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公开(公告)号：US11591070B2
公开(公告)日：2023-02-28
申请号：US16658359
申请日：2019-10-21
申请人： The Boeing Company
摘要： Methods, apparatus, and articles of manufacture for a distributed aircraft actuation system are disclosed. An example apparatus includes a non-responsive component detector to determine a position difference between a first position of a first control surface of an aircraft and a second position of a second control surface of the aircraft, the first position lagging the second position, and a command generator, in response to determining that the position difference satisfies a threshold, the command generator is to cease movement of the second control surface at the second position, attempt to move the first control surface to the second position, and cease movement of the first control surface when moved to the second position.
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公开(公告)号：US20180362147A1
公开(公告)日：2018-12-20
申请号：US15653257
申请日：2017-07-18
申请人： The Boeing Company
摘要： Methods, apparatus, and articles of manufacture for a distributed aircraft actuation system are disclosed. An example apparatus includes a collection engine to obtain first monitoring information corresponding to a first set of control surfaces of an aircraft, the first set including a first control surface on a first side of the aircraft and a second control surface on a second side of the aircraft, the second side opposite the first, and obtain second monitoring information corresponding to a second set of control surfaces of the aircraft, the second set including a third control surface on the first side and a fourth control surface on the second side. The example apparatus further includes a non-responsive component detector to determine if one of the control surfaces is non-responsive based on the first and the second monitoring information, and a command generator to deactivate the first set when the non-responsive component detector determines that the first control surface is non-responsive while the second set remains active.
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公开(公告)号：US20180022441A1
公开(公告)日：2018-01-25
申请号：US15216963
申请日：2016-07-22
申请人： The Boeing Company
CPC分类号： B64C13/40 , B64C13/36 , B64C13/50 , B64C13/504 , F15B15/12 , F15B15/18 , F15B15/202 , F15B2211/20515 , F15B2211/633 , F15B2211/6336 , F15B2211/6651 , F15B2211/6653 , F15B2211/6656 , Y02T50/44 , Y02T50/54
摘要： A method and apparatus for positioning a control surface. A desired position for the control surface associated with an aerodynamic aircraft structure is identified. The control surface is moved to the desired position using an electronically controlled rotary actuator system located inside of the aerodynamic aircraft structure, wherein a shape of the aerodynamic aircraft structure with the electronically controlled rotary actuator system has a desired aerodynamic performance.
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公开(公告)号：US10479484B2
公开(公告)日：2019-11-19
申请号：US15695749
申请日：2017-09-05
申请人： The Boeing Company
摘要： Methods and apparatus for controlling aircraft flight control surfaces are disclosed. An example apparatus includes a flight control surface controller to move a control surface of an aircraft to a target position via at least one of a first actuator or a second actuator associated with the control surface based on a command input received by the flight control surface controller. The flight control surface controller to: obtain a flight characteristic of the aircraft; compare the flight characteristic to a flight characteristic threshold; in response to a first comparison result, cause the first actuator to move the control surface to the target position based on the command input without moving the second actuator; and in response to a second comparison result, cause the first actuator and the second actuator to move the control surface to the target position based on the command input.
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公开(公告)号：US20180362149A1
公开(公告)日：2018-12-20
申请号：US15695749
申请日：2017-09-05
申请人： The Boeing Company
CPC分类号： B64C13/42 , B64C13/503 , B64C13/504
摘要： Methods and apparatus for controlling aircraft flight control surfaces are disclosed. An example apparatus includes a flight control surface controller to move a control surface of an aircraft to a target position via at least one of a first actuator or a second actuator associated with the control surface based on a command input received by the flight control surface controller. The flight control surface controller to: obtain a flight characteristic of the aircraft; compare the flight characteristic to a flight characteristic threshold; in response to a first comparison result, cause the first actuator to move the control surface to the target position based on the command input without moving the second actuator; and in response to a second comparison result, cause the first actuator and the second actuator to move the control surface to the target position based on the command input.
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公开(公告)号：US20200047873A1
公开(公告)日：2020-02-13
申请号：US16658359
申请日：2019-10-21
申请人： The Boeing Company
摘要： Methods, apparatus, and articles of manufacture for a distributed aircraft actuation system are disclosed. An example apparatus includes a non-responsive component detector to determine a position difference between a first position of a first control surface of an aircraft and a second position of a second control surface of the aircraft, the first position lagging the second position, and a command generator, in response to determining that the position difference satisfies a threshold, the command generator is to cease movement of the second control surface at the second position, attempt to move the first control surface to the second position, and cease movement of the first control surface when moved to the second position.
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公开(公告)号：US10450055B2
公开(公告)日：2019-10-22
申请号：US15653257
申请日：2017-07-18
申请人： The Boeing Company
摘要： Methods, apparatus, and articles of manufacture for a distributed aircraft actuation system are disclosed. An example apparatus includes a collection engine to obtain first monitoring information corresponding to a first set of control surfaces of an aircraft, the first set including a first control surface on a first side of the aircraft and a second control surface on a second side of the aircraft, the second side opposite the first, and obtain second monitoring information corresponding to a second set of control surfaces of the aircraft, the second set including a third control surface on the first side and a fourth control surface on the second side. The example apparatus further includes a non-responsive component detector to determine if one of the control surfaces is non-responsive based on the first and the second monitoring information, and a command generator to deactivate the first set when the non-responsive component detector determines that the first control surface is non-responsive while the second set remains active.
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