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    REDUNDANT FLY-BY-WIRE SYSTEMS WITH FAULT RESILIENCY
    1.
    发明申请
    REDUNDANT FLY-BY-WIRE SYSTEMS WITH FAULT RESILIENCY 审中-公开

    公开(公告)号：US20200031454A1

    公开(公告)日：2020-01-30

    申请号：US16048612

    申请日：2018-07-30

    Applicant: HONEYWELL INTERNATIONAL INC.

    Inventor： Dean Wilkens

    IPC: B64C13/50

    Abstract: Aircraft fly-by-wire systems and related vehicle electrical systems are provided. In one embodiment, an electrical system suitable for use with a control surface of a vehicle, such as an aircraft, is provided. The electrical system includes a plurality of communications buses and a plurality of control modules, wherein each of the plurality of control modules is connected to a respective subset of the plurality of communications buses that is unique among the plurality of control modules, and a plurality of actuation control modules associated with the control surface, wherein each of the plurality of actuation control modules is connected to a respective subset of the plurality of communications buses that is unique among the plurality of actuation control modules. Thus, each of the control modules is isolated from at least one of the communications buses.

    AUTOMATIC FLIGHT CONTROL ACTUATOR SYSTEMS
    2.
    发明申请
    AUTOMATIC FLIGHT CONTROL ACTUATOR SYSTEMS 审中-公开

    公开(公告)号：US20170350491A1

    公开(公告)日：2017-12-07

    申请号：US15171733

    申请日：2016-06-02

    Applicant: HONEYWELL INTERNATIONAL INC.

    Inventor： Dean Wilkens

    IPC: F16H49/00 ,  B64C13/28 ,  B64C13/18 ,  B64C27/605 ,  B64C13/04

    CPC classification number: F16H49/001 ,  B64C13/04 ,  B64C13/18 ,  B64C13/24 ,  B64C13/28 ,  B64C13/34 ,  B64C27/605

    Abstract: An automatic actuator system is provided. The automatic actuator system includes an input linkage that receives an input and an output linkage adapted to control a flight surface actuator. The automatic actuator system includes a first strain wave gear having a first circular spline coupled to the input linkage and a first flex spline rotatably coupled to the first circular spline. The automatic actuator system includes a second strain wave gear having a second circular spline coupled to the first flex spline. The second strain wave gear includes a second flex spline, and the second flex spline is coupled to the output linkage such that at least a portion of the input from the input linkage is transferred to the output linkage via the first strain wave gear and the second strain wave gear.

    HIGH-INTEGRITY ACTUATOR CONTROLLER AND CONTROL SYSTEMS
    4.
    发明公开
    HIGH-INTEGRITY ACTUATOR CONTROLLER AND CONTROL SYSTEMS 审中-公开

    公开(公告)号：US20230291336A1

    公开(公告)日：2023-09-14

    申请号：US18152803

    申请日：2023-01-11

    Applicant: HONEYWELL INTERNATIONAL INC.

    Inventor： Darrell Horner ,  Ronald Vaughan ,  Dean Wilkens

    IPC: H02P6/24 ,  H03K7/08

    CPC classification number: H02P6/24 ,  H03K7/08 ,  H02P2101/30

    Abstract: A high-integrity electromechanical actuator control system includes a system function controller, a plurality of actuator controllers, and at least one electromechanical actuator. Each actuator controller includes a first controller, a second controller, and a duty cycle computation circuit. The first controller receives digital actuator control commands supplied from two of the function control channels and supplies first digital duty cycle commands. The second controller receives digital actuator control commands supplied from two function control channels and supplies second digital duty cycle commands. The duty cycle computation circuit receives the first digital duty cycle commands and the second digital duty cycle commands, computes an average of the first and second duty cycle commands, and generates pulse width modulated (PWM) commutation control signals based on the computed average.

    FLY-BY-WIRE SYSTEMS AND RELATED OPERATING METHODS
    5.
    发明申请
    FLY-BY-WIRE SYSTEMS AND RELATED OPERATING METHODS 审中-公开

    公开(公告)号：US20200262544A1

    公开(公告)日：2020-08-20

    申请号：US16279552

    申请日：2019-02-19

    Applicant: Honeywell International Inc.

    Inventor： Dean Wilkens

    IPC: B64C13/50 ,  G05D1/00 ,  H04L12/40 ,  B64D43/00

    Abstract: Aircraft fly-by-wire systems and related vehicle electrical systems are provided. In one embodiment, an electrical system suitable for use with a control surface of a vehicle, such as an aircraft, is provided. The electrical system includes an asynchronous intermodule bus arrangement, a first vehicle control module, and a second vehicle control module. Each vehicle control module includes a respective interface arrangement to obtain and exchange data from different sensing arrangements with a first frequency, and a respective processing system to obtain the sensed data and determine actuator commands based on the sensed data with a lower frequency.

    High-integrity actuator controller and control systems
    6.
    发明授权
    High-integrity actuator controller and control systems 有权

    公开(公告)号：US12244258B2

    公开(公告)日：2025-03-04

    申请号：US18152803

    申请日：2023-01-11

    Applicant: HONEYWELL INTERNATIONAL INC.

    Inventor： Darrell Horner ,  Ronald Vaughan ,  Dean Wilkens

    IPC: H02P6/24 ,  H02P101/30 ,  H03K7/08

    Abstract: A high-integrity electromechanical actuator control system includes a system function controller, a plurality of actuator controllers, and at least one electromechanical actuator. Each actuator controller includes a first controller, a second controller, and a duty cycle computation circuit. The first controller receives digital actuator control commands supplied from two of the function control channels and supplies first digital duty cycle commands. The second controller receives digital actuator control commands supplied from two function control channels and supplies second digital duty cycle commands. The duty cycle computation circuit receives the first digital duty cycle commands and the second digital duty cycle commands, computes an average of the first and second duty cycle commands, and generates pulse width modulated (PWM) commutation control signals based on the computed average.

    Redundant fly-by-wire systems with fault resiliency
    8.
    发明授权
    Redundant fly-by-wire systems with fault resiliency 有权

    公开(公告)号：US11155341B2

    公开(公告)日：2021-10-26

    申请号：US16048612

    申请日：2018-07-30

    Applicant: HONEYWELL INTERNATIONAL INC.

    Inventor： Dean Wilkens

    IPC: B64C13/50 ,  H04L12/40

    Abstract: Aircraft fly-by-wire systems and related vehicle electrical systems are provided. In one embodiment, an electrical system suitable for use with a control surface of a vehicle, such as an aircraft, is provided. The electrical system includes a plurality of communications buses and a plurality of control modules, wherein each of the plurality of control modules is connected to a respective subset of the plurality of communications buses that is unique among the plurality of control modules, and a plurality of actuation control modules associated with the control surface, wherein each of the plurality of actuation control modules is connected to a respective subset of the plurality of communications buses that is unique among the plurality of actuation control modules. Thus, each of the control modules is isolated from at least one of the communications buses.

    Hydrostatic automatic flight servo systems
    9.
    发明授权
    Hydrostatic automatic flight servo systems 有权

    公开(公告)号：US10118689B2

    公开(公告)日：2018-11-06

    申请号：US14823128

    申请日：2015-08-11

    Applicant: HONEYWELL INTERNATIONAL INC.

    Inventor： Pablo Bandera ,  Jon Bartling ,  Dean Wilkens

    IPC: B64C13/36 ,  B64C13/16

    Abstract: A hydrostatic automatic flight servo system is provided. The automatic flight servo system includes a manifold that defines a first fluid chamber, and a hydraulic fluid is received in the first fluid chamber. The first fluid chamber includes a first bellows and a second bellows. The automatic flight servo system includes a stick received at least partially within the manifold and pivotally coupled to the manifold. The stick includes a control arm fixedly coupled to the first bellows, and the stick is to receive an input. The automatic flight servo system includes a flight output system pivotally coupled to the manifold. The flight output system includes a second control arm received at least partially within the manifold and coupled to the second bellows such that the pivotal movement of the stick pivots the flight output system relative to the manifold.

    Fly-by-wire systems and related operating methods
    10.
    发明授权
    Fly-by-wire systems and related operating methods 有权

    公开(公告)号：US11097834B2

    公开(公告)日：2021-08-24

    申请号：US16279552

    申请日：2019-02-19

    Applicant: HONEYWELL INTERNATIONAL INC.

    Inventor： Dean Wilkens

    IPC: B64C13/50 ,  G05D1/00 ,  B64D43/00 ,  H04L12/40

    Abstract: Aircraft fly-by-wire systems and related vehicle electrical systems are provided. In one embodiment, an electrical system suitable for use with a control surface of a vehicle, such as an aircraft, is provided. The electrical system includes an asynchronous intermodule bus arrangement, a first vehicle control module, and a second vehicle control module. Each vehicle control module includes a respective interface arrangement to obtain and exchange data from different sensing arrangements with a first frequency, and a respective processing system to obtain the sensed data and determine actuator commands based on the sensed data with a lower frequency.

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