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    In-flight loadable and refuelable unmanned aircraft system for continuous flight
    51.
    发明授权
    In-flight loadable and refuelable unmanned aircraft system for continuous flight 失效

    公开(公告)号：US06540179B2

    公开(公告)日：2003-04-01

    申请号：US09738227

    申请日：2000-12-15

    Applicant: J. Kirston Henderson

    Inventor： J. Kirston Henderson

    IPC: B64D3700

    CPC classification number: B64C39/024 ,  B64C2201/082 ,  B64C2201/104 ,  B64C2201/121 ,  B64C2201/123 ,  B64C2201/126 ,  B64C2201/127 ,  B64C2201/128 ,  B64C2201/146 ,  B64D5/00 ,  B64D39/00

    Abstract: A method for refueling and reloading an unmanned aircraft for continuous flight is disclosed herein wherein the unmanned aircraft is maintained and supported by a support aircraft. Both aircraft maintain cargo bays and in-flight operable doors located on the underside of each aircraft for the purposes of docking and exchanging goods. Preferably the goods comprise loadable cartridges and may contain such items as weapons, cargo, or fuel for example. In one embodiment, when both aircraft are in a docked configuration for exchange of goods during flight, the in-flight operable doors open and the support aircraft is capable of loading such cartridges aboard the unmanned aircraft. When necessary the support aircraft may load gear for the purposes of landing the unmanned aircraft. Alternate methods of reloading an unmanned aircraft for continuous flight is disclosed wherein the unmanned aircraft does not have cargo bay doors and the aircraft is supported by a support aircraft.

    Sonotube compatible unmanned aerial vehicle and system
    52.
    发明授权
    Sonotube compatible unmanned aerial vehicle and system 失效
    Sonotube兼容无人机和系统

    公开(公告)号：US6056237A

    公开(公告)日：2000-05-02

    申请号：US882368

    申请日：1997-06-25

    Applicant: Richard L. K. Woodland

    Inventor： Richard L. K. Woodland

    IPC: B64C3/40 ,  B64C3/56 ,  B64C5/12 ,  B64C39/02 ,  B64D1/02 ,  B64D7/08 ,  B64D33/02 ,  F41G3/02 ,  F42B12/36 ,  F42B15/10 ,  F41G7/00 ,  B64C1/00

    CPC classification number: B64C3/40 ,  B64C3/56 ,  B64C39/024 ,  B64C5/12 ,  B64D1/02 ,  B64D33/02 ,  B64D7/08 ,  F41G3/02 ,  F42B12/365 ,  F42B15/105 ,  F42B15/22 ,  B64C2201/046 ,  B64C2201/048 ,  B64C2201/082 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/121 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/167 ,  B64C2201/185 ,  B64C2201/203 ,  Y02T50/145

    Abstract: The present invention is generally comprised of a sonotube-compatible unmanned aerial vehicle apparatus, hereinafter referred to as a UAV, and systems for launch and control of the UAV. The UAV is generally comprised of modular sections including a nose section, a payload section, a wing and fuel tank section, and a powerplant section. The modular sections are attached to adjacent sections by uniform lock sealing rings and related components. The present invention comprises an apparatus enabling very small, man portable, ballistically launched, autonomously or semi-autonomously controlled vehicle to be deployed with preprogrammed, communicated, or telemetry mission programming. A wide range of payload packages, including emergency supplies, sensors, and antenna assemblies, may be carried, used or deployed in flight. Man-portable operation is accomplished by the use of a launch canister apparatus. The launch canister comprises retractable launch stabilizing legs, turbine engine exhaust orifices, and various antennas. The launch canister apparatus alternatively comprises a modified type "A", "B", or "C" sonotube launch canister. The system of the invention also comprises a portable Command, Control, Communications, Computer, and Intelligence (C4I) control and sensing analysis console. The console is preferably ruggedized, waterproof, shockproof, and comprises necessary control and analysis computers, input/output devices, antennas, and related hardware and software for vehicle and mission control. A C4I console and/or launch canisters may be transported by means of a backpack adapted for man portability.

    Abstract translation: 本发明通常由声纳管相容的无人驾驶飞行器装置（以下称为无人机）和用于发射和控制无人机的系统组成。 无人机通常包括模块化部分，包括鼻部，有效载荷部分，机翼和燃料箱部分以及动力装置部分。 模块化部分通过均匀的锁定密封环和相关部件连接到相邻部分。 本发明包括一种能够进行预编程，通信或遥测任务编程的非常小的，便携式的，弹道发射的，自主的或半自主控制的车辆的装置。 可以在飞行中携带，使用或部署各种有效载荷包，包括应急用品，传感器和天线组件。 便携式操作通过使用发射罐装置来实现。 发射罐包括可伸缩发射稳定腿，涡轮发动机排气孔和各种天线。 发射罐装置可选地包括修改型“A”，“B”或“C”型超声波发射罐。 本发明的系统还包括便携式命令，控制，通信，计算机和智能（C4I）控制和感测分析控制台。 控制台最好是坚固耐用，防水，防震，并且包括必要的控制和分析计算机，输入/输出设备，天线以及用于车辆和任务控制的相关硬件和软件。 C4I控制台和/或发射罐可以通过适于人的便携性的背包来运输。

    Airborne Launch of Inflatable Devices
    55.
    发明申请
    Airborne Launch of Inflatable Devices 审中-公开

    公开(公告)号：US20170355462A1

    公开(公告)日：2017-12-14

    申请号：US15621100

    申请日：2017-06-13

    Applicant: Raymond Hoheisel

    Inventor： Raymond Hoheisel

    IPC: B64D1/12 ,  B64B1/62 ,  B64B1/40 ,  B64D1/02

    CPC classification number: B64D1/12 ,  B64B1/40 ,  B64B1/64 ,  B64C2201/082 ,  B64C2201/101 ,  B64D17/02 ,  B64D17/38

    Abstract: Aspects described herein relate to an apparatus, system, and method for the airborne launch of inflatable, lighter-than-air devices from aircraft. In some instances, a container comprising a drag parachute and a main parachute assembly may be deployed from an aircraft. Drag forces on the container may cause the drag parachute to be expelled from the container. Drag forces on the drag parachute may cause the main parachute assembly to be expelled from the container. The main parachute assembly may include a canopy with an opening and a release channel connecting the opening with the container. The container may further include a balloon inflation mechanism, which may be used to inflate one or more balloon envelopes. The one or more balloon envelopes, after being inflated, may be configured to be released from the container, traverse the release channel, and exit the main parachute assembly through the opening.

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