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公开(公告)号：US09821903B2
公开(公告)日：2017-11-21
申请号：US14330824
申请日：2014-07-14
申请人： The Boeing Company
发明人： Abraham J. Pachikara , Matthew A. Moser , Paul H. Carpenter , Michael R. Finn , Thomas S. Koch , Stefan R. Bieniawski , Brian T. Whitehead
CPC分类号： B64C13/16 , B64C3/44 , B64C9/00 , B64C9/12 , B64D45/0005 , G05D1/0825 , Y02T50/32 , Y02T50/44
摘要： Closed loop control of control surfaces is described herein. One disclosed example method includes measuring a flight metric of an aircraft during flight and calculating, using a processor, a deflection of a control surface of the aircraft based on the flight metric. The disclosed example method also includes adjusting the deflection to an effective deflection level based on the calculated deflection to reduce a drag coefficient of the aircraft.
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公开(公告)号：US20140214243A1
公开(公告)日：2014-07-31
申请号：US13752119
申请日：2013-01-28
申请人： The Boeing Company
IPC分类号： B64C19/00
CPC分类号： B64C19/00 , G05D1/0202 , G05D1/0825 , G05D1/104
摘要： An apparatus for controlling the formation flight of a trailing aircraft relative to a vortex generated by a leading aircraft includes a position module, peak-seeking module, limiter module, and control module. The position module is configured to determine a position of the vortex relative to the trailing aircraft. The peak-seeking module is configured to determine a desired position of the trailing aircraft for providing desired vortex-induced aerodynamic benefits based on the position of the vortex relative to the trailing aircraft and a mapping function of an individual performance metric. The limiter module is configured to modify the desired position of the trailing aircraft to avoid unintended crossings of the trailing aircraft into the vortex. Finally, the control module is configured to control flight of the trailing aircraft based on one of the desired position of the trailing aircraft and modified desired position of the trailing aircraft.
摘要翻译： 用于控制尾飞机相对于由主飞机产生的涡流的飞行的装置包括位置模块，寻峰模块，限制模块和控制模块。 位置模块被配置成确定涡流相对于后方飞行器的位置。 峰值寻求模块被配置为基于相对于后方飞行器的涡流的位置以及单个性能度量的映射函数来确定拖尾飞行器的期望位置，以提供期望的涡流引起的空气动力学优点。 限制器模块被配置为修改拖尾飞行器的期望位置，以避免尾随飞机进入涡流的意外交叉。 最后，控制模块被配置成基于拖尾飞行器的期望位置和后方飞行器的修改的期望位置之一来控制尾翼飞行器的飞行。
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公开(公告)号：US08949090B2
公开(公告)日：2015-02-03
申请号：US13752119
申请日：2013-01-28
申请人： The Boeing Company
IPC分类号： B64C19/00 , B60R16/023 , G05D1/02 , G05D1/08 , G05D1/10
CPC分类号： B64C19/00 , G05D1/0202 , G05D1/0825 , G05D1/104
摘要： An apparatus for controlling the formation flight of a trailing aircraft relative to a vortex generated by a leading aircraft includes a position module, peak-seeking module, limiter module, and control module. The position module is configured to determine a position of the vortex relative to the trailing aircraft. The peak-seeking module is configured to determine a desired position of the trailing aircraft for providing desired vortex-induced aerodynamic benefits based on the position of the vortex relative to the trailing aircraft and a mapping function of an individual performance metric. The limiter module is configured to modify the desired position of the trailing aircraft to avoid unintended crossings of the trailing aircraft into the vortex. Finally, the control module is configured to control flight of the trailing aircraft based on one of the desired position of the trailing aircraft and modified desired position of the trailing aircraft.
摘要翻译： 用于控制尾飞机相对于由主飞机产生的涡流的飞行的装置包括位置模块，寻峰模块，限制模块和控制模块。 位置模块被配置成确定涡流相对于后方飞行器的位置。 峰值寻求模块被配置为基于相对于后方飞行器的涡流的位置以及单个性能度量的映射函数来确定拖尾飞行器的期望位置，以提供期望的涡流引起的空气动力学优点。 限制器模块被配置为修改拖尾飞行器的期望位置，以避免尾随飞机进入涡流的意外交叉。 最后，控制模块被配置成基于拖尾飞行器的期望位置和后方飞行器的修改的期望位置之一来控制尾翼飞行器的飞行。
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公开(公告)号：US20160229522A1
公开(公告)日：2016-08-11
申请号：US14330824
申请日：2014-07-14
申请人： THE BOEING COMPANY
发明人： Abraham J. Pachikara , Matthew A. Moser , Paul H. Carpenter , Michael R. Finn , Thomas S. Koch , Stefan R. Bieniawski , Brian T. Whitehead
CPC分类号： B64C13/16 , B64C3/44 , B64C9/00 , B64C9/12 , B64D45/0005 , G05D1/0825 , Y02T50/32 , Y02T50/44
摘要： Closed loop control of control surfaces is described herein. One disclosed example method includes measuring a flight metric of an aircraft during flight and calculating, using a processor, a deflection of a control surface of the aircraft based on the flight metric. The disclosed example method also includes adjusting the deflection to an effective deflection level based on the calculated deflection to reduce a drag coefficient of the aircraft.
摘要翻译： 这里描述了控制表面的闭环控制。 一个公开的示例性方法包括在飞行期间测量飞行器的飞行量度，并且使用处理器根据飞行量度来计算飞行器的控制表面的偏转。 所公开的示例性方法还包括基于所计算的偏转将偏转调整到有效偏转水平以减少飞行器的阻力系数。
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