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    Methods and apparatuses for launching unmanned aircraft, including releasably gripping aircraft during launch and braking subsequent grip motion
    301.
    发明申请
    Methods and apparatuses for launching unmanned aircraft, including releasably gripping aircraft during launch and braking subsequent grip motion 有权
    用于发射无人机的方法和装置，包括在发射期间可释放地夹持飞行器并制动随后的抓地力

    公开(公告)号：US20050178895A1

    公开(公告)日：2005-08-18

    申请号：US10808725

    申请日：2004-03-24

    Applicant: Brian McGeer ,  Andreas von Flotow ,  Cory Roeseler

    Inventor： Brian McGeer ,  Andreas von Flotow ,  Cory Roeseler

    IPC: B64C3/56 ,  B64F1/06

    CPC classification number: B64F1/06 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/084 ,  B64C2201/104 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/165

    Abstract: Methods and apparatuses for launching unmanned aircraft and other flight devices or projectiles are described. In one embodiment, the aircraft can be launched from an apparatus that includes a launch carriage that moves along a launch guide. The carriage can accelerate when portions of the carriage and/or the launch guide move relative to each other. A gripper carried by the launch carriage can have at least one grip portion in contact with the aircraft while the launch carriage accelerates along the launch axis. The at least one grip portion can move out of contact with the aircraft as the launch carriage decelerates, releasing the aircraft for takeoff. A brake can arrest the motion of the gripper after launch.

    Abstract translation: 描述了发射无人机和其他飞行装置或射弹的方法和装置。 在一个实施例中，飞行器可以从包括沿发射导向装置移动的发射台的装置发射。 当滑架和/或发射引导件的部分相对于彼此移动时，托架可以加速。 由发射托架携带的夹具可以具有至少一个与飞行器接触的抓握部分，同时发射托架沿着发射轴加速。 当发射架减速时，至少一个把手部分可以与飞行器脱离接触，释放飞机起飞。 制动器可以在发射后阻止夹具的运动。

    Launch and recovery system for unmanned aerial vehicles
    305.
    发明申请
    Launch and recovery system for unmanned aerial vehicles 有权
    无人机的发射和恢复系统

    公开(公告)号：US20050017129A1

    公开(公告)日：2005-01-27

    申请号：US10754251

    申请日：2004-01-09

    Applicant: William McDonnell

    Inventor： William McDonnell

    IPC: B64C25/68 ,  B64C39/02 ,  B64D3/00 ,  B64F1/02 ,  B64F1/04 ,  B64F1/10

    CPC classification number: B64F1/02 ,  B64C25/68 ,  B64C39/024 ,  B64C2201/084 ,  B64C2201/104 ,  B64C2201/165 ,  B64C2201/182 ,  B64C2201/205 ,  B64D3/00 ,  B64F1/04 ,  B64F1/10

    Abstract: A method of launching and retrieving a UAV (Unmanned Aerial Vehicle) (10). The preferred method of launch involves carrying the UAV (10) up to altitude using a parasail (8) similar to that used to carry tourists aloft. The UAV is dropped and picks up enough airspeed in the dive to perform a pull-up into level controlled flight. The preferred method of recovery is for the UAV to fly into and latch onto the parasail tow line (4) or cables hanging off the tow line and then be winched back down to the boat (2).

    Abstract translation: 一种发射和检索无人机（无人机）的方法（10）。 优选的发射方法是将UAV（10）运送到高度，使用类似于用来搭载高层游客的伞（8）。 无人机被丢弃，并在潜水中获得足够的空速，执行上升到等级控制飞行。 回收的首选方法是使UAV飞入并锁定在悬挂拖线（4）上或悬挂在拖绳上的电缆，然后被绞盘回到船（2）。

    Transformable gun launched aero vehicle
    306.
    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。

    Unmanned craft
    307.
    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。

    DEVICE WHEREBY AN AIRCRAFT CAN LAND ON WATER
    309.
    发明公开
    DEVICE WHEREBY AN AIRCRAFT CAN LAND ON WATER 审中-公开
    VORRICHTUNG ZURERMÖGLICHUNGDER LANDUNG EINES FLUGZEUGES AUF WASSER

    公开(公告)号：EP3135583A1

    公开(公告)日：2017-03-01

    申请号：EP11761644.1

    申请日：2011-06-20

    Applicant: Wake Engineering, S.L.

    Inventor： TURRILLAS LAS HERAS, Arturo

    IPC: B64C25/56 ,  B64C35/00

    CPC classification number: B64C25/56 ,  B64C35/00 ,  B64C2201/028 ,  B64C2201/044 ,  B64C2201/084 ,  B64C2201/123 ,  B64D2241/00

    Abstract: The device comprises at least one folding, inflatable chamber (3), at least one runner (4) for landing on water, which is coupled to the aircraft (2) by means of the chamber (3), and at least one air intake (6) connected to the chamber. The intake (6) allows the entry of incident air into the chamber (3) in order to inflate and deploy the chamber (3), extending the runner (4) from a retracted-runner position into an extended-runner position

    Abstract translation: 该装置包括至少一个折叠的可充气室（3），至少一个用于着陆在水面上的流道（4），其通过腔室（3）联接到飞行器（2），并且至少一个进气口 （6）连接到腔室。 入口（6）允许入口空气进入腔室（3），以便使空腔（3）膨胀和展开，从而将流道（4）从缩回流道位置延伸到延伸流道位置

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