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    Aircraft fuselage and method for constructing a floor in such a fuselage
    21.
    发明授权
    Aircraft fuselage and method for constructing a floor in such a fuselage 有权

    公开(公告)号：US10005537B2

    公开(公告)日：2018-06-26

    申请号：US14062069

    申请日：2013-10-24

    申请人： Airbus Operations (S.A.S.)

    发明人： Bernard Guering

    IPC分类号： B64C1/06 ,  B64C1/18

    CPC分类号： B64C1/061 ,  B64C1/18 ,  Y10T29/49622

    摘要： Such a fuselage includes cross-members adapted for the formation of a floor, at least one of said cross-members including an upper part, a lower part, linkage for the lower part to the upper part, and at least one opening for the passage of systems which is delimited between the lower part and the upper part. The upper part of the cross-member is fastened to the fuselage and is dimensioned so as to bear the stresses to which said cross-member may be subjected when the aircraft remains on the ground. The lower part is fastened to the upper part so as to reinforce it such that when assembled, the upper part and the lower part are adapted to bear the stresses to which the cross-member may be subjected in flight conditions of the aircraft.

    Fuselage Skin Panel Connection System and Method for Connecting Skin Panels
    22.
    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.

    DAMAGE VISUALIZATION
    24.
    发明申请
    DAMAGE VISUALIZATION 审中-公开

    公开(公告)号：US20180065725A1

    公开(公告)日：2018-03-08

    申请号：US15689539

    申请日：2017-08-29

    申请人： Airbus Operations GmbH

    发明人： Hermann Benthien ,  Matthias Hegenbart

    IPC分类号： B64C1/06 ,  B64G1/22

    CPC分类号： B64C1/061 ,  B29C70/56 ,  B64C2001/0072 ,  B64G1/10 ,  B64G1/22

    摘要： A structural member for an aircraft or spacecraft has at least one fiber plastic composite, the fiber plastic composite having at least one or a plurality of plies. The structural member also has at least one pre-stressing means providing internal stresses to the fiber plastic composite. The fiber plastic composite and the pre-stressing means are configured and arranged to form a balanced system the internal stresses of which are essentially balanced to zero in a cured state of the said system. The balanced system of the structural member is able to counteract loading stresses exerted to the airframe in service such, that a damage caused by the loading stress is easily detectable visually.