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    Small unmanned aircraft
    111.
    发明申请
    Small unmanned aircraft 有权
    小型无人机

    公开(公告)号：US20070063096A1

    公开(公告)日：2007-03-22

    申请号：US10569653

    申请日：2004-05-12

    Applicant: Yasutada Tanabe ,  Chiharu Totsuka ,  Takeshi Akasaka ,  Masato Okamoto

    Inventor： Yasutada Tanabe ,  Chiharu Totsuka ,  Takeshi Akasaka ,  Masato Okamoto

    IPC: B64C39/02

    CPC classification number: A63H27/02 ,  B64C39/028 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/165 ,  Y10S244/903

    Abstract: A small unmanned airplane includes; a main wing having a camber airfoil whose under surface is approximately flat, narrowing in the shape of taper to a blade tip, leading edge of which holds sweepback angle, of flying wing type which has an aerodynamic surface of tailless wing type and is low aspect ratio; movable flaps extending approximately extreme breadth in trailing edge part of both left and right sides of the main wing, having a dihedral angle at least in level flight; vertical stabilizers placed at blade tips of left and right of the main wing; and two propellers installed on the top surface of the main wing. This can materialize miniaturization and weight saving of a small unmanned airplane for individual carrying capability and for suitability for such as lift-off by hand throw.

    Abstract translation: 一架小型无人机包括 主翼具有下表面近似平坦的弧形翼型，其锥形形状变窄为其前端具有遮光角度的叶片尖端，具有无风翼型的空气动力学表面的飞翼型，低侧面 比; 在主翼的左右两侧的后缘部分中大致极宽的可动翼片至少在水平飞行中具有二面角; 放置在主翼左右叶片尖端的垂直稳定器; 并安装在主翼顶面的两个螺旋桨。 这可以实现小型化和轻量化的小型无人驾驶飞机的个人承载能力和适合性，例如用手抛出。

    Method and apparatus for supporting aircraft components, including actuators
    112.
    发明授权
    Method and apparatus for supporting aircraft components, including actuators 有权
    用于支撑飞行器部件的方法和装置，包括致动器

    公开(公告)号：US07182297B2

    公开(公告)日：2007-02-27

    申请号：US10758294

    申请日：2004-01-15

    Applicant: Clifford Jackson

    Inventor： Clifford Jackson

    IPC: B64C13/28

    CPC classification number: B64C39/024 ,  B64C2201/028 ,  B64C2201/104 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165

    Abstract: Methods and apparatuses for supporting aircraft components, including actuators are disclosed. An apparatus in accordance with one embodiment of the invention includes an actuator housing having an actuator receptacle that securely yet releasably receives an actuator. The actuator receptacle can include conformal walls that conform at least in part to the shape of the actuator and can accordingly squeeze the actuator and properly align the actuator. At least one of the actuator walls can further include a projection that is releasably received in a corresponding recess of the actuator. One of both of these features can releasably secure the actuator relative to the aircraft, reducing and/or eliminating the likelihood that the actuator will be misaligned and/or mispositioned relative to the aircraft during installation and/or replacement.

    Abstract translation: 公开了用于支持飞机部件（包括致动器）的方法和装置。 根据本发明的一个实施例的装置包括具有可靠地可释放地接收致动器的致动器插座的致动器壳体。 致动器容器可以包括至少部分地符合致动器的形状的适形壁，并且可以相应地挤压致动器并且正确对准致动器。 致动器壁中的至少一个还可以包括可释放地容纳在致动器的相应凹部中的突起。 这两个特征之一可以相对于飞行器可释放地固定致动器，减少和/或消除在安装和/或更换期间致动器相对于飞行器不对准和/或错位的可能性。

    Force feedback refueling system for unmanned aircraft
    113.
    发明授权
    Force feedback refueling system for unmanned aircraft 失效
    无人机强制反馈加油系统

    公开(公告)号：US07021586B2

    公开(公告)日：2006-04-04

    申请号：US10782253

    申请日：2004-02-19

    Applicant: John G. Bolling

    Inventor： John G. Bolling

    IPC: B64C1/00

    CPC classification number: B64D39/00 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/028 ,  B64C2201/104

    Abstract: An in-flight refueling system for an unmanned aircraft is responsive to sensed forces acting on a refueling receptacle of the aircraft by a separate refueling probe, to control movements of the aircraft as it is being refueled to reduce the magnitude of the sensed forces and thereby maintain the coupling of the aircraft with the refueling probe.

    Abstract translation: 用于无人驾驶飞机的飞行中加油系统响应于通过单独的加油探针作用在飞机的加油容器上的感测力，以控制飞机在被加油时的运动，以减小感测力的大小，从而 保持飞机与加油探头的耦合。

    Methods and systems for controlling the pitch of a propeller
    114.
    发明申请
    Methods and systems for controlling the pitch of a propeller 审中-公开
    用于控制螺旋桨桨距的方法和系统

    公开(公告)号：US20050226727A1

    公开(公告)日：2005-10-13

    申请号：US11071890

    申请日：2005-03-02

    Applicant: Brian Dennis ,  Kenneth Hillen

    Inventor： Brian Dennis ,  Kenneth Hillen

    IPC: F03D1/00

    CPC classification number: B64C11/44 ,  B64C2201/028 ,  B64C2201/127 ,  B64C2201/165

    Abstract: Apparatuses and methods for controlling the motion of a propeller blade are disclosed. In one embodiment, the apparatus can include a first motor that rotates a propeller about a first axis with a first shaft. A first signal transmission portion, fixed relative to the first motor, can transmit signals to a second signal transmission portion that rotates with the first shaft. A second motor can be carried by the first shaft and can receive signals from the second signal transmission portion. The second motor can drive blades of the propeller about a second axis generally transverse to the first axis via a second shaft to vary the pitch of the blades.

    Abstract translation: 公开了用于控制螺旋桨叶片运动的装置和方法。 在一个实施例中，该装置可以包括第一马达，第一马达使螺旋桨围绕第一轴线与第一轴旋转。 相对于第一电动机固定的第一信号传输部分可以将信号发送到与第一轴一起旋转的第二信号传输部分。 第二电动机可以由第一轴承载并且可以从第二信号传输部分接收信号。 第二马达可以通过第二轴驱动螺旋桨的叶片大致横过第一轴线的第二轴线，以改变叶片的桨距。

    Aircraft control system
    115.
    发明申请
    Aircraft control system 有权
    飞机控制系统

    公开(公告)号：US20030141409A1

    公开(公告)日：2003-07-31

    申请号：US10310415

    申请日：2002-12-05

    Inventor： Derek L. Lisoski ,  Greg T. Kendall

    IPC: B64C001/00 ,  B64C003/00 ,  B64C005/00

    CPC classification number: B64C3/42 ,  B64C3/52 ,  B64C15/02 ,  B64C39/024 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/102 ,  B64C2201/122 ,  B64C2201/126 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  B64D27/24 ,  B64D31/06 ,  B64D2211/00 ,  G05D1/0022 ,  G05D1/0077 ,  H04B7/18504 ,  Y02T50/12 ,  Y02T50/14 ,  Y02T50/44 ,  Y02T50/55 ,  Y02T50/62

    Abstract: A solar rechargeable, long-duration, span-loaded flying wing, having no fuselage or rudder. Having a two-hundred foot wingspan that mounts photovoltaic cells on most all of the wing's top surface, the aircraft uses only differential thrust of its eight propellers to turn, pitch and yaw. The wing is configured to deform under flight loads to position the propellers such that the control can be achieved. Each of five segments of the wing has one or more motors and photovoltaic arrays, and produces its own lift independent of the other segments, to avoid loading them. Five two-sided photovoltaic arrays, in all, are mounted on the wing, and receive photovoltaic energy both incident on top of the wing, and which is incident also from below, through a bottom, transparent surface.

    Abstract translation: 太阳能可再充电，长时间，跨度的飞翼，没有机身或方向舵。 拥有两百英尺的翼展，将光伏电池安装在大部分机翼的顶部表面上，飞机只使用其八个螺旋桨的差速推力来转弯，俯仰和偏航。 机翼构造成在飞行载荷下变形以定位螺旋桨，使得可以实现控制。 翼的五个部分中的每一个具有一个或多个电动机和光伏阵列，并且独立于其它部分产生其自身的升降机，以避免加载它们。 五个双面光伏阵列总体上安装在机翼上，并且接收能量入射到机翼的顶部并且从下方入射的光能通过底部的透明表面。

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