AIRCRAFT SOLID POWER CONTROLLER, AIRCRAFT POWER SUPPLY SYSTEM, AND METHOD OF SWITCHING AN AIRCRAFT SOLID STATE POWER CONTROLLER

    公开(公告)号:EP4443685A1

    公开(公告)日:2024-10-09

    申请号:EP23166927.6

    申请日:2023-04-06

    发明人: Greither, Markus

    IPC分类号: H02J1/08 H02J1/14

    摘要: An aircraft solid state power controller (8) for controlling electric power in an aircraft (1) comprises: a first input terminal (16a) for being electrically coupled to a first power supply output (5a) of a symmetric electric power supply (4); a first output terminal (19a); and a first electric power switching device (10a), which is switchable between an on-state, in which the first electric power switching device (10a) electrically couples the first output terminal (19a) with the first input terminal (16a), and an off-state, in which the first electric power switching device (10a) electrically isolates the first output terminal (19a) from the first input terminal (16a); a second input terminal (16b) for being electrically coupled to a second power supply output (5b) of the symmetric electric power supply (4); a second output terminal (19b); and a second electric power switching device (10b), which is switchable between an on-state, in which the second electric power switching device (10b) electrically couples the second output terminal (19b) with the second input terminal (16b), and an off-state, in which the second electric power switching device (10b) electrically isolates the second output terminal (19b) from the second input terminal (16b); an energy dumping circuit (18) coupled to the first and second input terminals (16a, 16b) for dissipating inductive energy that is generated when the first and second electric power switching devices (10a, 10b) are switched from their respective on-states into their respective off-states; and a switch controller (20) for controlling the operation of the first and second electric power switching devices (10a, 10b). The switch controller (20) is configured for synchronously switching the first and second electric power switching devices (10a, 10b) from their respective on-states into their respective off-states.

    Actively clamped transistor circuit
    9.
    发明公开
    Actively clamped transistor circuit 审中-公开
    Transistorschaltung mit aktiver Klemmung

    公开(公告)号:EP2549649A1

    公开(公告)日:2013-01-23

    申请号:EP12177543.1

    申请日:2012-07-23

    发明人: Greither, Markus

    IPC分类号: H03K17/082

    摘要: An active clamped transistor circuit (100, 200) comprises a transistor (110) and a bi-directional transient voltage suppression (TVS) diode (120) connected across a gate (116) and a drain (112) of said transistor.

    摘要翻译: 有源钳位晶体管电路(100,200)包括跨过所述晶体管的栅极(116)和漏极(112)连接的晶体管(110)和双向瞬态电压抑制(TVS)二极管(120)。

    AIRCRAFT GROUND FAULT DETECTION CIRCUIT AND METHOD OF CALIBRATING AN AIRCRAFT GROUND FAULT DETECTION CIRCUIT

    公开(公告)号:EP4343342A1

    公开(公告)日:2024-03-27

    申请号:EP22197473.6

    申请日:2022-09-23

    发明人: Greither, Markus

    IPC分类号: G01R31/00 G01R31/50 G01R31/52

    摘要: An aircraft ground fault detection circuit (2) comprises: a first electric power supply line (4a), and a second electric power supply line (4b); a first shunt resistor (6a) arranged in the first electric power supply line (4a); a second shunt resistor (6b) arranged in the second electric power supply line (4b); a first voltage detector (8a) configured for detecting a first voltage drop (Ui) over the first shunt resistor (6a); a second voltage detector (8b) configured for detecting a second voltage drop (U2) over the second shunt resistor (6b); an electric test current power supply (10) for applying an electric test voltage (U test ) to the first and second electric power supply lines (4a, 4b) causing an electric test current (I test ) to flow through the first and second electric power supply lines (4a, 4b) and the first and second shunt resistors (6a, 6b); and a controller (14), which is configured for receiving voltage signals provided by the first and second voltage detectors (8a, 8b) indicating the first and second voltage drops (U 1 , U 2 ), and determining a difference (ΔR) between the resistivities (R 1 , R 2 ) of the first and second shunt resistors (6a, 6b) from said voltage drops (U 1 , U 2 ).