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    SLOT SEAL
    42.
    发明申请
    SLOT SEAL 有权
    缝隙密封

    公开(公告)号：US20110174933A1

    公开(公告)日：2011-07-21

    申请号：US12783642

    申请日：2010-05-20

    申请人： Paul BLADES

    发明人： Paul BLADES

    IPC分类号： B64C1/38 ,  B64C3/00 ,  B64C3/58 ,  B64C25/10

    CPC分类号： B64C9/02 ,  B64C7/00 ,  B64C9/16 ,  B64C25/16 ,  B64C2009/143 ,  Y02T50/32

    摘要： A panel assembly for an aircraft comprises a panel rotatably connected to a support structure and moveable between a first position and a second position. The panel has an aerodynamic surface with a slot at one edge thereof which receives a portion of the support structure when the panel is in the first position. The assembly further comprises a resilient seal member which occupies the slot when the panel is in the second position. The panel may be an aircraft flight control surface, or an aircraft landing gear bay door.

    摘要翻译： 用于飞机的面板组件包括可旋转地连接到支撑结构并可在第一位置和第二位置之间移动的面板。 该面板具有空气动力学表面，在其一个边缘处具有槽，当面板处于第一位置时，该空气动力学表面接收支撑结构的一部分。 组件还包括弹性密封构件，当面板处于第二位置时占据槽的弹性密封构件。 面板可以是飞机飞行控制面，也可以是飞机起落架舱门。

    PIPE COUPLING DEVICE FOR AIRCRAFT WING
    43.
    发明申请
    PIPE COUPLING DEVICE FOR AIRCRAFT WING 有权
    用于飞机的管道联接装置

    公开(公告)号：US20110147523A1

    公开(公告)日：2011-06-23

    申请号：US12832118

    申请日：2010-07-08

    申请人： Colin John WEST ,  David Alistair SUTTON

    发明人： Colin John WEST ,  David Alistair SUTTON

    IPC分类号： B64D37/00 ,  B64C3/00 ,  B64C1/00 ,  B82Y30/00

    CPC分类号： B64D37/005 ,  F16L25/01 ,  F16L27/11 ,  Y02T50/44

    摘要： An aircraft wing comprising first and second fuel pipe segments which are coupled together with a pipe coupling device comprising a corrugated tube formed from an elastomer filled with conductive material. The pipe coupling device is particularly useful for connecting together fuel pipe segments in an aircraft wing as it removes the need to attach bonding leads between fuel pipe segments to dissipate lightning currents and static.

    摘要翻译： 一种飞机机翼，包括第一和第二燃料管段，其与管连接装置连接在一起，该管连接装置包括由填充有导电材料的弹性体形成的波纹管。 管连接装置特别适用于将飞机机翼中的燃料管段连接在一起，因为它消除了在燃料管段之间附接结合引线以消散雷电流和静电的需要。

    Process for making a composite material assembly and aircraft wing and stabilizing element obtained by this process
    47.
    发明授权
    Process for making a composite material assembly and aircraft wing and stabilizing element obtained by this process 失效
    通过该方法制备复合材料组件和飞机机翼和稳定元件的方法

    公开(公告)号：US07874517B2

    公开(公告)日：2011-01-25

    申请号：US11147011

    申请日：2005-06-06

    申请人： Franck Bequet

    发明人： Franck Bequet

    IPC分类号： B64C5/00 ,  B64C3/00

    CPC分类号： B29C70/30 ,  B29L2031/3085 ,  Y02T50/43

    摘要： Process for manufacturing an assembly made of a composite material and wing and stabilizing element obtained by this process.The junction zone for a part (P) made of a composite material comprising two parts (A1, A2) in which the principal directions intersect at a non-singular angle, is made in a single operation by continuous lay-up. The 0° directions of the lay-up coordinate systems (R1, R2) of the parts (A1, A2) are oriented such that these directions make an angle of close to 180°−θ°, where ±θ° represents the other directions of the lay-up coordinate systems (R1, R2). Thus, the layers of fibers oriented at 0° in one of the coordinate systems correspond approximately to a lay-up direction of ±θ° in the other coordinate system.

    摘要翻译： 用于制造由该方法获得的复合材料和翼和稳定元件制成的组件的方法。 由包括主要方向以非奇异角相交的两个部分（A1，A2）的复合材料制成的部分（P）的接合区域通过连续叠层进行单次操作。 部件（A1，A2）的叠层坐标系（R1，R2）的0°方向取向为使得这些方向形成接近180°的角度，其中±＆ 叠层坐标系（R1，R2）的其他方向。 因此，在一个坐标系中以0°取向的纤维层大致对应于另一个坐标系中的±＆Thetas;°的叠层方向。

    METHOD OF FORMING AN INTERNAL STRUCTURE WITHIN A HOLLOW COMPONENT
    48.
    发明申请
    METHOD OF FORMING AN INTERNAL STRUCTURE WITHIN A HOLLOW COMPONENT 审中-公开
    在中空组件中形成内部结构的方法

    公开(公告)号：US20110002788A1

    公开(公告)日：2011-01-06

    申请号：US12796231

    申请日：2010-06-08

    申请人： John H. Mason

    发明人： John H. Mason

    IPC分类号： F01D5/14 ,  B29C65/00 ,  B64C3/00

    CPC分类号： B21D53/78 ,  B21D26/055 ,  F01D5/005 ,  Y02T50/672

    摘要： A method of forming an internal structure within a hollow component (2), the component comprising first and second panels (4, 6) and at least one membrane (8; 10) disposed between the first and second panels (4, 6), the method comprising: selectively bonding the at least one membrane (8; 10) to the first and/or second panels (4, 6); inflating the component (2) by passing a pressurised fluid between the first and second panels (4, 6) such that the first and second panels (4, 6) are inflated into contact with a die assembly (38) and such that the membrane (8; 10) forms an internal structure between the first and second panels (4, 6); and deforming the internal structure by applying the pressurised fluid at a first pressure (P1) on one side of the membrane (8; 10) and at a second pressure (P2) on the other side of the membrane (8; 10).

    摘要翻译： 一种在中空部件（2）内形成内部结构的方法，所述部件包括第一和第二面板（4,6）以及设置在第一和第二面板（4,6）之间的至少一个薄膜（8; 10） 所述方法包括：将所述至少一个膜（8; 10）选择性地粘合到所述第一和/或第二面板（4,6）上; 通过在第一和第二面板（4,6）之间通过加压流体使组件（2）膨胀，使得第一和第二面板（4,6）被膨胀成与模具组件（38）接触，并且使得膜 （8; 10）在所述第一和第二面板（4,6）之间形成内部结构; 以及通过在膜（8; 10）的一侧上的第一压力（P1）和膜（8; 10）的另一侧的第二压力（P2）施加加压流体来使内部结构变形。

    CROSS-BLEED DAM
    49.
    发明申请
    CROSS-BLEED DAM 有权
    交叉ED

    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。