公开(公告)号：US08751197B2

公开(公告)日：2014-06-10

申请号：US11796744

申请日：2007-04-27

Applicant: Raúl Burgos Gallego ,  José Villarrubia Cortés

Inventor： Raúl Burgos Gallego ,  José Villarrubia Cortés

IPC: G06F17/50

CPC classification number: G06F17/50 ,  G06F2217/12 ,  G06F2217/42 ,  G06F2217/44 ,  Y02P90/265

Abstract: The invention relates to a method for designing a composite material part with a curved surface (65) to which a plurality of stiffening elements will be joined, in which the design of a 3D fabric model comprises the following steps: generating a planar surface (63) developed in 2D of the surface (65) of the curved part in 3D as well as the same geometric references (71) in 2D as the references (51) of the surface in 3D; associating the surface (63) developed in 2D and the surface (65) in 3D as well as their geometric references (71, 51), such that any action in one of them is reflected in the other; initially computing the fabric model in the surface (63) developed in 2D; carrying out any subsequent modification of the fabric model either in the surface (63) developed in 2D or in the surface (65) in 3D.

Abstract translation: 本发明涉及一种用于设计具有弯曲表面（65）的复合材料部件的方法，多个加强元件将被连接到该弯曲表面，其中3D织物模型的设计包括以下步骤：产生平面（63） ）在3D中的弯曲部分的表面（65）的2D中开发，以及2D中与3D表面的参考（51）相同的几何参考（71）; 将以2D形成的表面（63）和3D的表面（65）以及它们的几何参考（71,51）相关联，使得其中一个中的任何动作反映在另一个中; 最初计算出在2D中开发的表面（63）中的织物模型; 在2D中或在3D表面（65）中显影的表面（63）中进行织物模型的任何后续修改。

公开(公告)号：US08733689B2

公开(公告)日：2014-05-27

申请号：US12882251

申请日：2010-09-15

Applicant: Vicente Martínez Valdegrama ,  José Luis Lozano García ,  Gonzalo Ramírez Blanco

Inventor： Vicente Martínez Valdegrama ,  José Luis Lozano García ,  Gonzalo Ramírez Blanco

IPC: B64D3/00

CPC classification number: H01R4/64 ,  B64C1/26 ,  B64C5/02 ,  B64C7/00 ,  B64D45/02 ,  H01R35/04 ,  H01R41/00 ,  H01R2201/26

Abstract: A device provides electrical continuity between aeronautical components including a first fixed component and a second component displaceable with respect to the first component. The first and second components include electrically conducting surfaces. A first conductive piece is fixed to the first component and a second conductive piece is fixed to the second component. The first and second pieces are joined together with the possibility of sliding one on the other, in such a way that the first piece is connected to the conductive surface of the first component and the second piece is connected to the conductive surface of the second component, so that, when displacements take place of the second component with respect to the first component, the first piece slides on the second piece maintaining the electrical conductivity between the first and second components.

Abstract translation: 一种装置提供包括第一固定部件和可相对于第一部件移动的第二部件的航空部件之间的电连续性。 第一和第二部件包括导电表面。 第一导电片被固定到第一部件，第二导电片固定到第二部件。 第一和第二部件以可能性彼此滑动的方式接合在一起，使得第一部件连接到第一部件的导电表面，并且第二部件连接到第二部件的导电表面 使得当相对于第一部件发生第二部件的位移时，第一部件在第二部件上滑动，保持第一和第二部件之间的导电性。

公开(公告)号：US08678314B2

公开(公告)日：2014-03-25

申请号：US13339897

申请日：2011-12-29

Applicant: Esteban Martino Gonzalez ,  Eduardo Vinue Santolalla ,  Diego Folch Cortes ,  Pablo Goya Abaurrea ,  Enrique Guinaldo Fernandez ,  Julien Guillemaut

Inventor： Esteban Martino Gonzalez ,  Eduardo Vinue Santolalla ,  Diego Folch Cortes ,  Pablo Goya Abaurrea ,  Enrique Guinaldo Fernandez ,  Julien Guillemaut

IPC: B64C1/10

CPC classification number: B64C1/068 ,  B64C1/06 ,  B64C1/061 ,  B64C1/062 ,  B64D27/14 ,  B64D2027/005 ,  Y02T50/66

Abstract: Aircraft fuselage section (32) subjected to impacts of external bodies, the aircraft fuselage having a curved shape with at least a vertical symmetry plane (A-A) and a central longitudinal axis and comprising a skin (35) and a plurality of frames (37) arranged perpendicularly to said longitudinal axis (33), the aircraft fuselage section also comprising at least an inner reticular structure (51, 53) mounted on a supporting structure (41, 43) comprising longitudinal beams (39) attached to the skin (35) and interconnected with said frames (37), said inner reticular structure (51, 53) being arranged for creating at least one closed cell (75) with the skin (35) for improving its resistance and its damage tolerance to said impacts. Said inner reticular structure (51, 53) can be formed by panels (61), rods (65, 65′), cables (67, 67′) or belts (69, 69′).

Abstract translation: 飞机机身部分受到外部物体的撞击，飞机机身具有至少具有垂直对称平面（AA）和中心纵向轴线的弯曲形状并且包括皮肤（35）和多个框架（37） 飞行器机身部分还包括安装在支撑结构（41,43）上的至少一个内部网状结构（51,53），该内部网状结构（51,53）包括连接到皮肤（35）的纵向梁（39） 并且与所述框架（37）相互连接，所述内网状结构（51,53）布置成用于产生具有皮肤（35）的至少一个闭孔（75），以改善其抵抗力及其对所述冲击的损伤容限。 所述内网状结构（51,53）可以由面板（61），杆（65,65'），电缆（67,67'）或皮带（69,69'）形成。

公开(公告)号：US08657233B2

公开(公告)日：2014-02-25

申请号：US13305289

申请日：2011-11-28

Applicant: Alejandro Meseguer Mata ,  Angel Postigo Rodriguez ,  Rafael Villanueva Montero ,  Daniel De La Sen Perez

Inventor： Alejandro Meseguer Mata ,  Angel Postigo Rodriguez ,  Rafael Villanueva Montero ,  Daniel De La Sen Perez

IPC: B64C1/14

CPC classification number: B64D41/00 ,  B64D2041/002

Abstract: A tail-cone of an aircraft includes a skin provided with a movable fairing which, by a swing articulated mechanism, is supported on the skin in order to allow the opening/closing of the movable fairing and gain access to the inside of the tail-cone. The tail-cone includes actuators for operating the swing articulated mechanism in order to permit the automatic opening and closing of the movable fairing to be carried out.

Abstract translation: 飞机的尾锥包括设置有可移动整流罩的皮肤，其通过摆动铰接机构支撑在皮肤上，以允许可移动整流罩的打开/关闭并且进入尾部的内侧， 锥体。 尾锥包括用于操作摆动铰接机构的致动器，以允许执行可移动整流罩的自动打开和关闭。

公开(公告)号：US20130287954A1

公开(公告)日：2013-10-31

申请号：US13871089

申请日：2013-04-26

Applicant: AIRBUS OPERATIONS, S.L.

Inventor： Jose David CANO CEDIEL ,  Pedro Nogueroles Vines

IPC: B29C63/00

CPC classification number: B29C63/0047 ,  B29C70/547

Abstract: The invention discloses a method for prevention of porosity in composite material parts (1), which is applied when the curing stage of the part (1) is being carried out on a female tool (2). In the curing stage, an adhesive (4) is placed on at least one of the areas of the radii (5) of the composite material part (1), so that the possible subsequent appearance of porosity in said areas of the composite material part (1) is prevented. Thus, the adhesive (4) acquires the fluidization temperature before the resin of the composite material and it is displaced filling the holes generated during the placement of the part (1) on the female tool (2), in the area of the radii (5) of the part (1), during the coupling between the part (1) and the female tool (2).

Abstract translation: 本发明公开了一种用于在复合材料部件（1）中防止孔隙率的方法，该方法在将部件（1）的固化阶段在母工具（2）上进行时应用。 在固化阶段，将粘合剂（4）放置在复合材料部分（1）的半径（5）的至少一个区域上，使得随后在复合材料部分的所述区域中出现孔隙率 （1）。 因此，粘合剂（4）获得复合材料的树脂之前的流化温度，并且在半体（1）的区域中填充在将部件（1）放置在阴工具（2）上时产生的孔， 在部分（1）和阴工具（2）之间的联接期间，部分（1）的图5）。

公开(公告)号：US20130280008A1

公开(公告)日：2013-10-24

申请号：US13845272

申请日：2013-03-18

Applicant: AIRBUS OPERATIONS S.L.

Inventor： Jose Sanz Torrijos ,  Marcos Alazarki

IPC: B64C3/26

CPC classification number: B64C3/26 ,  B64C1/1446 ,  B64C3/34 ,  F16B5/025

Abstract: A bolted joint for connecting a cover of an opening in a primary structure of a lifting surface of an aircraft to the primary structure. The bolted joint includes two first bolted joints on either side of a symmetry axis of the cover arranged without any lateral clearance, two second bolted joints on either side of the symmetry axis on the side of the cover opposite to that of the two first bolted joints, arranged without any lateral clearance in the holes of the primary structure and with a linear lateral clearance in the holes of the cover; a plurality of third bolted joints along the border of the cover arranged without any lateral clearance in the holes of the primary structure and with a radial clearance in the holes of the cover.

Abstract translation: 用于将飞行器的提升表面的主结构中的开口的盖连接到主结构的螺栓接头。 螺栓接头包括两个第一螺栓接头，其位于盖的对称轴线的任一侧，其布置为没有任何侧向间隙，两个第二螺栓连接在对称轴线的两侧上，与盖子的两个第一螺栓接头 在第一结构的孔中没有任何侧向间隙并且在盖的孔中具有线性侧向间隙; 沿着盖的边界的多个第三螺栓接头，其布置成在主结构的孔中没有任何侧向间隙，并且在盖的孔中具有径向间隙。

公开(公告)号：US08562237B2

公开(公告)日：2013-10-22

申请号：US13339578

申请日：2011-12-29

Applicant: Jose Maria Pina Lopez ,  Enrique Vera Villares

Inventor： Jose Maria Pina Lopez ,  Enrique Vera Villares

IPC: F16C11/00 ,  F16C23/04

CPC classification number: F16C35/02 ,  F16C11/0614 ,  F16C23/045 ,  F16C2226/60

Abstract: A ball-joint support for thin parts, through which a ball-joint is operably coupled to a thin part, and where the ball-joint includes an inner part with a central coaxial orifice through which a longitudinal axis is introduced, and an outer part that engages complementarily to the inner part is provided. The ball joint support includes a cap including a central through hole in which the ball joint is embedded inside via the outer part, and externally, the cap is embedded in a cylindrical opening included in the thin part, and mechanical means for axial retention of the thin part to the cap, wherein the thickness of the cap is greater than the thickness of the thin part where the cap engages.

Abstract translation: 用于薄部件的球形接头支撑件，球形接头通过该支撑件可操作地联接到薄部分，并且其中球形接头包括具有中心同轴孔口的内部部件，纵向轴线穿过该中心同轴孔口，外部部件 提供与内部部件互补配合的部件。 球形接头支撑件包括一个盖子，该盖子包括一个中心通孔，球形接头通过外部部分嵌入到该中心孔中，外部盖子包埋在包括在薄部分中的圆柱形开口中，以及用于轴向保持 帽的薄部分，其中帽的厚度大于帽接合的薄部分的厚度。

公开(公告)号：US08550398B2

公开(公告)日：2013-10-08

申请号：US13091202

申请日：2011-04-21

Applicant: José Javier Almendros Gómez ,  Yolanda De Gregorio Hurtado

Inventor： José Javier Almendros Gómez ,  Yolanda De Gregorio Hurtado

IPC: B64C5/02 ,  B64C3/36 ,  B64C7/00

CPC classification number: B64C5/02 ,  B64C7/00

Abstract: Optimization of structures subjected to hot gas streams. The invention refers to a fairing (10) for aircraft horizontal stabilizer (3) comprising a front part (11) and a rear part (12), the front part (11) covering a limited extent of the fairing (10) surface, which is the part of the fairing (10) receiving hot air stream (6) coming from the aircraft engines (4), this front part (11) being made of an anti-erosion material, the rear part (12) covering the rest of the surface of the fairing (10), this rear part (12) being made of a material resisting the aerodynamic loads existing on the fairing (10). The invention also refers to an aircraft comprising a horizontal stabilizer (3) with a fairing (10) such as the one described.

Abstract translation: 优化热气流的结构。 本发明涉及一种用于飞机水平稳定器（3）的整流罩（10），其包括前部（11）和后部（12），所述前部（11）覆盖整流罩（10）表面的有限程度， 是整流罩（10）接收来自飞机发动机（4）的热气流（6）的一部分，该前部（11）由抗侵蚀材料制成，后部（12）覆盖其余部分 整流罩（10）的表面，该后部（12）由抵抗存在于整流罩（10）上的空气动力学负载的材料制成。 本发明还涉及一种包括具有诸如所描述的整流罩（10）的水平稳定器（3）的飞行器。

公开(公告)号：US20130212883A1

公开(公告)日：2013-08-22

申请号：US13771379

申请日：2013-02-20

Applicant: Airbus Operations S.L.

Inventor： Jorge Juan Soto Martinez ,  Juan Francisco Garcia Amado ,  Marta Gimenez Olazabal ,  Jose Gorrotxategi Txurruka ,  Jokin Lekunberri Urkidi ,  Jon Ander Altamira Ugarte

IPC: B23P19/06 ,  B23P19/00

CPC classification number: B23P19/06 ,  B21J15/022 ,  B21J15/142 ,  B21J15/32 ,  B23P19/001 ,  B23P19/005 ,  B23P19/006 ,  B23P19/04 ,  B23P19/10 ,  B23P2700/01 ,  B23Q16/00 ,  B25B1/04 ,  B25B21/002 ,  B25B23/1415 ,  B25J9/1697 ,  B25J11/005 ,  B25J11/007 ,  B25J15/0019 ,  B25J19/0058 ,  B64F5/10 ,  F16B31/021 ,  G05B2219/45088 ,  G05B2219/45126 ,  Y10T29/49622 ,  Y10T29/49908 ,  Y10T29/49948 ,  Y10T29/49956 ,  Y10T29/53078 ,  Y10T29/53091 ,  Y10T29/53096 ,  Y10T29/53774 ,  Y10T29/53991

Abstract: A head of a riveting device—for Hi-Lite type rivets—of at least two components of a structure for installing automatically collars on pins previously inserted in the structure. The head comprises: a collar installation tool; a collar supply to supply collars to the collar installation tool; a tool actuating device; a linear displacement device to linearly move the tool during the threading operation; a withdrawal device arranged to withdraw the second part of the collars; a control arrangement configured to automatically perform the installation of collars on pins and after this the withdrawal of the second part of the collars, using tools and collars appropriate for the pins. Also a robot having as end-effector the head and to a method of riveting two components of an aircraft fuselage are provided.

Abstract translation: 铆钉装置的头部，用于Hi-Lite型铆钉，其至少两个部件组件用于自动地将套环安装在先前插入结构中的销上。 头部包括：衣领安装工具; 一个领子供应，以提供领子安装工具的领子; 工具致动装置; 线性位移装置，用于在穿线操作期间线性地移动工具; 撤回装置，其布置成撤回所述套环的第二部分; 控制装置被配置为自动地执行在销上的套环的安装，并且在这之后使用适合于销的工具和套环撤回套环的第二部分。 还提供了具有端部执行器头部的机器人和铆接飞行器机身的两个部件的方法。

公开(公告)号：US08504340B2

公开(公告)日：2013-08-06

申请号：US12956831

申请日：2010-11-30

Applicant: Daniel Redondo Garcia ,  Javier De Bona Piedrabuena

Inventor： Daniel Redondo Garcia ,  Javier De Bona Piedrabuena

IPC: G06G7/57 ,  G06T11/00 ,  G01M9/08

CPC classification number: G06F17/5018 ,  G06F17/5095 ,  G06F2217/16

Abstract: Methods and systems for optimizing the design of aerodynamic surfaces are provided. They include in the design process of an aerodynamic surface of a body which moves through a flow field, the following: preparation of a CFD simulation of said body; resolution of the CFD calculation for specific conditions of the flow field and for obtaining flow lines of the flow on said surface; calculation of at least one geometrical variable of the surface, such as, for example, the normal curvature, according to the direction of said flow lines; and simultaneous visualization of the surface of said body and of at least one geometric variable. Additionally, at least one variable of the aerodynamic flow, such as, for example, a pressure gradient, may be calculated and visualized.

Abstract translation: 提供了优化空气动力学表面设计的方法和系统。 它们包括在通过流场移动的身体的空气动力学表面的设计过程中，以下：准备所述身体的CFD模拟; 对流场的特定条件进行CFD计算的分辨率和用于获得在所述表面上的流动的流动线; 根据所述流动线的方向计算表面的至少一个几何变量，例如正常曲率; 以及所述身体的表面和至少一个几何变量的同时可视化。 此外，可以计算和可视化空气动力流的至少一个变量，例如压力梯度。