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    MULTI-MODE UNMANNED AND MANNED VEHICLEL SYSTEMS AND METHODS
    142.
    发明申请
    MULTI-MODE UNMANNED AND MANNED VEHICLEL SYSTEMS AND METHODS 有权
    多模式无人驾驶和机动车辆系统及方法

    公开(公告)号：US20090045296A1

    公开(公告)日：2009-02-19

    申请号：US12135055

    申请日：2008-06-06

    Applicant: Dino A. Cerchie ,  Gregory E. Dockter ,  William Mark Hardesty

    Inventor： Dino A. Cerchie ,  Gregory E. Dockter ,  William Mark Hardesty

    IPC: B64C13/22 ,  G05D1/00

    CPC classification number: B64C39/024 ,  B64C13/22 ,  B64C13/46 ,  B64C13/50 ,  B64C2201/024 ,  B64C2201/146 ,  G05D1/0044

    Abstract: An apparatus for converting a manned aircraft of a type including at least one pilot control capable of manipulation to affect operation of the aircraft for unmanned flight operations includes first and second actuators, each configured to selectively provide movement or resistance to movement in a first manner including linear or rotational motion, first and second clutches, each configured to selectively couple movement of the associated actuator to the pilot control, and a vehicle controller capable of being selectively enabled to operate the pilot control actuators and clutches and thereby provide unmanned operation of the aircraft, or of being disabled, thereby providing for manned operation of the aircraft. The first actuator has a first scope describing a first amount of allowable movement, while the second actuator has a second scope larger than the first scope.

    Abstract translation: 一种用于转换类型的载人飞机的装置，包括能够操纵以影响飞行器的无人驾驶操作的至少一个先导控制的装置包括第一和第二致动器，每个致动器被配置为以第一方式选择性地提供对运动的运动或阻力，包括 线性或旋转运动，第一和第二离合器，每个离合器被配置为选择性地将相关联的致动器的运动耦合到先导控制器，以及车辆控制器，其能够被选择性地启用以操作先导控制致动器和离合器，从而提供飞行器的无人操作 或被禁用，从而提供飞机的载人操作。 第一致动器具有描述第一允许移动量的第一范围，而第二致动器具有大于第一范围的第二范围。

    Miniature aircraft
    143.
    发明申请
    Miniature aircraft 审中-公开
    微型飞机

    公开(公告)号：US20070012818A1

    公开(公告)日：2007-01-18

    申请号：US11202213

    申请日：2005-08-12

    Applicant: Osamu Miyazawa ,  Tsuyoshi Iwamoto

    Inventor： Osamu Miyazawa ,  Tsuyoshi Iwamoto

    IPC: B64C27/52

    CPC classification number: B64C39/028 ,  A63H27/12 ,  B64C2201/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/108 ,  B64C2201/146

    Abstract: A miniature aircraft 1 has a center axle 22, two rotors 3 and 5 provided substantially axially to the center axle 22 and capable of rotating in opposite directions, rotary wings 34 and 54 provided to the rotors 3 and 5, vibrating members 4 for rotating the rotary wings 34 and 54 via the rotors 3 and 5, and cables 471 and 472 connected to the vibrating members 4. A hollow part 221 is formed in the center axle 22 along the longitudinal direction thereof, and the cables 471 and 472 are easily positioned in the hollow part 221.

    Abstract translation: 小型飞机1具有中心轴22，两个转子3和5，其基本上轴向设置到中心轴22并能够沿相反方向旋转，设置在转子3和5上的旋转翼34和54，用于旋转 旋转翼34和54经由转子3和5以及连接到振动构件4的电缆471和472。 沿中心轴22的长度方向形成有中空部221，电缆471,472容易地定位在中空部221中。

    TAILBOOM-STABILIZED VTOL AIRCRAFT
    144.
    发明申请
    TAILBOOM-STABILIZED VTOL AIRCRAFT 失效
    TAILBOOM稳定的垂直起降飞机

    公开(公告)号：US20060032971A1

    公开(公告)日：2006-02-16

    申请号：US11042666

    申请日：2005-01-24

    Applicant: G. Baldwin

    Inventor： G. Baldwin

    IPC: B64C27/22

    CPC classification number: B64C29/02 ,  B64C29/0033 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/024 ,  B64C2201/048 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/128 ,  B64C2201/165

    Abstract: A disclosed flying craft includes a suspension structure having a first end and a second end, a lift unit, and a payload unit. The lift unit includes a nacelle and a tailboom, and pivotally couples to the first end of the suspension structure, and a payload unit couples to the structure's second end. Thus the tailboom can pivotally couple with respect to the payload unit, which advantageously permits the tailboom to assume an orientation desirable for a particular mode of flight. During vertical flight or hover, the tailboom can hang from the lift unit in an orientation that is substantially parallel to the suspension structure and that minimizes resistance to downwash from the lift unit. During horizontal flight, the tailboom can be orthogonal to the suspension structure, extending rearward in an orientation where it can develop pitching and yawing moments to control and stabilize horizontal flight. Advantageous variations and methods are also disclosed.

    Abstract translation: 公开的飞行技术包括具有第一端和第二端的悬挂结构，升降单元和有效载荷单元。 提升单元包括机舱和尾巴，并且枢转地联接到悬架结构的第一端，并且有效载荷单元耦合到结构的第二端。 因此，尾巴可以相对于有效载荷单元枢转地联接，这有利地允许尾巴呈现对于特定飞行方式所需的取向。 在垂直飞行或悬停期间，尾巴可以以与悬挂结构基本平行的方向从提升单元悬挂，并且使得抵抗来自提升单元的降洗的阻力最小化。 在水平飞行期间，尾翼可以与悬架结构正交，向后延伸，在该方向上可以产生俯仰和偏转力矩以控制和稳定水平飞行。 还公开了有利的变型和方法。

    Unmanned helicopter, takeoff method of unmanned helicopter, and landing method of unmanned helicopter
    145.
    发明申请
    Unmanned helicopter, takeoff method of unmanned helicopter, and landing method of unmanned helicopter 有权
    无人直升机，无人直升机起飞方式，无人直升机着陆方式

    公开(公告)号：US20040075018A1

    公开(公告)日：2004-04-22

    申请号：US10679984

    申请日：2003-10-06

    Applicant: Fuji Jukogyo Kabushiki Kaisha

    Inventor： Akihiro Yamane

    IPC: B64C011/34 ,  B64C011/44 ,  B64C027/54

    CPC classification number: B64C13/20 ,  B64C39/024 ,  B64C2201/024 ,  B64C2201/108 ,  B64C2201/141 ,  B64C2201/165 ,  G05D1/0669 ,  G05D1/0676

    Abstract: An unmanned helicopter 20 includes altitude control device for giving a command of a collective pitch rudder angle based on an altitude change rate command, etc., and performing altitude control of an airframe and takeoff device, upon reception of a takeoff start command from the ground, for causing the airframe to take off and climbing the airframe to a first altitude while increasing the collective pitch rudder angle without performing the altitude control of the altitude control device and then causing the altitude control device to start the altitude control. The unmanned helicopter further includes descending device for causing the airframe to descend to a second altitude while changing descent rate command of the altitude control device and giving a descent rate command smaller than the descent rate command to the second altitude to the altitude control device for causing the airframe to descend from the second altitude to the ground.

    Abstract translation: 无人直升机20包括高度控制装置，用于基于高度变化率命令等给出集体俯仰舵角的命令，并且在从地面接收到起飞开始命令时执行机体和起飞装置的高度控制 用于使机身在不进行高度控制装置的高度控制的同时增加集体桨距方向舵角度使机身起飞并爬升到第一高度，然后使高度控制装置开始高度控制。 无人直升机进一步包括下降装置，用于使机身下降到第二高度，同时改变高度控制装置的下降速率指令，并将低于下降速率指令的下降率指令提供给第二高度，以向高度控制装置引起 机身从第二高度下降到地面。

    Atmospheric autorotating imaging device
    146.
    发明授权
    Atmospheric autorotating imaging device 失效
    大气自动成像装置

    公开(公告)号：US4886222A

    公开(公告)日：1989-12-12

    申请号：US205899

    申请日：1988-06-13

    Applicant: James D. Burke

    Inventor： James D. Burke

    IPC: B64C11/00 ,  B64D47/08 ,  H04N7/00

    CPC classification number: B64C39/024 ,  B64C11/00 ,  B64D47/08 ,  H04N7/002 ,  B64C2201/024 ,  B64C2201/127 ,  B64C2201/141

    Abstract: An imaging device that automatically rotates upon descent through an atmosphere provides an onboard image detector a sweeping panoramic scan as it descends. No moving parts or propulsion system are required. The location, angle and pitch of the winged structure, together with its inertia properties, passively induces rotation. The angled location of the image detector takes advantage of the resulting rotation. Data generated by the image detector may be transmitted to a remote receiver or, alternatively, stored for subsequent recovery.

    Abstract translation: 随着气氛下降而自动旋转的成像装置为车载图像检测器下降时扫描全景扫描。 不需要移动部件或推进系统。 翼形结构的位置，角度和间距及其惯性特性被动地引起旋转。 图像检测器的倾斜位置利用所得到的旋转。 由图像检测器产生的数据可以被发送到远程接收器，或者替代地存储以用于随后的恢复。

    Helicopter target
    147.
    发明授权
    Helicopter target 失效
    直升机目标

    公开(公告)号：US4765567A

    公开(公告)日：1988-08-23

    申请号：US24039

    申请日：1987-03-10

    Applicant: Meyer M. Gutman ,  Christopher N. Lash

    Inventor： Meyer M. Gutman ,  Christopher N. Lash

    IPC: B64C27/02 ,  B64C39/02

    CPC classification number: B64C39/024 ,  B64C27/02 ,  B64C2201/024 ,  B64C2201/108 ,  B64C2201/121 ,  B64C2201/146

    Abstract: A remote-controlled autogyro visually and functionally simulates a helicopter with stub wings (e.g. the Hind D), so that an expendable helicopter-simulating target is produced. The target has a fixed angle rotor shaft, the rotor being solely aerodynamically controlled. The rotor blades have a negative pitch angle, and a positive conning angle. The engine is mounted at the front of the fuselage and has a downthrust angle, and the horizontal stabilizer also slopes downwardly aft. The rotor is at about the center of lift (horizontally) of the wings, and the wing span is about 50-60 percent the length of the fuselage. The ailerons and tail rudder are electrically interconnected. Remote control is provided for the elevators ailerons, and engine speed.

    Abstract translation: 视觉上和功能上模拟具有短截翼（例如Hind D）的直升机的远程控制自动扶梯，从而产生消耗性直升机模拟目标。 目标具有固定角度的转子轴，转子仅在空气动力学上被控制。 转子叶片具有负桨距角和正转角。 发动机安装在机身前部，具有推力角，水平稳定器也向下倾斜。 转子位于机翼的升降中心（水平）的左右，机翼的跨度约为机身长度的50-60％。 副翼和尾舵电气互连。 为电梯副翼提供遥控和发动机转速。

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