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公开(公告)号：US20210001991A1
公开(公告)日：2021-01-07
申请号：US16916559
申请日：2020-06-30
Applicant: Airbus Operations S.L.
Inventor： Esteban MARTINO-GONZALEZ , Juan Tomas PRIETO PADILLA
Abstract: An air management system with a set of compressed air sources for supplying pressurized air to air consumer equipment. In particular, either an air bleed system, electrical compressors, or a combination thereof may perform such supplying of compressed air depending on the aircraft operation condition.
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公开(公告)号：US20200291854A1
公开(公告)日：2020-09-17
申请号：US16814484
申请日：2020-03-10
Applicant: Airbus SAS , Airbus Operations SAS , Airbus Operations, S.L.
Inventor： Bruno MEDDA , Esteban MARTINO-GONZALEZ , Thomas STEVENS , Julien CAYSSIALS , Juan Tomas PRIETO PADILLA , Adeline SOULIE , Didier POIRIER , Pierre-Alain PINAULT , Diego BARRON VEGA
Abstract: An aircraft propulsion system including a turbojet and a heat exchanger system including a main heat exchanger, a hot air supply pipe and a regulating valve, a first pipe bleeding high pressure stage hot air through a first valve, a second pipe bleeding intermediate pressure stage hot air through a second valve, a transfer pipe transferring the hot air to an air management system, a main supply pipe supplying cold fan duct air via a main regulating valve, an evacuation pipe expelling air to the outside, a sub heat exchanger, wherein the first pipe goes through the sub heat exchanger, a sub supply pipe supplying cold fan duct air and including a sub regulating valve, a sub evacuation pipe expelling air to the fan duct, a temperature sensor measuring a hot air temperature exiting the main heat exchanger, and a controller controlling the valves according to the measured temperature.
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公开(公告)号：US20200023934A1
公开(公告)日：2020-01-23
申请号：US16515330
申请日：2019-07-18
Applicant: AIRBUS OPERATIONS S.L.
Inventor： Esteban MARTINO-GONZALEZ , Alberto ARANA HIDALGO , Melania SANCHEZ PEREZ , Carlos GARCIA NIETO , Jesus Javier VAZQUEZ CASTRO , Edouard MENARD , Fernando INIESTA LOZANO , Maria Almudena CANAS RIOS
Abstract: A method for manufacturing a composite rear section assembly having a continuous skin solution including obtaining a vertical tail plane tooling that has intermediate tooling for tooling intermediate preforms of a vertical tail plane (800), obtaining a fuselage barrel tooling (420a), (420b), (420c) and (420d) the fuselage barrel tooling having a cut-out (503a), (503b), (503c) and longitudinal cavities (501a), (501b), (501c) and (501d), attaching the vertical tail plane tooling to the fuselage barrel tooling by the cut-out of the fuselage barrel tooling, performing a composite skin lay-up (801) over the fuselage barrel tooling and the vertical tail plane tooling to obtain a continuous skin, curing the composite skin lay-up, the vertical tail plane tooling and the fuselage barrel tooling and demolding the tools to obtain the composite assembly with a continuous skin (1300), (1600).
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公开(公告)号：US20190382096A1
公开(公告)日：2019-12-19
申请号：US16442688
申请日：2019-06-17
Applicant: Airbus Operations S.L.
Inventor： Esteban MARTINO-GONZALEZ , Alberto ARANA HIDALGO , Melania SANCHEZ PEREZ , Carlos GARCIA NIETO , Jesus Javier VAZQUEZ CASTRO , Edouard MENARD , Fernando INIESTA LOZANO , Maria Almudena CANAS RIOS
IPC: B64C1/26
Abstract: A method for manufacturing a composite assembly with a continuous skin for a rear end of an aircraft by obtaining an upper part of the rear end by composite tooling. The upper part comprises a multi-spar vertical tail plane. The spars of the vertical tail plane comprise widening roots that form an upper shell of the rear end and an upper skin. Furthermore, a lower part comprises a lower shell of the rear end including semi-complete frames and stringers and a lower skin. The upper and lower parts are assembled with a joining procedure. The upper and lower skins are joined to obtain the composite assembly with the continuous skin.
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公开(公告)号：US20200291869A1
公开(公告)日：2020-09-17
申请号：US16814494
申请日：2020-03-10
Applicant: Airbus SAS , Airbus Operations SAS , Airbus Operations, S.L.
Inventor： Bruno MEDDA , Esteban MARTINO-GONZALEZ , Thomas STEVENS , Julien CAYSSIALS , Juan Tomas PRIETO PADILLA , Adeline SOULIE , Didier POIRIER , Pierre-Alain PINAULT , Diego BARRON VEGA
Abstract: An aircraft propulsion system, including a turbojet and a heat exchanger system which includes a main heat exchanger, a hot air supply pipe, a transfer pipe transferring hot air to an air management system, a main supply pipe supplying cold air from the fan duct, an evacuation pipe expelling air to the outside, a sub heat exchanger with a high pressure pipe going therethrough, a sub supply pipe supplying cold air and including a sub regulating valve, a sub evacuation pipe expelling air, a temperature sensor, and a controller controlling the system according to the temperature measured The sub regulating valve comprises a door articulated between closed and open positions, a return spring constraining the door in the open position, and a realizing system, controlled by the controller, mobile between a blocking position and a realizing position in which the door is released to move to the open position.
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Patent Agency Ranking
公开(公告)号：US20190382137A1
公开(公告)日：2019-12-19
申请号：US16441448
申请日：2019-06-14
Applicant: AIRBUS OPERATIONS S.L.
Inventor： Esteban MARTINO-GONZALEZ , Alberto ARANA HIDALGO , Melania SANCHEZ PEREZ , Carlos GARCIA NIETO , Jesus Javier VAZQUEZ CASTRO , Edouard MENARD , Fernando INIESTA LOZANO , Maria Almudena CANAS RIOS
Abstract: A method for manufacturing a composite assembly of an empennage and rear-fuselage having a continuous skin solution. The method obtains parts of the sub-structure. For each part, it is obtained a plurality of stringers performs and frames preforms by composite tooling. The frames are transferred to curing frames molds and a sub-structure skin is obtained. Furthermore, the method includes integrating the parts over an integration tool having cavities for locating the curing frames molds and the stringer performs. Furthermore, the method includes co-curing the integration tool in one shot on an autoclave, demolding the sub-structure skin sections and disassembling the curing frame molds to obtain the composite assembly of the rear section.
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公开(公告)号：US20200347782A1
公开(公告)日：2020-11-05
申请号：US16814506
申请日：2020-03-10
Applicant: Airbus SAS , Airbus Operations SAS , Airbus Operations, S.L.
Inventor： Bruno MEDDA , Esteban MARTINO-GONZALEZ , Thomas STEVENS , Julien CAYSSIALS , Juan Tomas PRIETO PADILLA , Adeline SOULIE , Didier POIRIER , Pierre-Alain PINAULT , Diego BARRON VEGA
Abstract: An aircraft propulsion system, including a turbojet and a heat exchanger system including a main heat exchanger, a hot air supply pipe and regulating valve, a high pressure pipe bleeding high pressure stage hot air through a first valve, an intermediate pressure pipe bleeding intermediate pressure stage hot air through a second valve, a pipe transferring hot air to an air management system, a main supply pipe supplying fan duct cold air including a main regulating valve, an evacuation pipe expelling air to the outside, a sub heat exchanger, wherein the supply pipe from the regulating valve goes through the sub heat exchanger, a sub supply pipe supplying cold air from the main supply pipe, a sub evacuation pipe expelling air to the fan duct, a temperature sensor measuring hot air temperature exiting the main heat exchanger, and a controller controlling the valves according to the measured temperature.
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公开(公告)号：US20190264610A1
公开(公告)日：2019-08-29
申请号：US16281799
申请日：2019-02-21
Applicant: Airbus Operations S.L.
Inventor： Esteban MARTINO-GONZALEZ , Iker VELEZ DE MENDIZABAL ALONSO , Vasilis VOTSIOS , Guillermo NICOLAS GUTIERREZ , Diego SANCHEZ FRANCO , David MATESANZ HIDALGO , Jose Angel HERNANZ-MANRIQUE
IPC: F02C7/042
Abstract: An auxetic bi-stable structure that comprises an auxetic curved shell movable between a first and a second stable position, and a rigid element. At least part of the surface of the auxetic curved shell is joined to the rigid element such that the curved shell is movable with respect to the rigid element between the first and second stable positions.
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公开(公告)号：US20190168480A1
公开(公告)日：2019-06-06
申请号：US16205973
申请日：2018-11-30
Applicant: Airbus Operations S.L.
Abstract: A deformable auxetic structure for absorbing energy of an impact that comprises a plurality of interconnected adjoining tridimensional auxetic cells where each tridimensional auxetic cell comprises at least one surface element and a plurality of legs extending from the surface, the plurality of legs and the surface element being configured such that the sectional cut of the structure in at least two planes perpendicular to the surface element follows an auxetic pattern.
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10.发明公开公开(公告)号：US20230406477A1
公开(公告)日：2023-12-21
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
CPC classification number: B64C1/1469 , B64D45/0061
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.
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