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公开(公告)号：US07641152B2
公开(公告)日：2010-01-05
申请号：US11734842
申请日：2007-04-13
Applicant: Dan Onu , John D. Winter , Candy L. Carr , Paul M. Vijgen , Gary A. Emch , Michael E. Renzelmann
Inventor： Dan Onu , John D. Winter , Candy L. Carr , Paul M. Vijgen , Gary A. Emch , Michael E. Renzelmann
IPC: G05D1/00
Abstract: The movable surfaces affecting the camber of a wing are dynamically adjusted to optimize wing camber for optimum lift/drag ratios under changing conditions during a given flight phase. In a preferred embodiment, an add-on dynamic adjustment control module provides command signals for optimum positioning of trailing edge movable surfaces, i.e., inboard flaps, outboard flaps, ailerons, and flaperons, which are used in place of the predetermined positions of the standard flight control system. The dynamic adjustment control module utilizes inputs of changing aircraft conditions such as altitude, Mach number, weight, center of gravity, vertical speed and flight phase. The dynamic adjustment control module's commands for repositioning the movable surfaces of the wing are transmitted through the standard flight control system to actuators for moving the flight control surfaces.
Abstract translation: 在给定的飞行阶段期间，在变化的条件下，动态地调整影响机翼弧度的可移动表面，以优化机翼弧度以获得最佳升力/牵引比。 在优选实施例中，附加动态调节控制模块提供用于最终定位后缘可移动表面（即，内侧翼片，外侧翼片，副翼和襟翼）的命令信号，其用于代替标准的预定位置 飞行控制系统。 动态调整控制模块利用改变飞行器条件的输入，如高度，马赫数，重量，重心，垂直速度和飞行阶段。 动态调整控制模块用于重新定位机翼的可移动表面的命令通过标准飞行控制系统传输到用于移动飞行控制表面的致动器。
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公开(公告)号：US08447445B2
公开(公告)日：2013-05-21
申请号：US12620698
申请日：2009-11-18
Applicant: Dan Onu , John D. Winter , Candy L. Carr , Paul M. Vijgen , Gary A. Emch , Michael E. Renzelmann
Inventor： Dan Onu , John D. Winter , Candy L. Carr , Paul M. Vijgen , Gary A. Emch , Michael E. Renzelmann
IPC: B64C13/00
Abstract: The movable surfaces affecting the camber of a wing are dynamically adjusted to optimize wing camber for optimum lift/drag ratios under changing conditions during a given flight phase. In a preferred embodiment, an add-on dynamic adjustment control module provides command signals for optimum positioning of trailing edge movable surfaces, i.e., inboard flaps, outboard flaps, ailerons, and flaperons, which are used in place of the predetermined positions of the standard flight control system. The dynamic adjustment control module utilizes inputs of changing aircraft conditions such as altitude, Mach number, weight, center of gravity (CG), vertical speed and flight phase. The dynamic adjustment control module's commands for repositioning the movable surfaces of the wing are transmitted through the standard flight control system to actuators for moving the flight control surfaces.
Abstract translation: 在给定的飞行阶段期间，在变化的条件下，动态地调整影响机翼弧度的可移动表面，以优化机翼弧度以获得最佳升力/牵引比。 在优选实施例中，附加动态调节控制模块提供用于最终定位后缘可移动表面（即，内侧翼片，外侧翼片，副翼和襟翼）的命令信号，其用于代替标准的预定位置 飞行控制系统。 动态调整控制模块利用高度，马赫数，重量，重心（CG），垂直速度和飞行阶段等改变飞机状态的输入。 动态调整控制模块用于重新定位机翼的可移动表面的命令通过标准飞行控制系统传输到用于移动飞行控制表面的致动器。
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公开(公告)号：US20080255713A1
公开(公告)日：2008-10-16
申请号：US11734842
申请日：2007-04-13
Applicant: Dan Onu , John D. Winter , Candy L. Carr , Paul M. Vijgen , Gary A. Emch , Michael E. Renzelmann
Inventor： Dan Onu , John D. Winter , Candy L. Carr , Paul M. Vijgen , Gary A. Emch , Michael E. Renzelmann
Abstract: The movable surfaces affecting the camber of a wing are dynamically adjusted to optimize wing camber for optimum lift/drag ratios under changing conditions during a given flight phase. In a preferred embodiment, an add-on dynamic adjustment control module provides command signals for optimum positioning of trailing edge movable surfaces, i.e., inboard flaps, outboard flaps, ailerons, and flaperons, which are used in place of the predetermined positions of the standard flight control system. The dynamic adjustment control module utilizes inputs of changing aircraft conditions such as altitude, Mach number, weight, center of gravity, vertical speed and flight phase. The dynamic adjustment control module's commands for repositioning the movable surfaces of the wing are transmitted through the standard flight control system to actuators for moving the flight control surfaces.
Abstract translation: 在给定的飞行阶段期间，在变化的条件下，动态地调整影响机翼弧度的可移动表面，以优化机翼弧度以获得最佳升力/牵引比。 在优选实施例中，附加动态调节控制模块提供用于最终定位后缘可移动表面（即，内侧翼片，外侧翼片，副翼和襟翼）的命令信号，其用于代替标准的预定位置 飞行控制系统。 动态调整控制模块利用改变飞行器条件的输入，如高度，马赫数，重量，重心，垂直速度和飞行阶段。 动态调整控制模块用于重新定位机翼的可移动表面的命令通过标准飞行控制系统传输到用于移动飞行控制表面的致动器。
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公开(公告)号：US20100152926A1
公开(公告)日：2010-06-17
申请号：US12620698
申请日：2009-11-18
Applicant: Dan Onu , John D. Winter , Candy L. Carr , Paul M. Vijgen , Gary A. Emch , Michael E. Renzelmann
Inventor： Dan Onu , John D. Winter , Candy L. Carr , Paul M. Vijgen , Gary A. Emch , Michael E. Renzelmann
IPC: G05D1/00
Abstract: The movable surfaces affecting the camber of a wing are dynamically adjusted to optimize wing camber for optimum lift/drag ratios under changing conditions during a given flight phase. In a preferred embodiment, an add-on dynamic adjustment control module provides command signals for optimum positioning of trailing edge movable surfaces, i.e., inboard flaps, outboard flaps, ailerons, and flaperons, which are used in place of the predetermined positions of the standard flight control system. The dynamic adjustment control module utilizes inputs of changing aircraft conditions such as altitude, Mach number, weight, center of gravity (CG), vertical speed and flight phase. The dynamic adjustment control module's commands for repositioning the movable surfaces of the wing are transmitted through the standard flight control system to actuators for moving the flight control surfaces.
Abstract translation: 在给定的飞行阶段期间，在变化的条件下，动态地调整影响机翼弧度的可移动表面，以优化机翼弧度以获得最佳升力/牵引比。 在优选实施例中，附加动态调节控制模块提供用于最终定位后缘可移动表面（即，内侧翼片，外侧翼片，副翼和襟翼）的命令信号，其用于代替标准的预定位置 飞行控制系统。 动态调整控制模块利用高度，马赫数，重量，重心（CG），垂直速度和飞行阶段等改变飞机状态的输入。 动态调整控制模块用于重新定位机翼的可移动表面的命令通过标准飞行控制系统传输到用于移动飞行控制表面的致动器。
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