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    Small-size high-speed transmission system for use in microturbine-powered aircraft
    43.
    发明申请
    Small-size high-speed transmission system for use in microturbine-powered aircraft 有权
    用于微型涡轮动力飞机的小型高速传动系统

    公开(公告)号：US20070051846A1

    公开(公告)日：2007-03-08

    申请号：US11398375

    申请日：2006-06-14

    Applicant: J. Box ,  Jules Kish

    Inventor： J. Box ,  Jules Kish

    IPC: B64D35/00

    CPC classification number: B64C27/14 ,  B64C39/028 ,  B64C2201/048 ,  B64C2201/104 ,  B64C2201/121 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  B64D35/02

    Abstract: A transmission system that is used in conjunction with a microturbine engine for propelling an aircraft body, such as a propeller-based fixed-wing aircraft or a rotor-based vertical lift aircraft, or for a wide variety of other applications. The output shaft of the microturbine engine preferably operates at a rotational speed in a range between 72,000 RPM and 150,000 RPM with an output power between 150 HP and 5 HP (and most preferably operates in an extended range between 50,000 RPM and 200,000 RPM with an output power between 200 HP and 5 HP). The two reduction stages provide a reduction ratio preferably having a value of at least 19, and most preferably greater than 24. The transmission system is of small-size preferably having a maximum diameter less than twelve inches. The two stages of the transmission system may comprise any one (or parts of) of a number of configurations, including an in-line lay shaft configuration, an in-line star-star configuration, an offset star-spur configuration, an offset compound idler configuration, an inline traction-internal gear configuration, and an inline traction-planetary gear configuration. Preferably, the input stage of the transmission system is self-equilibrating such that first shaft can be supported without bearings and is operably coupled to the output shaft of the microturbine engine by an outside diameter piloted spline coupling mechanism. For vertical lift applications, a single traction stage along with a bevel gear assembly or other shaft transmission mechanism can be used to provide the necessary RPM reduction.

    Abstract translation: 与微型涡轮发动机结合使用的用于推进飞机机体（例如基于螺旋桨的固定翼飞行器或基于转子的垂直升降飞机）或用于各种其它应用的传动系统。 微型涡轮发动机的输出轴优选地在72,000RPM和150,000RPM之间的转速下工作，输出功率在150HP和5HP之间（最优选地在50,000RPM和200,000RPM之间的扩展范围内工作，并且输出 功率在200 HP和5 HP之间）。 两个还原阶段提供优选具有至少19的值，最优选大于24的减小率。传动系统的尺寸最小，最好具有小于12英寸的最大直径。 传动系统的两个阶段可以包括许多构造的任何一个（或部分）构造，包括在线卧轴构造，直列星星构造，偏移星形支路构造，偏移化合物 惰轮构造，在线牵引内齿轮配置和在线牵引行星齿轮配置。 优选地，传动系统的输入级是自平衡的，使得第一轴可以被支撑而没有轴承，并且通过外径引导的花键联接机构可操作地联接到微型涡轮发动机的输出轴。 对于垂直升降应用，可以使用单个牵引台以及锥齿轮组件或其他轴传动机构来提供必要的RPM减小。

    Small remotely controllable aircraft
    44.
    发明申请
    Small remotely controllable aircraft 审中-公开
    小型遥控飞机

    公开(公告)号：US20060255205A1

    公开(公告)日：2006-11-16

    申请号：US11314316

    申请日：2005-12-22

    Applicant: Peter Gleich ,  Franz Maier

    Inventor： Peter Gleich ,  Franz Maier

    IPC: B64C3/56

    CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/102 ,  B64C2201/121 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/201 ,  F42B15/105

    Abstract: A small aircraft has a fuselage (airframe), control apparatus, and a drive. A propeller electric drive, a power supply, a TV camera, data transmission and steering electronics, and a warhead and/or a weapon system are integrated in the fuselage. Collapsible and/or foldable wings, control surfaces, and propellers are positioned on the fuselage. The small aircraft according to the invention may be equipped with different weapon systems for combating different targets or for different missions.

    Abstract translation: 一架小型飞机有机身（机体），控制装置和驱动器。 在机身中集成有螺旋桨电动驱动器，电源，电视摄像机，数据传输和转向电子装置以及弹头和/或武器系统。 可折叠和/或可折叠的机翼，控制表面和螺旋桨位于机身上。 根据本发明的小型飞机可配备有用于对抗不同目标或不同任务的不同武器系统。

    SURVIVABLE AND REUSABLE LAUNCH VEHICLE
    46.
    发明申请
    SURVIVABLE AND REUSABLE LAUNCH VEHICLE 有权

    公开(公告)号：US20040108411A1

    公开(公告)日：2004-06-10

    申请号：US10453777

    申请日：2003-06-03

    Inventor： Henry August

    IPC: B64D005/00 ,  B64C037/02

    CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/046 ,  B64C2201/104 ,  B64C2201/121 ,  F42B10/16 ,  F42B10/62 ,  F42B12/58 ,  F42B12/62 ,  F42B15/00

    Abstract: A reusable, mach-velocity mobile platform delivers a weapons payload via vertical launch, powerless glide, weapons release, and landing operation phases. The platform includes a generally tubular shaped body having an aft and forward end, and a payload section. An arch wing is supported by the body aft end. The arch wing has an upper and a lower wing joined at distal ends by two curved end plates. A nose assembly is connected at the forward end having an upward directed fixed angle-of-attack to generate forward end lift. Thermal tiles attached under the body and the lower wing under-side radiate/dissipate heat generated during a high angle-of-attack platform reentry. Radar absorptive or radar translucent material is used. The platform preferably discharges payload from the aft end for safe separation. A landing gear is extended for the landing phase of operation.

    In-flight loadable and refuelable unmanned aircraft system for continuous flight
    47.
    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
    48.
    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。

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