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    METHODS AND SYSTEMS FOR SYNCHROPHASING USING ASYNCHRONOUS BUSES
    1.
    发明公开
    METHODS AND SYSTEMS FOR SYNCHROPHASING USING ASYNCHRONOUS BUSES 审中-公开

    公开(公告)号：EP4429133A1

    公开(公告)日：2024-09-11

    申请号：EP24157367.4

    申请日：2024-02-13

    申请人： Honeywell International Inc.

    发明人： PARK, Sean ,  STERBENZ, Ryan

    IPC分类号： H04J3/06 ,  G06F13/42 ,  H04L12/40 ,  B64C11/50

    CPC分类号： H04J3/0664 ,  G06F13/42 ,  H04L2012/402820130101 ,  H04L2012/4021520130101 ,  B64C11/50 ,  H04L2012/4027320130101

    摘要： Vehicle systems and methods are provided for synchronizing control modules over a communications bus for synchrophasing propellers. A vehicle electrical system includes a communications bus, a bus control module to transmit a first message over the communications bus, a vehicle control module coupled to the bus control module to identify a first timestamp associated with the first message being transmitted in a first clock domain associated with the vehicle control module and provide a subsequent message to the bus control module including the first timestamp, and an actuator control module coupled to the communications bus to identify a second timestamp associated with the first message being received over the communications bus and determine an adjustment to synchronize a second clock domain associated with the actuator control module with the first clock domain based at least in part on a relationship between the first timestamp and the second timestamp.

    APPARATUS AND METHODS FOR AIRCRAFT PROPELLER CONTROL
    2.
    发明公开
    APPARATUS AND METHODS FOR AIRCRAFT PROPELLER CONTROL 审中-公开

    公开(公告)号：EP3974313A1

    公开(公告)日：2022-03-30

    申请号：EP21203536.4

    申请日：2017-08-17

    申请人： PRATT & WHITNEY CANADA CORP.

    发明人： YAKOBOV, Ella ,  JARVO, James Robert

    IPC分类号： B64C11/30 ,  B64C11/50

    摘要： An aircraft propeller control system for an aircraft propeller (30) with adjustable blade angle has a blade angle feedback ring (104) and a sensor (112), one of which is mounted for rotation with the propeller. The blade angle feedback ring (104) moves longitudinally along with adjustment of the blade angle and has position markers (102) circumferentially spaced apart at distances that vary along a longitudinal axis. The sensor (112) is positioned adjacent the feedback ring (104) for producing signals indicative of passage of the position markers (102). Intervals between signals are indicative of circumferential distances between position markers (102). A controller (115) measures longitudinal position of the feedback ring (104) based on the intervals and is configured to produce a warning signal if the longitudinal position is outside a first threshold range.

    Propeller blade position controller
    4.
    发明公开
    Propeller blade position controller 失效
    Stellungsbedienung eines Luftschraubenblattes。

    公开(公告)号：EP0663337A1

    公开(公告)日：1995-07-19

    申请号：EP95200109.7

    申请日：1995-01-17

    申请人： FOKKER AIRCRAFT B.V.

    发明人： Kaptein, Dick

    IPC分类号： B64C11/50

    CPC分类号： G10K11/175 ,  B64C11/50

    摘要： System (1) for reducing vibrations in the cabin of an air-craft driven by two or more propellers each having n blades, where n is an integer equal or larger than 2, of which the relative phase angle can be adjusted, said system comprising synchrophase means (2) for adjusting said relative phase angle such that a predetermined relative phase angle is maintained. The system furthermore comprises means (3) supplying information about the vibration level at one or more positions within the cabin or information related thereto and for generating a corresponding vibration level signal, and a control unit (4) which in response to said vibration level signal supplies an error signal to the synchrophase means (2) causing the synchrophase means to adjust the blades of the various propellers such that a new relative phase angle is maintained which differs m.(2π/n) radians, where m is an integer, from the previous relative phase angle. Each propeller comprises at least one recognising means (60, 61) attached to one of its propeller blades, the recognising means (60, 61) being detectable by a sensor (35, 36) in order to establish the absolute position of the various propeller blades.

    摘要翻译： 一种用于减少由两个或更多个具有n个叶片的螺旋桨驱动的飞行器的机舱中的振动的系统（1），其中n是等于或大于2的整数，其中可以调节相对相位角，所述系统包括 同步酶装置（2）用于调节所述相对相位角，使得保持预定的相对相位角。 该系统还包括提供关于机舱内的一个或多个位置处的振动水平的信息或与其相关的信息的装置（3），以及用于产生相应的振动水平信号的装置（3），以及响应于所述振动水平信号 向同步酶装置（2）提供误差信号，使得同步酶装置调节各种螺旋桨的叶片，使得保持新的相对相位角，其不同于m（2π/ n）弧度，其中m是整数， 从前一个相对相位角。 每个螺旋桨包括至少一个附接到其螺旋桨叶片之一的识别装置（60,61），识别装置（60,61）可由传感器（35,36）检测，以便确定各种螺旋桨的绝对位置 刀片。

    Propeller phase control apparatus
    5.
    发明公开
    Propeller phase control apparatus 失效
    螺旋桨相位控制装置

    公开(公告)号：EP0322343A3

    公开(公告)日：1989-10-25

    申请号：EP88630228.0

    申请日：1988-12-14

    申请人： UNITED TECHNOLOGIES CORPORATION

    发明人： Martin, Anthony Newman

    IPC分类号： B64C11/50 ,  B64D31/12

    CPC分类号： B64C11/50 ,  B64D31/12 ,  Y02T50/66

    摘要： Propeller phase control apparatus for use on multi-engine aircraft having, for each engine (12,14), an electronic engine control (EEC) (21,22) for providing an EEC command speed and phase (S/P) signal to control propeller phase and shaft speed, and a speed and phase control (SPC) (23,24) for regulating the propeller's blade pitch angle to adjust the shaft speed thereof in dependence on the EEC command S/P signal value, includes: a SYNCHROPHASER Reference Unit (SRU) (18) having a signal processor with signal memory, the memory including stored signals definitive of a speed and phase algorithm, the signal processor calculating a common SRU command S/P signal value for all SPCs in accordance with the algorithm and in dependence on the sensed values of selected flight data indicative of engine performance, and further includes an electronic switch (19,20) for each SPC, for selecting either the SRU command S/P signal or the engine's EEC command S/P signal for presentation to the SPC.

    PROPELLER BLADE SYNCHROPHASING USING PHONIC WHEEL
    8.
    发明公开
    PROPELLER BLADE SYNCHROPHASING USING PHONIC WHEEL 审中-公开

    公开(公告)号：EP3967607A1

    公开(公告)日：2022-03-16

    申请号：EP21199601.2

    申请日：2019-07-01

    申请人： PRATT & WHITNEY CANADA CORP.

    发明人： YAKOBOV, Ella ,  JARVO, James ,  TABAR, Roja

    IPC分类号： B64D31/12 ,  B64C11/50

    摘要： Herein provided are systems and methods for synchrophasing multi-engine aircraft. A phonic wheel (204) is coupled to a first propeller (130) of a first engine (110) of the aircraft. A sensor (212) is disposed and configured for producing a signal in response to passage of first and second position markers (420) on the phonic wheel (204). A control system (220) is communicatively coupled to the sensor (212) for obtaining the signal, and configured for: determining an expected delay between two subsequent signal pulses of the signal; identifying from within the plurality of signal pulses a particular pulse associated with the second position marker (420); determining, based on a particular time at which the particular pulse associated with the second position marker (420) was produced, that a rotational position of the first propeller (130) corresponds to a reference position at the particular time; and performing at least one synchrophasing operation for the aircraft based on the rotational position of the first propeller (130).