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

IPC分类号： B64C3/50 ,  F16J15/16

CPC分类号： B64C7/00 ,  B64C9/02 ,  B64C9/14 ,  B64C9/16 ,  B64C9/18

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。

公开(公告)号：US08286911B2

公开(公告)日：2012-10-16

申请号：US12370619

申请日：2009-02-13

申请人： Jon McAlinden ,  Kim Sharp

发明人： Jon McAlinden ,  Kim Sharp

IPC分类号： B64C1/00 ,  B64C23/00

CPC分类号： B64C9/02 ,  Y02T50/44

摘要： A method of installing an aerodynamic control element on an aircraft structure. The method comprising: attaching a fitting to the aircraft structure, the fitting comprising a pair of hinge ribs extending away from the aircraft structure and a spacer extending between the pair of hinge ribs; maintaining a desired distance between the pair of hinge ribs with the spacer as the fitting is attached; and pivotally mounting the aerodynamic control element to each hinge rib via a respective hinge.

摘要翻译： 一种在飞行器结构上安装空气动力学控制元件的方法。 该方法包括：将配件连接到飞行器结构，所述配件包括远离飞行器结构延伸的一对铰链肋和在所述一对铰链肋之间延伸的间隔件; 当所述配件附接时，在所述一对铰链肋与所述间隔件之间保持期望的距离; 并且经由相应的铰链将空气动力学控制元件枢转地安装到每个铰链肋。

公开(公告)号：US09533770B2

公开(公告)日：2017-01-03

申请号：US14005129

申请日：2012-03-09

申请人： Alan Quayle ,  James Wilson ,  Jon McAlinden ,  Paul Hadley

发明人： Alan Quayle ,  James Wilson ,  Jon McAlinden ,  Paul Hadley

IPC分类号： B64D45/02

CPC分类号： B64D45/02

摘要： An aircraft assembly comprising a plurality of structural components and an electrically conductive bonding network, wherein at least one of the structural components is formed of material of low electrical conductivity, and the bonding network includes either:at least one substantially planar strip of highly electrically conductive material attached to at least the one structural component, and wherein the strip includes a substantially omega-shaped loop extending out of the plane of the strip; orat least one strip of highly electrically conductive material attached to at least the one structural component, wherein the strip comprises first and second planar attachment portions for attaching the strip to the structural component(s) and an intermediate portion extending between the first and second attachment portions, and wherein the intermediate portion includes a loop which extends outwards from the plane of the first attachment portion.

摘要翻译： 至少一个高导电材料条至少连接在一个结构部件上，其中条带包括第一和第二平面附接部分，用于将条带附接到结构部件上，以及在第一和第二附件之间延伸的中间部分 部分，并且其中所述中间部分包括从所述第一附接部分的平面向外延伸的环。

公开(公告)号：US08220743B2

公开(公告)日：2012-07-17

申请号：US12481267

申请日：2009-06-09

申请人： Jon McAlinden ,  Simon King ,  Marcella Pizzo

发明人： Jon McAlinden ,  Simon King ,  Marcella Pizzo

IPC分类号： B64C3/00

CPC分类号： B64C9/02 ,  B64C9/16

摘要： An aircraft wing assembly comprising: a main wing element; an inboard rib and an outboard rib, each mounted to the main wing element; a bridging structure attaching the inboard rib to the outboard rib; an inboard flap and an outboard flap; and an inboard bearing and an outboard bearing, each mounted to the bridging structure and each engaging a respective one of the flaps. The bridging structure ensures that an accurate distance is maintained between the ribs during installation, and maximises the stiffness of the assembly. Also, the bridging structure can act as a shear plate supporting both the inboard and outboard bearings, thus removing any twisting moment on the ribs.

摘要翻译： 一种飞机机翼组件，包括：主翼元件; 内侧肋和外侧肋，每个安装到主翼元件; 将内侧肋附接到外侧肋的桥接结构; 内侧翼片和外侧翼片; 以及内侧轴承和外侧轴承，每个轴承和外侧轴承各自安装到桥接结构并且各自接合相应的一个翼片。 桥接结构确保在安装期间在肋之间保持精确的距离，并且使组件的刚度最大化。 此外，桥接结构可以用作支撑内侧和外侧轴承的剪切板，从而消除肋上的任何扭转力矩。

公开(公告)号：US20090218450A1

公开(公告)日：2009-09-03

申请号：US12370619

申请日：2009-02-13

申请人： Jon McALINDEN ,  Kim SHARP

发明人： Jon McALINDEN ,  Kim SHARP

IPC分类号： B64C9/00

CPC分类号： B64C9/02 ,  Y02T50/44

摘要： A method of installing an aerodynamic control element on an aircraft structure. The method comprising: attaching a fitting to the aircraft structure, the fitting comprising a pair of hinge ribs extending away from the aircraft structure and a spacer extending between the pair of hinge ribs; maintaining a desired distance between the pair of hinge ribs with the spacer as the fitting is attached; and pivotally mounting the aerodynamic control element to each hinge rib via a respective hinge.

摘要翻译： 一种在飞行器结构上安装空气动力学控制元件的方法。 该方法包括：将配件连接到飞行器结构，所述配件包括远离飞行器结构延伸的一对铰链肋和在所述一对铰链肋之间延伸的间隔件; 当所述配件附接时，在所述一对铰链肋与所述间隔件之间保持期望的距离; 并且经由相应的铰链将空气动力学控制元件枢转地安装到每个铰链肋。

公开(公告)号：US20090218442A1

公开(公告)日：2009-09-03

申请号：US12370637

申请日：2009-02-13

申请人： Jon McAlinden ,  Kim Sharp

发明人： Jon McAlinden ,  Kim Sharp

IPC分类号： B64C13/00 ,  B64C3/00

CPC分类号： B64C3/185 ,  B64C3/26 ,  B64C9/02 ,  Y02T50/44

摘要： An aircraft structure comprising: a rear spar; and a composite cover attached to the rear spar and having an overhanging portion extending to its rear. The overhanging portion of the cover comprises one or more ramps along which the thickness of the cover reduces. A second cover is attached to the rear spar and overhangs to its rear. A hinge rib is attached to one or both of the covers, and an aerodynamic control element such as an aileron, rudder or elevator is pivotally mounted to the hinge rib.

摘要翻译： 一种飞机结构，包括：后翼梁; 以及附接到后翼梁并具有延伸到其后部的伸出部分的复合盖。 盖的突出部分包括一个或多个斜面，盖的厚度沿着该斜面减小。 第二个盖子连接到后部翼梁上，并悬挂在其后部。 铰链肋连接到一个或两个盖，并且诸如副翼，方向舵或升降机的空气动力学控制元件枢转地安装到铰链肋。

公开(公告)号：US09260177B2

公开(公告)日：2016-02-16

申请号：US13144386

申请日：2010-01-21

申请人： Victor Willdig ,  Jon McAlinden

发明人： Victor Willdig ,  Jon McAlinden

IPC分类号： B23P11/00 ,  B23P17/00 ,  B64C1/00 ,  B64C3/00 ,  B64C5/00 ,  B64C1/06 ,  B66C1/12 ,  F16B2/14 ,  B64C3/28 ,  B64C3/26 ,  F16B5/00

CPC分类号： B64C3/28 ,  B64C3/26 ,  F16B5/0084 ,  Y10T29/49826 ,  Y10T403/635

摘要： A joint comprising first and second abutting components, and an adjustable strap assembly bridging the abutting components, the strap assembly including a first strap part attached to one of the components, and a second strap part attached to the other component, the first and second strap parts having mating inclined faces for adjustment of the second strap part with respect to the first strap part such that the position of the second strap part is adjustable with respect to the first strap part in the direction of the incline. Also, a method of forming the joint, comprising attaching the first strap part to the first component, providing the second strap part such that the inclined faces of the first and second strap parts are in mating engagement, adjusting the second strap part with respect to the first strap part in the direction of the incline to position the second strap part in a desired relationship with respect to the first strap part, and attaching the second strap part to the second component.

摘要翻译： 包括第一和第二邻接部件的接头以及桥接所述邻接部件的可调节带组件，所述带组件包括附接到所述部件之一的第一带部分和附接到所述另一部件的第二带部分，所述第一和第二带 具有配合倾斜面的部件，用于相对于第一带部分调节第二带部分，使得第二带部分的位置相对于第一带部分在倾斜方向上是可调节的。 另外，一种形成接头的方法，包括将第一带部件附接到第一部件，提供第二带部分，使得第一和第二带部分的倾斜面配合接合，相对于第二带部分调节第二带部分 所述第一带部分在所述倾斜方向上，以将所述第二带部分相对于所述第一带部分定位成期望的关系，以及将所述第二带部分附接到所述第二部件。

公开(公告)号：US08113465B2

公开(公告)日：2012-02-14

申请号：US12370637

申请日：2009-02-13

申请人： Jon McAlinden ,  Kim Sharp

发明人： Jon McAlinden ,  Kim Sharp

IPC分类号： B64C1/00

CPC分类号： B64C3/185 ,  B64C3/26 ,  B64C9/02 ,  Y02T50/44

摘要： An aircraft structure comprising: a rear spar; and a composite cover attached to the rear spar and having an overhanging portion extending to its rear. The overhanging portion of the cover comprises one or more ramps along which the thickness of the cover reduces. A second cover is attached to the rear spar and overhangs to its rear. A hinge rib is attached to one or both of the covers, and an aerodynamic control element such as an aileron, rudder or elevator is pivotally mounted to the hinge rib.

摘要翻译： 一种飞机结构，包括：后翼梁; 以及附接到后翼梁并具有延伸到其后部的伸出部分的复合盖。 盖的突出部分包括一个或多个斜面，盖的厚度沿着该斜面减小。 第二个盖子连接到后部翼梁上，并悬挂在其后部。 铰链肋连接到一个或两个盖，并且诸如副翼，方向舵或升降机的空气动力学控制元件枢转地安装到铰链肋。

公开(公告)号：US20100327121A1

公开(公告)日：2010-12-30

申请号：US12821517

申请日：2010-06-23

申请人： Jon MCALINDEN ,  Eric WILDMAN

发明人： Jon MCALINDEN ,  Eric WILDMAN

IPC分类号： B64C3/50 ,  B64C3/00

CPC分类号： B64C7/00 ,  B64C9/02 ,  B64C9/14 ,  B64C9/16 ,  B64C9/18

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。

公开(公告)号：US20090218446A1

公开(公告)日：2009-09-03

申请号：US12370657

申请日：2009-02-13

申请人： Jon McAlinden ,  Kim Sharp

发明人： Jon McAlinden ,  Kim Sharp

IPC分类号： B64C1/06 ,  B23P19/00

CPC分类号： B64C9/02 ,  Y02T50/32 ,  Y02T50/44 ,  Y10T29/49815

摘要： An aircraft structure comprising; a rear spar, an upper cover which is attached to the rear spar and overhangs to its rear; a lower cover which is attached to the rear spar and overhangs to its rear, a hinge rib assembly comprising: a first hinge rib arm attached to a first one of the covers; and a second hinge rib arm connected to the first hinge rib arm and attached to a second one of the covers; and an aerodynamic control element pivotally mounted to the hinge rib assembly. The first and second hinge rib arms are separate parts. This provides the ability to disassemble the hinge rib in-situ for repair or maintenance purposes; the ability to install or remove the hinge rib without having to move it inboard along the structure; reduced material wastage during manufacture; and the ability to install one or more elongate lines which extend in a span-wise direction along the aircraft structure.

摘要翻译： 一种飞机结构，包括： 后翼梁，上盖，其附接到后翼梁并突出到其后部; 下盖，其附接到后翼梁并伸出到其后部;铰链肋组件，包括：附接到所述盖中的第一个的第一铰链肋臂; 以及第二铰链肋臂，其连接到所述第一铰链肋臂并且附接到所述盖的第二个; 以及枢转地安装到铰链肋组件的空气动力学控制元件。 第一和第二铰链肋臂是分开的部分。 这提供了在现场拆卸铰链肋条以进行修理或维护的能力; 能够安装或拆卸铰链肋，而不必沿着结构移动铰链肋; 减少制造过程中的材料浪费; 以及安装沿飞机结构沿跨度方向延伸的一条或多条细长线的能力。