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    AN UNMANNED AERIAL VEHICLE
    271.
    发明公开
    AN UNMANNED AERIAL VEHICLE 有权
    UNBEMANNTES LUFTFAHRZEUG

    公开(公告)号：EP3087003A1

    公开(公告)日：2016-11-02

    申请号：EP13900333.9

    申请日：2013-12-24

    Applicant: Singapore Technologies Aerospace Ltd

    Inventor： CHAN, Keen Ian

    IPC: B64C27/08 ,  B64C27/10 ,  B64C29/02 ,  B64C25/32 ,  B64C39/10 ,  B64C11/46 ,  B64C39/02 ,  A63H27/127 ,  A63H27/133 ,  A63H27/18

    CPC classification number: B64C29/02 ,  A63H27/12 ,  B64C11/48 ,  B64C27/08 ,  B64C27/10 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/122 ,  B64C2201/141

    Abstract: An unmanned aerial vehicle (UAV) capable of vertical and horizontal flight modes, a method of assembling a UAV, and a kit of parts for assembling a UAV. The UAV comprises an elongated wing structure having an elongated axis along the longest dimension of the elongated wing structure, the elongated wing structure having a middle location at a substantially halfway point; a connecting structure extending substantially perpendicularly from the elongated wing structure, the connecting structure being offset from the middle location of the elongated wing structure at a first position along the elongated axis; and at least three sets of propellers, wherein at least two sets of propellers are mounted on the connecting structure, and wherein at least one set of propellers is mounted at a second position offset from the middle location in an opposite direction away from the connecting structure.

    Abstract translation: 一种能够进行垂直和水平飞行模式的无人驾驶飞行器（UAV），组装无人机的方法以及组装无人机的零件套件。 无人机包括细长机翼结构，其具有沿着细长机翼结构的最长尺寸的细长轴线，细长机翼结构在大致中途点处具有中间位置; 所述连接结构从所述细长翼结构基本上垂直延伸，所述连接结构在所述细长轴线的第一位置处从所述细长翼结构的中间位置偏移; 和至少三组螺旋桨，其中至少两组螺旋桨安装在连接结构上，并且其中至少一组螺旋桨安装在远离连接结构的相反方向偏离中间位置的第二位置 。

    MULTI-POSITION LANDING GEAR
    272.
    发明公开
    MULTI-POSITION LANDING GEAR 审中-公开
    MEHRPOSITIONS-FAHRWERK

    公开(公告)号：EP3031717A1

    公开(公告)日：2016-06-15

    申请号：EP15196209.9

    申请日：2015-11-25

    Applicant: The Boeing Company

    Inventor： HARRIS, John H. ,  NEWMAN, Daniel I

    IPC: B64C25/66 ,  B64C29/00

    CPC classification number: B64C25/14 ,  B64C25/36 ,  B64C25/52 ,  B64C25/66 ,  B64C29/0025 ,  B64C2201/088

    Abstract: A multi-position landing gear for an aircraft may include a first landing skid (102) disposed on a bottom side of the aircraft (200), and a second landing skid (104) disposed on one of a top side or the bottom side of the aircraft (200), wherein the first landing skid (102) and the second landing skid (2104) are rotatable relative to the aircraft (200).

    Abstract translation: 用于飞行器的多位起落架可以包括设置在飞行器（200）的底侧上的第一着陆滑道（102）和设置在飞行器（200）的底侧上的第一着陆滑道（104） 所述飞行器（200），其中所述第一着陆滑道（102）和所述第二着陆滑道（2104）可相对于所述飞机（200）旋转。

    WING ADJUSTING MECHANISM
    276.
    发明公开
    WING ADJUSTING MECHANISM 审中-公开
    WING调整机制

    公开(公告)号：EP2814734A1

    公开(公告)日：2014-12-24

    申请号：EP13709050.2

    申请日：2013-02-13

    Applicant: Reiter, Johannes

    Inventor： Reiter, Johannes

    IPC: B64C29/02 ,  B64C39/02 ,  B64C29/00 ,  B64C39/00 ,  B64C27/16 ,  B64C27/18

    CPC classification number: B64C27/00 ,  B64C3/385 ,  B64C27/001 ,  B64C27/16 ,  B64C27/18 ,  B64C29/00 ,  B64C29/0033 ,  B64C29/0075 ,  B64C29/02 ,  B64C39/008 ,  B64C39/024 ,  B64C2201/088 ,  B64C2201/102 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/165

    Abstract: The present invention relates to a device for generating aerodynamic lift and in particular an aircraft (100) for vertical take-off and landing. A wing arrangement (110) comprises at least one propulsion unit (111), wherein the propulsion unit (111) comprises a rotating mass which is rotatable around a rotary axis (117). The wing arrangement (110) is mounted to a fuselage (101) such that the wing arrangement (110) is tiltable around a longitudinal wing axis (112) of the wing arrangement (110) and such that the wing arrangement (110) is rotatable with respect to the fuselage (101) around a further rotary axis that differs to the longitudinal wing axis (112). An adjusting mechanism adjusts a tilting angle of the wing arrangement (110) around the longitudinal wing axis (112) under influence of a precession force (Fp) which forces the wing arrangement (110) to tilt around the longitudinal wing axis (112).

    Abstract translation: 用于产生气动升力的装置技术领域本发明涉及一种用于产生气动升力的装置，尤其涉及一种用于垂直起飞和着陆的飞机（100）。 机翼装置（110）包括至少一个推进单元（111），其中推进单元（111）包括可围绕旋转轴线（117）旋转的旋转质量。 机翼装置（110）安装到机身（101），使得机翼装置（110）可围绕机翼装置（110）的纵向机翼轴线（112）倾斜并且使得机翼装置（110）可旋转 相对于机身（101）绕与纵向机翼轴线（112）不同的另一旋转轴线旋转。 调节机构在迫使机翼布置（110）围绕纵向机翼轴线（112）倾斜的进动力（Fp）的影响下调节机翼布置（110）围绕纵向机翼轴线（112）的倾斜角度。

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