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    Fuselage Skin Panel Connection System and Method for Connecting Skin Panels
    1.
    发明申请
    Fuselage Skin Panel Connection System and Method for Connecting Skin Panels 审中-公开

    公开(公告)号：US20180148153A1

    公开(公告)日：2018-05-31

    申请号：US15364473

    申请日：2016-11-30

    申请人： The Boeing Company

    发明人： Angelina M. Conti ,  Robert E. Grip ,  Ted K. Rothaupt

    IPC分类号： B64C1/12 ,  B64C1/06 ,  B64F5/00

    CPC分类号： B64C1/12 ,  B64C1/061 ,  B64C1/08 ,  B64F5/00

    摘要： An aircraft is provided. The aircraft includes truss elements configured to form a space frame fuselage, and skin panels connected with the truss elements and configured to form a skin over said space frame fuselage. The skin panels are movable relative to one another so as to prevent loading of the space frame fuselage from inducing loading in the skin. The aircraft includes a fitting. The fitting includes a first intermediate portion, a first outer portion, and a first inner portion. The first outer and inner portions are spaced apart from each other and interconnected by the first intermediate portion. The skin panels include first and second skin panels that are adjacent to each other. The first skin panel has a first end portion that is adjacent to a second end portion of the second skin panel. The fitting is positioned between the first and second skin panels such that the first and second end portions of the skin panels extend between the first inner and outer portions. The fitting is configured to enable the first and second skin panels to move towards each other along a first plane of first outer and inner surfaces of the first and second skin panels while constraining non-planar movement of the skin panels with respect to the first plane.

    MORPHING AIRFOIL LEADING EDGE
    4.
    发明申请
    MORPHING AIRFOIL LEADING EDGE 有权
    MORPHING AIRFOIL引领边缘

    公开(公告)号：US20160009372A1

    公开(公告)日：2016-01-14

    申请号：US14196461

    申请日：2014-03-04

    申请人： The Boeing Company

    发明人： Robert E. Grip ,  John J. Brown ,  Neal A. Harrison ,  Blaine K. Rawdon ,  John C. Vassberg

    IPC分类号： B64C9/24 ,  B64C3/38 ,  B64C3/26

    CPC分类号： B64C9/24 ,  B64C3/26 ,  B64C3/28 ,  B64C3/38 ,  B64C3/48 ,  B64C3/50 ,  B64C2003/445 ,  Y02T50/14

    摘要： An airfoil may include a leading edge and a shape control mechanism. The leading edge may include a flexible leading edge skin having a first end, a second end, and an arc length defined therebetween. The shape control mechanism may be attached to the flexible leading edge skin at a plurality of support locations and may transition the flexible leading edge skin from a first shape having a first curvature profile to a second shape having a second curvature profile different than the first curvature profile without a change in the arc length.

    摘要翻译： 翼型件可以包括前缘和形状控制机构。 前缘可以包括柔性前缘皮肤，其具有第一端部，第二端部和在其间限定的弧形长度。 形状控制机构可以在多个支撑位置处附接到柔性前缘皮肤，并且可以将柔性前缘皮肤从具有第一曲率轮廓的第一形状转变到具有不同于第一曲率的第二曲率轮廓的第二形状 轮廓没有弧长变化。

    Sandwich structure having hinge assemblies for accommodating differential in-plane expansion of face sheets
    6.
    发明授权
    Sandwich structure having hinge assemblies for accommodating differential in-plane expansion of face sheets 有权

    公开(公告)号：US10288008B2

    公开(公告)日：2019-05-14

    申请号：US15382603

    申请日：2016-12-17

    申请人： The Boeing Company

    发明人： Robert E. Grip ,  John J. Brown

    IPC分类号： B64C3/48 ,  F01D25/26 ,  F02K1/80 ,  F02K1/82 ,  B64C1/12 ,  B64D27/26 ,  B64D29/00 ,  F01D25/30 ,  B64D29/06 ,  F04D29/44

    摘要： A sandwich structure includes a first skin and a second skin spaced apart from each other and interconnected by a hinge assembly including a first hinge member and a second hinge member. The first hinge member proximal end is coupled to the first skin. The second hinge member proximal end is coupled to the second skin. The first hinge member distal end is coupled to the second member distal end at a member joint. The hinge assembly: prevents movement of the first skin relative to the second skin in an in-plane longitudinal direction of the first skin, allows movement of the first skin relative to the second skin in an in-plane transverse direction of the first skin, and allows movement of the first skin relative to the second skin in an out-of-plane direction that is normal to the in-plane longitudinal direction and the in-plane transverse direction.

    Preloading a fastener of a mechanical fitting
    9.
    发明授权
    Preloading a fastener of a mechanical fitting 有权
    预先安装机械配件的紧固件

    公开(公告)号：US09574587B2

    公开(公告)日：2017-02-21

    申请号：US14291210

    申请日：2014-05-30

    申请人： The Boeing Company

    发明人： Robert E. Grip ,  Michael K. Hughes

    IPC分类号： B23Q17/00 ,  F16B5/00 ,  B64C1/00 ,  F16B5/02 ,  B64C1/26 ,  E04B1/24

    CPC分类号： F16B5/02 ,  B64C1/26 ,  E04B2001/2415 ,  E04B2001/2448 ,  F16B5/0092 ,  Y10T29/49766 ,  Y10T29/49771 ,  Y10T29/49826 ,  Y10T29/53022

    摘要： A system for preloading a fastener of a mechanical fitting includes a strain measuring device to measure a strain on the fastener as the fastener is tightened. The mechanical fitting may include a base structure and a plate member. A support structure supports the plate member at a predetermined spacing from the base structure. The support structure may include a first sloping plate and a second sloping plate each extending between the plate member and the base structure. The fastener extends through a first hole in the plate member and a second hole in the base structure. The fastener is accessible through an opening on each side of the support structure. At least a portion of the strain measuring device is positioned relative to the fastener through a first opening of the openings to measure the strain on the fastener correlating to the preload as the fastener is tightened.

    摘要翻译： 用于预加载机械配件的紧固件的系统包括应变测量装置，用于在紧固件被紧固时测量紧固件上的应变。 机械配件可以包括基座结构和板构件。 支撑结构以与基座结构预定的间隔支撑板构件。 支撑结构可以包括在板构件和基座结构之间延伸的第一倾斜板和第二倾斜板。 紧固件延伸穿过板构件中的第一孔和底座结构中的第二孔。 紧固件可通过支撑结构的每一侧上的开口接近。 应变测量装置的至少一部分通过开口的第一开口相对于紧固件定位，以在紧固件被紧固时测量与预紧相关的紧固件上的应变。