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    FIBER OPTIC SLAT FLAP SYSTEM AND CONTROL LEVER
    3.
    发明公开
    FIBER OPTIC SLAT FLAP SYSTEM AND CONTROL LEVER 审中-公开

    公开(公告)号：EP4371875A1

    公开(公告)日：2024-05-22

    申请号：EP23210977.7

    申请日：2023-11-20

    申请人： Hamilton Sundstrand Corporation

    发明人： ANKNEY, Darrell E.

    IPC分类号： B64C13/50 ,  G05D1/49

    CPC分类号： B64C13/503

    摘要： A control system performs a method of controlling a wing of an airplane. The control system includes an optical fiber (112, 114), a bending device (410) and a processor (210). The optical fiber is configured to receive light having an input optical phase. The bending device applies an external force on the optical fiber. The external force causes the light exiting the optical fiber to have an output optical phase. a processor determines a phase shift between the input optical phase and the output optical phase and controls the wing based on the phase shift.

    WING FOR AN AIRCRAFT
    6.
    发明公开
    WING FOR AN AIRCRAFT 审中-公开

    公开(公告)号：EP4311766A1

    公开(公告)日：2024-01-31

    申请号：EP22187881.2

    申请日：2022-07-29

    申请人： Airbus Operations GmbH

    发明人： Schlipf, Bernhard ,  Haunert, Jan

    IPC分类号： B64C9/02 ,  B64C9/06 ,  B64C9/20 ,  B64C13/30 ,  B64C13/50

    摘要： Disclosed is a wing (3) for an aircraft (1), comprising a main wing (5) and a trailing edge high lift assembly (9) movably arranged at a trailing edge of the main wing (5), the trailing edge high lift assembly (9) comprising a flap (11) and a connection assembly (13) movably mounting the flap (11) to the main wing (5), wherein the connection assembly (13) comprises an actuator unit (35) for moving the flap (11) between a retracted position and at least one extended position, wherein the flap (11) comprises a leading edge part (23) and a trailing edge part (27) mounted to the leading edge part (23) in a manner pivotable about a pivot axis (31). The object to provide a wing having a simplified trailing edge high lift assembly that allows to reduce weight and costs of the wing, is achieved in that the actuator unit (35) is configured for moving the trailing edge part (27) relative to the leading edge part (23) in a way independent from moving the flap (11) between the retracted position and the at least one extended position, and/or in that the actuator unit (35) is configured for moving the flap (11) between the retracted position and the at least one extended position in a way independent from moving the trailing edge part (27) relative to the leading edge part (23)

    ERROR MONITORS FOR COLLECTIVE AND CYCLIC CONTROL STICKS
    7.
    发明公开
    ERROR MONITORS FOR COLLECTIVE AND CYCLIC CONTROL STICKS 审中-公开

    公开(公告)号：EP4310007A1

    公开(公告)日：2024-01-24

    申请号：EP23182294.1

    申请日：2023-06-29

    申请人： Textron Innovations Inc.

    发明人： ALFRED, Jillian Samantha ,  HOANG, Lan Nam ,  HARRELL, Clifton Lee

    IPC分类号： B64D45/00 ,  B64C27/57 ,  B64C13/50 ,  B64C13/10

    摘要： In an embodiment, a rotorcraft (101) includes a control element (201); a first detent sensor (235) connected to the control element, the first detent sensor being operable to generate detent slip rate data indicating movement of the control element and detent state data indicating pilot control (233) of the control element; a first trim motor (213) connected to the control element and operable to generate trim rate data; and an FCC (205) in signal communication with the first detent sensor and the first trim motor, the FCC including an error monitor (903, 905, 907) operable to compare the detent slip rate data with the trim rate data and determine whether the first detent sensor is functional or defective, operable to provide a first flight management function when the first detent sensor is determined to be functional, and operable to provide a second flight management function when the first detent sensor is determined to be defective.