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公开(公告)号：US10227143B2
公开(公告)日：2019-03-12
申请号：US14303443
申请日：2014-06-12
申请人： The Boeing Company
发明人： Mark S. Good
摘要： Described herein is a system that includes an actuator with a movable input, a first summing mechanism with an input, a first output, and a second output. The input of the first summing mechanism is movably driven by the movable input of the actuator and the first output of the first summing mechanism is movably coupled to a first actuatable element. The system also includes an end mechanism with an input and a first output. The input of the end mechanism is movably driven by the second output and the first output of the end mechanism is movably coupled to a second actuatable element. The system further includes a sensor that senses a position of the rotational input of the actuator. A status of the first and second actuatable elements is based on a sensed position of the movable input of the actuator.
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公开(公告)号：US09180962B2
公开(公告)日：2015-11-10
申请号：US14034987
申请日：2013-09-24
申请人： The Boeing Company
发明人： Matthew A. Moser , Mark J. Gardner , Michael R. Finn , Mark S. Good , Adam P. Malachowski , Monica E. Thommen , Stephen R. Amorosi , Dan Onu
CPC分类号： B64C3/50 , B64C9/06 , B64C9/12 , B64C9/24 , B64C13/00 , B64C13/16 , B64C13/26 , B64C13/503 , Y02T50/32 , Y02T50/44
摘要： A system for varying a wing camber of an aircraft wing may include a leading edge device coupled to the wing. The leading edge device may be configured to be actuated in an upward direction and a downward direction relative to a retracted position of the leading edge device.
摘要翻译： 用于改变飞机机翼的机翼弯曲的系统可以包括联接到机翼的前缘装置。 前缘装置可以被构造成相对于前缘装置的缩回位置沿向上的方向和向下的方向被致动。
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公开(公告)号：US20210061446A1
公开(公告)日：2021-03-04
申请号：US16552472
申请日：2019-08-27
申请人： The Boeing Company
发明人： Mark S. Good , Rene T. Nguyen , Gregor W. Dempster , Bryan J. Gruner , Kwan-Ho Bae , Patrick M. Fahey
摘要： Example methods and apparatus for mitigating aerodynamic flutter of aircraft wing flaps are disclosed. An example apparatus includes a fairing, an actuator, and a damper. The fairing is located on a bottom side of a wing of an aircraft. The actuator is disposed in the fairing. The actuator is coupled to and extends between the wing and a flap of the wing. The damper is disposed in the fairing. The damper is coupled to and extends between the fixed wing and the moveable flap.
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公开(公告)号：US10773795B2
公开(公告)日：2020-09-15
申请号：US16139423
申请日：2018-09-24
申请人： The Boeing Company
发明人： Mark S. Good
摘要： An actuation system for controlling flight control members of a vehicle. Each flight control member is controlled by two or more linear hydraulic actuators. Synchronization members extend between the hydraulic actuators on the same flight control members to synchronize the movements of the hydraulic actuators for consistent movement across the length of the flight control members. Brakes can maintain the positions of the synchronization members and thus the flight control members. Motors can provide for moving the synchronization members to control the positioning of the hydraulic actuators and flight control members.
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公开(公告)号：US09932107B2
公开(公告)日：2018-04-03
申请号：US15007172
申请日：2016-01-26
申请人： The Boeing Company
发明人： Mark S. Good , Steven Paul Walker
IPC分类号： B64C3/56
摘要： Disclosed is a method of enhancing aerodynamic performance of an aircraft wing assembly including a fixed section and a foldable section. The foldable section is hinged to the fixed section at a hinge axis. The method includes turning a torque box extending from the foldable section to rotate the foldable section about the hinge axis from a stowed position to a deployed position.
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公开(公告)号：US20130099060A1
公开(公告)日：2013-04-25
申请号：US13664416
申请日：2012-10-30
申请人： THE BOEING COMPANY
发明人： Paul W. Dees , Mark S. Good , Seiya Sakurai, , Jan A. Kordel , Stephen J. Fox , Matthew A. Lassen , Bruce Robert Fox , Steven Paul Walker , Gregory M. Santini
摘要： A wing assembly comprises a raked wing tip having an outboard portion hinged to one of a main wing having at least one moveable control surface and an inboard raked wing tip portion. The outboard portion of the raked wing tip does not carry any moveable flight control surfaces.
摘要翻译： 翼组件包括具有外侧部分的外侧翼部，所述外侧部分铰接到具有至少一个可移动控制表面和内侧倾斜翼尖部分的主翼中的一个。 倾斜翼尖的外侧部分不携带任何可移动的飞行控制表面。
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公开(公告)号：US20200094945A1
公开(公告)日：2020-03-26
申请号：US16139423
申请日：2018-09-24
申请人： The Boeing Company
发明人： Mark S. Good
摘要： An actuation system for controlling flight control members of a vehicle. Each flight control member is controlled by two or more linear hydraulic actuators. Synchronization members extend between the hydraulic actuators on the same flight control members to synchronize the movements of the hydraulic actuators for consistent movement across the length of the flight control members. Brakes can maintain the positions of the synchronization members and thus the flight control members. Motors can provide for moving the synchronization members to control the positioning of the hydraulic actuators and flight control members.
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公开(公告)号：US10538307B2
公开(公告)日：2020-01-21
申请号：US13664416
申请日：2012-10-30
申请人： The Boeing Company
发明人： Paul W. Dees , Mark S. Good , Seiya Sakurai , Jan A. Kordel , Stephen J. Fox , Matthew A. Lassen , Bruce Robert Fox , Steven Paul Walker , Gregory M. Santini
摘要： A wing assembly comprises a raked wing tip having an outboard portion hinged to one of a main wing having at least one moveable control surface and an inboard raked wing tip portion. The outboard portion of the raked wing tip does not carry any moveable flight control surfaces.
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公开(公告)号：US10173766B2
公开(公告)日：2019-01-08
申请号：US15881248
申请日：2018-01-26
申请人： The Boeing Company
发明人： Mark S. Good , Charles E. Jokisch
摘要： A folding wing tip system of an aircraft includes a latch pin actuator having a primary mechanical lock and a secondary hydraulic lock. The mechanical lock may include a lock cam movable between a lock position, in which the lock cam engages the latch pin, and an unlock position, in which the lock cam is disengaged from the latch pin, and a first lock actuator mechanically coupled to the lock cam and configured to provide a bias force pushing the lock cam toward the lock position. The hydraulic lock may be disposed in an unlatching hydraulic line and has an initial state, in which fluid flow through the unlatching hydraulic line is blocked thereby to hold the latch pin in the latched position, and an open state, in which fluid flow through the unlatching hydraulic line is permitted thereby to permit retraction of the latch pin to the unlatched position.
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公开(公告)号：US09914524B2
公开(公告)日：2018-03-13
申请号：US14824858
申请日：2015-08-12
申请人： The Boeing Company
发明人： Mark S. Good , Charles E. Jokisch
CPC分类号： B64C3/56 , B64C23/072 , F15B11/003 , F15B13/01 , F15B15/261 , F15B2015/268 , F15B2211/30515 , F15B2211/329 , F15B2211/72 , Y02T50/164
摘要： A folding wing tip system of an aircraft includes a latch pin actuator having a primary mechanical lock and a secondary hydraulic lock. The mechanical lock may include a lock cam movable between a lock position, in which the lock cam engages the latch pin, and an unlock position, in which the lock cam is disengaged from the latch pin, and a first lock actuator mechanically coupled to the lock cam and configured to provide a bias force pushing the lock cam toward the lock position. The hydraulic lock may be disposed in an unlatching hydraulic line and has an initial state, in which fluid flow through the unlatching hydraulic line is blocked thereby to hold the latch pin in the latched position, and an open state, in which fluid flow through the unlatching hydraulic line is permitted thereby to permit refraction of the latch pin to the unlatched position.
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