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    AIRCRAFT AND METHOD FOR CONTROLLING AN AIRCRAFT FOR VERTICAL TAKE-OFF AND LANDING WITH A WIN ARRANGEMENT COMPRISING AN EXTENDIBLE LIFT INCREASING SYSTEM
    112.
    发明申请
    AIRCRAFT AND METHOD FOR CONTROLLING AN AIRCRAFT FOR VERTICAL TAKE-OFF AND LANDING WITH A WIN ARRANGEMENT COMPRISING AN EXTENDIBLE LIFT INCREASING SYSTEM 审中-公开
    用于控制垂直起落​​架的飞机的飞行器和方法，其中包括具有可扩展提升系统的绕组

    公开(公告)号：WO2014118299A1

    公开(公告)日：2014-08-07

    申请号：PCT/EP2014/051847

    申请日：2014-01-30

    Applicant: REITER, Johannes

    Inventor： REITER, Johannes

    IPC: B64C29/02 ,  B64C39/02

    CPC classification number: B64C29/02 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/048 ,  B64C2201/088 ,  B64C2201/102

    Abstract: The present invention relates to an aircraft comprising a fuselage (100) comprising a fuselage axis (101), a first wing arrangement (110) and a second wing arrangement (120). The first wing arrangement (110) is mounted to the fuselage (100) such that the first wing arrangement (110) is tiltable around a first rotary wing axis (111) of the first wing arrangement (110) and such that the first wing arrangement (110) is rotatable around the fuselage axis (101). The first wing arrangement (110) is adapted in such a way that, in a fixed-wing flight mode, the first wing arrangement (110) do not rotate around the fuselage axis (101). The first wing arrangement (110) is further adapted in such a way that, in a hover flight mode, the first wing arrangement (110) is tilted around the respective first rotary wing axis (111) with respect to its orientation in the fixed-wing flight mode and that the first wing arrangement (110) rotates around the fuselage axis (101). The aircraft further comprises an extendible lift increasing system which is arranged to the first wing arrangement (110) for selectively amending a lift area of the first wing arrangement (110) in the fixed-wing flight mode and the hover flight mode.

    Abstract translation: 本发明涉及一种飞行器，其包括机身（100），其包括机身轴线（101），第一机翼装置（110）和第二机翼装置（120）。 第一机翼装置（110）被安装到机身（100），使得第一机翼装置（110）围绕第一机翼装置（110）的第一旋转翼轴线（111）可倾斜，并且使得第一机翼装置 （110）能够围绕机身轴线（101）旋转。 第一机翼装置（110）以这种方式适配，使得在固定翼飞行模式中，第一机翼装置（110）不围绕机身轴线（101）旋转。 第一机翼装置（110）进一步适应于在悬停飞行模式中，第一机翼装置（110）围绕其相应的第一旋转翼轴线（111）相对于其固定方向的取向倾斜， 机翼飞行模式，并且第一机翼装置（110）围绕机身轴线（101）旋转。 该飞机还包括可伸缩提升增加系统，该系统布置在第一机翼装置（110）上，用于以固定翼飞行模式和悬停飞行模式选择性地修理第一机翼装置（110）的提升区域。

    AERIAL VEHICLE AND METHOD OF FLIGHT
    113.
    发明申请
    AERIAL VEHICLE AND METHOD OF FLIGHT 审中-公开
    空中客车和飞行方法

    公开(公告)号：WO2011117619A3

    公开(公告)日：2011-11-17

    申请号：PCT/GB2011050562

    申请日：2011-03-22

    Applicant: ATHENE WORKS LTD ,  DEAKIN NICHOLAS JAMES

    Inventor： DEAKIN NICHOLAS JAMES

    IPC: B64B1/00

    CPC classification number: B64B1/02 ,  B64B1/08 ,  B64B1/10 ,  B64B1/12 ,  B64B1/14 ,  B64B1/20 ,  B64B1/38 ,  B64B1/64 ,  B64B2201/00 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/101 ,  B64C2201/122 ,  B64C2201/127 ,  B64C2201/165 ,  B64C2201/167 ,  H01Q1/36 ,  H01Q9/27

    Abstract: An aerial vehicle is described which comprises: a first compartment (13) for holding a lighter than air gas; a second compartment (6, 4) for holding atmospheric air and having an inlet and an outlet; a solar panel (41) for converting sunlight into electricity; a compressor (242) for pumping atmospheric air through the inlet into the second compartment; control means (1,3) for controlling the pitch and yaw of the vehicle; and a controller (209) for controlling the buoyancy of the vehicle via the compressor and the outlet such that the vehicle is either lighter than the surrounding air and rising or heavier than the surrounding air and falling, and for controlling the control means such that the rising and falling motion includes a horizontal component. In another embodiment the solar panel is replaced by an engine and a fuel tank for storing fuel for the engine is also provided. The aerial vehicle can remain airborne for extended periods by using buoyancy propulsion. In the embodiments including a solar panel, a system including a light transmission station may be provided to supply energy to the solar panel from the light transmission station rather than relying on the incident sunlight alone. A method of flight using buoyancy propulsion is also described.

    Abstract translation: 描述了一种飞行器，其包括：用于保持比气体气体轻的第一隔室（13）; 用于保持大气空气并具有入口和出口的第二隔间（6,4）; 用于将太阳光转换成电的太阳能电池板（41） 压缩机（242），用于将大气通过所述入口排入所述第二隔室; 控制装置（1,3），用于控制车辆的俯仰和偏航; 以及用于经由压缩机和出口控制车辆的浮力的控制器（209），使得车辆比周围空气要轻，并且比周围空气上升或者重，并且为了控制控制装置， 上升和下降运动包括水平分量。 在另一个实施例中，太阳能电池板被发动机代替，并且还提供了用于储存用于发动机的燃料的燃料箱。 航空器可以通过使用浮力推进长时间保持空中。 在包括太阳能电池板的实施例中，可以提供包括光传输站的系统，以从光传输站向太阳能电池板提供能量，而不是仅依赖于入射的太阳光。 还描述了使用浮力推进的飞行方法。

    AIRCRAFT AND METHOD FOR FOREST FIRE EXTINGUISHING
    114.
    发明申请
    AIRCRAFT AND METHOD FOR FOREST FIRE EXTINGUISHING 审中-公开
    飞机和森林灭火方法

    公开(公告)号：WO2009150478A4

    公开(公告)日：2010-03-04

    申请号：PCT/GR2009000037

    申请日：2009-06-10

    Applicant: KALIVAS IOANNIS

    Inventor： KALIVAS IOANNIS

    IPC: B64C39/02 ,  A62C3/02 ,  B64C27/20 ,  B64D1/16

    CPC classification number: B64C39/024 ,  A62C3/0207 ,  B64C27/20 ,  B64C2201/027 ,  B64C2201/048 ,  B64C2201/108 ,  B64D1/16

    Abstract: The new method used with the new aircraft for forest fire extinguishing is a concept which consists of a new means by which the new method of fire extinction, especially forested areas, will be applied and consists of an aircraft that will fly with the help of 4 turbine engines of vertical reaction and with the support of propellers it will transport to the fire front water and materials for extinguishment and due to its peculiar shape it will be able to remain close to the fire and combat it with water, with an impulsive force of large amounts of gas that exit from its turbine engines, amounts that will contain oxygen, as well as be enriched with carbon monoxide or other extinguishing material that it possesses and will lower the temperature locally with the air currents that will be produced. This construction allows small speeds, and even idling in the air, which benefits the purpose of the fire extinction and allows the aircraft to land in small areas or close to the fire without danger but also to escape immediately if the direction of the wind changes etc. It can constructed in small, medium, or large sizes.

    Abstract translation: 用于森林灭火新型飞机的新方法是一种概念，其中包括采用新的灭火方法，特别是森林地区的新手段，并将由飞机在4号的帮助下飞行 涡轮发动机的垂直反作用和螺旋桨的支撑，它将运输到火前的水和材料灭火，由于其特殊的形状，它将能够保持靠近火源并用水冲击，以冲击力 从涡轮发动机排出的大量气体，将含有氧气的量，以及富含一氧化碳或其拥有的其他灭火材料，并将随着将产生的气流局部降低温度。 这种结构允许小的速度，甚至在空中空转，这有利于灭火的目的，并允许飞机在小的地方或靠近火的地方登陆没有危险，但如果风的方向等等，也立即逃离 它可以以小，中或大尺寸构造。

    A SYSTEM FOR AIRBORNE LAUNCH OF AN AIRCRAFT FROM A LARGER CARRIER AIRCRAFT
    115.
    发明申请
    A SYSTEM FOR AIRBORNE LAUNCH OF AN AIRCRAFT FROM A LARGER CARRIER AIRCRAFT 审中-公开
    来自大型航空器飞机的AIRBORNE发射系统

    公开(公告)号：WO2002076826A1

    公开(公告)日：2002-10-03

    申请号：PCT/GB2002/000719

    申请日：2002-02-20

    Applicant: BAE SYSTEMS PLC ,  HARRISON, Richard, George

    Inventor： HARRISON, Richard, George

    IPC: B64D5/00

    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）是可拆卸地连接的，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），由此能够发射UAV，其与保持器（22）分离，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。

    DRONE ET ÉQUIPEMENT D'INTERVENTION AÉROPORTÉE ASSOCIÉ
    116.
    发明公开
    DRONE ET ÉQUIPEMENT D'INTERVENTION AÉROPORTÉE ASSOCIÉ 有权
    DRONE ETÉQUIPEMENTD'INTERVENTIONAÉROPORTÉEASSOCIÉ

    公开(公告)号：EP3233632A1

    公开(公告)日：2017-10-25

    申请号：EP15816171.1

    申请日：2015-12-18

    Applicant: DAE

    Inventor： DEMONFORT, Thierry

    IPC: B64C39/02 ,  B64D5/00

    CPC classification number: B64C39/026 ,  B64C2201/048 ,  B64C2201/082 ,  B64C2201/128 ,  B64C2201/141 ,  B64C2201/145 ,  B64C2201/185 ,  B64D5/00

    Abstract: The present invention relates; - to a drone comprising a fuselage (1) provided with carrying means (11, 12) capable of allowing a belly-to-ground flight position and an inverted flight position, at least one propulsion means (2), autonomous navigation instruments and an axial compartment (10) forming a recess incorporated into an upper part of the fuselage in order to receive a parachutist (h) in the lying position, avionics provided with programmable control means coupled to the autonomous navigation instruments and means for releasing said parachutist controlled by said avionics, characterised in that said release means are designed and intended to ensure the release of said parachutist in the inverted flight position, and, - to a piece of airborne intervention equipment.

    Abstract translation: 本发明涉及; - 包括机身（1）的无人机，所述机身（1）设置有能够允许腹部至地面飞行位置和倒飞位置的携带装置（11,12），至少一个推进装置（2），自主导航仪器和 （10）形成结合到机身上部中的凹部以便接纳躺卧位置的伞兵（h），配备有耦合到自主导航仪器的可编程控制装置的航空电子设备以及用于释放由所述控制装置控制的所述伞兵的装置 所述航空电子设备的特征在于，所述释放装置被设计并且旨在确保所述伞兵在所述倒转飞行位置中的释放，以及 - 至一件空中传播设备。

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