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    SYSTEM AND METHOD FOR CONTROLLING AN AIRCRAFT ELECTRICAL DISRIBUTION SYSTEM
    1.
    发明公开
    SYSTEM AND METHOD FOR CONTROLLING AN AIRCRAFT ELECTRICAL DISRIBUTION SYSTEM 审中-公开

    公开(公告)号：EP4436002A1

    公开(公告)日：2024-09-25

    申请号：EP24164306.3

    申请日：2024-03-18

    申请人： PRATT & WHITNEY CANADA CORP.

    发明人： GARIEPY, Raphael ,  LAM, Simon ,  ROBACHE, Remi ,  SHENOUDA, Antwan ,  FREER, Richard ,  JOSHI, Ninad

    IPC分类号： H02J7/00 ,  H02J7/34

    CPC分类号： H02J7/0031 ,  H02J7/0013 ,  H02J7/34 ,  H02J2310/4420200101 ,  B64D2221/0020130101

    摘要： An assembly for an aircraft includes an aircraft electrical distribution bus (66), a battery (70), and a control system (23). The battery (70) includes a plurality of battery strings (80). Each battery string (80) includes a string contactor (92). The control system (23) is in signal communication with the string contactor (92) of each battery string (80). The control system (23) is configured to control a position of the string contactor (92) of each battery string (80) in a closed string position or an open string position. The control system (23) is configured to: detect a fault in a faulted first battery string (80) of the plurality of battery strings (80) and position the string contactor (92) of the faulted first battery string (80) in the open string position, in response to the detected fault in the faulted first battery string (80) and maintain the string contactor (92) of at least one unfaulted second battery string (80) of the plurality of battery strings (80) in the closed string position.

    EMERGENCY BACKUP POWER SOURCE AND CONTROL CIRCUIT FOR ELECTRICALLY OPERATED AIRCRAFT WINDOW SHADES
    4.
    发明公开
    EMERGENCY BACKUP POWER SOURCE AND CONTROL CIRCUIT FOR ELECTRICALLY OPERATED AIRCRAFT WINDOW SHADES 审中-实审

    公开(公告)号：EP4395119A2

    公开(公告)日：2024-07-03

    申请号：EP23220749.8

    申请日：2023-12-29

    申请人： Ceste, Mario ,  Mohamed, Mohamed

    发明人： Ceste, Mario ,  Mohamed, Mohamed

    IPC分类号： H02J7/34 ,  H02J9/06

    CPC分类号： H02J9/061 ,  H02J7/345 ,  H02J2207/5020200101 ,  H02J2310/4420200101

    摘要： An emergency backup power source for an electrically controlled and motorized window shade unit includes an input power switch, and charge and discharge control circuit, and a supercapacitor bank. During normal operation a nominal voltage level from a main power source of the aircraft is provided directly to the window shade unit through the input power switch, and the supercapacitor bank is charged. The input voltage is monitored by the emergency backup power source, which controls the input power switch. When the input voltage drops below a threshold level, the input power switch is opened and the charge and discharge circuit operates to provide an emergency output voltage to the window shade unit from the supercapacitor bank so that the window shade can be fully opened or closed, as is required.

    SYSTEM AND METHOD FOR CONTROLLING AN AIRCRAFT BATTERY ASSEMBLY
    10.
    发明公开
    SYSTEM AND METHOD FOR CONTROLLING AN AIRCRAFT BATTERY ASSEMBLY 审中-实审

    公开(公告)号：EP4415213A3

    公开(公告)日：2024-08-21

    申请号：EP24156408.7

    申请日：2024-02-07

    申请人： PRATT & WHITNEY CANADA CORP.

    发明人： FREER, Richard ,  SHENOUDA, Antwan ,  LAM, Simon ,  ROBACHE, Remi ,  GARIEPY, Raphael

    IPC分类号： H02J7/00

    CPC分类号： B64D2221/0020130101 ,  H02J2310/4420200101 ,  H02J7/0013 ,  H02J7/0025 ,  H02J7/0047

    摘要： An assembly (24) for an aircraft (1000) includes an aircraft electrical distribution bus (66), a battery (70), and a battery monitoring system (72). The battery includes a plurality of battery strings (80). The plurality of battery strings is configured as a main subset (106) and a reserve subset (108). The battery monitoring system further includes a processor (100) in communication with a non-transitory memory (102) storing instructions, which instructions when executed by the processor, cause the processor to electrically connect the reserve subset to the aircraft electrical distribution bus by: determining the bus voltage and the battery string voltage of each battery string of the reserve subset, identifying a threshold voltage range of the reserve subset for electrically connecting the reserve subset to the aircraft electrical distribution bus, where identifying the threshold voltage range is based at least on the bus voltage, and electrically connecting at least one battery string of the reserve subset to the aircraft electrical distribution bus with the bus voltage within the identified threshold voltage range.