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    MOTOR WEAR METRIC GENERATOR
    1.
    发明公开
    MOTOR WEAR METRIC GENERATOR 审中-公开

    公开(公告)号：US20240190587A1

    公开(公告)日：2024-06-13

    申请号：US18410629

    申请日：2024-01-11

    Applicant: Kitty Hawk Corporation

    Inventor： Dennis Young Kwon ,  Alexander David Selwa

    IPC: B64F5/60 ,  B64D45/00 ,  B64U50/19 ,  G07C5/08

    CPC classification number: B64F5/60 ,  G07C5/0808 ,  G07C5/0816 ,  B64D2045/0085 ,  B64U50/19

    Abstract: First and second signals respectively associated with first and second motors are obtained. First and second motor wear metric that respectively represent an amount of wear associated with the first and second motors are determined based at least in part on the first and second signals, respectively. It is determined whether at least one of the first or second motor wear metrics exceeds a failure threshold. The VTOL vehicle is automatically prevented from performing a vertical takeoff attempt if least one of the first or second motor wear metrics exceeds the failure threshold. The first and second rotors are respectively positioned at first and second angles relative to a horizontal plane, at least during a hovering mode of the VTOL vehicle. The first and second angles are different angles. The first and second motors are respectively associated with the first and second rotors.

    SUPPLEMENTAL ATTITUDE WITH ENGAGED AND DISENGAGED INPUT DEVICE MODES
    5.
    发明申请
    SUPPLEMENTAL ATTITUDE WITH ENGAGED AND DISENGAGED INPUT DEVICE MODES 审中-公开

    公开(公告)号：US20190171234A1

    公开(公告)日：2019-06-06

    申请号：US16107833

    申请日：2018-08-21

    Applicant: Kitty Hawk Corporation

    Inventor： Alexander David Selwa ,  Mark Johnson Cutler

    IPC: G05D1/08 ,  B64C29/00 ,  B64C17/00 ,  B64C19/00

    Abstract: An input attitude associated with an input device of an aircraft is received. A supplemental attitude is generated, including by selecting a position-based supplemental attitude to be the supplemental attitude in the event the input device is in a disengaged state and selecting a velocity-based supplemental attitude to be the supplemental attitude in the event the input device is in an engaged state. The input attitude and the supplemental attitude are combined in order to obtain a combined attitude. The aircraft is controlled using the combined attitude.

    Motor wear metric generator
    6.
    发明授权
    Motor wear metric generator 有权

    公开(公告)号：US11091279B1

    公开(公告)日：2021-08-17

    申请号：US16902005

    申请日：2020-06-15

    Applicant: Kitty Hawk Corporation

    Inventor： Dennis Young Kwon ,  Alexander David Selwa

    IPC: B64F5/60 ,  G07C5/08 ,  B64D45/00

    Abstract: In an embodiment, a system for generating a motor wear metric includes a process configured to obtain a signal associated with a motor of an aircraft, determine a motor wear metric based at least in part on the obtained signal, and output information about motor wear based at least in part on the determined motor wear metric. The system includes a memory coupled to the processor and configured to provide the processor with instructions and store the determined motor wear metric.

    AUTONOMOUS TAKEOFF AND LANDING WITH OPEN LOOP MODE AND CLOSED LOOP MODE
    9.
    发明申请
    AUTONOMOUS TAKEOFF AND LANDING WITH OPEN LOOP MODE AND CLOSED LOOP MODE 审中-公开

    公开(公告)号：US20190179343A1

    公开(公告)日：2019-06-13

    申请号：US15848847

    申请日：2017-12-20

    Applicant: Kitty Hawk Corporation

    Inventor： Mark Johnson Cutler ,  Alexander David Selwa

    IPC: G05D1/06 ,  G05D1/04 ,  G05D1/00 ,  B64C29/00

    Abstract: Autonomous flight is performed in an open loop mode over a first range of altitudes, wherein a plurality altitude-related data from a plurality of altitude-related sensors is ignored while performing the autonomous flight in the open loop mode. The autonomous flight is performed in a closed loop mode over a second range of altitudes, wherein: the plurality of altitude-related data from the plurality of altitude-related sensors is used while performing the autonomous flight in the closed loop mode, and the first range of altitudes is a non-overlapping, lower range of altitudes compared to the second range of altitudes. The altitude-related data may include, among other things, a radar signal or a phase associated with a radar signal.

    Autonomous takeoff and landing with open loop mode and closed loop mode
    10.
    发明授权
    Autonomous takeoff and landing with open loop mode and closed loop mode 有权

    公开(公告)号：US10303184B1

    公开(公告)日：2019-05-28

    申请号：US15848847

    申请日：2017-12-20

    Applicant: Kitty Hawk Corporation

    Inventor： Mark Johnson Cutler ,  Alexander David Selwa

    IPC: B64C39/12 ,  G05D1/06 ,  G05D1/04 ,  B64C29/00 ,  G05D1/00

    Abstract: Autonomous flight is performed in an open loop mode over a first range of altitudes, wherein a plurality altitude-related data from a plurality of altitude-related sensors is ignored while performing the autonomous flight in the open loop mode. The autonomous flight is performed in a closed loop mode over a second range of altitudes, wherein: the plurality of altitude-related data from the plurality of altitude-related sensors is used while performing the autonomous flight in the closed loop mode, and the first range of altitudes is a non-overlapping, lower range of altitudes compared to the second range of altitudes. The altitude-related data may include, among other things, a radar signal or a phase associated with a radar signal.

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