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    Aircraft wing composed of composite and metal panels
    1.
    发明授权
    Aircraft wing composed of composite and metal panels 有权
    飞机机翼由复合材料和金属板组成

    公开(公告)号：US07387277B2

    公开(公告)日：2008-06-17

    申请号：US11027570

    申请日：2004-12-29

    申请人： Jan A. Kordel ,  Richard B. Tanner ,  Ian C. Burford ,  Victor A. Munsen ,  Daniel E. McGinty ,  Scott N. Rampton ,  Bruce R. Fox ,  James M. Kelly ,  Miles O. Johnson

    发明人： Jan A. Kordel ,  Richard B. Tanner ,  Ian C. Burford ,  Victor A. Munsen ,  Daniel E. McGinty ,  Scott N. Rampton ,  Bruce R. Fox ,  James M. Kelly ,  Miles O. Johnson

    IPC分类号： B64C3/20

    CPC分类号： B64C3/00

    摘要： Aircraft wing assemblies having both composite and metal panels are disclosed. In one embodiment, a wing assembly includes a support structure, an upper panel assembly formed from a metal material and coupled to the support structure, and a lower panel assembly formed from a composite material and coupled to the support structure. The metal material may be aluminum, titanium, or any other suitable metal, and the composite material may be a carbon fiber reinforced plastic (CFRP) material or other suitable composite material. In another embodiment, the upper panel assembly includes a downwardly depending first web portion, and the lower panel assembly includes an upwardly depending second web portion, the second web portion being proximate the first web portion, and an interface member of an isolating material is disposed between the first and second web portions.

    摘要翻译： 公开了具有复合材料和金属板的飞机机翼组件。 在一个实施例中，翼组件包括支撑结构，由金属材料形成并联接到支撑结构的上面板组件，以及由复合材料形成并联接到支撑结构的下部面板组件。 金属材料可以是铝，钛或任何其它合适的金属，并且复合材料可以是碳纤维增强塑料（CFRP）材料或其它合适的复合材料。 在另一个实施例中，上面板组件包括向下悬垂的第一腹板部分，并且下面板组件包括向上悬垂的第二腹板部分，第二腹板部分靠近第一腹板部分，并且设置隔离材料的接口构件 在第一和第二纤维网部分之间。

    AIRCRAFT WING COMPOSED OF COMPOSITE AND METAL PANELS
    2.
    发明申请
    AIRCRAFT WING COMPOSED OF COMPOSITE AND METAL PANELS 有权
    飞机组成的复合材料和金属面板

    公开(公告)号：US20080023585A1

    公开(公告)日：2008-01-31

    申请号：US11027570

    申请日：2004-12-29

    申请人： Jan A. Kordel ,  Richard B. Tanner ,  Ian C. Burford ,  Victor A. Munsen ,  Daniel E. McGinty ,  Scott N. Rampton ,  Bruce R. Fox ,  James M. Kelly ,  Miles O. Johnson

    发明人： Jan A. Kordel ,  Richard B. Tanner ,  Ian C. Burford ,  Victor A. Munsen ,  Daniel E. McGinty ,  Scott N. Rampton ,  Bruce R. Fox ,  James M. Kelly ,  Miles O. Johnson

    IPC分类号： B64C3/00

    CPC分类号： B64C3/00

    摘要： Aircraft wing assemblies having both composite and metal panels are disclosed. In one embodiment, a wing assembly includes a support structure, an upper panel assembly formed from a metal material and coupled to the support structure, and a lower panel assembly formed from a composite material and coupled to the support structure. The metal material may be aluminum, titanium, or any other suitable metal, and the composite material may be a carbon fiber reinforced plastic (CFRP) material or other suitable composite material. In another embodiment, the upper panel assembly includes a downwardly depending first web portion, and the lower panel assembly includes an upwardly depending second web portion, the second web portion being proximate the first web portion, and an interface member of an isolating material is disposed between the first and second web portions.

    摘要翻译： 公开了具有复合材料和金属板的飞机机翼组件。 在一个实施例中，翼组件包括支撑结构，由金属材料形成并联接到支撑结构的上面板组件，以及由复合材料形成并联接到支撑结构的下部面板组件。 金属材料可以是铝，钛或任何其它合适的金属，并且复合材料可以是碳纤维增强塑料（CFRP）材料或其它合适的复合材料。 在另一个实施例中，上面板组件包括向下悬垂的第一腹板部分，并且下面板组件包括向上悬垂的第二腹板部分，第二腹板部分靠近第一腹板部分，并且设置隔离材料的接口构件 在第一和第二纤维网部分之间。

    Structural attach method for thin fairings
    3.
    发明授权
    Structural attach method for thin fairings 失效
    薄整流罩的结构附着方法

    公开(公告)号：US06830218B2

    公开(公告)日：2004-12-14

    申请号：US10334452

    申请日：2002-12-31

    申请人： Jan A. Kordel ,  Richard B. Tanner

    发明人： Jan A. Kordel ,  Richard B. Tanner

    IPC分类号： B64C326

    CPC分类号： B64C3/26 ,  B64F5/10 ,  F16B2200/30

    摘要： A method, system, and apparatus for attaching a fairing to a body or aircraft wing are disclosed. A plurality of attach anchors is disposed on the body or aircraft wing to which the fairing is to be attached. Disposed in the fairing is a plurality of core pockets that are alignable with the plurality of attach anchors, and each of the core pockets defines a channel. The fairing is placed over the body or the aircraft wing such that the heads of the attach anchors are received in the core pockets. The fairing is then slid across the body or the aircraft wing with the channels sliding along the heads of the attach anchors such that the fairing is prevented from being lifted away from the body or aircraft wing.

    摘要翻译： 公开了一种用于将整流罩附接到身体或飞机机翼上的方法，系统和装置。 多个附接锚固件设置在整流罩将要连接到的主体或飞机机翼上。 布置在整流罩中的是多个可与多个连接锚固件对准的芯袋，并且每个芯袋限定通道。 整流罩放置在身体或飞机机翼上，使得附接锚的头部被容纳在芯袋中。 然后，整流罩滑过身体或飞机机翼，通道沿连接锚的头部滑动，从而防止整流罩从身体或飞机机翼上抬起。

    Wing tip joint in airfoils
    5.
    发明授权
    Wing tip joint in airfoils 有权
    机翼翼尖接头

    公开(公告)号：US07975965B2

    公开(公告)日：2011-07-12

    申请号：US12119898

    申请日：2008-05-13

    申请人： James F. Ackermann ,  Richard B. Tanner

    发明人： James F. Ackermann ,  Richard B. Tanner

    IPC分类号： B64C5/00

    CPC分类号： B64C3/18 ,  B64C23/069 ,  Y02T50/164

    摘要： An aircraft joint comprises a wing structure and a wing tip. The wing structure has a first part of a clevis and lug fastening system located around an outer end of the wing structure. The wing tip has a second part of the clevis and lug fastening system located around an end of the wing tip. The wing tip is capable of being joined to the outer end of the wing structure. An upper aerodynamic surface and a lower aerodynamic surface are formed by joining the wing structure and the wing tip. The first part and the second part are located about a center between the upper aerodynamic surface and the lower aerodynamic surface. The first part and the second part engage each other such that a moment reaction occurs around the upper aerodynamic surface and the lower aerodynamic surface.

    摘要翻译： 飞机接头包括机翼结构和翼尖。 机翼结构具有位于翼结构的外端周围的U形夹和凸耳紧固系统的第一部分。 翼尖具有位于翼尖端部周围的U形夹和凸耳紧固系统的第二部分。 翼尖能够连接到机翼结构的外端。 通过连接翼结构和翼尖形成上空气动力学表面和下空气动力学表面。 第一部分和第二部分围绕上部空气动力学表面和下部空气动力学表面之间的中心定位。 第一部分和第二部分彼此接合，使得在上部空气动力学表面和下部空气动力学表面周围发生力矩反作用力。

    Wing panel structure
    6.
    发明授权
    Wing panel structure 有权
    翼板结构

    公开(公告)号：US07628358B2

    公开(公告)日：2009-12-08

    申请号：US11553017

    申请日：2006-10-26

    申请人： James F. Ackermann ,  Richard B. Tanner ,  Ian C. Burford ,  Thomas V. Gendzwill

    发明人： James F. Ackermann ,  Richard B. Tanner ,  Ian C. Burford ,  Thomas V. Gendzwill

    IPC分类号： B64C3/20

    CPC分类号： B64C3/26

    摘要： A wing panel structure for an aerospace vehicle or the like may include an outer layer of material having a predetermined thickness. A core structure may be placed on at least a portion of the outer layer of material. An inner layer of material may be placed at least on the core structure. The inner layer of material may have a selected thickness less than the predetermined thickness of the outer layer of material.

    摘要翻译： 用于航空航天车辆等的翼板结构可以包括具有预定厚度的外层材料。 核心结构可以放置在外层材料的至少一部分上。 材料的内层可以至少放置在芯结构上。 材料的内层可以具有小于外层材料的预定厚度的选定厚度。

    WING TIP JOINT IN AIRFOILS
    9.
    发明申请
    WING TIP JOINT IN AIRFOILS 有权
    翅膀联合在空中飞行

    公开(公告)号：US20090283639A1

    公开(公告)日：2009-11-19

    申请号：US12119898

    申请日：2008-05-13

    申请人： James F. Ackermann ,  Richard B. Tanner

    发明人： James F. Ackermann ,  Richard B. Tanner

    IPC分类号： B64C3/18

    CPC分类号： B64C3/18 ,  B64C23/069 ,  Y02T50/164

    摘要： An aircraft joint comprises a wing structure and a wing tip. The wing structure has a first part of a clevis and lug fastening system located around an outer end of the wing structure. The wing tip has a second part of the clevis and lug fastening system located around an end of the wing tip. The wing tip is capable of being joined to the outer end of the wing structure. An upper aerodynamic surface and a lower aerodynamic surface are formed by joining the wing structure and the wing tip. The first part and the second part are located about a center between the upper aerodynamic surface and the lower aerodynamic surface. The first part and the second part engage each other such that a moment reaction occurs around the upper aerodynamic surface and the lower aerodynamic surface.

    摘要翻译： 飞机接头包括机翼结构和翼尖。 机翼结构具有位于翼结构的外端周围的U形夹和凸耳紧固系统的第一部分。 翼尖具有位于翼尖端部周围的U形夹和凸耳紧固系统的第二部分。 翼尖能够连接到机翼结构的外端。 通过连接翼结构和翼尖形成上空气动力学表面和下空气动力学表面。 第一部分和第二部分围绕上部空气动力学表面和下部空气动力学表面之间的中心定位。 第一部分和第二部分彼此接合，使得在上部空气动力学表面和下部空气动力学表面周围发生力矩反作用力。