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公开(公告)号：US12110093B2
公开(公告)日：2024-10-08
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： B64C1/20
CPC分类号： B64C1/20
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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2.发明公开公开(公告)号：US20240327019A1
公开(公告)日：2024-10-03
申请号：US18616576
申请日：2024-03-26
发明人： François Pons , Christian Flemin
摘要： An aircraft propulsion assembly with at least one ventilation device to cool at least one zone of the propulsion assembly. The ventilation device is regulated and includes at least one ventilation hole emerging in the zone to be cooled, at least one valve movable between a closed position where the valve shuts the ventilation hole and an open position where the valve at least partially frees the ventilation hole, at least one thermoelectric generator to generate an electric current and at least one automatic control to control the position of the valve by using the electrical current generated by the thermoelectric generator. The bleed air flow rate can be adjusted as a function of the cooling needs. An aircraft including at least one such propulsion assembly is disclosed.
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公开(公告)号：US12023879B2
公开(公告)日：2024-07-02
申请号：US16584555
申请日：2019-09-26
发明人： Alain Porte , Jacques Lalane , Hassan Menay
CPC分类号： B29C70/882 , B29C65/02 , B29C70/545 , B32B37/06 , B64D33/02 , B32B2038/047 , B32B2305/02 , B32B2305/07 , B32B2305/38 , B32B2313/04 , B64D2033/0206 , B64D2033/0233
摘要： A method for manufacturing deicing acoustic skin for an aircraft acoustic panel, using a fiber spacing device. The manufacturing method includes at least one step for manufacturing a layer assembly having a deicing layer supplied with electrically conductive fibers embedded in a resin and two insulating layers arranged on either side of the deicing layer, and a baking step. The method provides for fitting, during baking, a spacing device on the layer assembly, the spacing device having pins passing through said layer assembly, perforations being produced at the locations of the pins after the withdrawal of the spacing device, the fitting of the spacing device making it possible to produce perforations with desired sizes and shapes, in a simple and effective manner, and with a reduced manufacturing duration.
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公开(公告)号：US12017756B2
公开(公告)日：2024-06-25
申请号：US17983782
申请日：2022-11-09
发明人： Benoit Orteu , Ludovic Mil , Lionel Laganier , Dominique Marty , Philippe Robert
摘要： A structural assembly for an aircraft having pairs of main gantries distributed in the longitudinal direction, two transverse panels fixed to the front and the rear of the pairs of main gantries to together define a compartment for a landing gear of the aircraft, at least one pair of secondary gantries between the main gantries, at least one crossmember parallel to the transverse panels and that straddles at least one secondary gantry, and, for each secondary gantry and each crossmember straddling the secondary gantry, a connecting rod mounted to be able to freely rotate, via a first end, on a lower part of the crossmember and, via a second end, on an outer lateral part of the secondary gantry. Such an arrangement reduces the vertical bulk of the structural assembly.
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公开(公告)号：US12011754B2
公开(公告)日：2024-06-18
申请号：US17871482
申请日：2022-07-22
发明人： César Garnier
IPC分类号： B21D26/021 , B21D53/92
CPC分类号： B21D26/021 , B21D53/92
摘要： A method and a device for manufacturing a part starting from a cushion made of deformable material, in particular for an edge of an element of an aircraft. The device includes a preparation unit to create a cushion with two plates and, between the plates, an internal space with an opening, and a molding unit comprising a mold in which the cushion is positioned, the mold comprising two shells and an imprint corresponding to the shape of the part to be manufactured, the molding unit configured to inject a pressurized fluid into the internal space of the cushion through the opening to deform the cushion such that it matches the imprint and forms the part, the device being capable of manufacturing one-piece parts of various sizes, and in particular parts having complex shapes, in particular non-developable shapes.
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公开(公告)号：US11987390B2
公开(公告)日：2024-05-21
申请号：US17165076
申请日：2021-02-02
CPC分类号： B64F5/10 , B64C2001/0045 , B64C1/18
摘要： To make an aircraft assembly installation modulable, the latter includes a floor, assembly stations distributed on the floor, and structures for accessing the aircraft during their assembly, each structure being mobile on the ground. The access structures include at least one access structure at an orbital junction between two fuselage sections, at least one access structure at the two junctions between a fuselage section and each of the two aircraft wings, and at least one access structure at the junctions between a rear fuselage section and tail units. In addition, the installation is designed to be able to adopt several distinct configurations, each having a different distribution of the access structures between the assembly stations.
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公开(公告)号：US20240151184A1
公开(公告)日：2024-05-09
申请号：US18519489
申请日：2023-11-27
发明人： Petros Manaras , Brian Sagar
CPC分类号： F02C7/232 , B64D37/005 , B64F5/60 , F16K37/0083 , F05D2260/80
摘要： A method of determining an operating condition of a valve of an aircraft system includes obtaining a first time period associated with actuating the valve, and a second time period associated with actuating the valve. The method includes providing an indication of an altered operating condition associated with actuation of the valve based on the first and second time periods.
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8.发明公开公开(公告)号：US20240124148A1
公开(公告)日：2024-04-18
申请号：US18333897
申请日：2023-06-13
CPC分类号： B64D29/06 , F02K1/763 , B64D2033/0206
摘要： A nacelle includes a thrust reverser having a cowl movable in translation and an ejection structure also movable in translation and forming with the cowl a moving assembly, the moving assembly configured to moved, alternately, into a closed position in which the ejection structure is inserted into a housing formed in the nacelle and the cowl closes an ejection opening in the nacelle, and an open position in which the cowl releases the ejection opening in the nacelle and the ejection structure is located in this ejection opening, the positioning of the ejection structure in the housing in the closed position making it possible, in particular, to make space in the ejection opening and to reduce the size of the thrust reverser.
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9.发明授权公开(公告)号：US11919259B2
公开(公告)日：2024-03-05
申请号：US17161062
申请日：2021-01-28
发明人： Jago Pridie
IPC分类号： B29C70/46 , B29K105/08 , B29K307/04 , B29L31/30
CPC分类号： B29C70/462 , B29K2105/089 , B29K2307/04 , B29L2031/3085
摘要： A method for fabricating a central caisson of an aircraft wing including a frame formed from U-section crossmembers. Formation of at least one crossmember includes forming a stack comprising at least one layer of resin film applied to a layer of dry fibers, pressing this stack to confer on it a U-section form and such as to compress the layers thereof, and pre-polymerization and/or polymerization of the resin of the stack. The manipulated fiber layers are layers of dry fibers, such that manipulation thereof by an automated machine may be effected for a reasonable cost and at a high throughput. Deposition of resin films carried by removable leaves, i.e., of which one of the faces is not adhesive, likewise facilitates manipulation by an automated installation.
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公开(公告)号：US11878809B2
公开(公告)日：2024-01-23
申请号：US16355999
申请日：2019-03-18
IPC分类号： B64D33/02 , F02K3/077 , B64C7/02 , F02K3/12 , B64D29/00 , F01D25/24 , F02K3/04 , B64D33/04 , B64D27/10 , B64D27/16
CPC分类号： B64D33/02 , B64C7/02 , B64D27/10 , B64D27/16 , B64D29/00 , B64D33/04 , F01D25/24 , F02K3/04 , F02K3/077 , F02K3/12 , B64D2033/0266 , F05D2220/323
摘要： An aircraft propulsion assembly includes a first engine and a second engine that are adjacent and a nacelle in which the engines are installed. The nacelle includes a common air inlet lip for the first engine and the second engine, the air flow being divided between the first engine and the second engine by a median lip which extends, at least partly, set back from said common air inlet lip. The common are inlet lip includes, directly in line with the median lip, a bottom lobe and a top lobe extending forward of the nacelle. Such a configuration makes it possible to be able to provide a high aerodynamic form between the fairings of the engines, without the risk of generating overspeeds in the air flow.
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