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    LOAD-CARRYING SYSTEM FOR TRANSPORT AEROPLANE
    21.
    发明申请
    LOAD-CARRYING SYSTEM FOR TRANSPORT AEROPLANE 有权
    运输机场装载系统

    公开(公告)号：US20120292444A1

    公开(公告)日：2012-11-22

    申请号：US13574457

    申请日：2011-01-19

    Applicant: Benoit Jaurand

    Inventor： Benoit Jaurand

    IPC: B64D1/10 ,  B64C1/22

    CPC classification number: B64D1/02 ,  B64C39/024 ,  B64C2201/082 ,  B64C2201/201 ,  B64C2201/206

    Abstract: The system comprises an outer container which is fixed, directly and fully, in the hold of the transport aeroplane (AC), and in which there is an inner container that can be moved longitudinally and brought from a first carrying position (AC) in which it is situated fully inside said outer container into a second off-loading position (P2), position (P2) in which it is longitudinally offset towards the rear of the aircraft (AC) so that a part of said inner container is then situated outside the transport aeroplane (AC).

    Abstract translation: 该系统包括直接和完全固定在运输飞机（AC）的保持件中的外部容器，并且其中存在能够纵向移动并从第一运送位置（AC）带动的内部容器 它完全位于所述外部容器内部进入第二卸载位置（P2），位置（P2）中，其朝向飞行器（AC）的后部纵向偏移，使得所述内部容器的一部分然后位于外部 运输飞机（AC）。

    Modular articulated-wing aircraft
    22.
    发明授权
    Modular articulated-wing aircraft 有权
    模块化铰接翼飞机

    公开(公告)号：US07789339B2

    公开(公告)日：2010-09-07

    申请号：US11475085

    申请日：2006-06-27

    Applicant: Geoffrey S. Sommer

    Inventor： Geoffrey S. Sommer

    IPC: B64D5/00

    CPC classification number: B64C39/024 ,  B64C37/02 ,  B64C2201/021 ,  B64C2201/082 ,  B64C2201/143 ,  B64C2201/165 ,  B64C2201/206

    Abstract: Systems and/or methods for forming a multiple-articulated flying system (skybase) having a high aspect ratio wing platform, operable to loiter over an area of interest at a high altitude are provided. In certain exemplary embodiments, autonomous modular flyers join together in a wingtip-to-wingtip manner. Such modular flyers may derive their power from insolation. The autonomous flyers may include sensors which operate individually, or collectively after a skybase is formed. The skybase preferably may be aggregated, disaggregated, and/or re-aggregated as called for by the prevailing conditions. Thus, it may be possible to provide a “forever-on-station” aircraft.

    Abstract translation: 提供了用于形成具有高纵横比翼平台的多关节飞行系统（天基）的系统和/或方法，其可操作以在高海拔地区的感兴趣区域上游荡。 在某些示例性实施例中，自主模块化飞行器以翼尖到翼尖的方式连接在一起。 这样的模块化飞行器可以从日晒中获得其功率。 自主传单可以包括单独操作的传感器，或者在形成天空基础之后集体运行。 天空基优选地可以按照主要条件的要求进行聚合，分解和/或再聚集。 因此，可能提供“永远在车”的飞机。

    UNMANNED AERIAL VEHICLE AND LAUNCH ASSEMBLY
    23.
    发明申请
    UNMANNED AERIAL VEHICLE AND LAUNCH ASSEMBLY 有权
    无人驾驶的航空母舰和发射装置

    公开(公告)号：US20090134273A1

    公开(公告)日：2009-05-28

    申请号：US11064287

    申请日：2005-02-22

    Applicant: Mark A. Page ,  Doug McLarty ,  Adrian Fazio ,  Christian Durand ,  Bob Emerick

    Inventor： Mark A. Page ,  Doug McLarty ,  Adrian Fazio ,  Christian Durand ,  Bob Emerick

    IPC: B64C1/00 ,  B28B5/00 ,  B64F1/04

    CPC classification number: B64C39/024 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/082 ,  B64C2201/084 ,  B64C2201/165 ,  B64C2201/201

    Abstract: An unmanned aerial vehicle (UAV) is provided, that is cost effective to use and manufacture and that includes a low count of component parts, allowing mission planners to use the UAVs in a disposable manner. The UAV includes an airframe having a central body and wings extending from the central body, defining an interior cavity. The airframe includes an upper and a lower shell, each configured of a unitary piece of plastic. The upper and lower shells have walls among them that define a fuel tank and a payload bay in a stacked configuration. The airframe can further include a payload cover configured to enclose the payload bay and to contribute to the central body of the airframe. A launch assembly is also provided. In a first configuration, a launch assembly is provided, that includes a container for housing multiple UAVs and a deployment mechanism that initiates rapid ejection of the UAVs from the container. In a second configuration, a launch assembly is provided, that includes an elastic tether connecting a UAV to an accelerated mass for gentle acceleration to flight speed under a stable tow.

    Abstract translation: 提供无人驾驶飞行器（UAV），使用和制造具有成本效益，并且包括低数量的部件，允许任务规划人员以一次性方式使用无人机。 无人机包括具有中心体的机身和从中心体延伸的翼，限定内腔。 机身包括一个上部和下部壳体，每个都由整体塑料构成。 上壳体和下壳体之间具有限定了堆叠构造的燃料箱和有效载荷的壁。 机身还可以包括配置成包围有效载荷舱并有助于机身的中心体的有效载荷盖。 还提供发射组件。 在第一配置中，提供了一种发射组件，其包括用于容纳多个UAV的容器和启动无人机从容器的快速喷射的展开机构。 在第二构造中，提供了一种发射组件，其包括将UAV连接到加速质量块的弹性系绳，以在稳定的丝束下平缓加速到飞行速度。

    In-flight loadable and refuelable unmanned aircraft system for continuous flight
    24.
    发明申请
    In-flight loadable and refuelable unmanned aircraft system for continuous flight 失效
    用于连续飞行的飞行中可加载和可加油的无人驾驶飞机系统

    公开(公告)号：US20020074454A1

    公开(公告)日：2002-06-20

    申请号：US09738227

    申请日：2000-12-15

    Inventor： J. Kirston Henderson

    IPC: B64D037/00

    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.

    Abstract translation: 本文公开了一种用于加油和重新加载用于连续飞行的无人驾驶飞行器的方法，其中无人飞行器由支撑飞行器维护和支撑。 两架飞机都保持位于每架飞机下侧的货舱和飞行中可操作的门，以便对接和交换货物。 优选地，货物包括可装载的盒，并且可以包含诸如武器，货物或燃料的物品。 在一个实施例中，当两架飞机处于用于在飞行中交换货物的对接配置时，飞行中可操作的门打开，并且支撑飞机能够在无人驾驶飞机上装载这样的卡盘。 必要时，支援飞机可以为无人机着陆而装载装备。 公开了重新装载用于连续飞行的无人飞行器的替代方法，其中无人驾驶飞机没有货舱并且飞机由支撑飞机支撑。

    Combined Vertical Takeoff and Landing UAV
    25.
    发明公开
    Combined Vertical Takeoff and Landing UAV 审中-公开

    公开(公告)号：US20230159164A1

    公开(公告)日：2023-05-25

    申请号：US18058262

    申请日：2022-11-22

    Applicant: Autoflight (Kunshan) Co., Ltd.

    Inventor： Yu Tian

    IPC: B64C39/02

    CPC classification number: B64C39/024 ,  B64C2201/02 ,  B64C2201/082 ,  B64C2201/088 ,  B64C2201/206

    Abstract: A combined vertical takeoff and landing UAV having a large vertical takeoff and landing UAV, a connecting device, and a small vertical takeoff and landing UAV. The connecting device having a clamping component and an adsorption component. The clamping component includes a clamping part, and a clamping groove is arranged on the clamping part. The clamping component having a snap-fitting part, and a snap-fitting groove is arranged on the snap-fitting part. The clamping groove and the snap-fitting groove are correspondingly set. A first holding space is arranged on the clamping part, and a second holding space is arranged on the snap-fitting part. The adsorption component comprises a first magnetic element located in the first holding space, and the adsorption component also comprises a second magnetic element, which is located in the second holding space.

    AUTOMATED DETERMINATION OF ROCKET CONFIGURATION
    30.
    发明申请
    AUTOMATED DETERMINATION OF ROCKET CONFIGURATION 审中-公开

    公开(公告)号：US20180142997A1

    公开(公告)日：2018-05-24

    申请号：US15357407

    申请日：2016-11-21

    Applicant: BAE SYSTEMS Information and Electronic Systems Integration Inc.

    Inventor： David J. Schorr ,  Matthew F. Damiano ,  James H. Steenson, JR.

    IPC: F42B15/01 ,  G06F17/50 ,  G06F17/13 ,  F42B35/00

    CPC classification number: F42B15/01 ,  B64C2201/027 ,  B64C2201/082 ,  F42B15/08 ,  F42B35/00 ,  G06F17/5086 ,  G06F2217/16

    Abstract: Techniques are provided for automated determination of a rocket configuration based on acceleration during rocket motor burn-out and temperature. The rocket configuration is associated with a class of warhead affixed to the rocket. A methodology implementing the techniques according to an embodiment includes measuring the acceleration of the rocket over a period of time associated with the flight of the rocket. The method also includes calculating an acceleration difference between the measured acceleration associated with the start of rocket motor burn-out and the measured acceleration associated with the end of rocket motor burn-out. The method further includes measuring an internal temperature of the rocket and selecting a delta acceleration threshold based on the measured temperature. The method further includes comparing the calculated acceleration difference to the selected delta acceleration threshold, to estimate the rocket configuration. The estimated rocket configuration is used by guidance and control circuitry to select autopilot parameters.

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