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    Unmanned aerial vehicle with integrated wing battery
    211.
    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。

    System for airborn launch of an aircraft from a larger carrier aircraft
    213.
    发明申请
    System for airborn launch of an aircraft from a larger carrier aircraft 有权
    飞机从较大的载具飞机发射飞机的系统

    公开(公告)号：US20040089767A1

    公开(公告)日：2004-05-13

    申请号：US10472230

    申请日：2003-09-22

    Inventor： Richard G. Harrison

    IPC: H04B007/185

    CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/048 ,  B64C2201/082 ,  B64C2201/206 ,  B64D3/00 ,  B64D5/00 ,  B64D39/02 ,  B64D39/06

    Abstract: A system for launching, refuelling and recovering in flight an aircraft (10) such as an unmanned aerial vehicle (UAV) from a larger carrier aircraft (16) comprising a holder (22) on the carrier aircraft (16) to which the UAV (10) is detachably connectable and an extendable and retractable refuelling device (23, 24) on the carrier aircraft (16) detachably connectable to the UAV (10) whereby to launch the UAV it is disconnected from the holder (22), the refuelling device (23, 24) is extended with the UAV connected thereto to cause the UAV to trail behind the carrier aircraft and the UAV is then disconnected from the refuelling device.

    Abstract translation: 一种用于从飞机上起飞，加油和恢复飞行器（10）的系统，所述飞机（10）从诸如无人飞行器（UAV）的大型载客飞机（16）起飞，所述飞机（10）包括在所述载体飞机（16）上的载具飞机（16） 10）可拆卸地连接，并且可拆卸地连接到UAV（10）的载体飞行器（16）上的可伸缩的加油装置（23,24），由此能够将UAV从保持器（22）断开，加油装置 （23,24）在与其连接的UAV的情况下延伸，使得UAV在载客飞行器后行驶，然后UAV从加油装置断开。

    Circular vertical take off and landing aircraft
    214.
    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。

    Airship system
    215.
    发明申请
    Airship system 失效
    飞艇系统

    公开(公告)号：US20030025034A1

    公开(公告)日：2003-02-06

    申请号：US10189796

    申请日：2002-07-03

    Inventor： Yutaka Akahori

    IPC: B64B001/02 ,  B64B001/06

    CPC classification number: G08G5/0052 ,  B64B1/06 ,  B64C39/024 ,  B64C2201/022 ,  B64C2201/042 ,  B64C2201/048 ,  B64C2201/101 ,  B64C2201/122 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/167 ,  B64F1/18 ,  G01S5/20 ,  G01S5/22 ,  G05D1/0202 ,  G08G5/00 ,  G08G5/0013

    Abstract: An airship system according to the invention has an airship (110), a base station (120), and at least three measurement points. The airship (110) emits ultrasonic waves upon receiving an instruction from the base station (120). Measurement point units (S1-S3) receive the ultrasonic waves, and thereby measure distances from the airship (110) to the respective measurement points. An MPU that is incorporated in the base station (120) calculates a position of the airship (110). The base station (120) controls a route of the airship (110) based on the calculated position by sending a flight instruction to the airship (110). In this manner, an airship system can be provided that makes it unnecessary for an operator to pilot the airship and that can reduce the load weight and the power consumption of the airship.

    Abstract translation: 根据本发明的飞艇系统具有飞艇（110），基站（120）和至少三个测量点。 飞艇（110）在接收到来自基站（120）的指令时发射超声波。 测量点单元（S1-S3）接收超声波，从而测量从飞艇（110）到相应测量点的距离。 并入基站（120）的MPU计算飞艇（110）的位置。 基站（120）通过向飞艇（110）发送飞行指令，基于计算出的位置来控制飞艇（110）的路线。 以这种方式，可以提供一种飞艇系统，使得飞行员不需要飞行飞艇，并且可以减少飞艇的负载重量和功率消耗。

    VTOL aircraft with movable undercarriage
    216.
    发明授权
    VTOL aircraft with movable undercarriage 失效
    垂直起降飞机具有可移动的底盘

    公开(公告)号：US5056737A

    公开(公告)日：1991-10-15

    申请号：US499809

    申请日：1990-03-27

    Applicant: Douglas R. Taylor

    Inventor： Douglas R. Taylor

    IPC: B64C25/66 ,  B64C29/02 ,  B64C39/02 ,  B64F1/12

    CPC classification number: B64C25/66 ,  B64C29/02 ,  B64C39/024 ,  B64F1/12 ,  B64C2201/048 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/165 ,  B64C2201/167

    Abstract: A vertical take-off and landing aircraft is configured so as to provide, when landing tail-first with its fuselage (1) in a generally vertical attitude, a touchdown area (21) at the tail of the aircraft at a position offset from a line extending along the length of the fuselage through the centre of gravity (23) of the aircraft such that after the touchdown area contacts a landing surface the aircraft topples under the action of gravity to bring an undercarriage (11, 13) of the aircraft into contact with the landing surface, thereby to attain a stable landed position.

    Abstract translation: 垂直起飞和着陆飞机被配置为当其以机身（1）以大致垂直的姿态着陆尾部时，提供在飞行器尾部处的偏移的位置处的触地区域（21） 沿着机身的长度通过飞行器的重心（23）延伸，使得在着陆区域接触着陆表面之后，飞行器在重力作用下俯仰，使飞机的起落架（11,13）进入 与着陆面接触，从而达到稳定的着陆位置。

    Drone aircraft with telescopic fuselage
    217.
    发明授权
    Drone aircraft with telescopic fuselage 失效
    DRONE飞机与TELESCOPIC FUSELAGE

    公开(公告)号：US3703998A

    公开(公告)日：1972-11-28

    申请号：US3703998D

    申请日：1970-12-28

    Applicant: TELEDYNE RYAN AERONAUTICAL CO

    Inventor： GIRARD PETER F

    IPC: B64C1/00 ,  B64C39/02 ,  B64C1/28 ,  B64C3/56

    CPC classification number: B64C39/024 ,  B64C1/00 ,  B64C2001/0045 ,  B64C2201/048 ,  B64C2201/102 ,  B64C2201/121 ,  B64C2201/146 ,  B64C2201/162 ,  B64C2201/167

    Abstract: A drone type aircraft having a telescopic fuselage and folding aerodynamic surfaces to facilitate installation in a limited capacity bomb bay or storage compartment of a launch aircraft. Prior to launch, the drone is lowered from the aircraft on a supporting frame, the aerodynamic surfaces are extended, and the nose section of the fuselage is extended. The added fuselage capacity is used as fuel tankage, which is filled from the launch aircraft to increase the operating range of the drone.

    Abstract translation: 具有伸缩机身和折叠空气动力学表面的无人机型飞机，以便于安装在发射飞机的有限容量的炸弹舱或储藏室中。 在发射之前，无人机在支架上从飞机上下降，空气动力学表面延伸，机身的鼻部延伸。 增加的机身容量用作燃油箱，由发射机充满，以增加无人机的运行范围。

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