公开(公告)号：US11845565B2

公开(公告)日：2023-12-19

申请号：US16978682

申请日：2019-03-05

申请人： DESAUTEL

发明人： Claude Beck

IPC分类号： B64F1/28 ,  B64D37/02 ,  B64D37/16 ,  B64F5/10

CPC分类号： B64F1/28 ,  B64D37/02 ,  B64D37/16 ,  B64F5/10

摘要： Aircraft refuelling device including a fuel circulation pipe of which the downstream end is equipped with a wing coupling for connecting it to an inlet orifice of a fuel tank of the aircraft. The wing coupling includes a body which defines a fuel circulation duct at the end of the pipe, a sensor for measuring the value of a parameter indicative of a flow of fuel passing through the wing coupling, and at least one battery electrically powering the sensor. The sensor and the electrical power supply battery are housed in two half-shells mounted together around the body of the wing coupling.

公开(公告)号：US20230022291A1

公开(公告)日：2023-01-26

申请号：US17870052

申请日：2022-07-21

申请人： Airbus SAS ,  Airbus Operations SAS

发明人： Jorge A. CARRETERO BENIGNOS ,  Lionel CZAPLA

IPC分类号： B64D27/26 ,  B64D29/06 ,  B64D37/02 ,  B64D33/02 ,  B64D33/04

摘要： A propulsion assembly for an aircraft, comprising a nacelle, a propulsion system housed in the nacelle and comprising a fairing, a rotary assembly that has a combustion chamber and is housed in the fairing, an exhaust nozzle delimited by a nozzle wall of the fairing, a fuel tank, a supply duct which connects the tank and the combustion chamber, and a heat exchanger system ensuring, during operation of the propulsion system, an exchange of heat energy between the hot combustion gases circulating in the nozzle and the colder fuel circulating in the supply duct by thermal radiation through the nozzle wall.

公开(公告)号：US20230020058A1

公开(公告)日：2023-01-19

申请号：US17787409

申请日：2020-12-17

申请人： UNIVERSITÉ DE TECHNOLOGIE DE COMPIÈGNE (UTC) ,  CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE (CNRS)

发明人： Eric NOPPE ,  Jérôme DEMIRAS

IPC分类号： B64C39/02 ,  B64D27/02 ,  B64D35/04 ,  B64D35/08 ,  B64D37/02 ,  B64F1/36 ,  F15B11/042 ,  F15B11/16

摘要： Multi-rotor hydraulic drone (1) comprising: —a plurality of hydraulic motors (6) each receiving a pressurised fluid, —propellers (5) driven by the hydraulic motors (6), —at least one hydraulic pump (10) driven by at least one motor (11) for pressurising the fluid, —a system for supplying the hydraulic motors (6) with pressurised fluid, —a flight controller (14) for controlling the supply system according to the desired rotation speed for the hydraulic motors (6), the supply system comprising several channels (35; 36; 37; 38) for adjusting the power of at least one portion of the hydraulic motors (6).

公开(公告)号：US11358732B2

公开(公告)日：2022-06-14

申请号：US16380358

申请日：2019-04-10

申请人： Zodiac Aerotechnics

发明人： Patrick Epalle ,  Michel Vacher

IPC分类号： B64D37/32 ,  F16K24/04 ,  B64D37/02 ,  F16K31/22 ,  B60K15/03 ,  B60K15/035

摘要： A fuel tank with a venting system includes a flap for closing and opening a vent made in the tank. The flap is coupled to a float. The flap includes a valve coupled to a second float mounted in a hinged manner in the tank so that the valve adopts a closed position, being pushed by the second float when the level of fuel in the tank reaches a certain threshold, and an open venting position in order to prevent overpressure within the tank, being driven by the second float when the level of fuel is below the threshold and the force exerted by the internal pressure on the valve is less than the sum of the forces exerted on the valve by the atmospheric pressure and by the weight of the second float.

公开(公告)号：US20210339859A1

公开(公告)日：2021-11-04

申请号：US17246133

申请日：2021-04-30

申请人： Volansi, Inc.

发明人： Emily Agostino ,  Curtis Leo ,  Stephen Morris

IPC分类号： B64C39/02 ,  B64D47/08 ,  B64D1/10 ,  B64D37/02 ,  B64D37/00 ,  B64D1/22 ,  B64D41/00 ,  G06Q10/08

摘要： A dual use UAV or “drone” can include a battery and primary processor located at a fuselage, as well as two separate modular units removably coupled to the fuselage and in communication with the primary processor. The two separate modular units can interact with each other to provide an enhanced operation while the drone is in flight. One modular unit can be an ISR unit having a video camera, and the other modular unit can be a cargo unit. The enhanced operation can involve the ISR unit using its video camera to identify a delivery location for a cargo pod of the cargo unit. Alternative modular units can include a secondary ISR unit, a cargo fuel pod unit, or a robotic arm assembly. Standardized interfaces coupled to the fuselage can enable the ready removal of one modular unit and installation of another one.

公开(公告)号：US20210253224A1

公开(公告)日：2021-08-19

申请号：US17032965

申请日：2020-09-25

申请人： Khaldoun L. Hameed

发明人： Khaldoun L. Hameed

IPC分类号： B64C17/02 ,  B64C39/02 ,  B64D27/04 ,  B64D35/04 ,  B64D33/08 ,  B64D37/02

摘要： This present patent application discloses an unmanned aerial vehicle (UAV) that features a stable and easy way of steering and controlling the unmanned aerial vehicle. The unmanned aerial vehicle comprises of four vanes attached to extension arms, a single engine coupled to a special gearbox and sliding weights. The unmanned aerial vehicle features sliding weights below the extension arms and are used for steering the UAV in a desired direction in air. The sliding weights and the engine are used to control the UAV. The single engine leads to less power consumption, longer battery life, longer flight time and higher flight attitude.

公开(公告)号：US10858117B2

公开(公告)日：2020-12-08

申请号：US16245601

申请日：2019-01-11

申请人： 3M INNOVATIVE PROPERTIES COMPANY

发明人： Jonathan D. Zook ,  Larry S. Hebert ,  Michael D. Swan ,  Sheng Ye ,  Susan E. DeMoss ,  Robin E. Wright

IPC分类号： F16B33/00 ,  B64D37/06 ,  F16B37/14 ,  B64D45/02 ,  B64D37/02

摘要： A lightning protective seal cap comprising a seal cap that defines an interior, and a quantity of an uncured sealant that is curable by the application of actinic radiation so as to bind the seal cap to a fastener. The interior of the seal cap contains the quantity of uncured sealant, the seal cap is positionable over the fastener such that at least a portion of the fastener resides in the interior of the seal cap, and when the seal cap is in position over the fastener, the sealant containing seal cap prevents electrical arcing to the fastener from a lightning strike.

公开(公告)号：US10677206B2

公开(公告)日：2020-06-09

申请号：US15653936

申请日：2017-07-19

申请人： AIRBUS OPERATIONS LIMITED

发明人： Jay Wheelwright ,  Jacob Dobbs ,  Christian Martin

IPC分类号： B01D36/00 ,  B60K15/03 ,  C10G33/06 ,  F02M37/22 ,  F02M37/24 ,  B64D37/28 ,  B01D61/36 ,  B01D69/10 ,  B01D71/02 ,  B64D37/02

摘要： A combination of a fuel tank assembly and a tool for opening an outlet of the fuel tank assembly. The assembly includes a tank for storing a liquid hydrocarbon; and an operator-openable valve arrangement configured to move between a closed flow condition in which flow through the valve arrangement is prevented and an open flow condition in which liquid is allowed to drain out of the tank. The tool is connectable to the valve arrangement, such that in a connected condition of the tool and the arrangement a liquid flow path exists between the interior and the exterior of the tank. The liquid flow path is at least partly defined by a conduit in the tool. A filter, in the flow path, includes a water-permeable member configured to enable water to pass through the water-permeable member and substantially prevent passage of liquid hydrocarbon.

公开(公告)号：US10556811B2

公开(公告)日：2020-02-11

申请号：US15496240

申请日：2017-04-25

申请人： AIRBUS OPERATIONS LIMITED

发明人： Neil Terence Frost

IPC分类号： C02F1/44 ,  B01D71/02 ,  B64D37/02 ,  B64D37/32

摘要： The present application relates to a fuel flow system. In particular, the application relates to a fuel flow system for an aircraft. The fuel flow system has a fuel conduit having a fuel inflow and a fuel outflow along which a fuel/water mix is configured to flow from the fuel inflow to the fuel outflow. The fuel conduit is fluidly communicable with a fuel tank. A peripheral conduit surrounds at least part of the fuel conduit. A water-permeable member is disposed between the fuel conduit and the peripheral conduit. The water-permeable member enables water from the fuel/water mix to flow through the water-permeable member from the fuel conduit into the peripheral conduit, but at least substantially prevents liquid fuel from the fuel/water mix from doing so.

公开(公告)号：US10358821B2

公开(公告)日：2019-07-23

申请号：US14635272

申请日：2015-03-02

申请人： THE BOEING COMPANY

发明人： Matthew Howard Cawthorne ,  Christopher Eliot Wummer ,  Danielle Raiko Craig

IPC分类号： E04C2/36 ,  B64C1/06 ,  B64C27/473 ,  B29C65/00 ,  B29D99/00 ,  B29C65/02 ,  B64C3/22 ,  B64C3/20 ,  B64D37/02 ,  B64C3/00 ,  B64C27/32 ,  B29L31/30 ,  B29L31/08 ,  B29C65/78 ,  B29C65/16 ,  B29L28/00 ,  B29K701/12

摘要： The present disclosure generally relates to thermoplastic truss structures and methods of forming the same. The truss structures are formed using thermoplastic materials, such as fiber reinforced thermoplastic resins, and facilitate directional load support based on the shape of the truss structure. In one example, multiple two-dimensional patterns of fiber reinforced thermoplastic resin are disposed on one another in a saw tooth pattern, sinusoidal pattern, or other repeating pattern, and adhered to one another in selective locations. The two dimensional patterns may then be expanded in a third dimension to form a three-dimensional, cross-linked truss structure. The three-dimensional, cross-linked truss structure may then be heated or otherwise treated to maintain the three-dimensional shape.