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11.发明公开公开(公告)号：US20230365252A1
公开(公告)日：2023-11-16
申请号：US18317207
申请日：2023-05-15
发明人： Jérôme Antypas
IPC分类号： B64C25/16
CPC分类号： B64C25/16
摘要： A set of doors includes two front doors and two rear doors to open or close the front landing gear bay of the aircraft to enable lowering or retraction of a landing gear, each of the front doors including at least one deflector arranged on an internal face of the front door near a rear leading edge thereof, the deflector extending along the rear leading edge, the set therefore enabling action on an aerodynamic flow between the front doors to disturb it in such a manner as significantly to attenuate undesirable transitory vibratory phenomena that can arise in a particular configuration in which the front doors are open and the rear doors are closed.
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公开(公告)号：US11807374B2
公开(公告)日：2023-11-07
申请号：US17947273
申请日：2022-09-19
CPC分类号： B64D27/26 , F02C7/20 , B64D2027/268
摘要： A propulsion assembly includes an engine below a pylon by engine attachments, including a thrust force uptake device, the engine having a longitudinal axis and a vertical median plane parallel to the longitudinal axis, the thrust force uptake device having a main fitting fixed below the pylon and two links disposed on either side of the vertical median plane and which each have a rear end articulated to the main fitting by a spreader mounted to pivot on the main fitting about an axis of rotation which, on the one hand, is orthogonal to a mean plane for transmitting thrust forces parallel to the longitudinal axis of each of the links, and which is disposed in the vertical median plane, each link being articulated to the spreader by a connecting pin extending parallel to the mean plane for transmitting thrust forces and perpendicular to the longitudinal axis of the link.
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公开(公告)号：US11746705B2
公开(公告)日：2023-09-05
申请号：US16682271
申请日：2019-11-13
IPC分类号： F02C7/24 , B64D29/00 , G10K11/168
CPC分类号： F02C7/24 , B64D29/00 , G10K11/168 , F05D2260/96
摘要： A method for manufacturing an acoustic element of a sound absorption structure including at least one cylindrical, conical or truncated conical chamber obtained from a flat preform shaped and then assembled in order to obtain the cylindrical, conical or truncated conical shape of the chamber. This manufacturing method makes it possible to obtain an acoustic element that has thin walls and is made from a material suited to its environment. An acoustic element obtained using the manufacturing method, a sound absorption structure comprising at least one such acoustic element and an aircraft powerplant comprising at least one such structure are also described.
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公开(公告)号：US11686340B2
公开(公告)日：2023-06-27
申请号：US17104225
申请日：2020-11-25
发明人： Frédéric Goupil
CPC分类号： F16C11/045 , B64C1/06 , F16B5/02 , Y10T403/32861 , Y10T403/32909
摘要： A device for fitting two components together by a clevis is improved by a seal including a deformable ring subjected to axial compression between one of the cheeks and a mobile washer which is brought closer to the cheek when a bolt passing through the clevis is tightened. This axial compression causes the rod to be clamped by the seal, eliminating all play and giving the assembly good cohesion while at the same time eliminating the transmission of vibration and noise.
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公开(公告)号：US11679889B2
公开(公告)日：2023-06-20
申请号：US16440214
申请日：2019-06-13
CPC分类号： B64D29/06 , B64C7/02 , F01D25/243 , F05D2260/30
摘要： A nacelle of an aircraft propulsion assembly includes a front section and a main section. The nacelle also includes a junction flange between the front section and the main section including a plurality of deformable damper elements distributed along the inner peripheral edge of a stiffening frame of the nacelle. The damper element allows significant stresses to be absorbed between the engine flange and the stiffening frame. This configuration is particularly adapted to large nacelles. An aircraft propulsion assembly including such a nacelle is also described.
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公开(公告)号：US20230182426A1
公开(公告)日：2023-06-15
申请号：US18064664
申请日：2022-12-12
发明人： Jago Pridie
CPC分类号： B29D99/0014 , B29C51/261 , B29C70/30 , B29C70/46 , B29C70/446 , B29C70/543 , B29K2105/253
摘要： A device for manufacturing a stiffened panel with reinforcements which each have a final thickness and a final height. The manufacturing device includes tools configured to each support a preform of fibers having a U-shaped or C-shaped cross section with a base and two wings. Each tool comprises, at at least one of its first and second lateral faces, a set-back portion which, when two tools are juxtaposed, delimits a recess configured to form a reinforcement during a consolidation or polymerization step. The tools are dimensioned such that each recess has a width, at the consolidation or polymerization temperature, that is substantially equal to the thickness of the reinforcements. This solution makes it possible to more effectively control the geometry of the stiffened panel by avoiding the formation of beads. A method for manufacturing a stiffened panel using the device is also disclosed.
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公开(公告)号：US20230141505A1
公开(公告)日：2023-05-11
申请号：US17982999
申请日：2022-11-08
发明人： Benoit Orteu , Ludovic Mil , Lionel Laganier , Dominique Marty , Philippe Robert
IPC分类号： B64C1/18
CPC分类号： B64C1/18
摘要： An aircraft including a floor positioned above a central wing box and in a front fuselage portion positioned in front of the central wing box. The floor includes at least one rail which has at least first and second rail portions and at least one articulation connecting the first and second rail portions and configured to allow a pivoting movement, about a transverse and horizontal pivot pin, between the connected first and second rail portions. By virtue of this articulation, it is possible to integrate the rails into the floor and not to position them on the floor.
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公开(公告)号：US11643223B2
公开(公告)日：2023-05-09
申请号：US17487617
申请日：2021-09-28
发明人： Cédric Godard , Florian Collado , Jacques Bouriquet , Jean-Marc Datas , Nicolas Darbonville , André Aquila
摘要： A facility for simplifying the facilities and tools required to assemble a first aircraft fuselage section and a second aircraft fuselage section by the ends thereof, these sections being fragile, large elements. The facility includes a logistics trolley that can be moved on the floor and immobilized in a position to carry the first section, at least one adjustable support installed on the floor at another position that is adjustable with six degrees of freedom, to carry the second section. Each support can be commanded to adjust the position of the second section in relation to the first section, such as to position one end of the second section in geometric conformity with one end of the first section. This arrangement enables all movements to be made directly on the floor, obviating the need to provide lifting machines or overhead traveling cranes within the assembly facility.
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公开(公告)号：US11642866B2
公开(公告)日：2023-05-09
申请号：US17218542
申请日：2021-03-31
发明人： Gautier Destombes , Benoît Penven
CPC分类号： B32B3/12 , B32B27/065 , B32B38/0004 , B32B2250/03 , B32B2262/106 , B32B2266/06 , B32B2266/08 , B32B2305/022 , B32B2605/18 , B65H35/02 , Y10T156/1067 , Y10T156/1087
摘要： A method for manufacturing structural rods to make it easier to manufacture a structural rod for an aircraft and to improve performance. Each rod includes a rod body and two end portions disposed at either end of the rod body along a longitudinal central rod axis, each end portion comprising at least one mounting lug that protrudes from the rod body along the longitudinal axis. The method includes producing a sandwich panel including two skins gripping a cellular inner body, at least one of the two outer skins having a skin extension for forming a part of the at least one mounting lug of at least one of the two end portions of the rod, and cutting the panel along parallel cutting lines to obtain the structural rods.
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20.发明授权公开(公告)号：US11623732B2
公开(公告)日：2023-04-11
申请号：US17155583
申请日：2021-01-22
发明人： Frédéric Goupil
摘要： To improve the seal between a wing and a ventral fairing of an aircraft, an assembly includes an air seal system arranged in an opening, between the ventral fairing and the wing. The seal system includes a sealing blade, a first end of which presses against the wing, and a connecting device, on the ventral fairing, for a second blade end that is opposite the first end. The connecting device includes at least one first connecting layer, of which a first connecting face is secured to a first surface of the sealing blade, and of which a second face, opposite the first face, is secured to the ventral fairing, the first connecting layer being made of a material including an elastomer.
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