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    Cable connections between an unmanned aircraft and a detachable data handling module
    141.
    发明授权
    Cable connections between an unmanned aircraft and a detachable data handling module 失效
    无人机与可拆卸数据处理模块之间的电缆连接

    公开(公告)号：US06615165B2

    公开(公告)日：2003-09-02

    申请号：US10255187

    申请日：2002-09-26

    Applicant: Ernest A. Carroll

    Inventor： Ernest A. Carroll

    IPC: B64C100

    CPC classification number: F02D41/2406 ,  B64C39/024 ,  B64C39/028 ,  B64C2201/044 ,  B64C2201/104 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  F02B75/34 ,  F02D35/0069 ,  F02D2200/0414 ,  F02D2200/703 ,  F02D2400/06 ,  F02D2400/11 ,  G05D1/101

    Abstract: A power and communications connection arrangement for a miniature, unmanned aircraft having data handling capability. The aircraft has a microprocessor for managing flight control, a GPS receiver, a communications radio frequency transceiver, and data handling apparatus. The latter may be any of a sensor for gathering environmental data, sensing aircraft altitude or attitude, a data relay station, or any combination of these. The data handling apparatus is part of a removable module mounted to and detachable from the aircraft. The connection arrangement includes stationary power and communications terminals fixed to the module, and corresponding free power and data cables completing respective power circuits and communications links within the aircraft. In the preferred embodiment, the microprocessor, at least one sensor, and a battery pack are located in the module, and a radio transceiver, a GPS receiver, controls such as rudder and elevator, and other sensors are located in the airframe.

    Abstract translation: 一种用于具有数据处理能力的微型无人飞机的电力和通信连接装置。 飞机具有用于管理飞行控制的微处理器，GPS接收器，通信射频收发器和数据处理装置。 后者可以是用于收集环境数据，感测飞机高度或姿态，数据中继站或这些的任何组合的传感器中的任何一个。 数据处理装置是安装到飞机上并可拆卸的可拆卸模块的一部分。 连接装置包括固定电源和固定到模块的通信终端，以及相应的空闲电源和数据电缆，完成飞机内各自的电力电路和通信链路。 在优选实施例中，微处理器，至少一个传感器和电池组位于模块中，并且无线电收发器，GPS接收器，诸如方向舵和电梯以及其它传感器的控制器位于机身中。

    Transformable gun launched aero vehicle
    142.
    发明授权
    Transformable gun launched aero vehicle 有权
    可变形枪发射航空车

    公开(公告)号：US06260797B1

    公开(公告)日：2001-07-17

    申请号：US09229599

    申请日：1999-01-13

    Applicant: Miles R. Palmer

    Inventor： Miles R. Palmer

    IPC: B64C356

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

    Abstract: A transformable gun launched aero vehicle having a ballistic projectile configuration and an aeroplane configuration includes a cylinder forming a shell of the vehicle in the ballistic projectile configuration and wings deployable from the cylinder. The wings are capable of achieving sufficient lift for sustained flight in the aeroplane configuration. The cylinder forms a fuselage of the vehicle in the aeroplane configuration. A wing includes plural rib elements, plural inflatable tubes where each tube is braced by the plural rib elements, and a wind shell disposed around the plural inflatable tubes and the plural rib elements. The vehicle includes an inflatable tail section that is inflated while the vehicle is in the aeroplane configuration. The vehicle includes a parachute that is reversibly deployable from a nose portion of the vehicle. The vehicle includes at least one landing rod. Each landing rod is reversibly extendable from the vehicle. A landing controller controls a first landing rod to extend after the vehicle has begun to vertically descend. The vehicle includes a folding propeller deployable from the fuselage in the aeroplane configuration. The vehicle includes a control system, and the control system includes a module to determine when the vehicle has reached a first predetermined state that defines an initiation of a transition from the ballistic projectile configuration to the aeroplane configuration.

    Abstract translation: 可变形枪发射具有弹道射弹配置的航空车辆，并且飞机配置包括形成弹道射出构造的车辆壳体的气缸和从气缸展开的翼。 机翼能够在飞机配置中实现足够的升力以持续飞行。 汽缸在飞机配置中形成车辆的机身。 翼包括多个肋元件，多个可充气管，其中每个管由多个肋元件支撑，以及设置在多个可充气管和多个肋元件周围的风壳。 车辆包括在车辆处于飞机配置中时充气的可充气尾部。 车辆包括可从车辆的鼻部部分可逆地展开的降落伞。 车辆包括至少一个着陆杆。 每个着陆杆可从车辆可逆地延伸。 着陆控制器控制第一着陆杆在车辆开始垂直下降之后延伸。 该车辆包括在飞机配置中可从机身部署的折叠螺旋桨。 车辆包括控制系统，并且控制系统包括用于确定车辆何时已经达到第一预定状态的模块，该第一预定状态定义了从弹道射弹配置到飞机配置的转变的开始。

    Rotor blade subassembly for a rotor assembly having ducted, coaxial counter-rotating rotors
    143.
    发明授权
    Rotor blade subassembly for a rotor assembly having ducted, coaxial counter-rotating rotors 失效
    用于转子组件的转子叶片子组件具有导管的同轴的反向旋转转子

    公开(公告)号：US5364230A

    公开(公告)日：1994-11-15

    申请号：US903061

    申请日：1992-06-22

    Applicant: Timothy A. Krauss ,  David H. Hunter ,  Robert D. Beatty

    Inventor： Timothy A. Krauss ,  David H. Hunter ,  Robert D. Beatty

    IPC: B64C27/10 ,  B64C27/12 ,  B64C27/20 ,  B64C27/33 ,  B64C27/46 ,  B64C27/605 ,  B64C39/02 ,  F02B75/02

    CPC classification number: B64C27/605 ,  B64C27/20 ,  B64C27/33 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/044 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/162 ,  F02B2075/025

    Abstract: A rotor blade subassembly for a rotor assembly having ducted, coaxial counter-rotating rotors includes a flexbeam, an integrated torque tube/spar member, and an aerodynamic fairing or rotor blade. The flexbeam is a laminated composite structure that reacts centrifugal loads and a majority of the bending loads of the rotor assembly. The flexbeam has a spanwise predetermined linear twist so that the pretwisted flexbeam is unstrained during specified forward flight conditions. The integrated torque tube/spar member is formed as a continuous, filament wound tubular composite structure having high torsional and bending stiffness that provides a continuous torsional load path and facilitates load coupling between the rotor blade and the pretwisted flexbeam. The spar segment of the functions as the primary structural member of the rotor blade subassembly and, is operative to react all bending, torsional, shear, and centrifugal dynamic loads of the rotor assembly. The torque tube segment reacts all torsional loads and some of the bending loads of the rotor assembly. The rotor blade is fabricated from a high modulus composite material and has a high aerodynamic taper such that the tapered rotor blade has a low outboard mass, a high inboard stiffness, and a high chordwise frequency. The high chordwise frequency allows the rotor assembly to be operated over a weaker modal response zone. The tapered rotor blade includes a triangularly shaped trailing edge segment that is responsive to the aerodynamic pressures encountered during operation of the shrouded counter-rotating rotors.

    Abstract translation: 具有导管的同轴反转转子的转子组件的转子叶片子组件包括柔性梁，集成的扭矩管/翼梁构件和空气动力学整流罩或转子叶片。 柔性梁是一种叠层复合结构，可使离心载荷和转子组件的大部分弯曲载荷反应。 柔性梁具有翼展方向预定的线性扭曲，使得预弯曲的柔性梁在指定的向前飞行条件下是不受约束的。 集成的扭矩管/翼梁构件形成为具有高扭转和弯曲刚度的连续的长丝缠绕管状复合结构，其提供连续的扭转载荷路径并且有助于转子叶片和预扭曲挠曲梁之间的负载耦合。 作为转子叶片子组件的主要结构构件的功能的翼梁段，可操作以对转子组件的所有弯曲，扭转，剪切和离心动态载荷作出反应。 扭矩管段对转子组件的所有扭转载荷和一些弯曲载荷作出反应。 转子叶片由高模量复合材料制成并且具有高空气动力学锥度，使得锥形转子叶片具有低的外侧质量，高的内侧刚度和高的弦向频率。 高弦弦频率允许转子组件在较弱的模态响应区域上运行。 锥形转子叶片包括三角形的后缘段，其响应于在遮蔽的反向旋转转子的操作期间遇到的空气动力学压力。

    Missile with highly backswept wing unit, in particular with delta wings
    145.
    发明授权
    Missile with highly backswept wing unit, in particular with delta wings 失效
    导弹与高度后卫的翼单位，特别是三角翼

    公开(公告)号：US4601442A

    公开(公告)日：1986-07-22

    申请号：US545083

    申请日：1983-10-25

    Applicant: Franz Friedel ,  Werner Fruhauf ,  Gunter Harms ,  Georg Heise ,  Heinrich Lukewille

    Inventor： Franz Friedel ,  Werner Fruhauf ,  Gunter Harms ,  Georg Heise ,  Heinrich Lukewille

    IPC: B64C39/02 ,  F16D7/02 ,  F42B10/64 ,  F42B15/10 ,  F42B15/02

    CPC classification number: F42B10/64 ,  B64C39/024 ,  F16D7/021 ,  F42B15/105 ,  B64C2201/028 ,  B64C2201/044 ,  B64C2201/165 ,  B64C2201/201

    Abstract: Unmanned missile with strongly backswept wing unit, in particular delta wings, which is transported in a container and is launched from the container by means of an auxiliary drive after release of a lock, and which during cruise flight is drivable by a propeller engine, lateral force surfaces (25) being deployable for stabilization of the missile during cruise flight, from retraction spaces (26) in the region of the wing root of the delta wings, and further a friction clutch (64, 65) is provided at the missile which, without supply of energy from the outside, couples the standing propeller 6 with the drive motor (7) running in the container, after leaving the container.

    Abstract translation: 具有强力后卫的翼单元，特别是三角翼的无人驾驶导弹，其在集装箱中运输并且在释放锁之后通过辅助驱动从容器发射，并且在巡航飞行期间由螺旋桨发动机驱动，横向 力表面（25）可展开用于在巡航飞行期间稳定导弹，来自三角翼机翼根部区域中的缩回空间（26），并且在该导弹处提供摩擦离合器（64,65） 在没有从外部供应能量的情况下，在离开容器之后将立式螺旋桨6与在容器中运行的驱动马达（7）相耦合。

    Unmanned remotely piloted aircraft
    146.
    发明授权
    Unmanned remotely piloted aircraft 失效
    无人驾驶飞机

    公开(公告)号：US4478379A

    公开(公告)日：1984-10-23

    申请号：US545609

    申请日：1983-10-27

    Applicant: John P. Kerr

    Inventor： John P. Kerr

    IPC: B64C27/10 ,  B64C39/02

    CPC classification number: B64C27/10 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/108 ,  B64C2201/146 ,  B64C2201/148 ,  B64C2201/165 ,  B64C2201/22

    Abstract: An unmanned aircraft of the remotely piloted type that is characterized by its configuration and outline using rigid counter rotating propellers, positioned substantially at the height of its center of mass or slightly below to allow producing a sufficiently large control moment to use a tether line for landing the aircraft and to allow using two substantially spheroidal surfaces at the top and bottom respectively rather than a single one relatively larger and more detectable surface as when the propellers are at the top.

    Abstract translation: 一种遥控飞行器类型的无人驾驶飞机的特点是其配置和轮廓使用刚性的反向旋转螺旋桨，其基本上位于其质心或稍低于其高度的高度，以便产生足够大的控制力矩以使用系绳进行着陆 并且允许在顶部和底部分别使用两个基本上球形的表面，而不是当螺旋桨在顶部时相对较大和更可检测的表面。

    AIRCRAFT AND FLIGHT SYSTEM
    148.
    发明申请
    AIRCRAFT AND FLIGHT SYSTEM 审中-公开

    公开(公告)号：US20180265191A1

    公开(公告)日：2018-09-20

    申请号：US15921881

    申请日：2018-03-15

    Applicant: Hideomi SAKUMA

    Inventor： Hideomi SAKUMA

    IPC: B64C29/02 ,  B64C39/02 ,  G05D1/08

    CPC classification number: B64C29/02 ,  B64C11/46 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/146 ,  B64C2201/165 ,  G05D1/0808

    Abstract: An aircraft includes propellers at a center of the airframe; a first power source; a pitch adjuster to change pitch angles of the propellers; a plurality of attitude control propellers; a second power source lower in output than the first power source; and a control circuit to control attitude of the airframe. The control circuit includes a first yaw rotation generation control unit to control first yaw rotation generated by torques of the propellers with the pitch adjuster; and a second yaw rotation generation control unit to control a second yaw rotation generated by torques generated by a difference in rotation speed between the attitude control propellers. The control circuit is configured to control the first yaw rotation generation control unit and the second yaw rotation generation control unit in accordance with a magnitude of a command value of yaw rotation.

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