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    Aircraft Battery Systems having Heat Activated Thermal Barriers
    4.
    发明申请
    Aircraft Battery Systems having Heat Activated Thermal Barriers 有权

    公开(公告)号：US20230078659A1

    公开(公告)日：2023-03-16

    申请号：US17472907

    申请日：2021-09-13

    申请人： Textron Innovations Inc.

    发明人： Yue Fan ,  Michael Raymond Hull ,  Zachary Edwin Dailey

    IPC分类号： B60L58/26 ,  B64C29/00 ,  B64D13/00 ,  H01M10/625 ,  H01M10/6567

    摘要： A battery system includes a plurality of battery modules each formed from a plurality of battery cells. A shared cooling structure is thermally coupled to each of the battery modules. The shared cooling structure is configured to conduct heat relative to the battery modules. A thermal interface is disposed between the battery cells of each battery module and the shared cooling structure. Each thermal interface is configured to transition from a first thermal conductivity state to a second thermal conductivity state when heat generated by the respective battery cells exceeds a threshold level. The second thermal conductivity state is lower than the first thermal conductivity state such that after one of the thermal interfaces has transitioned from the first thermal conductivity state to the second thermal conductivity state, heat transfer from the respective battery cells to the shared cooling structure is reduced.

    Aircraft battery systems having heat activated thermal barriers
    6.
    发明授权
    Aircraft battery systems having heat activated thermal barriers 有权

    公开(公告)号：US11752898B2

    公开(公告)日：2023-09-12

    申请号：US17472907

    申请日：2021-09-13

    申请人： Textron Innovations Inc.

    发明人： Yue Fan ,  Michael Raymond Hull ,  Zachary Edwin Dailey

    IPC分类号： B60L58/26 ,  H01M10/625 ,  H01M10/6567 ,  B64D13/00 ,  B64C29/00

    CPC分类号： B60L58/26 ,  B64C29/0033 ,  B64D13/006 ,  H01M10/625 ,  H01M10/6567 ,  B60L2200/10 ,  H01M2220/20

    摘要： A battery system includes a plurality of battery modules each formed from a plurality of battery cells. A shared cooling structure is thermally coupled to each of the battery modules. The shared cooling structure is configured to conduct heat relative to the battery modules. A thermal interface is disposed between the battery cells of each battery module and the shared cooling structure. Each thermal interface is configured to transition from a first thermal conductivity state to a second thermal conductivity state when heat generated by the respective battery cells exceeds a threshold level. The second thermal conductivity state is lower than the first thermal conductivity state such that after one of the thermal interfaces has transitioned from the first thermal conductivity state to the second thermal conductivity state, heat transfer from the respective battery cells to the shared cooling structure is reduced.

    Modular Battery Systems for Aircraft
    7.
    发明申请
    Modular Battery Systems for Aircraft 有权

    公开(公告)号：US20220376363A1

    公开(公告)日：2022-11-24

    申请号：US17327753

    申请日：2021-05-23

    申请人： Textron Innovations Inc.

    发明人： Michael Raymond Hull ,  Steven Loveland ,  Yue Fan

    IPC分类号： H01M50/512 ,  B64D27/24 ,  B60L50/64 ,  B64C29/00 ,  B60L58/10 ,  H01M10/42 ,  H01M50/209 ,  H01M50/249

    摘要： A modular battery system provides propulsive power to the rotor system of an aircraft. The modular battery system includes an array of battery modules arranged in at least one stack. Each battery module includes a plurality of battery cells, a first side having positive and negative receptacles and a second side, that is opposite of the first side, having positive and negative plugs. The receptacles and plugs are configured such that adjacent battery modules in a side-by-side relationship are electrically coupled together via plug and receptacle connections and such that the battery modules are electrically coupled together in parallel. An interconnection electrically couples each stack of battery modules together via plug and receptacle connections with one of the battery modules in each stack such that the stacks of battery modules are electrically coupled together in parallel.

    Battery system optimization for eVTOL aircraft
    8.
    发明授权
    Battery system optimization for eVTOL aircraft 有权

    公开(公告)号：US11447035B1

    公开(公告)日：2022-09-20

    申请号：US17307998

    申请日：2021-05-04

    申请人： Textron Innovations Inc.

    发明人： Michael Raymond Hull ,  Steven Loveland ,  Yue Fan

    IPC分类号： B60L58/21 ,  H02J7/00 ,  B64D27/24 ,  B64D31/06 ,  B64C29/00 ,  B60L50/64 ,  B60L58/14 ,  B60L58/15 ,  B60L53/53

    摘要： An electrical system provides propulsive power to a rotor system of an eVTOL aircraft. The electrical system includes a power battery system having a plurality of power cells and a power battery management system. An energy battery system includes a plurality of energy cells and an energy battery management system in communication with the power battery management system. A distribution system electrically couples the power battery system and the energy battery system to at least one electric motor that drives the rotor system. In a takeoff and landing power mode of the eVTOL aircraft, both the power battery system and the energy battery system provide electrical power to the at least one electric motor. In a cruise power mode of the eVTOL aircraft, the energy battery system provides electrical power to the at least one electric motor and to the power battery system to recharge the power cells.

    Configurable Electrical Architectures for eVTOL Aircraft
    9.
    发明申请
    Configurable Electrical Architectures for eVTOL Aircraft 有权

    公开(公告)号：US20220250755A1

    公开(公告)日：2022-08-11

    申请号：US17173989

    申请日：2021-02-11

    申请人： Textron Innovations Inc.

    发明人： Michael Raymond Hull ,  Steven Loveland ,  Yue Fan

    IPC分类号： B64D27/24 ,  B60L50/60 ,  B64D31/06 ,  B60L58/10 ,  B60L50/70 ,  B60L50/10 ,  B64C29/00 ,  B60L53/50

    摘要： A configurable electrical architecture for an eVTOL aircraft having a takeoff and landing power mode and a cruise power mode. The configurable electrical architecture includes a power-optimized power source including a high-power battery array and an energy-optimized power source selected from a plurality of interchangeable energy-optimized power sources including a high-energy battery array, a hydrogen fuel cell system and a turbo-generator system. A distribution system is electrically coupled to the power-optimized power source and the energy-optimized power source. At least one electric motor is electrically coupled to the distribution system. In the takeoff and landing power mode, both the power-optimized power source and the energy-optimized power source provide electrical power to the at least one electric motor. In the cruise power mode, the energy-optimized power source provides electrical power to the at least one electric motor and to the power-optimized power source to recharge the high-power battery array.