公开(公告)号：US11319047B2

公开(公告)日：2022-05-03

申请号：US15957289

申请日：2018-04-19

Applicant: Airbus Operations, S.L.

Inventor： Iker Vélez De Mendizábal Alonso ,  Esteban Martino González ,  David Apellaniz De La Fuente ,  Alfonso Parra Rubio ,  Elena Moya Sanz

IPC: B64D45/00 ,  B64D33/02 ,  B33Y10/00 ,  B33Y80/00 ,  B21D5/16 ,  B29K101/12 ,  B29L31/08 ,  B29L31/30 ,  B64C1/12 ,  F01D5/14 ,  A43B1/00 ,  B29D99/00 ,  F01D21/14 ,  B64C11/26 ,  F01D11/00 ,  B31D3/02 ,  A43B13/02 ,  A43B13/14 ,  B29C53/04 ,  B32B3/12 ,  B32B15/01 ,  B32B27/08 ,  B64C3/26 ,  B64C11/20 ,  B64C1/00 ,  F01D5/28 ,  B64C27/473 ,  F01D21/04

Abstract: A three-dimensional auxetic structure, comprising a plurality of adjoining hollow cells, each hollow cell having cell walls and a transversal cross section of the plurality hollow cells following a two-dimensional auxetic pattern, each cell wall comprising folding lines parallel to a plane containing the auxetic pattern such that peaks and valleys are defined in the cell walls and the cell walls being foldable along the folding lines.

公开(公告)号：US11215118B2

公开(公告)日：2022-01-04

申请号：US16712232

申请日：2019-12-12

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

Inventor： Bruno Medda ,  Thomas Stevens ,  Julien Cayssials ,  Adeline Soulie ,  Didier Poirier ,  Pierre-Alain Pinault ,  Esteban Martino González ,  Juan Tomas Prieto Padilla ,  Diego Barron Vega

IPC: F02C7/10 ,  B64D27/18 ,  B64D29/02 ,  B64D33/04 ,  F02C7/047 ,  F02C6/08 ,  F02C7/14 ,  B64D13/06

Abstract: An aircraft propulsion system including a turbojet and heat exchanger system including a heat exchanger. A supply connection and evacuation connection are forward, and aft are a transfer connection and a scoop connection, a supply pipe connected to the supply connection, and which bleeds hot air from the compression stages. A transfer pipe connected to the transfer connection transfers hot air to an air management system. A scoop connected to a scoop connection bleeds cold air from a fan duct and an evacuation pipe, including an inlet connected to the evacuation connection and an outlet, which emerges on the outside, where hot air through the heat exchanger from the supply pipe to the transfer pipe passes along a first transfer direction and cold air passes through the heat exchanger from each scoop to the inlet along a second transfer direction parallel to the first transfer direction in the opposite direction.

公开(公告)号：US10882597B2

公开(公告)日：2021-01-05

申请号：US15921399

申请日：2018-03-14

Applicant: AIRBUS OPERATIONS S.L.

Inventor： Edouard Menard ,  Esteban Martino González ,  Fernando Iniesta Lozano

IPC: B64C1/06 ,  F41H5/04

Abstract: An impact resistant fuselage of an aircraft, the fuselage extending along a central longitudinal direction, wherein transversal sections of the fuselage are comprised in a vertical plane perpendicular to the central longitudinal direction. The impact resistant fuselage comprises at least a ballistic material membrane extended along the longitudinal direction for absorbing high energy impacts. The membrane according to a transversal section, comprising at least one section between two tensional elements, wherein the material membrane is located inside the fuselage of the aircraft, the at least one section of the membrane is mechanically linked to the inside of the fuselage by the tensional elements, and the two tensional elements stress the membrane.

公开(公告)号：US10773790B2

公开(公告)日：2020-09-15

申请号：US15843203

申请日：2017-12-15

Applicant: AIRBUS OPERATIONS S.L.

Inventor： Edouard Menard ,  Esteban Martino González ,  Fernando Iniesta Lozano

IPC: B64C5/06 ,  B64C1/12 ,  B64C1/00 ,  B64D45/00

Abstract: An impact resistant dorsal fin structure of an aircraft comprises an upper support and ballistic material layer, wherein the ballistic material layer is configured to be joined to an aircraft fuselage and the ballistic material layer is arranged in a sliding manner around a sliding surface of the upper support.

公开(公告)号：US09359085B2

公开(公告)日：2016-06-07

申请号：US13724360

申请日：2012-12-21

Applicant: AIRBUS OPERATIONS S.L.

Inventor： Diego Folch Cortés ,  Eduardo Vinué Santolalla ,  Esteban Martino González ,  Julien Guillemaut ,  Pablo Goya Abaurrea

IPC: B64D45/00 ,  B64C1/06 ,  B64D27/14 ,  B64D27/02 ,  B64C1/10 ,  B64D27/20 ,  B64D27/00

CPC classification number: B64D45/00 ,  B64C1/06 ,  B64C1/10 ,  B64D27/02 ,  B64D27/14 ,  B64D27/20 ,  B64D2027/005 ,  Y02T50/66

Abstract: Internal shield in the rear fuselage of an aircraft having a propulsion system formed by two engines mounted on each side of it; the rear fuselage having at least a vertical symmetry plane; the rear fuselage being made of a composite material; the internal shield being located in said vertical symmetry plane and extended in an area that covers the possible trajectories of a set of pre-defined fragments detached from one of said engines in a failure event that would impact on critical elements of the opposite engine; the internal shield having a flat shape and an energy absorption capability that allows stopping said fragments. The invention also refers to a method for determining the area of an internal shield and to an aircraft having said internal shield.

Abstract translation: 具有由安装在其每侧的两个发动机形成的推进系统的飞行器的后机身中的内部盾构; 后机身至少具有垂直对称平面; 后机身由复合材料制成; 所述内部屏蔽件位于所述垂直对称平面中，并且延伸在覆盖一组预定义片段的可能轨迹的区域中，所述一组预先定义的片段在将影响相对发动机的关键元件的故障事件中与所述发动机中的一个分离; 内部屏蔽具有平坦的形状和能量吸收能力，其允许停止所述碎片。 本发明还涉及一种用于确定内部屏蔽件和具有所述内部屏蔽件的飞行器的面积的方法。

公开(公告)号：US10414497B2

公开(公告)日：2019-09-17

申请号：US15704114

申请日：2017-09-14

Applicant: AIRBUS OPERATIONS S.L.

Inventor： Iker Vélez De Mendizábal Alonso ,  Esteban Martino González ,  Carlos García Nieto ,  Edouard Menard ,  Enrique Guinaldo Fernández ,  Soledad Crespo Peña ,  Jesús Javier Vázquez Castro

IPC: B64D7/00 ,  B32B5/02 ,  B32B15/14 ,  B64C1/06 ,  B64C1/12 ,  F01D21/04 ,  F41H5/04

Abstract: A lightweight shield for aircraft protection against threat of high energy impacts, which comprises, a structural layer that has a first side and a second side, the first side being intended for receiving the impact, and a ballistic material layer for absorbing high energy impacts, having a first side and a second side. The first side of the ballistic material layer is faced to the second side of structural layer and joined to the structural layer via a progressively detachable interface and, the second side of the ballistic material layer is a free surface.

公开(公告)号：US10358206B2

公开(公告)日：2019-07-23

申请号：US14975338

申请日：2015-12-18

Applicant: AIRBUS OPERATIONS S.L. ,  AIRBUS OPERATIONS (S.A.S.)

Inventor： Javier Toral Vázquez ,  Diego Folch Cortes ,  Esteban Martino González ,  Pablo Goya Abaurrea ,  Vasillis Votsios ,  Michel Fouinnetau ,  Sylvain Roumegas

IPC: B64C11/20

Abstract: A self-destruction device adapted to be installed in a propeller blade, the self-destruction device including a detector adapted to detect a release of the propeller blade, a warning mechanism adapted to send a release alarm in the event of the detector detecting release of the propeller blade, and a destruction mechanism adapted to destroy the propeller blade in the event of receiving a release alarm from the warning mechanism. An engine and an aircraft are also provided.