公开(公告)号：US10369762B2

公开(公告)日：2019-08-06

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: B32B5/18 ,  B32B3/12 ,  B32B15/01 ,  B32B27/20 ,  B32B5/26 ,  B32B5/28 ,  B32B7/02 ,  B32B15/20 ,  B29D99/00 ,  B32B3/02 ,  B64C1/06 ,  B33Y80/00

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.

公开(公告)号：US10124876B2

公开(公告)日：2018-11-13

申请号：US14952376

申请日：2015-11-25

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

Inventor： Esteban Martino Gonzalez ,  Diego Folch Cortes ,  Pablo Goya Abaurrea ,  Angel Pascual Fuertes ,  Sandra Linares Mendoza ,  Julien Guillemaut ,  Eric Bouchet ,  Jerome Colmagro ,  Jonathan Blanc

IPC: B64C1/06 ,  B64C1/12 ,  B64C1/16 ,  B64C1/26 ,  B64C3/32

Abstract: An aircraft fuselage frame including a central element adapted to be located within the perimeter of the fuselage, and two lateral extensions projecting outside the perimeter of the fuselage from both sides of the central element that are a portion of a longitudinal structure of a lifting surface. The central element and the two lateral extensions are configured as an integrated piece.

公开(公告)号：US10046848B2

公开(公告)日：2018-08-14

申请号：US15089675

申请日：2016-04-04

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

Inventor： Diego Folch Cortes ,  Esteban Martino Gonzalez ,  Jose Antonio Mariblanca Lopez ,  Lionel Diochon

IPC: B64C1/26 ,  B64C1/10 ,  B64C5/02 ,  B64C5/06

Abstract: An aircraft rear structure comprising a substantially flat rear pressure bulkhead, with a first side and a second side, opposite to the first side. The aircraft rear structure also comprises a horizontal stabilizer and a vertical stabilizer which in turn comprises a first spar and a second spar. The first spar is attached to a first attachment zone of the second side of the rear pressure bulkhead via first attaching elements, and the second spar is attached to a second attachment zone of the second side of the rear pressure bulkhead via second attaching elements. The second attachment zone being different from the first attachment zone.

公开(公告)号：US10023299B2

公开(公告)日：2018-07-17

申请号：US14757591

申请日：2015-12-23

Applicant: AIRBUS OPERATIONS, S.L.

Inventor： Javier Toral Vazquez ,  Diego Folch Cortes ,  Esteban Martino Gonzalez ,  Pablo Goya Abaurrea ,  Vasilis Votsios ,  Michel Fouinnetau ,  Sylvain Roumegas

IPC: B64C11/20 ,  B64C11/26

Abstract: The disclosure refers to a propeller blade for an aircraft engine that includes an airbag system contained inside the blade and comprising at least one bag and at least one gas generator, the at least one gas generator in fluid communication with at least one bag for inflating the bag, a detecting system for detecting a rupture of a part of the blade, a trigger for activating the at least one gas generator when the rupture is detected by the detecting system, and the blade skin being configured for allowing the at least one bag to pass through the blade skin for being expanded outside the blade upon the bag inflation by the gas generator.

公开(公告)号：US09656736B2

公开(公告)日：2017-05-23

申请号：US14695731

申请日：2015-04-24

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

Inventor： Julien Guillemaut ,  Esteban Martino Gonzalez ,  Diego Folch Cortes ,  Jerome Colmagro ,  Jonathan Blanc

IPC: B64C1/06 ,  B64C1/26

CPC classification number: B64C1/061 ,  B64C1/26 ,  B64D27/14

Abstract: In the case of an aircraft aft portion equipped with an engine mounting structure passing across the fuselage, assembly of the aft portion presents problems caused by the moving of the box structure of the mounting structure through lateral openings in the fuselage. In order to overcome these problems, a method of assembling an aircraft aft portion is proposed, in which method the box structure of the engine mounting structure is inserted into the fuselage through a top opening extending from one side of the fuselage to the other across a vertical midplane of the fuselage such that the top opening opens to the top and to the sides of the fuselage.