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    Control logic for a propeller system
    2.
    发明公开
    Control logic for a propeller system 有权
    Steuerlogikfürein螺旋桨系统

    公开(公告)号：EP1787906A2

    公开(公告)日：2007-05-23

    申请号：EP06255854.9

    申请日：2006-11-15

    申请人： Hamilton Sundstrand Corporation

    发明人： Danielson, David R.

    IPC分类号： B64C11/30 ,  B64C11/34

    CPC分类号： B64C11/303 ,  B64C11/305 ,  B64C11/34

    摘要： A propeller control system (20) includes a propeller control logic subsystem (22) in conjunction with an engine control logic subsystem (24) to provide an optimized transition from forward to reverse speed governing under all operating conditions. By creating a Propeller control Mode (PCM) map relative the blade angle and Power Lever Angle (PLA), the minimum blade angle allowed for forward speed governing and the maximum blade angle allowed for reverse speed governing is determined. By combining the actual propeller blade angle, the min and max angles for speed governing, and the PLA signal, the state of the propeller speed governor is determined.

    摘要翻译： 螺旋桨控制系统（20）包括结合发动机控制逻辑子系统（24）的螺旋桨控制逻辑子系统（22），以在所有操作条件下提供从正向转向速度控制的优化过渡。 通过创建相对于叶片角度和功率杆角度（PLA）的螺旋桨控制模式（PCM）图，确定允许前进速度调节的最小叶片角度和允许反转速度控制的最大叶片角度。 通过结合实际螺旋桨叶片角度，速度控制的最小和最大角度以及PLA信号，确定螺旋桨调速器的状态。

    MODULARIZED LOGIC
    3.
    发明公开
    MODULARIZED LOGIC 审中-公开

    公开(公告)号：EP3376314A1

    公开(公告)日：2018-09-19

    申请号：EP17425031.6

    申请日：2017-03-14

    申请人： Ge Avio S.r.l.

    发明人： LAI, Cristian

    IPC分类号： G05B19/042 ,  G06F9/50

    CPC分类号： B64D31/00 ,  B64C11/303 ,  G05B19/042 ,  G05B2219/23328 ,  G06F9/5061

    摘要： One example aspect of the present disclosure is directed to a method for implementing modularized logic. The method includes accessing, by one or more processors, control software implemented on a controller to control operation of an aircraft engine. The method includes accessing, by the one or more processors, at least one of a plurality of propeller configuration parameters. The method includes modifying, by the one or more processors, the accessed at least one of the propeller configuration parameters independently of the control software.

    ELECTROHYDRAULIC PROPELLER GOVERNOR
    4.
    发明公开
    ELECTROHYDRAULIC PROPELLER GOVERNOR 有权
    电液调节器PROPELLER

    公开(公告)号：EP2807079A2

    公开(公告)日：2014-12-03

    申请号：EP13814269.0

    申请日：2013-05-28

    申请人： Woodward, Inc.

    发明人： KLECKLER, Joel W.

    IPC分类号： B64C11/30 ,  B64C11/38 ,  F01D7/00 ,  F01D7/02

    CPC分类号： F02C9/58 ,  B64C11/303 ,  B64C11/385 ,  B64C11/40 ,  F05D2260/77 ,  Y02T50/671

    摘要： A propeller governor for controlling blade pitch of a variable pitch propeller has a hydraulic control circuit coupled to the propeller to change blade pitch in response to hydraulic pressure. The hydraulic control circuit has a first pressure path configured to adjust blade pitch within a first range of blade pitch, and a second, different pressure path configured to adjust blade pitch within a second range of blade pitch. An electrohydraulic servo valve of the governor is configured to adjust hydraulic pressure in the first pressure path to adjust blade pitch within the first range and to adjust hydraulic pressure in the second pressure path to adjust blade pitch within the second range.

    GOVERNOR FOR A ROTOR WITH A VARIABLE MAXIMUM COLLECTIVE PITCH AND METHOD
    5.
    发明授权
    GOVERNOR FOR A ROTOR WITH A VARIABLE MAXIMUM COLLECTIVE PITCH AND METHOD 有权
    调速器具有可变最大集体膜片角度和程序转子

    公开(公告)号：EP2132089B1

    公开(公告)日：2010-12-01

    申请号：EP08799661.7

    申请日：2008-03-12

    申请人： Bell Helicopter Textron Inc.

    发明人： SCHAEFFER, Joseph, Matthew

    IPC分类号： B64C11/30 ,  B64C29/00 ,  G05D1/08

    CPC分类号： B64C11/303 ,  B64C29/0033

    摘要： A governor configured, to regulate the rotational velocity of one or more rotors (14) of an aircraft (12) by adjusting a collective blade pitch of the one or more rotors. In one embodiment, the governor (30) comprises a control monitor (38), a maximum pitch module, a rotor module, and a pitch adjustment module (44). The control monitor is configured to monitor one or more flight control inputs that are controllable by an operator of the aircraft. The maximum pitch module (40) is configured to dynamically determine a maximum collective blade pitch based on the one or more flight control inputs monitored by the control monitor. The rotor module is configured to monitor information related to the rotational velocity of the one or more rotors. The pitch adjustment module is configured to (i) receive information related to the rotational velocity of the one or more rotors from the rotor module and (ii) adjust the collective blade pitch of the one or more rotors to regulate the rotational velocity of the one or more rotors.

    COUNTERWEIGHTED PROPELLER CONTROL SYSTEM
    6.
    发明授权
    COUNTERWEIGHTED PROPELLER CONTROL SYSTEM 失效
    控制系统及气动螺丝配重

    公开(公告)号：EP0939725B1

    公开(公告)日：2001-09-12

    申请号：EP97949571.0

    申请日：1997-11-21

    申请人： UNITED TECHNOLOGIES CORPORATION

    发明人： AREL, David ,  PERKINSON, Robert, H. ,  DEGEORGE, Charles, L.

    IPC分类号： B64C11/38

    CPC分类号： B64C11/303 ,  B64C11/38 ,  B64C11/40

    摘要： A system (10) for controlling functions of a propeller having a plurality of blades (12) is disclosed. The system (10) comprises an electronic control (16) for controlling the functions of the propeller. A plurality of backup devices are provided for backing up the electronic control (16) upon the occurrence of conditions. These conditions include at least one of testing, manual override, and a malfunction in the electronic control (16) causing at least one of the functions to endanger safety. The system (10) further includes a bypass device (24) for bypassing the electronic control (16) and for invoking at least one of the plurality of backup devices to acquire control over at least one of the functions. The bypass devices include a mechanism for determining the occurrence of at least one of the conditions and for actuating electronic control override.

    Propeller speed governor having a derivative inhibit at high flight speeds
    7.
    发明公开
    Propeller speed governor having a derivative inhibit at high flight speeds 失效
    GeschwindigkeitsreglerfürPropellerantrieb mit Unterbrechung des differentnzierenden Zweiges bei hohen Fluggeschwindigkeiten。

    公开(公告)号：EP0392966A1

    公开(公告)日：1990-10-17

    申请号：EP90630084.3

    申请日：1990-04-10

    申请人： UNITED TECHNOLOGIES CORPORATION

    发明人： Schneider, Roy W. ,  DiValentin, Eugenio

    IPC分类号： B64C11/30 ,  G05B5/01

    CPC分类号： B64C11/303 ,  G05B11/42

    摘要： A propeller speed governor having a derivative feedback of propeller speed and having a means such as a switch to open the derivative feed back loop when airspeed exceeds a predetermined amount is shown and described. This derivative inhibit is used to provide improved dynamic compensation at high and low speeds.

    摘要翻译： 示出并描述了具有螺旋桨速度的微分反馈并且具有诸如开关的装置的螺旋桨调速器，当空速超过预定量时打开导数反馈回路。 该微分抑制用于在高速和低速下提供改进的动态补偿。