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    REINFORCED STRINGER AND METHOD OF MANUFACTURE THEREOF
    161.
    发明申请
    REINFORCED STRINGER AND METHOD OF MANUFACTURE THEREOF 有权
    加强型圆柱体及其制造方法

    公开(公告)号：US20140186578A1

    公开(公告)日：2014-07-03

    申请号：US14139147

    申请日：2013-12-23

    Applicant: AIRBUS OPERATIONS, S.L.

    Inventor： Ignacio OUTON HERNÁNDEZ ,  Yolanda MIGUEZ CHARINES ,  Oscar Miguel MACÍAS JARENO ,  Juan José PASTRANA BERMEJO ,  Antonio TORRES ESTEBAN

    IPC: B64C1/06

    CPC classification number: B64C1/064 ,  B29C70/34 ,  B29D99/0003 ,  Y02T50/43 ,  Y10T156/1043 ,  Y10T428/24174

    Abstract: The present invention relates to a stringer, particularly to a stiffening and structural longitudinal element for skin of aircraft airfoil surfaces, characterized in that it incorporates two separate and independent reinforcement areas, one in the foot and the other at the end of the web (head) of the stringer, where the reinforcement areas are obtained by a widening of the section of the stringer, the widening being formed by a localized stack of reinforcing plies of composite material which are embedded within the stringer. The invention also relates to the method of manufacture and is particularly applicable to stringers having an L-shaped or T-shaped section.

    Abstract translation: 技术领域本发明涉及一种纵梁，特别涉及一种用于飞机机翼表面的皮肤的加强和结构纵向元件，其特征在于，其包括两个独立且独立的加强区域，一个在脚部中，另一个位于腹板末端（头部 ），其中通过桁条的部分的加宽获得加强区域，该扩宽由嵌入在桁条内的复合材料的增强层的局部叠层形成。 本发明还涉及制造方法，特别适用于具有L形或T形截面的桁条。

    REPAIR PART AND REPAIR METHOD FOR REPAIRING LONGITUDINAL ELEMENTS MADE OF A COMPOSITE MATERIAL
    162.
    发明申请
    REPAIR PART AND REPAIR METHOD FOR REPAIRING LONGITUDINAL ELEMENTS MADE OF A COMPOSITE MATERIAL 审中-公开
    修复复合材料的长期元素修复部分和维修方法

    公开(公告)号：US20140017445A1

    公开(公告)日：2014-01-16

    申请号：US13928047

    申请日：2013-06-26

    Applicant: Airbus Operations, S.L.

    Inventor： Alberto Balsa Gonzalez ,  Jose Javier Almendros Gomez ,  Narciso Rodriguez Garcia ,  Maria Rocio Fernando Magarzo

    IPC: B23P6/00 ,  F16B5/04

    CPC classification number: B23P6/00 ,  B29C73/04 ,  B29C2073/268 ,  F16B5/04 ,  Y10T29/49732 ,  Y10T29/49739 ,  Y10T428/24322

    Abstract: The present invention relates to a repair part and to a repair method. The repair part is an elongated part made of a composite material comprising two attached portions forming an angle and holes in each portion arranged in the direction of the line joining both portions. The repair method includes: providing a fragment of a repair part, being long enough to cover the damaged area of the part to be repaired, maintaining a border for fixing the fragment of the repair part; making holes in both portions of the part to be repaired, such that the distance between the centers of consecutive repair holes is the same as the distance between the centers of the consecutive holes; and attaching the fragment of the repair part to the part to be repaired.

    Abstract translation: 本发明涉及修理部件和修理方法。 修复部分是由复合材料制成的细长部件，该复合材料包括形成角度的两个附接部分和沿连接两个部分的线的方向布置的每个部分中的孔。 修复方法包括：提供修复部分的片段，其长度足以覆盖待修复部件的损坏区域，保持用于固定修复部分的片段的边界; 在要修复的部件的两个部分中形成孔，使得连续修复孔的中心之间的距离与连续孔的中心之间的距离相同; 并将修理部分的片段附着到要修复的部件上。

    METHOD FOR PREVENTION OF POROSITY IN COMPOSITE MATERIAL PARTS
    163.
    发明申请
    METHOD FOR PREVENTION OF POROSITY IN COMPOSITE MATERIAL PARTS 有权
    用于防止复合材料部件中的孔隙度的方法

    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）。

    Bolted joint of the cover of an access opening in an aircraft lifting surface
    164.
    发明申请
    Bolted joint of the cover of an access opening in an aircraft lifting surface 审中-公开
    在飞机提升表面上的进入开口的盖的螺栓接头

    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。

    INTERFACE ARRANGEMENT FOR AIRCRAFT LIFTING SURFACE
    165.
    发明申请
    INTERFACE ARRANGEMENT FOR AIRCRAFT LIFTING SURFACE 审中-公开
    飞机提升表面接口装置

    公开(公告)号：US20130270392A1

    公开(公告)日：2013-10-17

    申请号：US13829629

    申请日：2013-03-14

    Applicant: Airbus Operations, S.L.

    Inventor： FERNANDO MAESTRE DERQUI ,  IGNACIO OUTON HERNÁNDEZ

    IPC: B64C23/00

    CPC classification number: B64C23/00 ,  B64C3/26 ,  B64C3/28

    Abstract: Interface arrangement for aircraft lifting surface between a first component and a second component made of composite materials and having an aerodynamic contour, wherein the first component comprises a primary joggled area and the second component comprises a secondary joggled area, such that the first component is joined to the second component by means of a supplementary part which accommodates in the primary joggled area and in the secondary joggled area, the secondary part being designed to maintain continuity of aerodynamic contour at the interface arrangement and to fill the gap between the first component and the second component, so the maximum thickness of the supplementary part being the depth of the primary joggled area, the depth of the primary joggled area being lower than the depth needed to accommodate the second component on the first component.

    Abstract translation: 用于在由复合材料制成并且具有空气动力学轮廓的第一部件和第二部件之间的飞机提升表面的接口装置，其中所述第一部件包括主要碰撞区域，并且所述第二部件包括辅助碰撞区域，使得所述第一部件被连接 通过一个辅助部件连接到第二部件上，该辅助部件容纳在主要的碰撞区域中，而在辅助碰撞区域中，辅助部件被设计成保持界面布置处的空气动力学轮廓的连续性，并且填充第一部件和 辅助部分的最大厚度是主要碰撞区域的深度，主要碰撞区域的深度低于在第一部件上容纳第二部件所需的深度。

    PROCESS FOR APPLYING RESIN ON THE SURFACE OF A MOULDING BASE TOOL, TREATED WITH MOULD-RELEASE SUBSTANCES, IN ORDER TO OBTAIN BODIES OF COMPOSITE MATERIAL
    167.
    发明申请
    PROCESS FOR APPLYING RESIN ON THE SURFACE OF A MOULDING BASE TOOL, TREATED WITH MOULD-RELEASE SUBSTANCES, IN ORDER TO OBTAIN BODIES OF COMPOSITE MATERIAL 审中-公开
    在模具底材工具的表面上施加树脂的方法，用模具释放物质处理，以便获得复合材料的物体

    公开(公告)号：US20130056150A1

    公开(公告)日：2013-03-07

    申请号：US13665564

    申请日：2012-10-31

    Applicant: AIRBUS OPERATIONS, S.L.

    Inventor： Jose David Cano Cediel ,  Asuncion Carrascal Iglesias ,  Georgina Galera Cordoba

    IPC: B32B37/00 ,  B32B38/16

    CPC classification number: B29C37/0067

    Abstract: The invention comprises, a first preliminary step of cleaning the treatment surface of the moulding base tool and a second step in which the necessary layers of mould-release agent are applied to the treatment surface of the moulding base tool. Based on said preliminary steps, the process is characterized in that, in a later step, the treatment surface (1), covered with a mould-release agent (3), is provided with a continuous uniform film (4) of resin having a low concentration of volatile elements and a laminar resin supporting a very high mould-release capability, which facilitates the transfer of resin to the treatment surface (1) of the moulding base tool (2).

    Abstract translation: 本发明包括清洁成型基础工具的处理表面的第一预备步骤和第二步骤，其中将必要的脱模剂层施加到成型基础工具的处理表面上。 基于所述预备步骤，该方法的特征在于，在后续步骤中，用脱模剂（3）覆盖的处理表面（1）设置有连续均匀的树脂（4），其具有 低浓度的挥发性元素和支撑非常高的脱模能力的层状树脂，这有助于树脂转移到模制基础工具（2）的处理表面（1）。

    Method for producing an armored wall in an aircraft and an aircraft section comprising an armored wall
    169.
    发明授权
    Method for producing an armored wall in an aircraft and an aircraft section comprising an armored wall 有权

    公开(公告)号：US12246818B2

    公开(公告)日：2025-03-11

    申请号：US18184049

    申请日：2023-03-15

    Applicant: Airbus Operations GmbH ,  Airbus Operations S.L.

    Inventor： Henning Scheel ,  César Rodriguez Barbero ,  Esteban Martino-Gonzalez

    IPC: B64C1/14 ,  B64D45/00

    Abstract: A method for producing an armored wall for an aircraft by determining an available thickness of the wall, an allowable areal mass of the wall, and an available space for a wall deformation due to ballistic impact. The method includes retrieving a parameterization of a plurality of armoring materials, which includes a parameter for each of a plurality of material characteristics for each of the plurality of armoring materials. The method also includes comparing the available wall thickness, the allowable areal mass, and the available deformation space with a corresponding parameter of the parameterization, selecting one armoring material for the wall from the plurality of armoring materials based on a result of comparing, and manufacturing a wall by supplementing the selected armoring material to a basic wall structure.

    Automated drilling optimization method
    170.
    发明授权
    Automated drilling optimization method 有权

    公开(公告)号：US12179301B2

    公开(公告)日：2024-12-31

    申请号：US17187212

    申请日：2021-02-26

    Applicant: AIRBUS SAS ,  AIRBUS OPERATIONS S.L.

    Inventor： Christophe Louat ,  Arnaud Zanni ,  Juan Carlos Southwood Carrasco

    IPC: B23Q15/22 ,  B23Q17/22 ,  G06N20/00

    Abstract: A method for optimizing the execution of automated drilling systems controlled by a numerical control, NC, machine, wherein the NC machine performs the following steps: (i) identifying each drill executed by an automated drilling tool at first drilling event (t); storing a theoretical position of each executed drill at the event (t); (iii) calculating a learned position using a machine learning model and based on the stored theoretical position at the event (t); (iv) estimating an intermediate position by applying a tendency statistical function, and (v), if the difference between the intermediate position and the learned position is less than a pre-configured threshold, using the intermediate position for the drilling tool to position a next drill and execute it at a subsequent event (t+1).

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