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公开(公告)号：US20100100355A1
公开(公告)日：2010-04-22
申请号：US12253747
申请日：2008-10-17
申请人： Alan D. Marx , Gary A. Emch , Mark J. Gardner , Richard I. Apfel , Michael E. Renzelmann , Christopher D. Feet , Michael R. Finn , Mark S. Good , Gregory J. Seehusen
发明人： Alan D. Marx , Gary A. Emch , Mark J. Gardner , Richard I. Apfel , Michael E. Renzelmann , Christopher D. Feet , Michael R. Finn , Mark S. Good , Gregory J. Seehusen
IPC分类号： G06F15/00
CPC分类号： B64D45/0005 , B64D2045/001
摘要： A method for detecting freewheeling skew failures in the wing flaps of an aircraft includes measuring the outputs of flap skew sensors when the aircraft is in flight (IF) and the flaps are extended to a selected position, and when the aircraft is next on the ground (OG) and the flaps are extended to the selected position. The respective differences between the IF and OG outputs of symmetrical pairs of the flap skew sensors are computed, and then the respective difference between the computed IF output difference and the computed OG output difference of each symmetrical pair of the sensors is computed. The computed IF and OG difference of each symmetrical pair of the sensors is then compared with each of predetermined maximum and minimum threshold value to determine whether a freewheeling skew failure exists in any of the flaps of the aircraft.
摘要翻译： 一种用于检测飞行器翼片中的续流偏斜故障的方法，包括当飞机处于飞行中（IF）时测量襟翼歪斜传感器的输出，并且襟翼延伸到选定的位置，并且当飞机在地面上时 （OG），并且襟翼延伸到所选位置。 计算襟翼偏斜传感器的对称对的IF和OG输出之间的各自的差异，然后计算计算的IF输出差和每对传感器对的计算的OG输出差的相应差。 然后将每个对称的传感器对的计算的IF和OG差与预定的最大和最小阈值中的每一个进行比较，以确定是否存在飞行器的任何襟翼中的空转歪斜故障。
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公开(公告)号：US07945425B2
公开(公告)日：2011-05-17
申请号：US12253747
申请日：2008-10-17
申请人： Alan D. Marx , Gary A. Emch , Mark J. Gardner , Richard I. Apfel , Michael E. Renzelmann , Christopher D. Feet , Michael R. Finn , Mark S. Good , Gregory J. Seehusen
发明人： Alan D. Marx , Gary A. Emch , Mark J. Gardner , Richard I. Apfel , Michael E. Renzelmann , Christopher D. Feet , Michael R. Finn , Mark S. Good , Gregory J. Seehusen
IPC分类号： G06F11/30
CPC分类号： B64D45/0005 , B64D2045/001
摘要： A method for detecting freewheeling skew failures in the wing flaps of an aircraft includes measuring the outputs of flap skew sensors when the aircraft is in flight (IF) and the flaps are extended to a selected position, and when the aircraft is next on the ground (OG) and the flaps are extended to the selected position. The respective differences between the IF and OG outputs of symmetrical pairs of the flap skew sensors are computed, and then the respective difference between the computed IF output difference and the computed OG output difference of each symmetrical pair of the sensors is computed. The computed IF and OG difference of each symmetrical pair of the sensors is then compared with each of predetermined maximum and minimum threshold value to determine whether a freewheeling skew failure exists in any of the flaps of the aircraft.
摘要翻译： 一种用于检测飞行器翼片中的续流偏斜故障的方法，包括当飞机处于飞行中（IF）时测量襟翼歪斜传感器的输出，并且襟翼延伸到选定的位置，并且当飞机在地面上时 （OG），并且襟翼延伸到所选位置。 计算襟翼偏斜传感器的对称对的IF和OG输出之间的各自的差异，然后计算计算的IF输出差和每对传感器对的计算的OG输出差的相应差。 然后将每个对称的传感器对的计算的IF和OG差与预定的最大和最小阈值中的每一个进行比较，以确定是否存在飞行器的任何襟翼中的空转歪斜故障。
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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
申请人： Dan Onu , John D. Winter , Candy L. Carr , Paul M. Vijgen , Gary A. Emch , Michael E. Renzelmann
发明人： Dan Onu , John D. Winter , Candy L. Carr , Paul M. Vijgen , Gary A. Emch , Michael E. Renzelmann
IPC分类号： G05D1/00
摘要： 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.
摘要翻译： 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
申请人： Dan Onu , John D. Winter , Candy L. Carr , Paul M. Vijgen , Gary A. Emch , Michael E. Renzelmann
发明人： Dan Onu , John D. Winter , Candy L. Carr , Paul M. Vijgen , Gary A. Emch , Michael E. Renzelmann
IPC分类号： B64C13/00
摘要： 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.
摘要翻译： 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
申请人： Dan Onu , John D. Winter , Candy L. Carr , Paul M. Vijgen , Gary A. Emch , Michael E. Renzelmann
发明人： Dan Onu , John D. Winter , Candy L. Carr , Paul M. Vijgen , Gary A. Emch , Michael E. Renzelmann
摘要： 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.
摘要翻译： 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
申请人： Dan Onu , John D. Winter , Candy L. Carr , Paul M. Vijgen , Gary A. Emch , Michael E. Renzelmann
发明人： Dan Onu , John D. Winter , Candy L. Carr , Paul M. Vijgen , Gary A. Emch , Michael E. Renzelmann
IPC分类号： G05D1/00
摘要： 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.
摘要翻译： 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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