公开(公告)号：US11745848B2

公开(公告)日：2023-09-05

申请号：US16999198

申请日：2020-08-21

Applicant: AIRBUS OPERATIONS S.L.

Inventor： Raul Olmo Mora ,  Tamara Blanco Varela

IPC: B64C1/40 ,  B29C70/22 ,  B32B5/02 ,  G10K11/168 ,  B29K307/04 ,  B29K309/08 ,  B64C1/00

CPC classification number: B64C1/40 ,  B29C70/228 ,  B32B5/024 ,  G10K11/168 ,  B29K2307/04 ,  B29K2309/08 ,  B32B2250/03 ,  B32B2250/05 ,  B32B2262/101 ,  B32B2262/106 ,  B32B2307/102 ,  B32B2605/18 ,  B64C2001/0072

Abstract: A sound wave absorbing laminate composite material structure for an aircraft including stacked plies of a hybrid composite material, wherein each of the hybrid composite material plies includes first polymer material tows parallel to a warp direction, second polymer material tows parallel to a weft direction, and sound absorbent material tows parallel to the warp direction, wherein the first and second polymer material tows carbon or glass fiber reinforcing polymer.

公开(公告)号：US20140011006A1

公开(公告)日：2014-01-09

申请号：US13929166

申请日：2013-06-27

Applicant: Airbus Operations, S.L.

Inventor： Enrique Guinaldo Fernandez ,  Tamara Blanco Varela

IPC: B64C1/40

CPC classification number: B64C1/40 ,  B32B5/022 ,  B32B5/024 ,  B32B5/12 ,  B32B5/26 ,  B32B7/02 ,  B32B7/045 ,  B32B7/12 ,  B32B2260/023 ,  B32B2260/046 ,  B32B2262/101 ,  B32B2262/106 ,  B32B2307/102 ,  B32B2307/202 ,  B32B2307/558 ,  B32B2605/18 ,  Y10T428/24851 ,  Y10T428/24995 ,  Y10T428/249951

Abstract: Provided is a structure of composite material, comprising a continuous first layer of composite material, a second layer of viscoelastic material, and a continuous impact-protection third layer. The first layer is formed by structural components in the form of a matrix and fibers. The second layer of viscoelastic material is added on top of the first layer and said second layer can be continuous or non-continuous. If a non-continuous second layer is used, elongate, circular or square cavities are arranged inside the layer. Optionally, reinforcements comprising carbon nanofibers or nanotubes are provided in either of the first and second layers. The third layer of impact-protection material is added in a continuous manner on top of the second layer, the third layer forming the outermost layer of the composite material. In addition, this third layer is electrically conductive. The composite material has noise attenuation,

Abstract translation: 提供了复合材料的结构，其包括连续的第一复合材料层，第二层粘弹性材料和连续冲击保护第三层。 第一层由基质和纤维形式的结构组分形成。 第二层粘弹性材料被添加在第一层的顶部上，而第二层可以是连续的或不连续的。 如果使用非连续的第二层，则在层内布置细长的圆形或方形空腔。 任选地，包含碳纳米纤维或纳米管的增强件设置在第一层和第二层中的任一层中。 第三层冲击保护材料以连续的方式添加到第二层的顶部，第三层形成复合材料的最外层。 另外，该第三层是导电的。 复合材料具有噪声衰减，

公开(公告)号：US20230094636A1

公开(公告)日：2023-03-30

申请号：US17946474

申请日：2022-09-16

Applicant: Airbus Operations, S.L. ,  Airbus Operations GmbH ,  Airbus (S.A.S.)

Inventor： Blanka Lenczowski ,  Tamara Blanco Varela ,  Peter Linde

IPC: H01M8/0228 ,  H01M8/0226 ,  H01M8/0213 ,  H01M8/0221 ,  H01M8/026 ,  H01M8/0263 ,  H01M8/1004 ,  H01M8/241 ,  H01M8/2484 ,  B32B3/30 ,  B32B5/12 ,  B32B5/26 ,  B64D27/24

Abstract: A bipolar plate for a proton exchange membrane fuel cell includes a laminate of carbon fiber reinforced plastic (CFRP) with a first outer ply. The CFRP includes a resin and carbon fibers. The first outer ply is arranged at a first lateral surface of the laminate, wherein the laminate includes a first plurality of carbon nanotubes (CNTs). The first outer ply includes a first groove, wherein the first groove is configured to define a first gas diffusion channel. At least some of the first plurality of CNTs extend through the first outer ply in a direction transversely to the first lateral surface of the laminate.

公开(公告)号：US10773824B2

公开(公告)日：2020-09-15

申请号：US15817826

申请日：2017-11-20

Applicant: Airbus Operations, S.L.

Inventor： Tamara Blanco Varela ,  José Sanchez Gomez ,  Leire Segura Martinez De Ilarduya ,  Mariano Morales Monge

IPC: B64D45/02 ,  B29C70/88 ,  B32B15/02 ,  H01M2/02 ,  B32B7/06 ,  B32B15/08 ,  B32B15/14 ,  B32B15/00 ,  B32B27/00 ,  B32B9/04 ,  B32B7/02 ,  B32B5/00 ,  B32B9/00 ,  B32B3/26 ,  B32B27/06 ,  B32B7/04 ,  B32B27/28 ,  B32B7/10 ,  B32B15/04 ,  B32B5/02 ,  B32B7/00 ,  B32B15/20

Abstract: A structural composite component, in particular for an aircraft or spacecraft, includes: a lightning strike protection layer; and a composite battery including a cathode layer and a separation layer, wherein the lightning strike protection layer is formed integrated with the cathode layer, and wherein the separation layer is configured for providing acoustic damping, and/or fire barrier, and/or impact resistance to the structural composite component. A method for configuring such a structural composite component; and an aircraft or spacecraft including such a structural composite component are also described.

公开(公告)号：US11466136B2

公开(公告)日：2022-10-11

申请号：US16494718

申请日：2018-03-16

Applicant: Airbus Operations S.L. ,  Consiglio Nazionale Delle Ricerche

Inventor： Tamara Blanco Varela ,  Jose Sánchez Gómez ,  Silvia Lazcano Ureña ,  Vincenzo Palermo ,  Emanuele Treossi ,  Nicola Mirotta

IPC: B32B5/02 ,  B32B5/16 ,  B32B5/26 ,  B32B5/30 ,  B32B27/12 ,  B32B27/14 ,  B32B27/18 ,  B32B27/38 ,  D06N3/12 ,  C08J7/06 ,  C08J7/04 ,  C08J3/20 ,  D06N3/00 ,  C08J7/043 ,  C08J7/046 ,  C08J7/048 ,  C08K3/04

Abstract: A multifunctional diffusion barrier comprising at least one organic polymer and a 2D graphene or 2D graphene derivative material and a method for preparing the multifunctional barrier. The multifunctional diffusion barrier can be used as a liquid and/or gas barrier, or as structural material, or as sealing material, or as a self-cleaning material or as protective material against UV radiation in aeronautical, automotive, marine or building field. The multifunctional diffusion barrier is suitable in producing parts of aircraft such as a fuel tank, a fuel tank conduit and a gasket.

公开(公告)号：US20180155055A1

公开(公告)日：2018-06-07

申请号：US15817826

申请日：2017-11-20

Applicant: Airbus Operations, S.L.

Inventor： Tamara Blanco Varela ,  José Sanchez Gomez ,  Leire Segura Martinez De Ilarduya ,  Mariano Morales Monge

IPC: B64D45/02 ,  B29C70/88 ,  B32B15/02 ,  H01M2/02 ,  B32B7/06 ,  B32B15/08 ,  B32B15/14

CPC classification number: B64D45/02 ,  B29C70/885 ,  B32B3/26 ,  B32B5/00 ,  B32B5/02 ,  B32B7/00 ,  B32B7/02 ,  B32B7/04 ,  B32B7/06 ,  B32B7/10 ,  B32B9/00 ,  B32B9/04 ,  B32B15/00 ,  B32B15/02 ,  B32B15/04 ,  B32B15/08 ,  B32B15/14 ,  B32B15/20 ,  B32B27/00 ,  B32B27/06 ,  B32B27/28 ,  B32B2250/00 ,  B32B2262/00 ,  B32B2262/106 ,  B32B2307/10 ,  B32B2307/102 ,  B32B2307/20 ,  B32B2307/202 ,  B32B2307/30 ,  B32B2307/3065 ,  B32B2307/50 ,  B32B2307/558 ,  B32B2307/56 ,  B32B2307/732 ,  B32B2457/00 ,  B32B2457/10 ,  B32B2571/00 ,  B32B2605/00 ,  B32B2605/18 ,  H01M2/0267 ,  H01M2/0295

Abstract: A structural composite component, in particular for an aircraft or spacecraft, includes: a lightning strike protection layer; and a composite battery including a cathode layer and a separation layer, wherein the lightning strike protection layer is formed integrated with the cathode layer, and wherein the separation layer is configured for providing acoustic damping, and/or fire barrier, and/or impact resistance to the structural composite component. A method for configuring such a structural composite component; and an aircraft or spacecraft including such a structural composite component are also described.

公开(公告)号：US09751612B2

公开(公告)日：2017-09-05

申请号：US13929166

申请日：2013-06-27

Applicant: Airbus Operations, S.L.

Inventor： Enrique Guinaldo Fernandez ,  Tamara Blanco Varela

IPC: B32B37/00 ,  B29C65/00 ,  F41H1/00 ,  B32B3/00 ,  B32B5/00 ,  B32B7/00 ,  B32B15/00 ,  B32B27/00 ,  B64C1/00 ,  B64C3/00 ,  B64C1/40 ,  B32B5/26 ,  B32B7/02 ,  B32B7/04 ,  B32B5/02 ,  B32B5/12 ,  B32B7/12

CPC classification number: B64C1/40 ,  B32B5/022 ,  B32B5/024 ,  B32B5/12 ,  B32B5/26 ,  B32B7/02 ,  B32B7/045 ,  B32B7/12 ,  B32B2260/023 ,  B32B2260/046 ,  B32B2262/101 ,  B32B2262/106 ,  B32B2307/102 ,  B32B2307/202 ,  B32B2307/558 ,  B32B2605/18 ,  Y10T428/24851 ,  Y10T428/24995 ,  Y10T428/249951

Abstract: Provided is a structure of composite material, comprising a continuous first layer of composite material, a second layer of viscoelastic material, and a continuous impact-protection third layer. The first layer is formed by structural components in the form of a matrix and fibers. The second layer of viscoelastic material is added on top of the first layer and said second layer can be continuous or non-continuous. If a non-continuous second layer is used, elongate, circular or square cavities are arranged inside the layer. Optionally, reinforcements comprising carbon nanofibers or nanotubes are provided in either of the first and second layers. The third layer of impact-protection material is added in a continuous manner on top of the second layer, the third layer forming the outermost layer of the composite material. In addition, this third layer is electrically conductive. The composite material has noise attenuation, impact resistance and electric conductivity properties.