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公开(公告)号：US08360438B2
公开(公告)日：2013-01-29
申请号：US12737705
申请日：2009-08-25
申请人： Eric Wildman , Simon John Parker
发明人： Eric Wildman , Simon John Parker
IPC分类号： F16J15/14
CPC分类号： B64C9/02 , B64C7/00 , F16J15/104
摘要： A seal (500) comprises a seal body (502) having a mounting portion (504), a first leg (506) and a second leg (508), a first stiffening member (514) and a second stiffening member (516) separated by an arcuate shear seal portion (529) in which the motions of the first leg (506) and second leg (508) are relatively constrained by the second stiffening member (516).
摘要翻译： 密封件（500）包括具有安装部分（504），第一腿部（506）和第二腿部（508）的密封体（502），第一加强构件（514）和第二加强构件（516） 通过弓形剪切密封部分（529），其中第一腿部（506）和第二腿部（508）的运动由第二加强部件（516）相对地约束。
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公开(公告)号：US20110133411A1
公开(公告)日：2011-06-09
申请号：US12737705
申请日：2009-08-25
申请人： Eric Wildman , Simon John Parker
发明人： Eric Wildman , Simon John Parker
CPC分类号： B64C9/02 , B64C7/00 , F16J15/104
摘要： A seal (500) comprises a seal body (502) having a mounting portion (504), a first leg (506) and a second leg (508), a first stiffening member (514) and a second stiffening member (516) separated by an arcuate shear seal portion (529) in which the motions of the first leg (506) and second leg (508) are relatively constrained by the second stiffening member (516).
摘要翻译： 密封件（500）包括具有安装部分（504），第一腿部（506）和第二腿部（508）的密封体（502），第一加强构件（514）和第二加强构件（516） 通过弓形剪切密封部分（529），其中第一腿部（506）和第二腿部（508）的运动由第二加强部件（516）相对地约束。
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公开(公告)号：US08424801B2
公开(公告)日：2013-04-23
申请号：US13064754
申请日：2011-04-13
IPC分类号： B64C13/28
CPC分类号： B64C9/22 , B64C9/02 , Y02T50/44 , Y10T74/18648 , Y10T74/18992
摘要： A support assembly for deployment and retraction of an aero surface from an aircraft is disclosed. The assembly comprises a guide track, a primary support arm having one end coupled to a carriage mounted on the track such that the primary support arm is rotatable relative to the carriage about multiple axes, and a control arm having one end coupled to the primary support arm and a second end pivotably attachable to a fixed support forming part of the structure of the aircraft. The assembly being configured such that, when the carriage is driven along the guide track, the control arm causes the primary support arm to pivot about said multiple axes to deploy and/or retract an aero surface pivotally attached to an opposite end of the primary support member along an arcuate path.
摘要翻译： 公开了一种用于从飞行器展开和缩回航空表面的支撑组件。 所述组件包括导轨，主支撑臂，其一端联接到安装在所述轨道上的滑架，使得所述主支撑臂可相对于所述滑架绕多个轴线旋转;以及控制臂，其一端联接到所述主支撑件 臂和可枢转地附接到形成飞行器的结构的一部分的固定支撑件的第二端。 组件被构造成使得当滑架沿着导轨被驱动时，控制臂使得主支撑臂围绕所述多个轴线枢转以展开和/或缩回枢转地附接到主支撑件的相对端的航空表面 沿着弧形路径的成员。
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公开(公告)号：US20110253832A1
公开(公告)日：2011-10-20
申请号：US13064754
申请日：2011-04-13
CPC分类号： B64C9/22 , B64C9/02 , Y02T50/44 , Y10T74/18648 , Y10T74/18992
摘要： A support assembly for deployment and retraction of an aero surface from an aircraft is disclosed. The assembly comprises a guide track, a primary support arm having one end coupled to a carriage mounted on the track such that the primary support arm is rotatable relative to the carriage about multiple axes, and a control arm having one end coupled to the primary support arm and a second end pivotably attachable to a fixed support forming part of the structure of the aircraft. The assembly being configured such that, when the carriage is driven along the guide track, the control arm causes the primary support arm to pivot about said multiple axes to deploy and/or retract an aero surface pivotally attached to an opposite end of the primary support member along an arcuate path.
摘要翻译： 公开了一种用于从飞行器展开和缩回航空表面的支撑组件。 所述组件包括导轨，主支撑臂，其一端联接到安装在所述轨道上的滑架，使得所述主支撑臂可相对于所述滑架绕多个轴线旋转;以及控制臂，其一端联接到所述主支撑件 臂和可枢转地附接到形成飞行器的结构的一部分的固定支撑件的第二端。 组件被构造成使得当滑架沿着导轨被驱动时，控制臂使得主支撑臂围绕所述多个轴线枢转以展开和/或缩回枢转地附接到主支撑件的相对端的航空表面 沿着弧形路径的成员。
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公开(公告)号：US08556214B2
公开(公告)日：2013-10-15
申请号：US12821517
申请日：2010-06-23
申请人： Jon McAlinden , Eric Wildman
发明人： Jon McAlinden , Eric Wildman
摘要： A panel assembly for an aircraft including a panel having an upper aerodynamic surface and a leading edge, and a hinge fitting connected to an underside of the panel, defining a hinge line for the direction of rotation of the panel. The upper surface of the leading edge has an arcuate portion centered about the hinge line, and has an upturned portion forward of the arcuate portion. The panel assembly is pivotally connected to its hinge fitting to the trailing edge of the fixed wing portion and rotatable between a first position wherein the upper surfaces of the fixed wing portion and the panel are substantially flush, and a second position wherein the panel is rotated downwardly from the first position. A seal member attached to the trailing edge of the fixed wing portion, has a lower surface which seals against the upper surface of the panel during its movement.
摘要翻译： 一种用于飞行器的面板组件，包括具有上空气动力学表面和前缘的面板，以及连接到面板下侧的铰链配件，其限定了用于面板旋转方向的铰链线。 前缘的上表面具有以铰链线为中心的弓形部分，并且在弓形部分的前方具有向上的部分。 所述面板组件枢转地连接到其铰链配合到固定翼部分的后缘，并且可在第一位置和第二位置之间旋转，其中固定翼部分和面板的上表面基本齐平，以及第二位置，其中面板旋转 从第一位置向下。 附接到固定翼部分的后缘的密封构件具有在其移动期间密封面板的上表面的下表面。
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公开(公告)号：US09038964B2
公开(公告)日：2015-05-26
申请号：US13513219
申请日：2010-12-06
申请人： Eric Wildman
发明人： Eric Wildman
CPC分类号： B64C13/28 , B64C9/20 , B64C9/323 , B64C2009/143 , Y10T29/49815
摘要： An aerodynamic control surface assembly comprising: an aerodynamic control surface (4); an actuator (10) for controlling deployment of the control surface; and a locking mechanism (30) moveable from a locked to an unlocked position. When the locking mechanism is set to the locked position, the actuator is operatively coupled to the control surface and the control surface can move in dependently of the actuator when the locking mechanism is set to the unlocked position. Such an assembly may be used in an aircraft to prevent clashing between a deployed flap (16) and a drooped spoiler (4) in the event of an actuator control systems failure.
摘要翻译： 一种空气动力学控制表面组件，包括：空气动力学控制表面（4）; 用于控制所述控制表面的展开的致动器（10）; 以及可从锁定位置移动到解锁位置的锁定机构（30）。 当锁定机构设置在锁定位置时，致动器可操作地联接到控制表面，并且当锁定机构被设置到解锁位置时，控制表面可以依靠致动器移动。 在发动机控制系统故障的情况下，这种组件可用于飞行器中以防止展开的挡板（16）和下垂的扰流器（4）之间的冲突。
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公开(公告)号：US20110031351A1
公开(公告)日：2011-02-10
申请号：US12805126
申请日：2010-07-14
申请人： Eric Wildman
发明人： Eric Wildman
IPC分类号： B64C9/02
摘要： A support assembly for guiding a flap on an aircraft wing during deployment of the flap is disclosed. The assembly comprises an arcuate guide track mountable to an aircraft wing and defining a two-dimensional path, a carriage mounted on the guide track so as to slide along the track during flap deployment, a part-spherical bearing, and a shaft having one end attachable to a flap and the opposite end coupled to the carriage via said part-spherical bearing. The shaft is free to pivot relative to the carriage about a centre of the part-spherical bearing in all directions, as the carriage slides along the track.
摘要翻译： 公开了一种用于在翼片展开期间引导飞机机翼上的翼片的支撑组件。 组件包括可安装到飞行器机翼并限定二维路径的弓形导轨，安装在导轨上的滑架，以便在翼片展开期间沿着轨道滑动，部分球形轴承和具有一端的轴 可附接到翼片，并且相对端通过所述部分球形轴承联接到滑架。 当滑架沿着轨道滑动时，轴可以相对于滑架绕着部分球面轴承的中心在所有方向上自由枢转。
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公开(公告)号：US20090267304A1
公开(公告)日：2009-10-29
申请号：US12382472
申请日：2009-03-17
申请人： Eric Wildman
发明人： Eric Wildman
IPC分类号： F16J15/16
CPC分类号： B64C7/00
摘要： A seal for sealing a gap between a first (252) and a second (207) component of an aircraft flight surface which has a first seal body (222) having a first sealing portion (246) arranged to seal against the first component, wherein the first seal body is movably mounted to the second component so as to seal at least part of the gap during relative movement of the first and second components. A seal is also provided with components movable relative to each other.
摘要翻译： 一种用于密封飞行器飞行器表面的第一（252）和第二（207）部件之间的间隙的密封件，其具有第一密封体（222），所述第一密封体具有布置成密封所述第一部件的第一密封部分（246），其中 第一密封体可移动地安装到第二部件，以便在第一和第二部件的相对运动期间密封间隙的至少一部分。 密封件还设置有可相对于彼此移动的部件。
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公开(公告)号：US20110031349A1
公开(公告)日：2011-02-10
申请号：US12805615
申请日：2010-08-10
CPC分类号： B64C9/02 , B64C9/16 , B64C9/323 , F16C11/04 , Y02T50/32 , Y10T29/49826 , Y10T403/32951
摘要： A pinned lug joint comprising: a first part comprising two first lugs projecting from a bridge which extends between them; a second part pivotally coupled to the first part, the second part comprising a second lug positioned between the first lugs; and a sealing member, the sealing member being mounted to the first lugs and extending between them to seal an air gap between the second lug and the bridge at least when the second part is in a first position. The pinned lug joint may be used to attach a panel assembly to part of an aircraft.
摘要翻译： 一种被钉扎的凸耳接头，包括：第一部分，包括两个在从它们之间延伸的桥部突出的第一凸耳; 第二部分枢转地联接到第一部分，第二部分包括位于第一凸耳之间的第二凸耳; 密封构件，密封构件安装到第一凸耳并且在它们之间延伸，至少当第二部分处于第一位置时密封第二凸耳和桥之间的空气间隙。 钉扎的接头可用于将面板组件附接到飞行器的一部分。
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公开(公告)号：US08684309B2
公开(公告)日：2014-04-01
申请号：US13495777
申请日：2012-06-13
申请人： Eric Wildman
发明人： Eric Wildman
IPC分类号： B64C3/00
CPC分类号： B64C1/26
摘要： An integrated bracket assembly for attachment to a convex outer corner surface of a torsion box of an aerofoil structure, the bracket assembly comprising a bracket strip having a plurality of brackets arranged spaced side by side, and connected by an infill rail integrally formed with the bracket strip, wherein the infill rail has a concave surface for mating with the convex surface of the torsion box. The torsion box may be of a “U-box” construction where a front spar and a rear spar are integrally formed with either an upper or lower torsion box cover to form an omega-shaped unitary component, and the other cover is attached to the omega-shaped component to provide an enclosed volume. The bracket strip may be used for attaching a leading/trailing edge structure of the aerofoil to the torsion box.
摘要翻译： 一种用于附接到机翼结构的扭转箱的凸形外角面的集成支架组件，所述支架组件包括支架条，所述支架条具有多个托架，所述多个支架并排布置，并且通过与支架一体形成的填充轨道连接 带，其中所述填充轨具有用于与所述扭转箱的凸表面配合的凹面。 扭转箱可以是“U形箱”结构，其中前翼梁和后翼梁与上部或下部扭转箱盖整体形成以形成Ω形整体部件，而另一个盖子附接到 欧米茄形组件提供封闭体积。 支架条可用于将机翼的前/后缘结构连接到扭转箱。
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