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    Missile with highly backswept wing unit, in particular with delta wings
    91.
    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
    92.
    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。

    Unmanned craft
    93.
    发明授权
    Unmanned craft 失效
    无人工艺

    公开(公告)号：US4410151A

    公开(公告)日：1983-10-18

    申请号：US182021

    申请日：1980-08-28

    Applicant: Heinz-Jochen Hoppner ,  Ulrich Kramer ,  Hugo Sgarz ,  Herbert Sadowski

    Inventor： Heinz-Jochen Hoppner ,  Ulrich Kramer ,  Hugo Sgarz ,  Herbert Sadowski

    IPC: B64C39/02 ,  F42B10/14 ,  B64F1/04 ,  F41F3/00

    CPC classification number: B64C39/024 ,  F42B10/14 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/165 ,  B64C2201/201 ,  B64C2201/208

    Abstract: A vehicle or craft is provided for propeller propulsion with start assist by a releasable rocket engine. The craft is launched from a silo of square-shaped cross-section containing the starter motor for the propeller, whose engine is started while the craft is still in the silo. Diagonally opposed corners of the silo are provided with rails, in which run guides on rudder fins of the craft. The wings are pivoted to the fuselage for deployment whereby the wing tips do not move forward. The rocket engine is jettisoned shortly after take-off by simple disengagement. Parts of the wings and/or the rear of the fuselage may be jettisoned shortly before the craft reaches the target area.

    Abstract translation: 提供用于螺旋桨推进的车辆或工具，由可释放的火箭发动机开始辅助。 该工艺是从一个方形截面的筒仓中推出的，包含用于螺旋桨的起动电机，当发动机仍然在筒仓中时，发动机起动。 筒仓的对角线相对的角落设有导轨，其中在工艺的方向舵鳍上的行进导轨。 机翼枢转到机身进行部署，由此机翼尖端不向前移动。 火箭发动机在起飞后不久就被简单的分离。 机翼的部分和/或机身的后部可能在飞机到达目标区域之前不久就被抛弃。

    Optimally Stabilized Multi Rotor Aircraft
    96.
    发明申请
    Optimally Stabilized Multi Rotor Aircraft 审中-公开

    公开(公告)号：US20190193840A1

    公开(公告)日：2019-06-27

    申请号：US16268825

    申请日：2019-02-06

    Applicant: Stephen Burtt ,  Jim Campbell ,  Lawrence Dennis

    Inventor： Stephen Burtt ,  Jim Campbell ,  Lawrence Dennis

    IPC: B64C17/06 ,  B64C39/02

    CPC classification number: B64C17/06 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/108 ,  B64C2201/165

    Abstract: A multi horizontal rotor drone having a propulsion unit coupled to a payload housing by a multi-axial gimbal assembly. The centers of mass of each of these three components resides at a common point that also coincides with the pitch and roll axes (and optionally the yaw axis) of the gimbal assembly's rotational orientations. The propulsion unit has the minimal operational mass necessary while the majority of the drone's mass is located onto the payload housing. With this arrangement, the payload housing can be stabilized on its center of gravity independent of the roll, pitch and yaw changes undergoing by the propulsion unit, during the drone's flight.

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