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    Autonomous launch pad for micro air vehicles
    341.
    发明申请
    Autonomous launch pad for micro air vehicles 审中-公开
    微型飞行器自动发射台

    公开(公告)号：US20070228214A1

    公开(公告)日：2007-10-04

    申请号：US11235057

    申请日：2005-09-26

    Applicant: Dan Horak

    Inventor： Dan Horak

    IPC: B64F1/04

    CPC classification number: B64C39/028 ,  A63H27/14 ,  B64C2201/044 ,  B64C2201/084 ,  B64C2201/088 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/162 ,  B64C2201/182 ,  B64F1/04

    Abstract: Autonomous micro air vehicles surveillance systems are provided. A MAV system of one embodiment includes an MAV and a launch pad. The MAV has an engine that is adapted to power the MAV. The launch pad has a starter that is adapted to start the engine in the MAV when the MAV is resting on a launching surface of the launch pad. The launch pad further has a battery to power the starter.

    Abstract translation: 提供自动微型飞行器车辆监视系统。 一个实施例的MAV系统包括MAV和发射台。 MAV具有适用于为MAV供电的发动机。 发射台具有一个启动器，当MAV在发射台的发射表面上时，该启动器适于在MAV中启动发动机。 发射台还有一个电池为起动器供电。

    Cycloidal VTOL UAV
    342.
    发明授权
    Cycloidal VTOL UAV 失效
    环形垂直起伏无人机

    公开(公告)号：US06932296B2

    公开(公告)日：2005-08-23

    申请号：US10690284

    申请日：2003-10-21

    Applicant: Glenn Martin Tierney

    Inventor： Glenn Martin Tierney

    IPC: B64B1/30 ,  B64C39/00 ,  B64C39/02 ,  B64C27/22

    CPC classification number: B64C39/005 ,  B64B1/30 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/088 ,  B64C2201/102 ,  B64C2201/104 ,  B64C2201/165

    Abstract: A system and method for moving an aerial vehicle along a flight path includes rotatable hubs mounted on opposite sides of the vehicle. Elongated airfoils are mounted on the hubs parallel to a common hub axis for rotation about the hub axis on a blade path. Each airfoil defines a chord line and the system includes a gear assembly changeable, during hub rotation, between a first modality wherein airfoil chord lines remain tangential to the blade path (curtate flight), and a second modality wherein airfoil chord lines remain parallel to the flight path of the vehicle (prolate flight). Also, rotation of the hub can be stopped and the airfoils used for fixed wing flight.

    Abstract translation: 沿着飞行路径移动飞行器的系统和方法包括安装在车辆的相对侧上的可旋转轮毂。 细长的翼型件平行于公共轮毂轴线安装在轮毂上，以便在叶片路径上围绕轮毂轴线旋转。 每个翼型件限定弦线，并且该系统包括齿轮组件，在轮毂旋转期间，其中翼型弦线保持与叶片路径相切的第一模态（curtate飞行）和第二模态，其中翼型弦线保持平行于 车辆的飞行路线（长跑）。 此外，轮毂的旋转可以停止，翼型件用于固定翼飞行。

    Runway-independent omni-role modularity enhancement (ROME) vehicle
    343.
    发明授权
    Runway-independent omni-role modularity enhancement (ROME) vehicle 有权
    跑道独立的全能模块化增强（ROME）车辆

    公开(公告)号：US06926235B2

    公开(公告)日：2005-08-09

    申请号：US10600400

    申请日：2003-06-20

    Applicant: Richard P. Ouellette ,  Aaron J. Kutzmann

    Inventor： Richard P. Ouellette ,  Aaron J. Kutzmann

    IPC: B64C1/00 ,  B64C29/00 ,  B64C39/02 ,  B64D7/00

    CPC classification number: B64C1/00 ,  B64C29/0058 ,  B64C39/024 ,  B64C2201/046 ,  B64C2201/086 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/121 ,  B64C2201/165 ,  B64C2201/167 ,  B64C2201/187 ,  B64D7/00

    Abstract: A modular component set is configurable to form a plurality of flight capable platforms. A plurality of end pieces each has contiguously connected curved outer portions each longitudinally expanding from a tip to terminate at a blunt attachment face. Body members have opposed ends to receive the end piece blunt attachment face, and a rectangular shaped mid-portion having opposed walls. A plurality of task specific panels are each releasably connectable to one of the opposed walls. At least one of the body members with the end pieces joined at the opposed ends, and at least one of the task specific panels connected to one of the opposed walls form a minimum component set for each of the flight capable platforms.

    Abstract translation: 模块化组件组可配置成形成多个具有飞行能力的平台。 多个端片各自具有连续地连接的弯曲外部部分，每个端部从尖端纵向扩展以终止于钝的附接面。 主体部件具有相对的端部以接收端部钝器附接面，以及具有相对壁的矩形中间部分。 多个任务专用面板各自可拆卸地连接到相对的壁之一。 至少一个具有端部件的主体部件在相对的端部连接，并且连接到相对的一个壁之一的任务专用面板中的至少一个为每个具有飞行能力的平台形成最小的部件组。

    Vehicle refueling system
    346.
    发明授权
    Vehicle refueling system 失效
    车辆加油系统

    公开(公告)号：US6142421A

    公开(公告)日：2000-11-07

    申请号：US231368

    申请日：1999-01-13

    Applicant: Miles R. Palmer

    Inventor： Miles R. Palmer

    IPC: B64C39/02 ,  B64D1/22 ,  B64D37/04 ,  B64D37/06 ,  B64D37/12 ,  B64D39/00 ,  F42B15/00 ,  B64C39/00 ,  B64D37/02

    CPC classification number: B64D37/12 ,  B64C39/024 ,  B64D1/22 ,  B64D37/04 ,  B64D37/06 ,  B64D39/00 ,  F42B15/00 ,  B64C2201/044 ,  B64C2201/084 ,  B64C2201/088 ,  B64C2201/105 ,  B64C2201/121 ,  B64C2201/126 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/205

    Abstract: A vehicle refueling system includes an aero vehicle and a fuel bladder system. The fuel bladder system includes a fuel bladder, a pickup loop of a predetermined loop size, a reel mechanism to retract at least one side of the pickup loop to reduce the loop size, a snag sensor to sense when the pickup loop has been hooked by the retractable hook, the snag sensor initiating the reel mechanism, a compass to sense the random orientation of the loop, a radio navigation receiver to sense a location of the loop, and a transmitter to transmit the random orientation and the location. The vehicle includes a fuselage, a retractable hook with a hook sensor to detect when a fuel bladder is hooked and the loop size has been reduced by the reel mechanism, a fuel bladder stowage chamber within the fuselage, a fuel intake tube capable of drawing fuel from the fuel bladder stowed in the stowage chamber, a retraction mechanism to retract the retractable hook, a fuel transfer mechanism to transfer fuel from the fuel bladder into an internal fuel tank, and a fuel bladder discard mechanism to discard the fuel bladder after the fuel has been drawn from the fuel bladder.

    Abstract translation: 车辆加油系统包括航空车辆和燃料囊系统。 燃料囊系统包括燃料囊，预定环尺寸的拾取环，卷绕机构，用于缩回拾取环的至少一侧以减小环的尺寸;阻挡传感器，用于感测拾取环何时已被钩住 可伸缩钩，启动卷轴机构的阻塞传感器，用于感测环路的随机取向的罗盘，用于感测回路位置的无线电导航接收器，以及发送器，以发送随机取向和位置。 车辆包括机身，具有钩传感器的可伸缩钩，用于检测燃料囊何时被钩住，并且通过卷轴机构减小了环路尺寸，机身内部的燃料囊存放室，能够吸引燃料的燃料进入管 从装载在储存室中的燃料气囊，收回缩回钩的缩回机构，用于将燃料从燃料气囊输送到内部燃料箱中的燃料转移机构，以及在燃料之后废弃燃料气囊的燃料气体排出机构 已从燃油囊中抽出。

    Equipment carrying remote controlled aircraft
    347.
    发明授权
    Equipment carrying remote controlled aircraft 失效
    装备遥控飞机的设备

    公开(公告)号：US5289994A

    公开(公告)日：1994-03-01

    申请号：US855254

    申请日：1992-03-23

    Applicant: Juan Del Campo Aguilera

    Inventor： Juan Del Campo Aguilera

    IPC: B64C27/22 ,  B64C29/02 ,  B64C39/02 ,  B64C29/00

    CPC classification number: B64C27/22 ,  B64C29/02 ,  B64C39/024 ,  B64C2201/028 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165

    Abstract: It works like a helicopter in vertical flight or like an airplane in horizontal flight, being able to land accurately on a small area. It is equipped with a rotor, a couple of wings fitted with ailerons and other control surfaces actuated differentially, with support wheels at their ends. It has a vertical stabilizer at the end of which there is a wheel. It has a horizontal stabilizer with elevators that are actuated simultaneously or differentially. It incorporates a propeller ahead of the rotor.

    Abstract translation: 它像垂直飞行中的直升机一样工作，或像水平飞行中的飞机一样工作，能够在一个小区域上准确地着陆。 它配备了一个转子，一对翅膀配有副翼和其他控制面差速驱动，其支撑轮在其末端。 它有一个垂直的稳定器，其末端有一个轮子。 它具有水平稳定器，其具有同时或差异地致动的电梯。 它在转子前方装有螺旋桨。

    Tail sitter airplane
    348.
    发明授权
    Tail sitter airplane 失效
    尾部坐飞机

    公开(公告)号：US5114096A

    公开(公告)日：1992-05-19

    申请号：US558612

    申请日：1990-07-27

    Applicant: Kenneth G. Wernicke

    Inventor： Kenneth G. Wernicke

    IPC: B64C29/02 ,  B64C39/02

    CPC classification number: B64C29/02 ,  B64C39/024 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/146 ,  B64C2201/165

    Abstract: A tail sitter airplane will take off and land on its tail section, with its fuselage and nose pointed up. The airplane has a single driven propeller mounted to the nose section. Wings extend outward from the fuselage. Four airfoils locate in the tail section, two horizontal and two vertical. Each has a control surface. Four additional airfoils locate in a forward section, behind the propeller and in front of the wings. Two of the airfoils in the forward section are horizontal and two vertical. Movable control surfaces on these airfoils control the flight during takeoff and landing. The airfoils have chord lengths selected to remove the twist from the slip-stream from the propeller, thereby balancing the torque from the propeller.

    Abstract translation: 尾巴飞机将起飞并着陆在其尾部，机身和鼻子指向。 飞机上有一个驱动螺旋桨安装在鼻部。 机翼从机身向外延伸。 尾翼部分有四个翼型，两个水平和两个垂直。 每个都有一个控制面。 四个额外的翼型位于螺旋桨后面和机翼前方的前部。 前段中的两个翼型是水平的，两个垂直的。 这些翼型件上的可移动控制面在起飞和着陆期间控制飞行。 机翼具有选择的弦长以从螺旋桨的滑流中除去扭曲，从而平衡来自螺旋桨的扭矩。

    VTOL aircraft with movable undercarriage
    349.
    发明授权
    VTOL aircraft with movable undercarriage 失效
    垂直起降飞机具有可移动的底盘

    公开(公告)号：US5056737A

    公开(公告)日：1991-10-15

    申请号：US499809

    申请日：1990-03-27

    Applicant: Douglas R. Taylor

    Inventor： Douglas R. Taylor

    IPC: B64C25/66 ,  B64C29/02 ,  B64C39/02 ,  B64F1/12

    CPC classification number: B64C25/66 ,  B64C29/02 ,  B64C39/024 ,  B64F1/12 ,  B64C2201/048 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/165 ,  B64C2201/167

    Abstract: A vertical take-off and landing aircraft is configured so as to provide, when landing tail-first with its fuselage (1) in a generally vertical attitude, a touchdown area (21) at the tail of the aircraft at a position offset from a line extending along the length of the fuselage through the centre of gravity (23) of the aircraft such that after the touchdown area contacts a landing surface the aircraft topples under the action of gravity to bring an undercarriage (11, 13) of the aircraft into contact with the landing surface, thereby to attain a stable landed position.

    Abstract translation: 垂直起飞和着陆飞机被配置为当其以机身（1）以大致垂直的姿态着陆尾部时，提供在飞行器尾部处的偏移的位置处的触地区域（21） 沿着机身的长度通过飞行器的重心（23）延伸，使得在着陆区域接触着陆表面之后，飞行器在重力作用下俯仰，使飞机的起落架（11,13）进入 与着陆面接触，从而达到稳定的着陆位置。

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