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    SPLICE ASSEMBLY FOR JOINING STRUCTURAL COMPONENTS
    83.
    发明公开
    SPLICE ASSEMBLY FOR JOINING STRUCTURAL COMPONENTS 审中-公开

    公开(公告)号：EP3388330A1

    公开(公告)日：2018-10-17

    申请号：EP18172583.9

    申请日：2015-11-25

    申请人： The Boeing Company

    发明人： REEVES, Andrew C.

    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 100 includes a first splice bracket 102a including first longitudinal axis Xa, a first connecting member 104a, and a first mating member 106a extending from the first connecting member 104a along the first longitudinal axis Xa, the first mating member 106a including a first mating surface 108a disposed as a non-zero first angle relative to the first longitudinal axis Xa. The disclosed slice assembly 100 further includes a second splice bracket 102b including second longitudinal axis Xb, a second connecting member 104b, and a second mating member 106b extending from the second connecting member 104b along the second longitudinal axis Xb, the second mating member 106b including a second mating surface 108b disposed as a non-zero second angle relative to the second longitudinal axis Xb. The first mating surface 108a and the second mating surface 108b are complementary. Surface contact between the first mating surface 108a and the second mating surface 108b defines a fastening location for connecting the first splice bracket 102a and the second splice bracket 102b.

    ROTORCRAFT, MOTOR HEAT DISSIPATION STRUCTURE, CONNECTING STRUCTURE FOR CRAFT ARM AND FUSELAGE, AND LANDING GEAR ASSEMBLY/DISASSEMBLY STRUCTURE
    85.
    发明公开
    ROTORCRAFT, MOTOR HEAT DISSIPATION STRUCTURE, CONNECTING STRUCTURE FOR CRAFT ARM AND FUSELAGE, AND LANDING GEAR ASSEMBLY/DISASSEMBLY STRUCTURE 审中-公开
    旋翼机，电机散热结构，工艺臂和机身连接结构，起落架总成/拆卸结构

    公开(公告)号：EP3213995A1

    公开(公告)日：2017-09-06

    申请号：EP15855700.9

    申请日：2015-10-12

    申请人： Guangzhou Xaircraft Technology Co., Ltd.

    发明人： PENG, Bin ,  XIAO, Dingfeng

    IPC分类号： B64D33/10 ,  B64C27/08 ,  B64C25/08

    CPC分类号： B64C25/08 ,  B64C1/069 ,  B64C25/52 ,  B64C25/58 ,  B64C27/08 ,  B64C39/024 ,  B64C2025/325 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/108 ,  B64D27/26 ,  B64D33/08 ,  H02K9/06

    摘要： A rotorcraft together with a heat dissipation structure for a motor, a connecting structure for an arm and an airframe and an assembly and disassembly structure for a foot stand are provided. The rotorcraft includes: the airframe, the arm having a first end connected to the airframe, a propeller connected to the second end of the arm and driven by a motor, and the heat dissipation structure for the motor. The heat dissipation structure for the motor includes: a casing being a hollow structure having a top opening and an air inlet in a bottom portion, in which a motor body is disposed inside of the casing, and an air channel is formed between a circumferential edge of the motor body and an inner wall of the casing; a head cover connected to a revolving shaft of the motor synchronously and provided with a plurality of air flow picks on the lower surface thereof; and a mounting stand fixed to an upper surface of the head cover and configured to be connected with the propeller.

    摘要翻译： 本发明提供一种旋翼飞行器以及用于马达的散热结构，用于臂和机身的连接结构以及用于脚架的组装和拆卸结构。 旋翼飞行器包括：机身，臂具有连接到机身的第一端，连接到臂的第二端并由马达驱动的螺旋桨以及用于马达的散热结构。 该电机的散热结构包括：壳体，该壳体为具有顶部开口和底部中的进气口的中空结构，其中马达主体布置在壳体内部，并且空气通道形成在周边边缘 所述马达本体和所述壳体的内壁; 盖罩，其与电机的旋转轴同步地连接并且在其下表面上设置有多个气流拾取器; 以及安装支架，其固定到所述头罩的上表面并被构造成与所述螺旋桨连接。

    AIRCRAFT STRUCTURAL COMPONENT ADAPTED FOR ABSORBING AND TRANSMITTING FORCES
    88.
    发明公开
    AIRCRAFT STRUCTURAL COMPONENT ADAPTED FOR ABSORBING AND TRANSMITTING FORCES 审中-公开
    ÜBERTRAGUNGVONKRÄFTENFLUGZEUGSTRUKTURKOMPONENTE ZUR ABSORPTION

    公开(公告)号：EP3112254A1

    公开(公告)日：2017-01-04

    申请号：EP15400026.9

    申请日：2015-06-29

    申请人： AIRBUS HELICOPTERS DEUTSCHLAND GmbH

    发明人： Von-Wilmowsky, Kaspar ,  Reichensperger, Christian ,  Rack, Andreas

    IPC分类号： B64C1/00

    CPC分类号： B64C1/069 ,  B64C1/00 ,  B64C1/064 ,  B64C25/10 ,  B64C25/20 ,  B64C25/34 ,  B64C27/00 ,  B64C27/04 ,  B64C2001/0054 ,  B64C2025/325 ,  F16B5/01 ,  F16B9/00 ,  F16B11/006

    摘要： The invention is related to an aircraft structural component (8a) that is adapted for absorbing and transmitting forces in an aircraft, said aircraft structural component (8a) comprising at least one panel element (10) and at least one reinforcing structure (9). Said at least one reinforcing structure (9) is rigidly attached to said at least one panel element (10) such that at least one cavity (21) is defined between said at least one panel element (10) and said at least one reinforcing structure (9), said at least one cavity (21) being adapted for distributing forces that are absorbed by said aircraft structural component (8a) in operation.

    摘要翻译： 本发明涉及一种适于在飞行器中吸收和传递力的飞行器结构部件（8a），所述飞机结构部件（8a）包括至少一个屏元件（10）和至少一个加强结构（9）。 所述至少一个加强结构（9）刚性地附接到所述至少一个屏元件（10），使得至少一个空腔（21）被限定在所述至少一个屏元件（10）和所述至少一个加强结构 （9），所述至少一个空腔（21）适于分配由所述飞机结构部件（8a）在操作中吸收的力。