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    SYSTEM AND METHOD FOR CONTROLLING AN AIRCRAFT BATTERY ASSEMBLY
    21.
    发明公开
    SYSTEM AND METHOD FOR CONTROLLING AN AIRCRAFT BATTERY ASSEMBLY 审中-公开

    公开(公告)号：US20240333007A1

    公开(公告)日：2024-10-03

    申请号：US18435601

    申请日：2024-02-07

    Applicant: Pratt & Whitney Canada Corp.

    Inventor： Remi Robache ,  Antwan Shenouda ,  Richard Freer ,  Simon Lam ,  Raphael Gariepy ,  Fraz Ahmad Kharal

    IPC: H02J7/00 ,  B64D41/00

    CPC classification number: H02J7/0063 ,  B64D41/00 ,  H02J7/0014 ,  H02J7/0031 ,  B64D2221/00 ,  H02J2310/44

    Abstract: An assembly for an aircraft includes an aircraft electrical distribution bus, a battery, and a battery monitoring system. The battery includes a plurality of battery strings and a main battery contactor. The plurality of battery strings are electrically connected in parallel. Each battery string includes a string contactor. The string contactor is positionable in a closed string position or an open string position. The main battery contactor is electrically connected in series with the string contactor of each battery string. The main battery contactor is positionable in a closed battery position or an open battery position. The battery monitoring system is configured to control a position of the string contactor of each battery string. Control of a position of the main battery contactor in the closed battery position and the open battery position is independent of the battery monitoring system.

    SYSTEM AND METHOD FOR CONTROLLING AN AIRCRAFT ELECTRICAL DISTRIBUTION SYSTEM
    22.
    发明公开
    SYSTEM AND METHOD FOR CONTROLLING AN AIRCRAFT ELECTRICAL DISTRIBUTION SYSTEM 审中-公开

    公开(公告)号：US20240308350A1

    公开(公告)日：2024-09-19

    申请号：US18123266

    申请日：2023-03-18

    Applicant: Pratt & Whitney Canada Corp.

    Inventor： Raphael Gariepy ,  Simon Lam ,  Remi Robache ,  Antwan Shenouda ,  Richard Freer ,  Ninad Joshi

    IPC: B60L3/04 ,  B60L3/00 ,  B64D27/24

    CPC classification number: B60L3/04 ,  B60L3/0046 ,  B64D27/24 ,  B64D2221/00

    Abstract: An assembly for an aircraft includes an aircraft electrical distribution bus, a battery, and a control system. The battery includes a plurality of battery strings. Each battery string includes a string contactor. The control system is in signal communication with the string contactor of each battery string. The control system is configured to control a position of the string contactor of each battery string in a closed string position or an open string position. The control system is configured to: detect a fault in a faulted first battery string of the plurality of battery strings and position the string contactor of the faulted first battery string in the open string position, in response to the detected fault in the faulted first battery string and maintain the string contactor of at least one unfaulted second battery string of the plurality of battery strings in the closed string position.

    METHOD AND SYSTEM FOR GLOW PLUG OPERATION
    27.
    发明申请
    METHOD AND SYSTEM FOR GLOW PLUG OPERATION 有权

    公开(公告)号：US20220154647A1

    公开(公告)日：2022-05-19

    申请号：US16951187

    申请日：2020-11-18

    Applicant: PRATT & WHITNEY CANADA CORP.

    Inventor： Mehmet Celal TANJU ,  Richard Freer

    IPC: F02C7/266 ,  F02C9/00

    Abstract: There are described methods and systems for operating a glow plug. The method comprises monitoring a glow plug current; applying a nominal voltage VN to the glow plug when the glow plug current is between an upper threshold I1 and a lower threshold I2 VN to the glow plug when the glow plug current exceeds the upper threshold I1; and applying substantially no voltage to the glow plug when the glow plug current falls below the lower threshold I2.

    DC bus voltage control
    30.
    发明授权
    DC bus voltage control 有权

    公开(公告)号：US12240625B2

    公开(公告)日：2025-03-04

    申请号：US18110565

    申请日：2023-02-16

    Applicant: PRATT & WHITNEY CANADA CORP.

    Inventor： Richard Freer

    IPC: H02M3/158 ,  B64D27/24 ,  B64D41/00 ,  H02J1/00 ,  H02M1/00 ,  H02M1/32

    Abstract: In accordance with at least one aspect of this disclosure, there is provided a system for aircraft power. The system includes a DC/DC converter having a DC input and a DC output and a switching circuit connecting the DC input to the DC output operable to vary voltage at the DC output. A control module is operatively connected to the switching circuit for variable control of the DC output. The control module includes machine readable instructions to cause the control module to receive input indicative of altitude and control the switching circuit to vary voltage of the DC output as a function of environmental conditions such as altitude and humidity. In embodiments the altitude sensor is operatively connected to the controller.

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