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公开(公告)号：EP4450400A1
公开(公告)日：2024-10-23
申请号：EP23382352.5
申请日：2023-04-17
摘要： The invention provides an aircraft section comprising a fuel storage tank, a first strap, a second strap, at least one anchoring structure and at least one coupling portion; wherein: the first strap comprises two attachment portions anchored to the at least one anchoring structure; the second strap comprises two attachment portions anchored to the at least one anchoring structure; and the first strap and the second strap are arranged under tension such that the tank is maintained pressed against the at least one coupling portion by the first strap and the second strap.
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2.发明公开
公开(公告)号：EP4432039A1
公开(公告)日：2024-09-18
申请号：EP23382231.1
申请日：2023-03-13
IPC分类号： G05D1/02
CPC分类号： G06Q10/08 , G06Q10/0631 , G06Q50/04 , G05D2109/1020240101 , G05D2107/7020240101 , G05D2105/4520240101 , G05D1/6985 , G05D2105/4720240101 , G05D1/697
摘要： The invention relates to a mobile autonomous manufacturing system comprising an autonomously mobile main device (10) performing a manufacturing task, a first auxiliary device (11) adapted to autonomously supply energy to the main device (10), a second auxiliary device (12), adapted to autonomously supply manufacturing items to the main device (10). The invention also relates to a method for operating such a mobile autonomous manufacturing system, in which the auxiliary devices (11,12) move autonomously to and from the main device (10) and synchronously with the main device (10) when supplying the main device (10).
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公开(公告)号：EP4417520A1
公开(公告)日：2024-08-21
申请号：EP23382141.2
申请日：2023-02-15
CPC分类号： B64D37/34 , B64D37/30 , B64D41/00 , F02D41/0025 , F02D41/0027 , F02D2200/040620130101 , F02D2200/041420130101 , F02C7/22 , F05D2220/5020130101 , B64D2041/00220130101 , F02M21/0206 , F02D19/027 , F02D19/022
摘要： The present invention relates to a conditioning system (100) for an aircraft. More particularly, the present invention relates to an auxiliary power system (20) with a new fuel feed architecture including a fuel tank (6). In addition, the present invention also refers to an aircraft comprising said conditioning system and a method for conditioning fuel of an auxiliary power system (20).
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公开(公告)号：EP4385902A1
公开(公告)日：2024-06-19
申请号：EP22383210.6
申请日：2022-12-13
发明人： DAVID, Benjamin , CHIABRANDO, Marcos Javier , ZAMARRO MARTÍN, María Cruz , ANDREU FERNÁNDEZ, Francisco Manuel , CASADO MONTERO, Carlos
CPC分类号： B64D2221/0020130101 , H02J2310/4420200101 , B64D41/00
摘要： The present invention relates to auxiliary power generator systems for an aircraft. More particular, the present invention relates to an auxiliary power system with a new architecture that include an essential auxiliary power unit (APU) with dual and fully redundant starter and electrical power generation systems that can connect independently to a normal electric network or an emergency electric network of an aircraft. In addition, the present invention also relates to an aircraft comprising said auxiliary power system and a method for supplying electric power to an aircraft by means of said system.
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5.发明公开
公开(公告)号：EP4350324A1
公开(公告)日：2024-04-10
申请号：EP22382930.0
申请日：2022-10-05
发明人： Vázquez Castro, Jesús Javier , Nogueroles Viñes, Pedro , López Romano, Bernardo , Perez Pastor, Augusto , Calero Casanova, Alvaro , Martín Isabel, Julian , Delgado Labrandero, Sofia
摘要： The invention relates to a device and a method for testing a material sample (10) in which the material sample is attached to a first fastening element (11) and a second fastening element (12), with and intermediate frame (13) in between, and the material sample is elongated along a longitudinal direction (18) by pulling the first fastening element (11) apart from the second fastening element (12), while at least one wedge (14.1, 14.2) is inserted between the intermediate frame (13) and a fastening element (11, 12) as the material sample deforms in order to maintain the elongation of the material sample (10) against an elastic retraction force.
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公开(公告)号：EP4306285A1
公开(公告)日：2024-01-17
申请号：EP22382677.7
申请日：2022-07-15
发明人： MIGUEZ CHARINES, Yolanda , CARRASCAL IGLESIAS, Asuncion , DÍAZ RABOSO, Irene , DE BENITO NAVARRO, Irache
摘要： Composite part manufacturing method comprising the following consecutive steps:
- providing a manufacturing tooling (1),
- providing a composite laminate (2) on the manufacturing tooling (1),
- providing a release film (6) covering the composite laminate (2),
- providing a breather fabric (3) covering the release film (6),
- providing a vacuum bag film (4) covering the composite laminate (2), the release film (6) and the breather fabric (3),
- sealing the vacuum bag film (4) to the manufacturing tooling (1),
- curing the composite laminate (2),
- unsealing the vacuum bag film (4) from the manufacturing tooling (1),
- removing the vacuum bag film (4),
- removing the breather fabric (3),
- inspecting the breather fabric (3) to detect resin residues,
- if any, removing the resin residues from the breather fabric (3),
- transporting the removed breather fabric (3) to a manufacturing process of another composite part.-
公开(公告)号：EP4257969A1
公开(公告)日：2023-10-11
申请号：EP22382341.0
申请日：2022-04-08
摘要： Non-destructive inspection device of structural parts of an aircraft, the aircraft structural parts comprising an area to be inspected, the inspection device comprising:
- at least one ultrasonic transducer (2) configured to emit an ultrasonic beam,
- a support element (1) holding the at least one ultrasonic transducer (2), the support element (1) configured to be in contact with the area to be inspected, and
- clamping means (3) in connection with the support element (1) and configured to clamp the support element (1) to the area to be inspected.-
8.发明公开
公开(公告)号：EP4198799A1
公开(公告)日：2023-06-21
申请号：EP21383166.2
申请日：2021-12-20
摘要： The present disclosure belongs to the field of configuring the shape or geometry of an aircraft airfoil (1.1 - 1.7). In particular, the present invention provides a method to design the external geometry of an aircraft airfoil.
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公开(公告)号：EP4191105A1
公开(公告)日：2023-06-07
申请号：EP21383094.6
申请日：2021-12-03
发明人： CALDERON GOMEZ, Pablo Manuel ,
IPC分类号： F16K11/085 , F16K11/065 , B64D37/34 , F02C7/224
摘要： The invention relates to a valve (10) for a hydraulic circuit (51) for an aircraft (50), said valve being adapted to unit or separate multiple circuit portions (31, 32, 33, 34) in at least two configurations. More particularly the valve allows to create one hydraulic circuit or two independent hydraulic circuits in order to circulate a coolant in two distinct manners and thus to adapt the function of the hydraulic circuit (51) to any of two distinct phases of the functioning of an engine of the aircraft.
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公开(公告)号：EP4124790A1
公开(公告)日：2023-02-01
申请号：EP21382694.4
申请日：2021-07-27
发明人： HERNAIZ LOPEZ, Guillermo , BALLESTERO MÉNDEZ, Jorge , VAZQUEZ CASTRO, Jesus Javier , FERNANDEZ RAMIREZ, Ana
IPC分类号： F17C3/08
摘要： Hydrogen tank (100) for aircrafts, comprising an inner vessel (110) adapted to contain hydrogen, first and second outer jacket domes (120a, 120b) having a semi-sphere shape and first L-shaped ends (125), a first cylindrical outer jacket (130a) established on top of the first and second outer jacket domes (120a, 120b), a second cylindrical outer jacket (130b) established in the bottom of the first and second outer jacket domes (120a, 120b), the first and second cylindrical outer jackets (130a, 130b) comprise second L-shaped ends (135) and in that the first and second L-shaped ends (125, 135) form L-shaped junctions (400) to attach the first and second outer jacket domes (120a, 120b) to the first and second cylindrical outer jackets (130a, 130b).
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