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    Immersible unmanned air vehicle and system for launch, recovery, and re-launch at sea
    51.
    发明申请
    Immersible unmanned air vehicle and system for launch, recovery, and re-launch at sea 失效
    潜艇无人机和发射，恢复和重新发射的系统

    公开(公告)号：US20050230535A1

    公开(公告)日：2005-10-20

    申请号：US10823434

    申请日：2004-04-13

    Applicant: Robert Ruszkowski

    Inventor： Robert Ruszkowski

    IPC: B63G8/28 ,  B63G8/30 ,  B63G13/00 ,  B64C1/00 ,  B64C1/06 ,  B64C35/00 ,  B64C37/00 ,  B64C39/00 ,  B64C39/02 ,  F41F3/07 ,  F42B15/20

    CPC classification number: B64C1/062 ,  B63G8/28 ,  B63G8/30 ,  B63G13/00 ,  B64C35/00 ,  B64C37/00 ,  B64C39/024 ,  B64C2001/0045 ,  B64C2201/048 ,  B64C2201/084 ,  B64C2201/121 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/205 ,  F41F3/07 ,  F42B15/20

    Abstract: A sea-launched and recovered unmanned aircraft is disclosed. The aircraft is jet-powered and has features and systems to maintain watertight integrity such that it may be released from a submerged submarine or dropped into a body of water by a ship or an aircraft. The aircraft is buoyant and remains at or near the water surface before its rockets are ignited. The rockets propel the air vehicle out of the sea and accelerate it to flying speed at which time a jet engine is started and the rockets are jettisoned. The air vehicle performs its mission independently or in conjunction with other ones of the air vehicles. The air vehicle then returns to an assigned splashdown point at sea via, for example, an engine-off “whip-stall” maneuver. A submarine or ship may retrieve the air vehicle and readies it for another mission.

    Abstract translation: 披露了一架海上发射和回收的无人机。 飞机是喷气式动力的，并具有保持水密完整性的特征和系统，使得其可以从潜水艇释放或由船或飞机落入水体。 这架飞机是浮力的，并且在其火箭点火之前保持在水面或附近。 火箭将空中车辆推出大海，并将其加速到飞行速度，此时喷气发动机起动，火箭被放弃。 机动车辆独立地或与其他机动车辆一起执行任务。 然后，空中飞行器通过例如发动机关闭“鞭炮”操纵返回到海上指定的飞溅点。 潜艇或船只可以检索空中飞行器并准备进行另一个飞行任务。

    Methods and apparatuses for launching airborne devices along flexible elongated members
    52.
    发明申请
    Methods and apparatuses for launching airborne devices along flexible elongated members 有权
    沿着柔性细长构件发射机载装置的方法和装置

    公开(公告)号：US20050189450A1

    公开(公告)日：2005-09-01

    申请号：US10813906

    申请日：2004-03-31

    Applicant: Cory Roeseler ,  Brian McGeer ,  Andreas von Flotow

    Inventor： Cory Roeseler ,  Brian McGeer ,  Andreas von Flotow

    IPC: B64C39/02 ,  B64F20060101 ,  B64F1/04

    CPC classification number: B64C39/024 ,  B64C2201/084

    Abstract: Methods and apparatuses for cable launching airborne devices (e.g., unmanned aircraft) are disclosed. In one embodiment, an apparatus includes an elongated structure, e.g., a tower, boom or derrick. At least one flexible elongated member (e.g., a cable or rope) can be attached toward one end to the structure and toward another end to the ground or another structure to form an elongated launch path. A cradle, which can carry the airborne device, can also be movably attached to the flexible elongated member and can be accelerated along the launch path. As the cradle decelerates, the aircraft can be released into flight.

    Abstract translation: 公开了用于电缆发射机载装置（例如，无人飞行器）的方法和装置。 在一个实施例中，装置包括细长结构，例如塔架，起重臂或井架。 至少一个柔性细长构件（例如，电缆或绳索）可以朝向结构的一端并且朝向地面或另一结构的另一端附接以形成细长的发射路径。 可以携带机载装置的托架也可以可移动地附接到柔性细长构件并且可以沿着发射路径被加速。 当支架减速时，飞机可以释放飞行。

    Methods and apparatuses for capturing and recovering unmanned aircraft, including a cleat for capturing aircraft on a line
    56.
    发明申请
    Methods and apparatuses for capturing and recovering unmanned aircraft, including a cleat for capturing aircraft on a line 有权
    用于捕获和恢复无人机的方法和装置，包括用于在线上捕获飞机的防滑板

    公开(公告)号：US20040232282A1

    公开(公告)日：2004-11-25

    申请号：US10758940

    申请日：2004-01-16

    Inventor： Brian D. Dennis

    IPC: B64C037/00

    CPC classification number: B64F1/06 ,  B63B27/26 ,  B64C39/024 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/182 ,  B64C2201/201 ,  B64F1/04

    Abstract: Methods and apparatuses for capturing and recovering unmanned aircraft and other flight devices or projectiles are described. In one embodiment, the aircraft can be captured by a recovery line in flight, a process that can be aided by a line capture device having a retainer with two portions spaced apart by a distance great enough to receive the recovery line, e.g., to capture the recovery line with increased security. The line capture device can be operatively mounted on a lifting surface of the aircraft.

    Abstract translation: 描述了用于捕获和恢复无人驾驶飞机和其他飞行装置或射弹的方法和装置。 在一个实施例中，飞行器可以由飞行中的恢复线捕获，该过程可以由具有保持器的线捕获装置辅助，该保持器具有两个间隔开足够大的距离以接收恢复线，例如捕获 恢复线增加了安全性。 线捕获装置可以可操作地安装在飞行器的提升表面上。

    Thrust vectoring free wing aircraft
    57.
    发明授权
    Thrust vectoring free wing aircraft 失效
    推力矢量自由翼飞机

    公开(公告)号：US5340057A

    公开(公告)日：1994-08-23

    申请号：US850913

    申请日：1992-03-13

    Applicant: Hugh Schmittle

    Inventor： Hugh Schmittle

    IPC: B64C3/38 ,  B64C29/00 ,  B64C29/02 ,  B64C39/02 ,  B64C39/04

    CPC classification number: B64C39/024 ,  B64C29/0033 ,  B64C29/02 ,  B64C3/385 ,  B64C39/04 ,  B64C2201/044 ,  B64C2201/046 ,  B64C2201/084 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/182 ,  B64D2201/00

    Abstract: The VTOL aircraft includes a free wing having wings on opposite sides of the fuselage connected to one another for joint free rotation and for differential pitch settings under pilot, computer or remote control. On vertical launch, pitch, yaw and roll control is effected by the elevators, rudder and the differential pitch settings of the wings, respectively. At launch, the elevator pitches the fuselage nose downwardly to alter the thrust vector and provide horizontal speed to the aircraft whereby the free wing freely rotates relative to the fuselage into a generally horizontal orientation to provide lift during horizontal flight. Transition from horizontal to vertical flight is achieved by the reverse process and tile aircraft may be gently recovered in or on a resilient surface such as a net.

    Abstract translation: 垂直起落架飞机包括一个自由翼，在机身的相对两侧具有彼此连接的翼，用于联合自由旋转，并在飞行员，计算机或遥控器下进行差距俯仰设置。 在垂直发射时，俯仰，偏航和侧倾控制分别由电梯，方向舵和翼的差距俯仰设置来实现。 在发射时，升降机将机身鼻部向下倾斜以改变推力矢量并向飞行器提供水平速度，由此自由翼相对于机身自由旋转成大致水平的方向以在水平飞行期间提供升力。 从水平飞行到垂直飞行的过渡是通过相反的过程实现的，瓦片飞机可以在诸如网络的弹性表面中或其上轻轻地回收。

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