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公开(公告)号：US20240208663A1
公开(公告)日：2024-06-27
申请号：US18088221
申请日：2022-12-23
发明人： Paul Weaver , Bruno Chatelois
CPC分类号： B64D27/24 , B64C3/00 , B64D27/10 , B64D29/00 , B64D35/08 , F02K5/00 , H02K7/116 , H02K7/1823 , B64D2027/026
摘要： An aircraft system is provided that includes a propulsor rotor, a geartrain, a thermal engine, a drivetrain and an electric machine. The geartrain includes a power output, a first power input and a second power input. The power output is coupled to the propulsor rotor. The thermal engine is configured to drive rotation of the propulsor rotor through the geartrain. The thermal engine is coupled to the first power input. The drivetrain includes a first driveshaft and a second driveshaft. The first driveshaft is coupled to and between the second power input and the second driveshaft. The second driveshaft is angularly offset from the first driveshaft. The electric machine is configured to drive rotation of the propulsor rotor through the drivetrain and the geartrain. The second driveshaft is coupled to and between the first driveshaft and the electric machine.
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公开(公告)号：US11780576B1
公开(公告)日：2023-10-10
申请号：US17901200
申请日：2022-09-01
CPC分类号： B64C29/0033 , B64C3/00 , B64C39/024 , G05D1/102 , B64U30/20
摘要： An aircraft includes a fuselage and a wing system having first and second oppositely disposed wings that extend laterally from the fuselage. A tiltable propulsion system is rotatably coupled to the fuselage between the first and second wings. The tiltable propulsion system includes a frame system having four diagonally extending arms each having a propulsion assembly coupled thereto. A flight control system is configured to independently control each of the propulsion assemblies and the orientation of the tiltable propulsion system. In a VTOL flight mode of the aircraft, the tiltable propulsion system is substantially perpendicular to the aircraft's yaw axis in a vertical thrust orientation such that the propulsion assemblies are configured to provide vertical thrust. In a forward cruise flight mode of the aircraft, the tiltable propulsion system is substantially perpendicular to the aircraft's roll axis in a forward thrust orientation such that the propulsion assemblies provide forward thrust.
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3.发明公开公开(公告)号：US20230249833A1
公开(公告)日：2023-08-10
申请号：US18165670
申请日：2023-02-07
发明人： Ayaz Janjua Zaid , Matthias Haisch
CPC分类号： B64D15/06 , B64D15/16 , B64C29/0008 , B64C3/00
摘要： An airfoil of an aircraft with an ice protection system, the airfoil having a leading edge, the ice protection system comprising a first applying mechanism for applying an ice protection fluid along at least a portion of the leading edge of the airfoil, and an ice protection fluid recovering mechanism for recovering the ice protection fluid applied by the first applying mechanism, the ice protection fluid recovering mechanism being arranged downstream of the leading edge of the airfoil. The ice protection system further comprises a second applying mechanism for applying the ice protection fluid recovered by the ice protection fluid recovering mechanism on at least one area of the airfoil arranged downstream of the leading edge of the airfoil. An aircraft may comprise at least one airfoil provided with the ice protection system. A method may be used to protect the airfoil of an aircraft from ice accumulation.
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公开(公告)号：US11485473B2
公开(公告)日：2022-11-01
申请号：US17086343
申请日：2020-10-31
发明人： Matthew Kruse
摘要： An airfoil body for an aircraft extending from an inner end to an outer end, and between a leading edge and a trailing edge. The airfoil body comprises an internal structure and an airfoil skin covering the internal structure. The skin has a pressure side and a suction side, and the suction side includes a light transmitting portion. The internal structure includes an array of transduce elements attached to a planar sheet with the airfoil body. The present disclosure further relates to wings and aerial vehicles.
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5.发明授权公开(公告)号：US11440288B2
公开(公告)日：2022-09-13
申请号：US16557107
申请日：2019-08-30
发明人： Mark A. Calder , John F. Ellis , William David Dennison , Martin A. Wimmer , Earl L. Stone, III
IPC分类号： B32B3/00 , B32B5/00 , B32B37/00 , B29C65/00 , B64C3/00 , B32B5/26 , B64C3/20 , B32B3/30 , B32B5/02 , B64C3/26 , B64C3/18 , B32B37/06 , B29C65/02 , B29C65/18 , B29C65/30 , B29C65/32
摘要： A composite wingbox structure formed of reinforced thermoplastic. The composite includes carbon fiber reinforcement and a plurality of insulation elements to localize the heat formed during the process of manufacturing the structure. The process of manufacturing the wingbox includes the steps of interleaving a series of insulations elements within a plurality of laminae and consolidating the insulation elements and laminae to form a laminate. The laminate is then aligned with a support structure such that the insulation elements overlie the supports structure. The laminate is then fused to the support structure using a non-contact heating process, such as inductive welding.
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公开(公告)号：US11267554B2
公开(公告)日：2022-03-08
申请号：US16775873
申请日：2020-01-29
发明人： David Brakes , Eric Wildman
IPC分类号： B64C3/56 , B64C3/00 , F16F1/38 , B64C23/06 , F16F7/08 , B64C3/58 , B64C1/06 , F16F1/32 , B64C3/40 , F16B21/00 , B64C3/38 , B64C3/42
摘要： A locking pin associated with one of a fixed wing and a wing tip device, and a bush associated with the other of the fixed wing and wing tip device, the bush configured to receive the locking pin. The bush is located within a bush housing arranged to allow relative movement of the bush in the direction of a longitudinal axis of the locking pin when the locking pin is received within the bush.
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公开(公告)号：US20200307769A1
公开(公告)日：2020-10-01
申请号：US16830590
申请日：2020-03-26
发明人： Florian Lorenz , Dennis Krey , Bernhard Schlipf , Dustin Shapi
摘要： A wing for an aircraft including a main wing, slat, and connection assembly movable connecting the slat to the main wing and including an elongate slat track. A front end of the slat track is mounted to the slat and a rear end and an intermediate portion of the slat track are mounted to the main wing by a roller bearing that includes a guide rail mounted to the main wing and a first roller unit mounted to the rear end of the slat track and engaging the guide rail. The wing has redundant main load paths as the guide rail includes a guide rail primary structure engaging with the first roller unit, and an additional reinforcement structure additionally reinforcing the guide rail primary structure in a lateral direction, wherein the guide rail primary structure forms a first main load path and the reinforcement structure forms a redundant second main load path.
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公开(公告)号：US10589833B2
公开(公告)日：2020-03-17
申请号：US15914447
申请日：2018-03-07
申请人： The Boeing Company
发明人： John Charles Walters
摘要： A drain grommet with integrated fire shield. In one embodiment, the drain grommet includes a drain tube configured to extend through a drain, and to pass fluid through the drain via an opening into a hollow channel of the drain tube. The drain grommet further includes a fire shield integrally coupled with the drain tube via a standoff, wherein the standoff supports the fire shield at a vertical distance above the opening of the drain tube, and wherein the fire shield is larger than the opening of the drain tube in a horizontal plane.
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公开(公告)号：US20200047871A1
公开(公告)日：2020-02-13
申请号：US16658432
申请日：2019-10-21
申请人： ROLLS-ROYCE plc
发明人： Matthew MOXON
摘要： An aircraft has an internal combustion engine and a wing including a hollow structural member. The aircraft has an electrical network including: an electrical motor configured to drive an aircraft propulsor; at least one conductor configured to electrically couple the electrical motor and an electrical storage device; wherein the electrical conductor is formed of the hollow structural member of the aircraft wing.
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公开(公告)号：US20190276130A1
公开(公告)日：2019-09-12
申请号：US15914447
申请日：2018-03-07
申请人： The Boeing Company
发明人： John Charles Walters
摘要： A drain grommet with integrated fire shield. In one embodiment, the drain grommet includes a drain tube configured to extend through a drain, and to pass fluid through the drain via an opening into a hollow channel of the drain tube. The drain grommet further includes a fire shield integrally coupled with the drain tube via a standoff, wherein the standoff supports the fire shield at a vertical distance above the opening of the drain tube, and wherein the fire shield is larger than the opening of the drain tube in a horizontal plane.
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