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    UNMANNED AERIAL VEHICLE SYSTEM
    41.
    发明申请
    UNMANNED AERIAL VEHICLE SYSTEM 审中-公开
    无人驾驶航空系统

    公开(公告)号：US20120043411A1

    公开(公告)日：2012-02-23

    申请号：US13149576

    申请日：2011-05-31

    Applicant: Peter Joseph Beck ,  Nikhil Raghu

    Inventor： Peter Joseph Beck ,  Nikhil Raghu

    IPC: F42B15/08 ,  F42B10/14 ,  H04N7/18 ,  B64D17/80

    CPC classification number: B64C39/024 ,  B64C2201/046 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/185 ,  B64C2201/201 ,  F41F3/042 ,  F41F3/045 ,  F42B15/08 ,  F42B15/10 ,  H04N7/183

    Abstract: A UAV includes: a rocket body, having a rocket motor and a payload section; a parachute coupled with the payload section; an image capture device; a magnetometer to provide a compass reference for images taken from the image capture device; and a transmitter to communicate image and compass data to a remote receiver. Compass bearings are overlaid on image data from the image capture device. A handheld launch unit includes an ignition system, having an activation mechanism and an igniter to activate the rocket motor. A safety pin prevents electrical current from flowing to the igniter until the pin is removed. An accelerometer and/or magnetometer determines an angular orientation of the UAV. Software verifies that the angle is within a user-defined safety limit before activating the igniter.

    Abstract translation: 无人机包括：具有火箭发动机和有效载荷部分的火箭主体; 与有效载荷部分相连的降落伞; 图像捕获装置; 磁力计，用于为从图像捕获装置拍摄的图像提供罗盘参考; 以及用于将图像和罗盘数据传送到远程接收器的发射器。 指南针轴承覆盖在图像捕获装置的图像数据上。 手持式发射单元包括具有启动机构和点火器来激活火箭发动机的点火系统。 一个安全销防止电流流到点火器，直到引脚被移除。 加速度计和/或磁力计确定无人机的角度取向。 激活点火器之前，软件将验证角度在用户定义的安全极限内。

    Runway-independent omni-role modularity enhancement (ROME) vehicle
    42.
    发明授权
    Runway-independent omni-role modularity enhancement (ROME) vehicle 有权
    跑道独立的全能模块化增强（ROME）车辆

    公开(公告)号：US06926235B2

    公开(公告)日：2005-08-09

    申请号：US10600400

    申请日：2003-06-20

    Applicant: Richard P. Ouellette ,  Aaron J. Kutzmann

    Inventor： Richard P. Ouellette ,  Aaron J. Kutzmann

    IPC: B64C1/00 ,  B64C29/00 ,  B64C39/02 ,  B64D7/00

    CPC classification number: B64C1/00 ,  B64C29/0058 ,  B64C39/024 ,  B64C2201/046 ,  B64C2201/086 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/121 ,  B64C2201/165 ,  B64C2201/167 ,  B64C2201/187 ,  B64D7/00

    Abstract: A modular component set is configurable to form a plurality of flight capable platforms. A plurality of end pieces each has contiguously connected curved outer portions each longitudinally expanding from a tip to terminate at a blunt attachment face. Body members have opposed ends to receive the end piece blunt attachment face, and a rectangular shaped mid-portion having opposed walls. A plurality of task specific panels are each releasably connectable to one of the opposed walls. At least one of the body members with the end pieces joined at the opposed ends, and at least one of the task specific panels connected to one of the opposed walls form a minimum component set for each of the flight capable platforms.

    Abstract translation: 模块化组件组可配置成形成多个具有飞行能力的平台。 多个端片各自具有连续地连接的弯曲外部部分，每个端部从尖端纵向扩展以终止于钝的附接面。 主体部件具有相对的端部以接收端部钝器附接面，以及具有相对壁的矩形中间部分。 多个任务专用面板各自可拆卸地连接到相对的壁之一。 至少一个具有端部件的主体部件在相对的端部连接，并且连接到相对的一个壁之一的任务专用面板中的至少一个为每个具有飞行能力的平台形成最小的部件组。

    Stealthy duffel bag airplane
    43.
    发明授权
    Stealthy duffel bag airplane 失效
    隐形行李袋飞机

    公开(公告)号：US06892981B2

    公开(公告)日：2005-05-17

    申请号：US10408981

    申请日：2003-04-08

    Applicant: Jay Lipeles

    Inventor： Jay Lipeles

    IPC: B64C3/30 ,  B64C3/56 ,  B64C39/02 ,  B64C39/10 ,  B64D33/04 ,  B64C39/00

    CPC classification number: B64C39/024 ,  B64C3/30 ,  B64C3/56 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/044 ,  B64C2201/046 ,  B64C2201/105 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/203 ,  B64C2201/22 ,  B64D33/04 ,  B64D2033/045

    Abstract: The Duffel Bag Airplane is an inflatable flying wing unmanned airborne vehicle (UAV). The fuselage will house everything but the wings. The wing can be rolled up around the fuselage into a small package when deflated for easy transportation, such as by being carried in a duffle bag. Fabric construction, a small internal combustion engine with cooled exhaust, and wing warping controls combine to make the airplane inexpensive and extremely stealthy. All the usual signatures have been suppressed, which allow it to be used to make observations from close range under combat conditions. Control of this airplane is accomplished by warping the wings and is supplemented with stability augmentation.

    Abstract translation: Duffel Bag飞机是一种充气飞翼无人机载机（UAV）。 机身将会容纳除翅膀之外的所有东西。 机翼可以卷绕在机身周围，当放气以便于运输时，例如通过携带在行李箱中，成为小包装。 织物结构，具有冷却排气的小型内燃机和机翼翘曲控制相结合，使飞机廉价而且非常隐蔽。 所有通常的签名已经被压制，这允许它用于在战斗条件下从近距离观察。 这架飞机的控制是通过扭转机翼来实现的，并补充了稳定性增强。

    Unmanned aerial vehicle with integrated wing battery
    44.
    发明申请
    Unmanned aerial vehicle with integrated wing battery 审中-公开
    无人机配有集成翼电池

    公开(公告)号：US20040211862A1

    公开(公告)日：2004-10-28

    申请号：US10423187

    申请日：2003-04-25

    Inventor： Daryl B. Elam

    IPC: B64D041/00

    CPC classification number: A63H27/02 ,  B64C39/024 ,  B64C2201/046 ,  B64C2201/048 ,  B64C2201/104 ,  B64C2201/126 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/167 ,  B64D27/24 ,  Y02T50/44 ,  Y02T50/62

    Abstract: An unmanned aerial vehicle, such as a remotely-piloted airplane, includes lift-producing wings that have batteries embedded or otherwise located within them. Locating the batteries within the wings allows more efficient use of the interior space of the unmanned vehicle. Space within a fuselage of the vehicle, which would otherwise be used for batteries, may be used for other components. Alternatively, fuselage, weight and/or size of the unmanned aerial vehicle may be reduced. In addition, locating the batteries within the wings may provide better structural performance of the wings, and/or may allow characteristics of the wings, such as inertia and moments, to be optimized.

    Abstract translation: 诸如遥控飞机的无人驾驶飞行器包括具有嵌入或以其他方式位于其中的电池的升降机翼。 将电池放置在机翼内可以更有效地利用无人驾驶车辆的内部空间。 车辆的机身中的空间，否则将用于电池，可用于其他部件。 或者，可以减少无人驾驶飞行器的机身，重量和/或尺寸。 此外，将电池定位在机翼内可以提供更好的机翼的结构性能，和/或可以允许优化机翼的特性，例如惯性和力矩。

    Survivable and reusable launch vehicle
    45.
    发明授权
    Survivable and reusable launch vehicle 有权
    生存和可重复使用的运载火箭

    公开(公告)号：US06749153B1

    公开(公告)日：2004-06-15

    申请号：US10309828

    申请日：2002-12-04

    Applicant: Henry August

    Inventor： Henry August

    IPC: B04B120

    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.

    Abstract translation: 可重复使用的马赫速度移动平台通过垂直发射，无力滑翔，武器释放和着陆操作阶段提供武器有效载荷。 平台包括具有尾部和前端的大致管状的主体和有效载荷部分。 一个弓翼由身体后端支撑。 拱翼具有通过两个弯曲端板在远端连接的上翼和下翼。 前端组件在前端连接，具有向上定向的固定迎角，以产生前端提升。 安装在车体下方的散热瓦片和下部翼片下侧辐射/消散在高角度攻角平台折返期间产生的热量。 使用雷达吸收或雷达半透明材料。 该平台优选地从尾端排出有效载荷以进行安全分离。 起落架延伸到着陆阶段。

    Circular vertical take off and landing aircraft
    46.
    发明授权
    Circular vertical take off and landing aircraft 失效
    圆形垂直起降飞机

    公开(公告)号：US06698685B2

    公开(公告)日：2004-03-02

    申请号：US10084749

    申请日：2002-02-26

    Applicant: Eric Ronald Walmsley

    Inventor： Eric Ronald Walmsley

    IPC: B64C3906

    CPC classification number: B64C27/20 ,  B64C29/0066 ,  B64C39/001 ,  B64C39/024 ,  B64C39/06 ,  B64C39/062 ,  B64C2201/027 ,  B64C2201/046 ,  B64C2201/048 ,  B64C2201/108 ,  B64C2201/121 ,  B64C2201/127

    Abstract: A circular VTOL aircraft with a central vertically mounted jet or rocket engine 7, (or engines) having below vertical thrust vents 14 at cardinal points, together with a jet/rocket engine 20 (or engines) horizontally mounted on turntable pod 16 which is steerable through 360 degrees and centrally situated below the vertical engine (s). Alternatively the horizontal engine can be replaced by central thrust vent 36 delivering thrust from the vertical engine to vectored thrust nozzle 37 attached to the turntable. Thrust from the four vertical thrust vents is controlled by valves 21 giving VTOL thrust control as well as pitch and bank control. The horizontal engine provides acceleration and retro-thrust for horizontal flight and directional control through 360 degrees. The passenger cabin is situated in the main body of the aircraft. Fuel tanks are installed around the central engines. The flight-deck is situated at the top-centre of the craft above the engines, which are detachable for maintenance.

    Abstract translation: 具有中心垂直安装的喷气式或火箭发动机7（或发动机）的圆形垂直起降飞机与在水平安装在可转向的转盘舱16上的喷气/火箭发动机20（或发动机）一起在主要点处具有下垂直推力通风口14 通过360度并位于垂直发动机下方的中心位置。 或者，水平发动机可以由中心推力孔36代替，其将来自垂直发动机的推力传递到附接到转盘的向量推力喷嘴37。 来自四个垂直推力通风口的推力由阀门21控制，提供垂直起动器推力控制以及俯仰和组合控制。 水平发动机提供加速度和逆向推力，用于水平飞行和360度方向控制。 客舱位于飞机的主体。 燃油箱安装在中央发动机周围。 飞行甲板位于发动机上方的工艺的顶部中心，可拆卸以进行维护。

    Unmanned aircraft
    47.
    发明授权
    Unmanned aircraft 失效
    无人机

    公开(公告)号：US4666105A

    公开(公告)日：1987-05-19

    申请号：US784484

    申请日：1985-10-04

    Applicant: Juergen Dellinger ,  Hans-Jochen Hoeppner ,  Ulrich Kraemer

    Inventor： Juergen Dellinger ,  Hans-Jochen Hoeppner ,  Ulrich Kraemer

    IPC: B64C39/02 ,  F42B15/36 ,  B64F1/04

    CPC classification number: F42B15/36 ,  B64C39/024 ,  B64C2201/046 ,  B64C2201/127 ,  B64C2201/128 ,  B64C2201/165 ,  B64C2201/185

    Abstract: An unmanned craft having a fuselage, a propeller drive with a propeller being arranged in the tail portion of the fuselage for purposes of cruising, and a rocket assist propulsion system for the takeoff phase is releasably mounted to the fuselage, the improvement includes three spring biased thrust rods being secured to the frame and releasably engaging peripheral points of the craft. The thrust rods are radially pivotal in outer direction. Support points on the wings and the rudder engage front ends of the rods in contourmatching relationship but are disengageable therefrom.

    Abstract translation: 具有机身的无人飞行器，具有推进器的螺旋桨驱动器布置在机身的尾部以用于巡航，并且用于起飞阶段的火箭辅助推进系统可释放地安装到机身，改进包括三个弹簧偏置 推杆被固定到框架并且可释放地接合工艺的外围点。 推力杆在外部方向上是径向枢转的。 机翼和方向舵上的支撑点以轮廓匹配关系与杆的前端接合，但是与其脱离接合。

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