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    Flapping wing aerial vehicles
    41.
    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
    45.
    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
    47.
    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。

    Passive Torque Balancing in a High-Frequency Oscillating System
    49.
    发明申请
    Passive Torque Balancing in a High-Frequency Oscillating System 有权
    高频振荡系统中的被动力矩平衡

    公开(公告)号：US20120292438A1

    公开(公告)日：2012-11-22

    申请号：US13519901

    申请日：2011-02-11

    Applicant: Pratheev Sabaratnam Sreetharan ,  Robert J. Wood

    Inventor： Pratheev Sabaratnam Sreetharan ,  Robert J. Wood

    IPC: B64C33/02 ,  F16H21/44

    CPC classification number: B64C33/02 ,  B64C33/00 ,  B64C39/028 ,  B64C2201/025 ,  Y10T74/18928 ,  Y10T74/18968

    Abstract: A passively torque-balanced device includes (a) a frame; (b) a drivetrain including a drive actuator mounted to the frame and configured for reciprocating displacement, an input platform configured for displacement by the drive actuator, a plurality of rigid links, including a proximate link and remote links, wherein the rigid links are collectively mounted to the frame, and a plurality of joints joining the rigid links and providing a plurality of non-fully actuated degrees of freedom for displacement of the rigid links, the plurality of joints including a fulcrum joint that is joined both to the input platform and to the proximate rigid link; and (c) at least two end effectors respectively coupled with the remote links and configured for displacement without full actuation.

    Abstract translation: 无源扭矩平衡装置包括（a）框架; （b）传动系统，其包括安装到所述框架并被构造成用于往复运动的驱动致动器，构造成用于由所述驱动致动器移位的输入平台，包括邻近链节和远程链节的多个刚性连杆，其中所述刚性连杆集体 安装到框架上的多个接头以及连接刚性连杆并且提供多个非完全致动的刚性连杆的移动自由度的多个接头，所述多个接头包括支撑接头，其连接到输入平台和 到邻近的刚性连接; 和（c）至少两个末端执行器，其分别与远程链节联接并被配置为在没有完全致动的情况下进行位移。

    RESONANCE ENGINE
    50.
    发明申请
    RESONANCE ENGINE 有权
    谐振发动机

    公开(公告)号：US20120248243A1

    公开(公告)日：2012-10-04

    申请号：US13515503

    申请日：2010-12-15

    Applicant: Guy Thomas Greenyer

    Inventor： Guy Thomas Greenyer

    IPC: B64C33/02 ,  F03G3/00 ,  H01L41/09

    CPC classification number: B64C39/028 ,  B64C33/02 ,  B64C2201/025

    Abstract: A resonance engine is disclosed comprising: a driver plate (12), to which is coupled at least one oscillatory transducer (14); a drive signal generator connected to the oscillatory transducer for excitation thereof; a first spring-mass resonator, having a first natural resonant frequency, with a proximal end attached to the driver plate (12) and a free distal end; and a reaction means attached to the driver plate substantially opposite to the first spring-mass resonator. When the oscillatory transducer (14) is excited by a drive signal from the generator having a component at or close to said natural resonant frequency, the first spring-mass resonator oscillates at resonance, substantially in anti-phase to the driver plate (12).Small vibrational strains in the oscillatory transducer (14) are converted to large strains of controllable kinematic movements.The resonance engine has particular application for nano air vehicles (10-10f), wherein at least one spring-mass resonator is fitted with a wing (RD, LD) capable of producing thrust by flapping in an insect like kinematic manner suitable for flight. Where additional spring-mass resonators are added to the engine, each may be fitted with a wing. Each different spring-mass resonator may be tuned to have a different natural resonant frequency (when measured in isolation), whereby flight may be controlled by adjusting the drive signal; at particular drive frequencies, certain of the resonators may resonate in preference to others, thereby increasing lift from the associated wings, and controlling flight. The wings may face in opposite directions in order to produce rotational flight.Further closely tuned spring-mass resonators that are tuned on a substantially different frequency band to the wing resonators can be added as legs for independently controllable terrestrial or aerial locomotion.

    Abstract translation: 公开了一种共振发动机，包括：驱动器板（12），其耦合到至少一个振荡换能器（14）; 驱动信号发生器，连接到所述振荡换能器以用于激励; 具有第一固有谐振频率的第一弹簧质量谐振器，其近端附接到驱动器板（12）和自由远端; 以及附接到驱动器板的基本上与第一弹簧质量谐振器相对的反作用装置。 当振荡换能器（14）被来自具有等于或接近于所述固有谐振频率的分量的发生器的驱动信号激发时，第一弹簧 - 质量谐振器以与驱动器板（12）基本上相反的谐振器振荡， 。 振荡换能器（14）中的小振动应变被转换为大的可控运动运动。 共振发动机具有对纳米空气车辆（10-10f）的特殊应用，其中至少一个弹簧 - 质量谐振器装配有能够以适于飞行的运动学方式的昆虫扑动产生推力的翼（RD，LD）。 在发动机附加额外的弹簧 - 质量谐振器的情况下，每个可以安装一个机翼。 每个不同的弹簧质量谐振器可以被调谐为具有不同的自然谐振频率（当隔离测量时），由此可以通过调节驱动信号来控制飞行; 在特定的驱动频率下，某些谐振器可能优先于其它谐振器共振，从而增加从相关联的机翼的升力并控制飞行。 机翼可能面向相反的方向，以产生旋转飞行。 调谐在与翼谐振器基本不同的频带上的进一步紧密调谐的弹簧 - 质量谐振器可以作为腿添加，用于独立可控的地面或空中运动。

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