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    Flight control laws for constant vector flat turns
    1.
    发明授权
    Flight control laws for constant vector flat turns 有权
    恒定矢量平转的飞行控制规律

    公开(公告)号：US08682505B2

    公开(公告)日：2014-03-25

    申请号：US13711234

    申请日：2012-12-11

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Kevin Thomas Christensen ,  Shyhpyng Jack Shue ,  Troy Sheldon Caudill

    IPC: G05D1/08 ,  B64C19/00 ,  G06F7/00

    CPC classification number: B64C19/00 ,  G05D1/0202 ,  G05D1/0858

    Abstract: An aircraft and method to control flat yawing turns of the aircraft while maintaining a constant vector heading across a ground surface. The aircraft includes a control system in data communication with a model, a lateral control architecture, a longitudinal control architecture, and an initialization command logic. The model decouples the directional movement of the aircraft into a lateral equation of motion and a longitudinal equation of motion. The lateral control architecture utilizes the lateral equation of motion to control the aircraft in the lateral direction, while the longitudinal control architecture utilizes the longitudinal equation of motion to control the aircraft in the longitudinal direction. The initialization command logic selectively activates the lateral control architecture and the longitudinal control architecture.

    Abstract translation: 一种飞机和方法，用于控制飞机的平面偏转转弯，同时保持恒定的向量横过地面。 飞机包括与模型进行数据通信的控制系统，横向控制架构，纵向控制架构和初始化命令逻辑。 该模型将飞机的方向运动分解为侧向运动方程和纵向运动方程。 横向控制结构利用横向运动方程来控制飞行器的横向方向，而纵向控制结构利用纵向运动方程来控制飞行器的纵向方向。 初始化命令逻辑选择性地激活横向控制架构和纵向控制架构。

    EXTENSION OF THREE LOOP CONTROL LAWS FOR SYSTEM UNCERTAINTIES, CALCULATION TIME DELAY AND COMMAND QUICKNESS
    2.
    发明申请
    EXTENSION OF THREE LOOP CONTROL LAWS FOR SYSTEM UNCERTAINTIES, CALCULATION TIME DELAY AND COMMAND QUICKNESS 有权
    延长系统不确定度的三环控制法，计算时间延迟和命令快速

    公开(公告)号：US20130274963A1

    公开(公告)日：2013-10-17

    申请号：US13926072

    申请日：2013-06-25

    Applicant: BELL HELICOPTER TEXTRON INC.

    Inventor： Shyhpyng Jack Shue ,  John J. Schillings

    IPC: B64C19/00

    CPC classification number: B64C19/00 ,  G05D1/0858

    Abstract: A system includes a plurality of actuators and a control system operably associated with the plurality of actuators. The control system having a control logic architecture having a dynamic command input shaping model associated with an input command, a robust inner loop associated with the dynamic command input shaping model, and a time delay cancellation model. The method includes selecting a control law based upon a flight performance of an aircraft, decoupling the control law into a first individual component and a second individual component of the aircraft flight motion, analyzing each individual component separately, regrouping the component of flight motion, analyzing the control law with a time delay cancellation model and providing the necessary dynamic flight quickness with a different command input condition.

    Abstract translation: 系统包括多个致动器和可操作地与多个致动器相关联的控制系统。 所述控制系统具有控制逻辑架构，其具有与输入命令相关联的动态命令输入整形模型，与所述动态命令输入整形模型相关联的鲁棒内部循环，以及时间延迟消除模型。 该方法包括基于飞行器的飞行性能来选择控制律，将控制律解耦到飞行器飞行运动的第一个单独部件和第二个单独部件，分别分析各个部件，重新组合飞行运动的分量，分析 具有时间延迟消除模型的控制规律，并使用不同的命令输入条件提供必要的动态飞行速度。

    Method and apparatus for aircraft sensor and actuator failure protection using reconfigurable flight control laws
    7.
    发明授权
    Method and apparatus for aircraft sensor and actuator failure protection using reconfigurable flight control laws 有权

    公开(公告)号：US10183743B2

    公开(公告)日：2019-01-22

    申请号：US15646680

    申请日：2017-07-11

    Applicant: BELL HELICOPTER TEXTRON INC.

    Inventor： Shyhpyng Jack Shue ,  John James Corrigan ,  Eric Thomas Bird ,  Tommie Lynn Wood ,  Alan Carl Ewing

    IPC: B64C27/54 ,  G05D1/00 ,  G05D1/08 ,  G05B19/042 ,  G05B23/02 ,  B64C19/00

    Abstract: A method and apparatus for reconfiguring flight control of an aircraft during a failure while the aircraft is flying. The method and apparatus provide a control law that is software-implemented and configured to automatically send flight control data to a mixing/mapping matrix. The method and apparatus also provide a reconfiguration management tool configured to communicate with the mixing/mapping matrix in order to safely transfer authority from a failed actuator to a back-up actuator. The method and apparatus also provide a sensor management tool for providing input to the reconfiguration management tool in order to smooth any transient conditions that may occur during reconfiguration. The method and apparatus provide for a way of smoothing any possible transient situation that might otherwise occur by employment of a fader, the fader being used to gradually convert positioning of failed actuators and positioning of reconfigured actuators. An exemplary aircraft for using the method and apparatus of a reconfigurable flight control system is a quad tilt rotor. The quad tilt rotor provides a variety of redundant and back-actuators, as such, having a robust and highly qualified reconfigurable flight control system is very desirable.

    Extension of three loop control laws for system uncertainties, calculation time delay and command quickness
    8.
    发明授权
    Extension of three loop control laws for system uncertainties, calculation time delay and command quickness 有权
    延长系统不确定度的三回路控制规律，计算时间延迟和指挥速度

    公开(公告)号：US08942866B2

    公开(公告)日：2015-01-27

    申请号：US13926072

    申请日：2013-06-25

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Shyhpyng Jack Shue ,  John J. Schillings

    IPC: G06F19/00 ,  G01C22/00

    CPC classification number: B64C19/00 ,  G05D1/0858

    Abstract: A system includes a plurality of actuators and a control system operably associated with the plurality of actuators. The control system having a control logic architecture having a dynamic command input shaping model associated with an input command, a robust inner loop associated with the dynamic command input shaping model, and a time delay cancellation model. The method includes selecting a control law based upon a flight performance of an aircraft, decoupling the control law into a first individual component and a second individual component of the aircraft flight motion, analyzing each individual component separately, regrouping the component of flight motion, analyzing the control law with a time delay cancellation model and providing the necessary dynamic flight quickness with a different command input condition.

    Abstract translation: 系统包括多个致动器和可操作地与多个致动器相关联的控制系统。 所述控制系统具有控制逻辑架构，其具有与输入命令相关联的动态命令输入整形模型，与所述动态命令输入整形模型相关联的鲁棒内部循环，以及时间延迟消除模型。 该方法包括基于飞行器的飞行性能来选择控制律，将控制律解耦到飞行器飞行运动的第一个单独部件和第二个单独部件，分别分析各个部件，重新组合飞行运动的分量，分析 具有时间延迟消除模型的控制规律，并使用不同的命令输入条件提供必要的动态飞行速度。

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