公开(公告)号：WO2012001206A3

公开(公告)日：2012-06-21

申请号：PCT/ES2011070477

申请日：2011-06-30

Applicant: AIRBUS OPERATIONS SL ,  AREVALO RODRIGUEZ ELENA ,  CRUZ DOMINGUEZ FRANCISCO JOSE

Inventor： AREVALO RODRIGUEZ ELENA ,  CRUZ DOMINGUEZ FRANCISCO JOSE

IPC: B64C1/06 ,  B64C1/14

CPC classification number: B64C1/064 ,  B64C1/1461 ,  B64C2001/0072 ,  Y02T50/433

Abstract: Reinforcement structure (1) for an opening (10) in the primary structure of an aircraft, said structure comprising a skin (2), frame members (3) which are transverse with respect to the flying direction of the aircraft, and stringers (4) which are longitudinal with respect to the flying direction of the aircraft, said reinforcing structure (1) comprising: - a perimetral reinforcing element (5) situated along the edge of the opening (10) and reproducing the geometrical form thereof; - at least one pair of transverse reinforcing elements (6) arranged on both transverse sides of the opening (10); at least one pair of longitudinal reinforcing elements (7) arranged on both longitudinal sides of the opening (10).

Abstract translation: 一种用于飞行器一次结构中的开口（10）的加强结构（1），所述结构包括皮肤（2），相对于飞行器的飞行方向横向的框架构件（3）和桁条 ），所述加强结构（1）包括：沿着所述开口（10）的边缘设置并再现其几何形状的周边加强元件（5）; - 布置在所述开口（10）的两个横向侧上的至少一对横向加强元件（6）; 至少一对纵向加强元件（7）布置在开口（10）的两个纵向侧上。

公开(公告)号：WO2010130863A8

公开(公告)日：2012-04-05

申请号：PCT/ES2010070318

申请日：2010-05-12

Applicant: AIRBUS OPERATIONS SL ,  NAVARRO LUNA ANTONIO ,  VALERIANO LA TORRE JOSE

Inventor： NAVARRO LUNA ANTONIO ,  VALERIANO LA TORRE JOSE

IPC: G06F17/50

CPC classification number: G06F17/5095 ,  G06F2217/42 ,  G06F2217/44 ,  G06F2217/46

Abstract: Computer-assisted method for optimising surfaces of composite material structures as part of a design process that includes the following steps: a) providing a multi-cell surface (11) of the structure obtained using aerodynamic calculations; b) transforming said multi-cell surface (11) into an optimised surface (13) with fewer cells, by concatenating contiguous cells and maintaining point and tangent continuity between them; c) using said optimised surface (13) as a geometric master pattern for designing the components of the structure. The method is particularly applicable to the design of structures with a plurality of components and in particular fuselages of aircraft made of composite material. The invention also relates to a computer program for performing the method.

Abstract translation: 用于优化复合材料结构表面的计算机辅助方法作为设计过程的一部分，其包括以下步骤：a）提供使用空气动力学计算获得的结构的多单元表面（11）; b）通过连接连续的单元并维持它们之间的点和切线连续性，将所述多单元表面（11）转换成具有较少单元的优化表面（13）; c）使用所述优化表面（13）作为用于设计结构部件的几何主图案。 该方法特别适用于具有多个组件，特别是由复合材料制成的飞机的机身的结构的设计。 本发明还涉及一种用于执行该方法的计算机程序。

公开(公告)号：WO2011154582A2

公开(公告)日：2011-12-15

申请号：PCT/ES2011070414

申请日：2011-06-09

Applicant: AIRBUS OPERATIONS SL ,  LATORRE PLAZA TERESA ,  INIESTA MENENDEZ JOSE GREGORIO ,  MORANCHO RODRIGUEZ JOSEP ,  MENENDEZ MARTIN JOSE MANUEL

Inventor： LATORRE PLAZA TERESA ,  INIESTA MENENDEZ JOSE GREGORIO ,  MORANCHO RODRIGUEZ JOSEP ,  MENENDEZ MARTIN JOSE MANUEL

IPC: B64C1/26

CPC classification number: B64C1/26 ,  B64C3/26

Abstract: Procedure for the manufacture of large parts of composite material, controlling the thickness of the edges thereof. It relates to the manufacture of a part (11) possessing edge zone (11) in an aeronautical structure through a join with joining plate (23) and backing plate (25) by means of the following stages: a) Definition of interface surface (15) of edge zone (13) to be in contact with joining plate (23); b) Manufacture of first panel (31) possessing the configuration planned for part (11); c) Obtainment of a map of differences between the thickness of first panel (31) and that which it should possess to be coincident with said interface surface (15); d) Manufacture of supplementary panel (33) having a thickness to be coincident with that of said map of differences; e) joining of supplementary panel (33) to first panel (31).

Abstract translation: 用于制造复合材料的大部件的程序，控制其边缘的厚度。 其涉及通过以下阶段通过与连接板（23）和背板（25）的连接来制造具有航空结构中的边缘区域（11）的部分（11）：a）界面表面的定义 15）边缘区域（13）与接合板（23）接触; b）制造具有第（11）部分规划的配置的第一面板（31）; c）获得第一面板（31）的厚度与其应该具有与所述界面（15）重合的厚度之间的差异的图; d）具有与所述差异图的厚度一致的补充板（33）的制造; e）将辅助面板（33）连接到第一面板（31）。

公开(公告)号：WO2011135132A1

公开(公告)日：2011-11-03

申请号：PCT/ES2011070286

申请日：2011-04-20

Applicant: AIRBUS OPERATIONS SL ,  CANO CEDIEL JOSE DAVID ,  CARRASCAL IGLESIAS ASUNCION ,  GALERA CORDOBA GEORGINA

Inventor： CANO CEDIEL JOSE DAVID ,  CARRASCAL IGLESIAS ASUNCION ,  GALERA CORDOBA GEORGINA

IPC: B32B37/16 ,  B29C41/36

CPC classification number: B29C37/0067

Abstract: The invention relates to a method essentially comprising a first step consisting in cleaning the surface to be treated and a second step consisting in applying the required layers of mould-release agent to the intended treatment surface of the moulding base tool. The invention is characterised in that a subsequent step in which the treatment surface (1) which has been covered with the 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 support a very high mould-release capability which facilitates the transfer of resin to the aforementioned treatment surface (1) of the moulding base tool (2).

Abstract translation: 本发明涉及一种基本上包括第一步骤和第二步骤的方法，该第一步骤包括清洁待处理的表面，该步骤包括将所需的脱模剂层施加到模制基础工具的预期处理表面上。 本发明的特征在于，在后续步骤中，已经用脱模剂（3）覆盖的处理表面（1）设置有具有低挥发性元素浓度的树脂的连续均匀膜（4），以及 层状树脂支持非常高的脱模能力，这有助于树脂转移到模制基础工具（2）的上述处理表面（1）。

公开(公告)号：WO2010133746A3

公开(公告)日：2011-06-30

申请号：PCT/ES2010070342

申请日：2010-05-21

Applicant: AIRBUS OPERATIONS SL ,  BALSA GONZALEZ ALBERTO ,  BURGOS GALLEGO FRANCISCO DE PAULA

Inventor： BALSA GONZALEZ ALBERTO ,  BURGOS GALLEGO FRANCISCO DE PAULA

IPC: B64C3/34

CPC classification number: B64C3/34

Abstract: The invention relates to a device (1) for joining torsion boxes (5, 6) of aircraft structures, said structures carrying fuel therein, characterized in that the mentioned device (1) comprises three sides (2, 3, 4) by means of which it is secured to the inner part of the structural parts of the joint of the torsion boxes (5, 6) of the aircraft in a permanent manner, said device (1) thus closing the joint of the boxes (5, 6) and preventing possible fuel leaks, the device (1) being a non¬ structural component of the mentioned joint since it does not withstand the loads of the structure of the joint of torsion boxes (5, 6).

Abstract translation: 本发明涉及一种用于连接飞机结构的扭转盒（5,6）的装置（1），所述结构在其中承载燃料，其特征在于，所述装置（1）包括三个侧面（2,3,4） 其以永久的方式固定到飞机的扭转箱（5,6）的接头的结构部件的内部部分，所述装置（1）因此封闭箱体（5,6）和 防止可能的燃料泄漏，所述装置（1）是所述接头的非结构部件，因为其不能承受扭转箱（5,6）的接头结构的载荷。

公开(公告)号：WO2010122200A3

公开(公告)日：2011-05-05

申请号：PCT/ES2010070242

申请日：2010-04-21

Applicant: AIRBUS OPERATIONS SL ,  FOLCH CORTES DIEGO ,  AREVALO RODRIGUEZ ELENA ,  VERA VILLARES ENRIQUE ,  CABEZA HUERTA JAVIER ,  PINA LOPEZ JOSE MARIA

Inventor： FOLCH CORTES DIEGO ,  AREVALO RODRIGUEZ ELENA ,  VERA VILLARES ENRIQUE ,  CABEZA HUERTA JAVIER ,  PINA LOPEZ JOSE MARIA

IPC: B64C1/26

CPC classification number: B64C1/26 ,  Y10T29/49826

Abstract: The invention relates to metal fittings (41, 71) for engaging the vertical tailplane of an aircraft in an area of the rear fuselage, which are made fully from a composite material and comprise: a) a first part (43, 73) including lugs (45, 45'; 75, 75') for engaging the vertical tailplane and vertical walls (47, 47'; 77, 77') joining the metal fittings (41, 71) to the ring frames (7); and b) at least one pair of additional parts (49, 49'; 79, 79') including horizontal walls (51, 51'; 81, 81') joining the metal fittings (41, 71) to the skin (5). The metal fitting (71) for engagement with an inclined load also includes a second pair of angle parts (90, 90') including vertical walls (93, 93') joining to the lugs (75, 75'). The invention also relates to methods for mounting said metal fittings (41, 71).

Abstract translation: 本发明涉及用于与后机身区域中的飞行器的垂直尾翼接合的金属配件（41,41），其由复合材料完全制成，并包括：a）第一部分（43,47），其包括凸耳 （45,45'; 75,75'），用于接合垂直尾翼和将金属配件（41,71）连接到环形框架（7）的垂直壁（47,47'; 77,77'）; 和b）包括将金属配件（41,71）连接到皮肤（5）的水平壁（51,51'; 81,81'）的至少一对附加部件（49,49'; 79,79'）， 。 用于与倾斜负载接合的金属配件（71）还包括第二对角部件（90,90'），其包括连接到凸耳（75,75'）的垂直壁（93,93'）。 本发明还涉及用于安装所述金属配件（41,41）的方法。

公开(公告)号：WO2011039402A2

公开(公告)日：2011-04-07

申请号：PCT/ES2010070637

申请日：2010-09-30

Applicant: AIRBUS OPERATIONS SL ,  VERA VILLARES ENRIQUE ,  PINA LOPEZ JOSE MARIA

Inventor： VERA VILLARES ENRIQUE ,  PINA LOPEZ JOSE MARIA

IPC: B64C1/06

CPC classification number: B64C1/064 ,  B29C65/60 ,  B29C66/5241 ,  B29C66/721 ,  B29L2031/3076 ,  B64C1/065 ,  F16B5/04

Abstract: Joining of a structural aircraft element (1 ) that has a section in an omega shape, to another structural aircraft element (10) with a differently shaped section, with the aforementioned joint of these structural elements (1, 10) with a different section comprising at least two joining elements (4) in an angular shape, which are joined with the external flanges (5) of the structural elements (1, 10), in such a manner that this joint allows the section change to take place continually, through simple elements (4) in its manufacturing and assembly, thanks to its geometric simplicity. The assembly of this joining of structural elements (1, 10) is also with a section change of great flexibility, allowing the tolerances of the joint to be absorbed, and achieving that the load distribution between the structural elements (1, 10) and the joining elements (4) is optimal.

Abstract translation: 具有ω形截面的结构飞行器元件（1）连接到具有不同形状截面的另一个结构飞行器元件（10），其中这些结构元件（1,10）的上述接头具有不同的部分，包括 至少两个与所述结构元件（1,10）的所述外部凸缘（5）接合的角形接合元件（4），使得所述接头允许所述部分变化连续地通过，通过 简单的元素（4）在其制造和组装，由于其几何简单。 结构元件（1,10）的这种连接的组装也具有很大柔性的截面变化，允许接头的公差被吸收，并且实现结构元件（1,10）和 连接元件（4）是最佳的。

公开(公告)号：WO2010070173A3

公开(公告)日：2010-10-28

申请号：PCT/ES2009070579

申请日：2009-12-11

Applicant: AIRBUS OPERATIONS SL ,  BURGOS GALLEGO FRANCISCO DE PAULA ,  MAROTO DE HOYOS MANUEL

Inventor： BURGOS GALLEGO FRANCISCO DE PAULA ,  MAROTO DE HOYOS MANUEL

IPC: B64C9/02

CPC classification number: B64C9/02

Abstract: A lifting or stabilising component (11) for an aircraft comprising in the area of its trailing edge a rotary control element (13) rotating around an axis (61) with at least one slot (21) between the tip (15) of the component (11) and the control element (13), the edges of which are configured such that the distance therebetween, that is, the dimension of the slot (21), is constant for different angles of deflection of the control element (13), being located between them sealing means (23) that assure the aerodynamic continuity of the component (11) when said control element (13) is at rest. In a preferred embodiment, the component (11) is a horizontal tail stabilizer and the control element (13) is a rudder.

Abstract translation: 一种用于飞行器的提升或稳定部件（11），在其后缘的区域中包括围绕轴线（61）旋转的旋转控制元件（13），在该部件的尖端（15）之间具有至少一个槽（21） （11）和控制元件（13），其边缘构造成使得其间的距离即狭槽（21）的尺寸对于控制元件（13）的不同偏转角度是恒定的， 位于它们之间的密封装置（23），当所述控制元件（13）静止时，所述密封装置（23）确保部件（11）的空气动力学连续性。 在优选实施例中，部件（11）是水平尾部稳定器，并且控制元件（13）是方向舵。

公开(公告)号：WO2010070182A3

公开(公告)日：2010-09-23

申请号：PCT/ES2009070596

申请日：2009-12-17

Applicant: AIRBUS OPERATIONS SL ,  LLAMAS SANDIN RAUL CARLOS ,  LUQUE BUZO MIGUEL

Inventor： LLAMAS SANDIN RAUL CARLOS ,  LUQUE BUZO MIGUEL

IPC: B64C1/26 ,  B64C5/02

CPC classification number: B64C5/02 ,  B64C1/26

Abstract: The invention relates to a horizontal stabilising surface (8) of an aircraft, in which the sweep angle (40) of said surface (8) is less than 90 degrees, whereby said angle (40) is that formed by the projection of the point reference line at 25% of the local chord (19) of the horizontal stabilising surface (8) onto a plane perpendicular to the plane of symmetry (21) of the aircraft, in the flight direction of the aircraft, with respect to the plane of symmetry (21) of the aircraft, said angle (40) being measured in the flight direction of the aircraft. In addition, the structural connection between the horizontal stabilising surface (8) and the fuselage (1) of the aircraft is provided by a ring frame (13) of said fuselage (1).

Abstract translation: 本发明涉及一种飞行器的水平稳定表面（8），其中所述表面（8）的扫掠角（40）小于90度，由此所述角度（40）是由点的投影形成的 参考线在水平稳定表面（8）的局部弦（19）的25％处，垂直于飞行器的对称平面（21）的平面在飞行器的飞行方向上相对于飞行器的飞行方向 所述飞机的对称（21），所述角度（40）在飞行器的飞行方向上被测量。 此外，飞行器的水平稳定表面（8）和机身（1）之间的结构连接由所述机身（1）的环形框架（13）提供。

公开(公告)号：WO2010063868A3

公开(公告)日：2010-07-29

申请号：PCT/ES2009070557

申请日：2009-12-04

Applicant: AIRBUS OPERATIONS SL ,  VERDE PRECKLER JORGE PABLO ,  VIZARRO TORIBIO JOSE MIGUEL

Inventor： VERDE PRECKLER JORGE PABLO ,  VIZARRO TORIBIO JOSE MIGUEL

IPC: B64C5/18 ,  B64C9/00 ,  B64C9/08

CPC classification number: B64C9/00 ,  B64C5/18 ,  B64C9/08 ,  Y02T50/32 ,  Y02T50/44

Abstract: Stabilizing and directional-control surface of an aircraft, said surface comprising a vertical stabilizer (2) and a rudder (3), it being possible fore said rudder to be deflected relative to the vertical stabilizer, and moreover the rudder comprises an internal profile (10) that can be extended and retracted by means of an actuating system (40) relative to the rest of the structure of the rudder, so that the stabilizing and control surface, in the retracted position of the internal profile of the rudder is an aerodynamic surface optimized for flying conditions, an increase of the aerodynamic control surface of the vertical stabilizer is achieved for requirements of controllability of the aircraft at low speeds of said aircraft and against strong yawing moments acting thereon, in the position in which the internal profile of the rudder is extended.

Abstract translation: 飞行器的稳定和方向控制表面，所述表面包括垂直稳定器（2）和方向舵（3），所述方向舵之前可能相对于垂直稳定器偏转，此外，舵包括内部轮廓（ 10），其可以通过相对于舵的结构的其余部分的致动系统（40）延伸和缩回，使得在方向舵的内部轮廓的缩回位置中的稳定和控制表面是空气动力学 对于飞行条件进行了优化的表面，垂直稳定器的空气动力学控制表面的增加是为了满足飞行器在所述飞行器的低速下的可控制性以及作用在其上的强偏转力矩的要求而实现的， 方向舵延伸。