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    METHOD OF REPAIRING DAMAGE TO FUSELAGE BARREL AND ASSOCIATED APPARATUS AND SYSTEM
    1.
    发明申请
    METHOD OF REPAIRING DAMAGE TO FUSELAGE BARREL AND ASSOCIATED APPARATUS AND SYSTEM 审中-公开

    公开(公告)号：US20190248463A1

    公开(公告)日：2019-08-15

    申请号：US16393716

    申请日：2019-04-24

    申请人： The Boeing Company

    发明人： Remmelt Andrew Staal ,  Narbeh Nersessian ,  Gary D. Oakes

    IPC分类号： B64C1/06 ,  B64F5/40

    CPC分类号： B64C1/06 ,  B64C1/068 ,  B64C1/069 ,  B64C2001/0072 ,  B64F5/40

    摘要： Disclosed herein is a method of repairing damage to a fuselage barrel, having a one-piece construction, of an aircraft. The method includes determining at least a first virtual splice line and a second virtual splice line along the fuselage barrel in a direction parallel to a longitudinal axis of the fuselage barrel. The method also includes detecting damage in a first section of the fuselage barrel between the first virtual splice line and the second virtual splice line. The method further includes cutting through the fuselage barrel along the first virtual splice line and the second virtual splice line to physically separate the first section from a main section of the fuselage barrel. The method also includes removing the first section from the main section of the fuselage barrel, and splicing a new section to the main section of the fuselage barrel in place of the first section.

    HELICOPTER WITH A FUSELAGE AND A COMPOSITE TAIL BOOM
    3.
    发明申请
    HELICOPTER WITH A FUSELAGE AND A COMPOSITE TAIL BOOM 审中-公开

    公开(公告)号：US20170297675A1

    公开(公告)日：2017-10-19

    申请号：US15471354

    申请日：2017-03-28

    申请人： AIRBUS HELICOPTERS DEUTSCHLAND GMBH

    发明人： Axel FINK

    IPC分类号： B64C1/06 ,  B64C27/04 ,  B64C1/00 ,  B64C27/82

    CPC分类号： B64C1/06 ,  B64C1/069 ,  B64C27/04 ,  B64C27/82 ,  B64C2001/0072 ,  Y02T50/43

    摘要： A helicopter with a fuselage and a composite tail boom. The composite tail boom has at least a tubular tail boom cone and a composite attachment ring segment that defines a mating face which is connected to the fuselage at an associated connection interface by means of a plurality of tension members that are oriented longitudinally with respect to a longitudinal extension direction of the composite tail boom. The plurality of tension members are distributed over a perimeter of the composite attachment ring segment 7. The composite attachment ring segment has a clamp ring section with a plurality of tension member accommodations. The clamp ring section defines the mating face of the composite attachment ring segment 7. The plurality of tension members is at least partly accommodated in the plurality of tension member accommodations.

    Splice assembly for joining structural components
    6.
    发明授权
    Splice assembly for joining structural components 有权
    用于连接结构部件的接头组件

    公开(公告)号：US09586667B2

    公开(公告)日：2017-03-07

    申请号：US14557812

    申请日：2014-12-02

    申请人： The Boeing Company

    发明人： Andrew C. Reeves

    IPC分类号： B64C1/06 ,  B64C1/12

    CPC分类号： B64C1/069 ,  B64C1/061 ,  B64C1/064 ,  B64C1/12 ,  Y10T29/49622

    摘要： A splice assembly may include a first splice bracket including first longitudinal axis, a first connecting member, and a first mating member extending from the first connecting member along the first longitudinal axis, the first mating member including a first mating surface disposed as a non-zero first angle relative to the first longitudinal axis. The disclosed slice assembly may further include a second splice bracket including second longitudinal axis, a second connecting member, and a second mating member extending from the second connecting member along the second longitudinal axis, the second mating member including a second mating surface disposed as a non-zero second angle relative to the second longitudinal axis. The first mating surface and the second mating surface are complementary. Surface contact between the first mating surface and the second mating surface defines a fastening location for connecting the first splice bracket and the second splice bracket.

    摘要翻译： 接头组件可以包括第一接头支架，其包括第一纵向轴线，第一连接构件和从第一连接构件沿着第一纵向轴线延伸的第一配合构件，第一配合构件包括作为非接触构件设置的第一配合表面， 零第一角度相对于第一纵向轴线。 所公开的切片组件还可以包括第二拼接支架，其包括第二纵向轴线，第二连接构件和从第二连接构件沿着第二纵向轴线延伸的第二配合构件，第二配合构件包括第二配合表面， 相对于第二纵向轴线的非零第二角度。 第一配合表面和第二配合表面是互补的。 第一配合表面和第二配合表面之间的表面接触限定了用于连接第一接合支架和第二接合支架的紧固位置。

    METHOD FOR MEASURING THE POSITION OF A MOBILE STRUCTURE
    8.
    发明申请
    METHOD FOR MEASURING THE POSITION OF A MOBILE STRUCTURE 审中-公开
    测量移动结构位置的方法

    公开(公告)号：US20160340016A1

    公开(公告)日：2016-11-24

    申请号：US15159240

    申请日：2016-05-19

    申请人： Airbus Operations (SAS)

    发明人： Jean-Christophe Bry ,  Claude Leonetti ,  Gregoire PEBERNAD DE LANGAUTIER

    IPC分类号： B64C1/06 ,  G06K9/46 ,  B64F5/00 ,  H04N5/247 ,  G01B11/14 ,  G01B11/24 ,  G06T7/00 ,  G06K9/66

    CPC分类号： B64C1/069 ,  B64F5/10 ,  G01B11/14 ,  G01B11/24 ,  G01C11/06 ,  G06K9/4604 ,  G06K9/66 ,  G06T7/0004 ,  G06T2207/30164 ,  H04N5/247

    摘要： A method for measuring the position of a mobile structure in a set of reference axes, the structure comprising a plurality of intrinsic recurrent structural elements, comprising the following steps undertaken by a processor. Acquiring simultaneous images of the structure from a plurality of optical devices, each recurrent element being in a field of view of at least three separate optical devices. Extracting the recurrent elements from each image and determining their position in the image. Computing at least one indicator for each recurrent element detected in each image. Identifying each recurrent element by associating a unique identifier with each element, the identifier being related to the position of each optical device in the set of reference axes, and to at least one indicator associated with each element in each image. Determining the position, by implementing a photogrammetric algorithm, of each recurrent element in the set of reference axes.

    摘要翻译： 一种用于测量一组参考轴中的移动结构的位置的方法，所述结构包括多个本征复原结构元件，包括由处理器执行的以下步骤。 从多个光学装置获取结构的同时图像，每个反射元件处于至少三个分离的光学装置的视野内。 从每个图像中提取循环元素并确定其在图像中的位置。 为每个图像中检测到的每个循环元素计算至少一个指标。 通过将唯一标识符与每个元素相关联来识别每个循环元件，所述标识符与所述参考轴集合中的每个光学设备的位置相关，以及与每个图像中的每个元素相关联的至少一个指示符。 通过实施摄影测量算法确定参考轴集合中每个循环元素的位置。

    FUSELAGE SECTION AND TRANSVERSE BUTT JOINT CONNECTING TWO FUSELAGE SECTIONS OF AN AIRCRAFT OR SPACECRAFT
    10.
    发明申请
    FUSELAGE SECTION AND TRANSVERSE BUTT JOINT CONNECTING TWO FUSELAGE SECTIONS OF AN AIRCRAFT OR SPACECRAFT 审中-公开
    连接部分和横向接头连接飞机或间隙的两个熔断部分

    公开(公告)号：US20160318594A1

    公开(公告)日：2016-11-03

    申请号：US15141078

    申请日：2016-04-28

    申请人： Airbus Operations GmbH

    发明人： Carsten Paul

    IPC分类号： B64C1/06 ,  B64F5/00

    CPC分类号： B64C1/069

    摘要： A fuselage section of an aircraft or spacecraft includes a stringer, an outer skin on the inside of which the stringer is arranged, and a stringer coupling. The stringer coupling includes a first coupling portion, by means of which the stringer coupling is connected to the stringer at a head end of the stringer, and a second coupling portion which is planar and by means of which the stringer coupling is connected to the outer skin so as to overlap the head end of the stringer in the longitudinal direction of the stringer. The second coupling portion has a wider surface area than the first coupling portion and the stringer, such that the stringer is widened beyond the head end in the longitudinal direction by means of the stringer coupling.

    摘要翻译： 飞机或航天器的机身部分包括桁条，其内部布置有桁条的外皮和桁架连接。 纵梁联接器包括第一联接部分，通过该第一联接部分，纵梁联接件在纵梁的头端处连接到纵梁，第二联接部分是平面的，通过该第二联接部分，纵梁联接件连接到外部 皮肤，以便在桁条的纵向方向上与桁条的头端重叠。 第二联接部分具有比第一联接部分和纵梁更宽的表面积，使得通过纵梁联接将纵梁在纵向方向上加宽到头端之外。