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    APPARATUS FOR GENERATING A SELF-CHECK LEAKAGE CURRENT
    1.
    发明公开
    APPARATUS FOR GENERATING A SELF-CHECK LEAKAGE CURRENT 审中-公开

    公开(公告)号：EP4447246A1

    公开(公告)日：2024-10-16

    申请号：EP23307046.5

    申请日：2023-11-24

    申请人： SCHNEIDER ELECTRIC INDUSTRIES SAS

    发明人： LU, Feng ,  CHEN, Xiaohang ,  WANG, Han ,  FENG, Jie ,  SONG, Yangfeng ,  TIAN, Jianwei ,  BAI, Wanlong

    IPC分类号： H02H3/33 ,  H02H3/02 ,  H01H83/04

    摘要： An apparatus for generating a self-check leakage current is disclosed. The apparatus includes: a mechanical switch (110) which is configured to simultaneously switch on and off a phase line (L) and a neutral line (N); a phase line solid-state switch (120) arranged on a phase line (L) and located upstream of the mechanical switch (110); a current transformer (130) arranged upstream of the phase line solid-state switch (120), and the phase line (L) and neutral line (N) pass through the current transformer (130); a bypass unit (140) including a bypass switch (141) and a bypass resistor (R1) connected in series, one end of the bypass unit is connected between the mechanical switch and the solid-state switch on the phase line (L), and the other end is connected to the upstream of the current transformer on the neutral line (N); A control unit (150), which is configured to control the switching on and off of the phase line solid-state switch (120) and the bypass switch (141) and to receive the current value detected by the current transformer (130), wherein the self-check leakage current is generated when the phase line solid-state switch and the bypass switch are switched on.

    SYSTEM AND METHOD FOR GROUND FAULT DETECTION OF STATIC STARTER CIRCUITRY
    4.
    发明公开
    SYSTEM AND METHOD FOR GROUND FAULT DETECTION OF STATIC STARTER CIRCUITRY 审中-公开

    公开(公告)号：EP4297268A1

    公开(公告)日：2023-12-27

    申请号：EP23178219.4

    申请日：2023-06-08

    申请人： General Electric Technology GmbH

    发明人： DESABHATLA, Sreedhar ,  SANKAR, Malepati Bhavani ,  LEONARD, John A. ,  PATHAK, Sudeep

    IPC分类号： H02P1/52 ,  H02H3/33 ,  H02P29/024

    摘要： A system, in one embodiment, may include a system includes a ground fault detection system (36). The ground fault detection system (36) includes a linear filter (72) configured to receive one or more signals from a static starter system (16) during operations of the static starter system (16) and to produce a linear filter output. The ground fault detection system (36) further includes a rectifier (74) configured to rectify the linear filter output and to produce a rectifier output, and a gain system (76) configured to multiply the rectifier output by a factor to produce a gain output. The ground fault detection system (36) additionally includes a fault indicator system (80) configured to indicate a ground fault based on the gain output, wherein the ground fault detection system (36) is configured to command an action based on the ground fault.

    PROTECTION SYSTEM FOR AIRCRAFT ELECTRIC PROPULSION MOTOR AND MOTOR CONTROLLER
    8.
    发明公开
    PROTECTION SYSTEM FOR AIRCRAFT ELECTRIC PROPULSION MOTOR AND MOTOR CONTROLLER 审中-公开

    公开(公告)号：EP4106126A1

    公开(公告)日：2022-12-21

    申请号：EP22177682.6

    申请日：2022-06-07

    申请人： The Boeing Company

    发明人： KHOZIKOV, Vyacheslav ,  SOLODOVNIK, Eugene V. ,  LACAUX, Frederic ,  KARIMI, Kamiar J.

    IPC分类号： H02H3/28 ,  H02H3/33 ,  H02H7/122

    摘要： Methods and apparatus for detecting and characterizing arc faults in an aerospace electric propulsion system and then coordinating the operation of various elements of the protection system to execute a fault-clearing sequence. In a currentbased method, the arc is detected and characterized based on differential readouts from current sensors. The difference between currents measured at two ends of a protection zone are compared to a difference threshold. In a power-based method, the arc is detected and characterized based on differential readouts from voltage and current sensors. The differential voltage and current readouts are used to compute the respective powers at two ends of a protection zone. The difference between the respective powers is integrated over a period of time and then the integrated difference is compared to a difference threshold. A differential protection trip mode is invoked when the difference threshold is exceeded.