公开(公告)号：US20180127081A1

公开(公告)日：2018-05-10

申请号：US15803559

申请日：2017-11-03

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

Inventor： Javier TORAL VÁZQUEZ ,  Esteban MARTINO GONZALEZ ,  Diego FOLCH CORTES ,  Pablo GOYA ABAURREA ,  Vasillis VOTSIOS ,  Michel FOUINNETAU ,  Sylvain ROUMEGAS

IPC: B64C1/12 ,  B32B5/02 ,  B32B5/18 ,  B64C5/02 ,  B64F5/10

CPC classification number: B64C1/12 ,  B32B5/028 ,  B32B5/18 ,  B32B2305/30 ,  B32B2305/38 ,  B32B2605/18 ,  B64C3/28 ,  B64C5/02 ,  B64C2001/0072 ,  B64D2045/0095 ,  B64F5/10

Abstract: A panel structure for an aircraft with at least one composite layer, and at least one net-shaped layer attached to the composite layer, wherein the net-shaped layer has a material suitable to improve the impact resistance of the panel structure. The net-shaped layer can be used to attach two composite layers. Alternatively, the net-shaped layer can be attached to a surface of one composite layer. In this last case, the net-shaped layer may be joined to a laminate sheet material and filled with a foam material. An impact reinforced panel structure is disclosed capable of withstanding any impact, such as a blade release, or a bird strike, without substantially modifying the manufacturing process.

公开(公告)号：US20180111673A1

公开(公告)日：2018-04-26

申请号：US15787202

申请日：2017-10-18

Applicant: Airbus Operations S.L.

Inventor： Carlos CASADO MONTERO ,  José Ángel HERNANZ MANRIQUE ,  Alberto MOLINA PARGA

IPC: B64C1/14 ,  B64D41/00

CPC classification number: B64C1/1453 ,  B64D41/00

Abstract: A drain mast for draining liquids from an aircraft, comprising a tube that comprises an internal rim connected to the internal surface of the tube, the internal rim being located in a plane inclined with respect to the horizontal plane of the aircraft and having its lowest part located on the second end of the tube, an aperture for evacuating the liquid, the aperture being located at the lowest part of the internal rim and in the face of the tube facing the incoming airflow, the internal rim and the aperture being configured such that at the second end, the liquid is directed by gravity through the internal rim to the aperture and wherein, in use, the drained liquid flowing from the aperture is pushed by the incoming airflow to the atmosphere.

公开(公告)号：US09944025B2

公开(公告)日：2018-04-17

申请号：US14982039

申请日：2015-12-29

Applicant: AIRBUS OPERATIONS, S.L.

Inventor： Gabriel Cruzado Parla ,  Pablo Lopez Fernandez ,  Aitor Echevarria Hernandez ,  Alberto Martinez Cerezo ,  Alberto Mulas De Lamo ,  Maria Mora Medias

IPC: B29C70/38 ,  B29L31/06

CPC classification number: B29C70/382 ,  B29C70/345 ,  B29C70/386 ,  B29C70/545 ,  B29D99/0003 ,  B29L2031/06

Abstract: The disclosure refers to a method for manufacturing rod-shaped components of composite material, for example rowings or fillers, wherein a laminate is layered by automatically laying up a plurality of plies of composite material, which is then cut in an automated machine to obtain a plurality of rods having substantially the same cross-sectional shape. The obtained rods are then simultaneously conformed by applying heat and pressure to obtain rods with the desired cross-sectional shape. With the method of the disclosure, a large number of these types of components are produced with improved quality and in a very simple manner, using the machinery and equipment already commonly existing in a factory of aeronautic components.

公开(公告)号：US20180022436A1

公开(公告)日：2018-01-25

申请号：US15654912

申请日：2017-07-20

Applicant: Airbus Operations, S.L.

Inventor： Alberto ARANA HIDALGO

IPC: B64C1/14 ,  E05C19/16

CPC classification number: B64C1/1446 ,  E05C19/16

Abstract: A union arrangement between a non-structural panel of the outer surface of an aircraft and a supporting member belonging to the aircraft resistant structure using mechanical and magnetic devices as an attachment arrangement. The magnetic devices comprise permanent magnets located in one of the non-structural panel or the supporting member and devices cooperating with the permanent magnets located in the other of the supporting member or the non-structural panel. The magnetic devices are used for both facilitating the self-clamping of the non-structural panel to the supporting member during the union operation and serving as fastening devices together with mechanical devices such as bolts installed in holes.

公开(公告)号：US09868510B2

公开(公告)日：2018-01-16

申请号：US14580456

申请日：2014-12-23

Applicant: Airbus Operations S.L.

Inventor： Fernando Pereira Mosqueira ,  Enrique Guinaldo Fernandez ,  Carlos Garcia Nieto ,  Francisco Javier Honorato Ruiz ,  Andrea Ivan Marasco ,  Francisco José Cruz Dominguez

IPC: B64C9/02 ,  B64C5/02 ,  B64C3/18 ,  B64C9/00

CPC classification number: B64C9/02 ,  B64C3/185 ,  B64C3/187 ,  B64C5/02 ,  B64C9/00 ,  B64C2009/005 ,  Y02T50/44

Abstract: A structure of a control surface for aircrafts, such as elevators, rudders, landing flaps, ailerons, and other similar lifting surfaces. The control surface includes a front spar, a rear spar, a plurality of ribs, at least one hinge fitting, and at least one actuator fitting, the hinge and actuator fittings joined with the front spar. A first rib is joined with a hinge fitting to form a first oblique angle with the front spar; a second rib is joined with an actuator fitting to form a second oblique angle with the front spar. The rear spar, located between the front spar and trailing edge of the control surface, extends only between the second rib and an outboard end of the control surface. The ribs are located in correspondence with the main torsion and bending load paths created in the control surface during flight, landing or takeoff.

公开(公告)号：US20170341729A1

公开(公告)日：2017-11-30

申请号：US15540480

申请日：2015-12-21

Applicant: Airbus Operations S.L.

Inventor： Elena ARÉVALO RODRÍGUEZ ,  Francisco José CRUZ DOMÍNGUEZ ,  Ana Reyes MONEO PEÑACOBA

IPC: B64C5/02 ,  B64C1/12 ,  B64C1/26 ,  B64C1/14 ,  B64C1/10 ,  B64C1/00

CPC classification number: B64C5/02 ,  B64C1/061 ,  B64C1/10 ,  B64C1/12 ,  B64C1/1446 ,  B64C1/16 ,  B64C1/26 ,  B64C7/00 ,  B64C2001/0072 ,  B64D29/04 ,  B64D29/08 ,  B64D2041/002

Abstract: A fuselage rear end of an aircraft, comprising a structural part comprising a skin and longitudinal and transversal reinforcing members and a fairing. The structural part longitudinally spans over the whole rear end and comprises a first portion in which the transversal reinforcing members occupy the whole perimeter of the corresponding fuselage section and at least a second portion in which the transversal reinforcing members occupy only a portion of the perimeter of the corresponding fuselage section. The fairing is located below the second portion of the structural part.

公开(公告)号：US20170334545A1

公开(公告)日：2017-11-23

申请号：US15523074

申请日：2015-10-30

Applicant: Airbus Operations, S.L.

Inventor： Enrique GUINALDO FERNANDEZ ,  Carlos GARCIA NIETO ,  Iker VELEZ DE MENDIZABAL ALONSO ,  Javier Francisco HONORATO RUIZ ,  Jose Francisco CRUZ DOMINGUEZ ,  Luis RAMOS GARCIA

IPC: B64C5/02 ,  B64C1/26

CPC classification number: B64C5/02 ,  B64C1/26

Abstract: An aircraft horizontal tail plane (HTP) of the continuous type, wherein the inner-most ribs of the right-hand side and left-hand side torsion boxes are arranged to have one end joined right at the joint zone where both rear spars meet at axis of symmetry of the HTP. In this way, the loads at this central region of the HTP are concentrated at the joint zone where the inner-most ribs and the rear spars converge. The HTP can be manufactured with a reduced number of components.

公开(公告)号：US09766210B2

公开(公告)日：2017-09-19

申请号：US13828815

申请日：2013-03-14

Applicant: Airbus Operations, S.L.

Inventor： Desirée Guzman Rabanillo ,  Juan Ramón Astorga Ramírez ,  Javier Camacho De Miguel ,  Agustín Sáenz Fernandez ,  Maria Asunción Rivero Rastrero

IPC: G01N29/07 ,  B21J15/28 ,  G01N29/34

CPC classification number: G01N29/07 ,  B21J15/28 ,  B21J15/285 ,  G01N29/348 ,  G01N2291/2691

Abstract: A method for evaluating installation of blind rivets including measuring the “cycle time” represented “y0”, transmitting sound waves through the blind rivet installed in the structure, measuring the “travel time” represented “x0”, relating “travel time” and “cycle time”, and obtaining a pair of times (x0,y0), providing a time relation pattern establishing a borderline between an area of suitable rivets and an area of unsuitable rivets, the border represented y=f(x), so for cycle time values greater than y=f(x), it is considered a “suitable area”, for cycle time values less than y=f(x), it is considered an “unsuitable area”, representing pair (x0,y0) in the graphic representation and verifying if the value of y0 is greater or less than the value of y=f(x0), classifying installation of the rivet as suitable or unsuitable according to the verification.

公开(公告)号：US20170259899A1

公开(公告)日：2017-09-14

申请号：US15444498

申请日：2017-02-28

Applicant: Airbus Operations, S.L.

Inventor： Felipe Abellán Alzallu ,  Alberto Ramos Guerrero ,  Adolfo Ávila Gutierrez ,  Juan Carlos Monje Martin

IPC: B64C1/06

CPC classification number: B64C1/068 ,  B64C1/061 ,  B64C1/065 ,  B64C1/26 ,  B64C5/02

Abstract: A harness routing electrically connects a rear fuselage section of an aircraft and a trimmable Horizontal Tail Plane (HTP) installed at this rear section. The aircraft rear section includes a first clipping point wherein the harness is attached to a fuselage frame located in front of the torsion box front spar, and a second clipping point wherein the harness is attached to a front spar of the HTP torsion box. The second clipping point is located downstream the first clipping point from the fuselage towards the torsion box interior, and the harness passes through the front spar towards the interior of the torsion box downstream the second clipping point. The harness installation and routing is optimized, in order to reduce harness length and weight, but at the same time assuring that any damage to the harness cables are prevented during the entire aircraft operative life.

公开(公告)号：US20170253004A1

公开(公告)日：2017-09-07

申请号：US15448800

申请日：2017-03-03

Applicant: Airbus Operations, S.L.

Inventor： Fernando Pereira Mosqueira ,  Andrea Ivan Marasco ,  Esteban Martino Gonzalez

IPC: B32B3/12 ,  B32B27/20 ,  B32B15/01

CPC classification number: B32B3/12 ,  B29D99/0089 ,  B32B3/02 ,  B32B5/26 ,  B32B5/28 ,  B32B7/02 ,  B32B15/01 ,  B32B15/016 ,  B32B15/20 ,  B32B27/20 ,  B32B2250/03 ,  B32B2250/05 ,  B32B2250/40 ,  B32B2307/50 ,  B32B2307/558 ,  B32B2571/00 ,  B32B2605/18 ,  B33Y80/00 ,  B64C1/062 ,  B64C1/12 ,  B64C7/00 ,  B64D45/00 ,  B64D2045/0095

Abstract: A sandwich structure architecture for high speed impact resistant structure includes sandwich skins which enclose a sandwich core formed by a plurality of spacing layers and a plurality of trigger layers, wherein these layers are stacked alternatively in the core. The walls of the trigger layers are thicker than the walls of the spacing layers and/or the walls of the trigger layers include at least one part inclined with respect to the walls of the spacing layers. The spacing and the trigger layers are made of the same type of material, preferably composite materials or metallic materials. The structure is capable of absorbing high-speed impacts, and at the same time can be used as load carrying structure in aircraft fuselages, wings, vertical or horizontal stabilizers.