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    Apparatus for pre-flight preparation for electric aircraft
    2.
    发明授权
    Apparatus for pre-flight preparation for electric aircraft 有权

    公开(公告)号：US12079010B2

    公开(公告)日：2024-09-03

    申请号：US17889495

    申请日：2022-08-17

    申请人： BETA AIR, LLC

    发明人： Thomas Henck ,  Sarah Overfield

    IPC分类号： G05D1/00 ,  B64D15/12 ,  G01C21/20 ,  B64C29/00

    CPC分类号： G05D1/101 ,  B64D15/12 ,  G01C21/20 ,  B64C29/0008

    摘要： An apparatus for pre-flight preparation for an electric aircraft including at least a processor and memory communicatively connected to the processor. The memory containing instructions configuring the at least a processor to generate a plurality of aircraft conditioning data using at least a sensor. The memory containing instructions further configuring the processor to engage at least an aircraft conditioning system using power from an auxiliary power supply, The aircraft conditioning system is configured to receive the plurality of aircraft conditioning data from the at least a sensor, test the output of the at least a sensor against an expected value of the at least a sensor, and initiate the aircraft conditioning system as a function of the aircraft conditioning data.

    SYSTEM AND METHOD FOR GENERATING ELECTRICAL ENERGY FROM THERMAL WASTE ENERGY AND REMOVING THERMAL WASTE ENERGY IN AN AIRCRAFT
    3.
    发明公开
    SYSTEM AND METHOD FOR GENERATING ELECTRICAL ENERGY FROM THERMAL WASTE ENERGY AND REMOVING THERMAL WASTE ENERGY IN AN AIRCRAFT 审中-公开

    公开(公告)号：US20240166358A1

    公开(公告)日：2024-05-23

    申请号：US18548685

    申请日：2022-03-04

    申请人： Eaton Intelligent Power Limited

    发明人： Chris ZUZELSKI ,  Christopher CANTRELL ,  William Hank NEWSOME

    IPC分类号： B64D15/12 ,  H10N10/13

    CPC分类号： B64D15/12 ,  H10N10/13

    摘要： A system for generating electrical energy from thermal waste energy and removing thermal waste energy in an aircraft is provided. The system includes a thermal management circuit configured to channel a flow of coolant fluid that collects thermal waste energy from a thermal energy generating component. A heat exchanger coupled in fluid communication with the thermal management circuit and downstream from the thermal energy generating component. The heat exchanger is coupled in thermal contact to an exterior skin wall and adapted to transfer thermal energy from the flow of coolant fluid to the exterior skin wall. A thermoelectric generator is configured to convert heat flux between the flow of coolant fluid within the heat exchanger and atmosphere surrounding an outside surface of the exterior skin wall into electrical energy. The thermoelectric generator includes thermo-electric interface material extending between an inside surface of the exterior skin wall and the heat exchanger.

    ICE PROTECTION BACKUP TEMPERATURE CONTROL LOGIC
    5.
    发明公开
    ICE PROTECTION BACKUP TEMPERATURE CONTROL LOGIC 审中-公开

    公开(公告)号：US20240132219A1

    公开(公告)日：2024-04-25

    申请号：US17969471

    申请日：2022-10-18

    申请人： GOODRICH CORPORATION

    发明人： Richard J. Carpino II

    IPC分类号： B64D15/22 ,  B64D15/12 ,  B64D33/02

    CPC分类号： B64D15/22 ,  B64D15/12 ,  B64D33/02 ,  B64D2033/0233

    摘要： A multi-zone anti-icing system for an aircraft part. The system includes at least two or more-part zones configured with the aircraft part and an electrothermal heater associated with at least one part zone of the aircraft part; at least one resistive temperature detector (RTD) associated with each part zone of the aircraft part configured to generate temperature data associated with each part zone. A controller coupled to the electrothermal heater and configured to implement an algorithm of a control logic for an anti-icing operation that uses feedback temperature data from at least one RTD at an associated part zone wherein the feedback temperature data is analyzed by the controller via the algorithm to assess reliability of the temperature data generated by the at least one RTD associated with each part zone.

    Electrical Power Transmission for Propeller Deicing
    8.
    发明公开
    Electrical Power Transmission for Propeller Deicing 审中-公开

    公开(公告)号：US20240109663A1

    公开(公告)日：2024-04-04

    申请号：US18274809

    申请日：2022-02-14

    申请人： UBIQ Aerospace AS

    发明人： Shibarchi Majumder ,  Kim Sørensen

    IPC分类号： B64D15/12 ,  B64C11/00

    CPC分类号： B64D15/12 ,  B64C11/00

    摘要： A propulsion system for a propeller of an aircraft is described, wherein the propulsion system allows for transmission of electrical power such as for a deicing system for the propeller. The propulsion system comprises a rotatable shaft for transmission of mechanical power; aircraft end electrical connections at an aircraft end of the shaft for connection to first and second terminals of a source of electrical power; propeller end electrical connections at a propeller end of the shaft and being for connection to first and second terminals for supplying electrical power to electrical components on the propeller; and a mechanical coupling at the propeller end of the shaft for mounting the propeller to the shaft. The shaft comprises: an inner conductor extending along the length of the shaft; an outer conductor extending along the length of the shaft; and an electrical insulator extending along the shaft in between the inner and outer conductor.

    Method of measuring airflow velocity using an integrated heating airspeed tube
    9.
    发明授权
    Method of measuring airflow velocity using an integrated heating airspeed tube 有权

    公开(公告)号：US11905031B2

    公开(公告)日：2024-02-20

    申请号：US18366678

    申请日：2023-08-08

    申请人： Shanghai Autoflight Co., Ltd.

    发明人： Yu Tian

    IPC分类号： B64C39/00 ,  B64D43/02 ,  B64D15/12 ,  G01P5/165 ,  B64C39/02

    CPC分类号： B64D43/02 ,  B64D15/12 ,  G01P5/165 ,  B64C39/024 ,  B64U2201/00

    摘要： A method of measuring airflow velocity using an integrated heating airspeed tube where the integrated heating airspeed tube has a tube body and a heating component. The tube body is provided with a heating cavity, the heating component is located inside the heating cavity, and the heating component and the tube body are integrally formed. The heating component and at least two static pressure air inlet channels are physically separate but overlap in a lengthwise directly within a horizontal portion of the airspeed tube. The tube body integrally forms the static pressure air inlet channel, the dynamic pressure air inlet channel, the heating cavity, the dynamic pressure air inlet hole, and the static pressure air inlet hole as a unitary one-piece structure.