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    Moving apparatus
    101.
    发明申请
    Moving apparatus 审中-公开
    移动装置

    公开(公告)号：US20050151010A1

    公开(公告)日：2005-07-14

    申请号：US10769304

    申请日：2004-01-30

    Applicant: Masaki Hamamoto ,  Yoshiji Ohta ,  Keita Hara

    Inventor： Masaki Hamamoto ,  Yoshiji Ohta ,  Keita Hara

    IPC: B25J5/00 ,  B64C33/02 ,  B64C39/02 ,  H02N2/00

    CPC classification number: B64C33/02 ,  B64C39/028 ,  B64C2201/025 ,  B64C2201/044 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/146

    Abstract: On a main body portion of a fluttering apparatus, a wing (left wing) is formed which has a front wing shaft, a rear wing shaft and a wing film provided spreading over the front and rear wing shafts. Further, on the main body portion, a rotary actuator for driving the front wing shaft and a rotary actuator for: driving the rear wing shaft are mounted. The front (rear) wing shafts reciprocate in a plane orthogonally crossing an axis of rotation with the actuator serving as the fulcrum. Thus, a moving apparatus is obtained which has superior maneuverability and can move not hindered by any obstacle or geometry both indoors and outdoors.

    Abstract translation: 在飘动装置的主体部分上，形成有一个翼翼（左翼），其具有前翼轴，后翼轴和设置在前翼和后翼轴上的翼片。 此外，在主体部分上安装有用于驱动前翼轴的旋转致动器和用于驱动后翼轴的旋转致动器。 前（后）翼轴在与作为支点的致动器正交的旋转轴线的平面中往复运动。 因此，获得具有优异的机动性并且可以在室内和室外不受任何障碍物或几何形状阻碍的移动装置。

    Compressed air engine and flying object equipped therewith
    102.
    发明授权
    Compressed air engine and flying object equipped therewith 失效
    压缩空气发动机和配备的飞行物体

    公开(公告)号：US06530541B1

    公开(公告)日：2003-03-11

    申请号：US10167728

    申请日：2002-06-11

    Applicant: Jong Bok Woo ,  Ja Kook Koo ,  Kwang Joon Yoon ,  Yun Je Kim

    Inventor： Jong Bok Woo ,  Ja Kook Koo ,  Kwang Joon Yoon ,  Yun Je Kim

    IPC: B64C3300

    CPC classification number: F01B17/02 ,  A63H27/008 ,  A63H29/16 ,  B64C33/025 ,  B64C39/028 ,  B64C2201/025 ,  B64D27/02

    Abstract: A compressed air engine and a flying object using the engine are disclosed. The flying object includes the following elements. That is, the compressed air engine includes: a top member 11 provided with an air inlet 16; an upper cylinder 12; a lower cylinder 13; a bottom member 14; an air pipe, for passing of a compressed air; a shuttle 20 for performing up/down movements within a cylinder formed by the upper and lower cylinders; and a pair of pistons 21a and 21b over and under the shuttle respectively. The pair of the wings are symmetrically and pivotally assembled to the shuttle and the lower cylinder through securing shafts so as to perform up/down movements in accordance with the up/down movements of the shuttle. A compressed air container 2 is assembled to the bottom of the bottom member, for storing the compressed air.

    Abstract translation: 公开了使用该发动机的压缩空气发动机和飞行物体。 飞行物体包括以下元件。 也就是说，压缩空气发动机包括：设置有进气口16的顶部构件11; 上筒12; 下筒13; 底部构件14; 用于通过压缩空气的空气管; 用于在由上下缸形成的缸内进行升/降运动的梭20; 以及分别在梭子上方和下方的一对活塞21a和21b。 一对翼通过固定轴对称地和枢转地组装到梭子和下部圆筒上，以便根据梭子的上下运动来进行上/下移动。 压缩空气容器2组装到底部件的底部，用于储存压缩空气。

    Flapping wing aerial vehicles
    104.
    发明授权
    Flapping wing aerial vehicles 有权

    公开(公告)号：US10017248B2

    公开(公告)日：2018-07-10

    申请号：US14698375

    申请日：2015-04-28

    Applicant: Daedalus Flight Systems, LLC ,  University of Maryland, College Park

    Inventor： Paul D. Samuel ,  Imraan Faruque ,  James Sean Humbert

    IPC: B64C33/00 ,  B64C33/02 ,  B64C39/02

    CPC classification number: B64C33/02 ,  B64C39/024 ,  B64C2201/025

    Abstract: An autonomous flapping wing aerial vehicle can have a vehicle body, a pair of flapping wings, tunable wing hinges, and elastic drive mechanisms. The tunable wing hinges can be coupled to the flapping wings. Each wing hinge can be constructed to deliver a force to a respective one of the flapping wings to alter end points of a stroke thereof. The elastic drive mechanisms can rotate the flapping wings about pivot points to produce the strokes of the flapping wings. The elastic drive mechanism can be driven at or near a resonance thereof. Alterations to the strokes of the flapping wings produced by the combined effect of the tunable wing hinges and the elastic drive mechanisms, operating in parallel, can provide steering control of the aerial vehicle.

    Wing flapping mechanism and method
    108.
    发明授权
    Wing flapping mechanism and method 有权
    翼拍机制及方法

    公开(公告)号：US09216823B2

    公开(公告)日：2015-12-22

    申请号：US14216381

    申请日：2014-03-17

    Applicant: Francois Matte

    Inventor： Francois Matte

    IPC: B64C33/02 ,  A63H27/00

    CPC classification number: B64C33/02 ,  A63H27/008 ,  B64C2201/025

    Abstract: The wing flapping mechanism (100) includes a main frame (110), a pair of opposite wings (120) laterally projecting from the main frame (110), and a linkage arrangement to convert rotation of a motor (150) into a three-dimensional cyclic wing motion of each of the wings (120). The linkage arrangement includes torque-transmitting couplings extending from inside the main frame (110) into the wing structures (122) to transmit an alternating pivoting motion, created as a result of the rotation of the motor (150), to the distal end of a corresponding third torsion-responsive tube (140, 144′″). Each torque-transmitting coupling extends inside a shoulder joint (130), a first torsion-responsive tube (132, 144′), an elbow joint (134), a second torsion-responsive tube (136, 144″), a wrist joint (138) and the third torsion-responsive tube (140, 144′″) of the corresponding wing structure (122).

    Abstract translation: 机翼拍动机构（100）包括主框架（110），从主框架（110）侧向突出的一对相对的翼片（120），以及将马达（150）的旋转转换成三维 每个翼（120）的三维循环翼运动。 联动装置包括从主框架（110）内部延伸到机翼结构（122）中的扭矩传递联接件，以将由马达（150）的旋转产生的交替的枢转运动传递到电动机（150）的远端 相应的第三扭转响应管（140,144'“）。 每个扭矩传递联接件在肩关节（130），第一扭转响应管（132,144'），肘关节（134），第二扭转响应管（136,144“），腕关节 （138）和相应翼结构（122）的第三扭转响应管（140,144'“）。

    Wing for generating lift from an incident flow
    110.
    发明授权
    Wing for generating lift from an incident flow 有权
    从事件流中产生电梯的翼

    公开(公告)号：US08973874B2

    公开(公告)日：2015-03-10

    申请号：US13640976

    申请日：2011-04-14

    Applicant: Robert Jan Musters

    Inventor： Robert Jan Musters

    IPC: B64C9/00 ,  B64C21/10 ,  B64C3/38 ,  A63H27/00 ,  B64C3/10 ,  B64C23/00 ,  B64C33/02 ,  F01D5/12

    CPC classification number: B64C3/38 ,  A63H27/008 ,  B64C3/10 ,  B64C23/00 ,  B64C33/02 ,  B64C2201/025 ,  F01D5/12

    Abstract: The invention relates to a wing for generating lift and comprises a trailing edge, a leading edge, an inner end, an outer end, a top surface and a bottom surface. The wing comprises an aerofoil with a chord line and a span direction. The leading edge comprises a kink between the inner end and the outer end. The leading edge comprises a forward sweep part between the inner end and the kink extending towards the kink presenting an angle relative to the span direction. The leading edge comprises a backward sweep part between the kink and the outer end extending from the kink presenting an angle relative to the span direction. The top surface comprises a flow control means for controlling the lift at least partly located between a leading edge part between the kink and the outer end and located between the leading edge and the trailing edge.

    Abstract translation: 本发明涉及一种用于产生升降机的机翼，包括后缘，前缘，内端，外端，顶表面和底面。 机翼包括具有弦线和跨度方向的机翼。 前缘包括在内端和外端之间的扭结。 前缘包括在内端和扭结之间的向前扫掠部分，其朝向扭结延伸，呈现出相对于跨度方向的角度。 前缘包括在扭结之间的反向扫掠部分和从扭结延伸的外端部，其相对于跨度方向呈现一个角度。 顶表面包括用于控制至少部分地位于扭结和外端之间的前缘部分之间且位于前缘和后缘之间的升力的流量控制装置。

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