64C1/00 ,  B29C65/48 ,  B29C65/52 ,  B64C3/20 ,  B64C3/26 ,  B64C7/00 ,  B82B1/00

CPC分类号： B64C1/00 ,  B29C65/4875 ,  B29C65/488 ,  B29C65/5057 ,  B29C66/112 ,  B29C66/131 ,  B29C66/543 ,  B29C66/71 ,  B29C66/721 ,  B29C66/7212 ,  B29C66/72141 ,  B29C66/72143 ,  B29C66/73711 ,  B29K2105/06 ,  B29K2105/167 ,  B29K2307/00 ,  B29L2031/3076 ,  B29L2031/3082 ,  B29L2031/3085 ,  B64C2001/0072 ,  B82Y30/00 ,  Y02T50/433 ,  Y10T428/24124 ,  Y10T428/24488 ,  Y10T428/249921 ,  Y10T428/31511 ,  B29K2307/04 ,  B29K2063/00

摘要： An aircraft structure including structural composite parts assembled together to form the aircraft structure. A bonding interlayer material bonds the structural composite parts to each other. The bonding interlayer material includes a nanostructure enhanced material. A method of producing an aircraft structure of assembled structural composite parts, being cured or semi-cured before assembly.