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    CARGO AIRCRAFT
    12.
    发明公开
    CARGO AIRCRAFT 有权
    FRACHTFLUGZEUG

    公开(公告)号：EP1833721A2

    公开(公告)日：2007-09-19

    申请号：EP05857018.5

    申请日：2005-11-22

    Applicant: Helou, Elie Jr.

    Inventor： Helou, Elie Jr.

    IPC: B64C1/22

    CPC classification number: B64C1/10 ,  B64C1/00 ,  B64C1/061 ,  B64C1/065 ,  B64C39/02 ,  B64C39/024 ,  B64C2001/0072 ,  B64C2201/021 ,  B64C2201/048 ,  B64C2201/086 ,  B64C2201/104 ,  B64C2201/128 ,  B64C2201/162 ,  B64C2201/167 ,  B64C2211/00 ,  Y02T50/43

    Abstract: In one embodiment, an aircraft for transporting at least one cargo container is disclosed. The aircraft comprises a forward fuselage, an empennage, a beam structure, and mounts to detachably and structurally engage the at least one cargo container with the beam structure. The beam structure is disposed between the forward fuselage and the empennage and the beam structure configured to receive the at least one cargo container. The beam structure and structurally engaged cargo container provide sufficient structural rigidity to support the aircraft in flight.

    Abstract translation: 在一个实施例中，公开了一种运送至少一个货物集装箱的飞机。 飞行器包括前机身，尾翼，梁结构，以及可拆卸地和结构地接合具有梁结构的至少一个货物集装箱的安装件。 梁结构设置在前机身和尾翼之间，梁结构构造成接收至少一个货物集装箱。 梁结构和结构上接合的货物集装箱提供足够的结构刚度以支持飞行中的飞机。

    AIRCRAFT WITH VERTICAL TAKEOFF AND LANDING AND ITS OPERATING PROCESS
    13.
    发明公开
    AIRCRAFT WITH VERTICAL TAKEOFF AND LANDING AND ITS OPERATING PROCESS 审中-公开

    公开(公告)号：EP3390224A1

    公开(公告)日：2018-10-24

    申请号：EP16831647.9

    申请日：2016-12-16

    Applicant: IOSIF, Taposu ,  RAZVAN, Sabie

    Inventor： RAZVAN, Sabie

    IPC: B64C39/00

    CPC classification number: B64C39/001 ,  B64C2201/027 ,  B64C2201/14 ,  B64C2201/162 ,  B64C2201/167 ,  B64C2201/185

    Abstract: The invention relates to an aircraft with vertical takeoff and landing and its operation method. Aircraft with vertical takeoff and landing of aerodyne type according to the invention comprises a circular symmetrical aerodynamic body (1) having an internal stiffening platform (2) located on the chord of the aerodynamic profile and which supports the components of the aircraft, at least four vertical ducted propellers (3a), (3b), (3c), (3d) arranged symmetrically to the central vertical axis of the carrier body (1), but also to the predetemined flight axis and to the transverse axis of the carrier body (1), propellers (3a) and (3c) having the same rotational direction opposite to that of propellers (3b) and (3d) at least two horizontal ducted propellers (4) with opposite rotation directions located inside the carrier body or outside of it, placed parallel symmetrical with the predetermined flight axis and on both sides of it, vector nozzles (5), one for each horizontal propeller (4), which provides vector orientation to jets of the horizontal ducted propellers (4), the means of power supply (6), which are designed to provide electricity necessary to operate all engines and all electrical and electronic devices on board, an electronic control and management flight module (7) and a landing gear (9), which aims to promote contact between the aircraft and the ground.

    DRONE LAUNCH SYSTEMS AND METHODS
    18.
    发明申请
    DRONE LAUNCH SYSTEMS AND METHODS 有权
    推动系统和方法

    公开(公告)号：US20170057635A1

    公开(公告)日：2017-03-02

    申请号：US14843329

    申请日：2015-09-02

    Applicant: THE BOEING COMPANY

    Inventor： James David Strayer

    IPC: B64C39/02 ,  B64C5/06 ,  B64D1/02

    CPC classification number: B64C39/024 ,  B63G3/04 ,  B63G2008/004 ,  B63G2008/008 ,  B64C2201/027 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/167 ,  B64C2201/201 ,  B64C2201/205

    Abstract: A drone launch system includes a canister defining an internal cavity, and a drone positioned within the internal cavity in a stowed state. The drone is configured to be ejected from the canister and transition from the stowed state into a deployed state outside of the canister. A method for launching a drone, the method includes positioning the drone in a stowed state in an internal cavity of a canister, ejecting the drone from the canister, and transitioning the drone into a deployed state after the ejecting operation.

    Abstract translation: 无人机发射系统包括限定内部空腔的罐和位于收纳状态的内部空腔内的无人机。 无人机被配置为从罐排出并从收起状态转换到罐外部的展开状态。 一种用于发射无人机的方法，该方法包括将无人机处于收起状态，将其从罐中排出，将喷射器从罐排出，并且在喷射操作之后将无人机转换成展开状态。

    Unmanned aerial vehicle based sonar buoy
    19.
    发明授权
    Unmanned aerial vehicle based sonar buoy 有权
    无人机基于声纳浮标

    公开(公告)号：US08492692B2

    公开(公告)日：2013-07-23

    申请号：US13097394

    申请日：2011-04-29

    Applicant: Jeremy F. Fisher

    Inventor： Jeremy F. Fisher

    IPC: F42B12/56 ,  F42B15/01 ,  F42B15/08 ,  H04B1/59 ,  F42B15/00 ,  H04B1/00

    CPC classification number: F42B15/10 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/122 ,  B64C2201/165 ,  B64C2201/167 ,  B64C2201/201 ,  B64C2201/205 ,  F41F1/08 ,  F41F3/042

    Abstract: A sonar buoy includes a fuselage having a tube-like shape, one or more wings coupled to the fuselage, an engine coupled to the fuselage and operable to propel the sonar buoy through flight, and a guidance computer operable to direct the sonar buoy to a predetermined location. The sonar buoy further includes a sonar detachably coupled to the fuselage and forming at least a part of the fuselage, and a rocket motor detachably coupled to the fuselage. The one or more wings are operable to be folded into a position to allow the sonar buoy to be disposed within a launch tube coupled to a vehicle and to automatically deploy to an appropriate position for flight after the sonar buoy is launched from the launch tube. The rocket motor propels the sonar buoy from the launch tube and detaches from the fuselage after launch.

    Abstract translation: 声纳浮标包括具有管状形状的机身，耦合到机身的一个或多个翼，耦合到机身的发动机，并且可操作以通过飞行推进声纳浮标;以及引导计算机，其可操作以将声纳浮标引导到 预定位置。 声纳浮标还包括可拆卸地联接到机身并形成机身的至少一部分的声纳和可拆卸地联接到机身的火箭发动机。 一个或多个翼可操作以折叠到允许声纳浮标布置在联接到车辆的发射管内并且在从发射管发射声纳浮标之后自动部署到适当位置用于飞行的位置。 火箭发动机从发射管推进声纳浮标，并在发射后从机身分离。

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