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21.发明公开公开(公告)号：US20240150028A1
公开(公告)日：2024-05-09
申请号：US18502248
申请日：2023-11-06
IPC分类号： B64D27/26
CPC分类号： B64D27/26 , B64D2027/264
摘要： An assembly including a wing with a pressure-side panel and a suction-side panel through which two bores pass, an engine pylon including a blade with three bores and two fastening lugs, each of which has a sixth bore, two first shackles fastened between the blade and the suction-side panel, two second shackles fastened between the blade and the suction-side panel and two fittings, which are fastened beneath the pressure-side panel and each have a female clevis for housing a fastening lug therein.
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公开(公告)号：US11975858B2
公开(公告)日：2024-05-07
申请号：US17971680
申请日：2022-10-24
发明人： Lionel Czapla , Frédéric Piard
IPC分类号： B64D29/00
CPC分类号： B64D29/00
摘要： An aircraft nacelle comprising first and second ducts, each including, in a radial direction, at least one first or second acoustically resistive layer, at least one first or second alveolar structure, as well as a first or second reflective layer. The first and second ducts include first and second flanges which are positioned on transverse planes, oriented towards the interior, and are connected respectively to the first and second reflective layers and are maintained placed against one another by connection elements accessible from the interior of the first and second ducts. The first and second ducts are configured to form at least one receptacle in which there are positioned the first and second flanges as well as the connection elements, the receptacle being closed by at least one cap.
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公开(公告)号：US11975857B2
公开(公告)日：2024-05-07
申请号：US17899673
申请日：2022-08-31
发明人： Michael Berjot , Thomas Robiglio
摘要： A front engine attachment system having an engine pylon having a frontal rib fastened against a front face, a front engine attachment having a beam fastened to the frontal rib, two rods articulated to the beam respectively via two connection points and one connection point, and a front casing of an engine, wherein the first rod is articulated to the front casing via a connection point and wherein the second rod is articulated to the front casing via a connection point, wherein each point of connection of a rod to the beam is positioned inside a volume that extends the front face of the engine pylon towards the front. Such a front engine attachment system has reduced bulk and therefore less drag.
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公开(公告)号：US20240133351A1
公开(公告)日：2024-04-25
申请号：US18490833
申请日：2023-10-19
IPC分类号： F02K1/76
CPC分类号： F02K1/766 , F02K1/763 , F05D2220/323 , F05D2260/50
摘要： A turbofan with a nacelle having a fixed structure, a mobile assembly bearing second blocking element and able to move between an advanced position and a withdrawn position, a set of deflectors able to move in translation between an advanced position and a withdrawn position, and an actuation system having a carriage, a blocking lever bearing first attachment element and able to move between a blocking position and a free position, and a transmission system configured to move the blocking lever from the blocking position to the free position when the mobile assembly reaches a tilting position between the advanced position and the withdrawn position.
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公开(公告)号：US20240125284A1
公开(公告)日：2024-04-18
申请号：US18484548
申请日：2023-10-11
发明人： Lionel CZAPLA , Benjamin THUBERT
IPC分类号： F02K1/32
CPC分类号： F02K1/32
摘要： An aircraft propulsion assembly equipped with a thrust-reversing device which includes at least one lateral aperture, passing through the nacelle of the propulsion assembly, configured to be in an open state or a closed state, at least one inflatable barrier configured to be in a deflated state in which the barrier does not protrude into an annular duct channeling a flow of air and an inflated state in which the barrier, substantially rigid or semi-rigid, is deployed and extends across the annular duct to deflect at least a part of the flow of air toward the lateral aperture, and at least one supply system configured to supply the inflatable barrier with fluid. An aircraft is provided which includes at least one such propulsion assembly.
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26.发明公开公开(公告)号：US20240116648A1
公开(公告)日：2024-04-11
申请号：US18363426
申请日：2023-08-01
发明人： Anthony MERTES
IPC分类号： B64D37/04
CPC分类号： B64D37/04
摘要： An aircraft comprising a structure, a tank housed in the fuselage, and fastening means which comprise a front fastening system, a rear fastening system and a lateral fastening system. The front system comprises a front plate, two lateral connecting rods and a central connecting rod that are fastened between the front plate and the tank. The rear system comprises a rear plate and a rear connecting rod fastened between the rear plate and the tank. The lateral system comprises a lateral connecting rod fastened between the structure and the tank, wherein one of the connection points is behind the other connection point.
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公开(公告)号：US11952135B2
公开(公告)日：2024-04-09
申请号：US17851407
申请日：2022-06-28
发明人： Cédric Poupon , Olivier Pautis , Jonathan Blanc
CPC分类号： B64D27/26 , F16C11/0628 , B64D2027/262
摘要： A shackle for fastening an aircraft engine including a ball joint with a pin including a ring including a first bore and a sleeve assembled in the first bore and having a second bore configured to receive the pin and the diameter of which progressively increases to have a flared inner surface at each of its ends, the fastening shackle being arranged such that a spherical outer surface of the ring bears an anti-friction coating produced on a region extending beyond the contact region with the body of the shackle, this first region being bordered by rims forming a projection around the coating, and/or the second bore bears an anti-friction coating on a region extending beyond its contact region with the pin, this region being bordered by rims forming a projection around this anti-friction coating, at the ends of the flared inner surface.
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公开(公告)号：US11952109B2
公开(公告)日：2024-04-09
申请号：US17725597
申请日：2022-04-21
申请人： Airbus SAS , Airbus Operations SAS
IPC分类号： B64C25/28
CPC分类号： B64C25/28
摘要： A system for an aircraft comprising a controller configured to obtain a first piece of information regarding whether the aircraft has achieved lift-off; to obtain a second piece of information regarding whether the aircraft is in a flight phase in an initial part of lift-off; to determine, on the basis of at least the first piece of information whether the gear is retractable, and, if the gear is retractable in an initial part of the lift-off, to trigger a landing-gear-retraction alarm taking an audio form and/or a visual form, and, if the gear is retractable after the initial part of the lift-off to optionally trigger a second landing-gear-retraction alarm taking an audio form and/or a visual form. A method implemented by the system is provided. Advantageously, an omission of the retraction of the landing gear of an aircraft is notified to its flight crew.
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29.发明公开公开(公告)号：US20240111277A1
公开(公告)日：2024-04-04
申请号：US18460921
申请日：2023-09-05
IPC分类号： G05B19/418
CPC分类号： G05B19/41875 , G05B19/4183 , G05B19/41885
摘要： A method for estimating a residual stress field in a workpiece. The method includes measuring geometric parameters of the workpiece during machining at which a residual stress field is to be known to determine a geometric profile of said workpiece, estimating, from the geometric profile and an estimation model, subsequent deformations that the workpiece is liable to undergo during further machining, said estimation model being trained by machine learning on training workpieces to use the geometric profile of the workpiece and prerecorded data on the training workpieces to estimate said subsequent deformations of the workpiece, and estimating from the subsequent deformations and a simulation model, the residual stress field in the workpiece, said simulation model being a generic physical model based on simulations defining a variability of the residual stress field in the workpiece as a function of manufacturing parameters of the raw workpiece.
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公开(公告)号：US20240077889A1
公开(公告)日：2024-03-07
申请号：US18455884
申请日：2023-08-25
发明人： Stéphane DELANNOY , José TORRALBA
CPC分类号： G05D1/0833 , B64C13/16
摘要： A system for controlling aircraft flight control surfaces implements a method including: obtaining a control law for the flight control surfaces as a function of flight controls of the aircraft; obtaining measurements of ground speed, true speed, roll angle, pitch angle, angle of attack, sideslip angle and slope angle; performing an estimation of the wind in three dimensions using the measurements obtained; performing an adjustment of the control law for the flight control surfaces, to counter the estimated wind effect and to obtain an adjusted control law for the flight control surfaces, by adding, to the control law, a term for wind compensation comprising a term proportional to the derivative of the wind estimation; and controlling the aircraft by applying the adjusted control law. Thus, the impact of the wind on the aircraft is reduced by digital processing and automatic adjustment of the control of the flight control surfaces.
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