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    AIRCRAFT
    191.
    发明公开
    AIRCRAFT 审中-公开
    飞机

    公开(公告)号：EP3209559A1

    公开(公告)日：2017-08-30

    申请号：EP15851788.8

    申请日：2015-10-20

    Applicant: Hohenthal, Markus

    Inventor： Hohenthal, Markus

    IPC: B64C29/02 ,  B64C39/02 ,  B64D27/24

    CPC classification number: B64C29/02 ,  B64C39/024 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/088 ,  B64C2201/104 ,  B64D27/24

    Abstract: An electrically powered vertical takeoff and vertical landing (VTOL) aircraft, which comprises at least two main propellers, wherein the main propellers are adapted to generate at least 70% of the aircraft propulsion. The aircraft also comprises at least one adjustment propeller, which has its propeller slipstream adapted to produce a torque relative to a first axis or the first and second axes with respect to a fuselage of the aircraft for turning the aircraft relative to said first axis or said first and second axes. In addition, not less than 35%, but not more than 85%, of the aircraft's mass is adapted to lie, during takeoff and/or landing, on a rear side of a propeller line of said main propellers with respect to a nose of the aircraft.

    Abstract translation: 一种电动垂直起飞和垂直着陆（VTOL）飞机，其包括至少两个主推进器（101a，101b），其中主推进器适于产生飞机推进的至少70％。 飞机还包括至少一个调节螺旋桨（101a，101b，102），其具有适于相对于第一轴线（103）或第一和第二（104）轴线产生扭矩（113,114,115）的螺旋桨滑流， 轴相对于飞行器的机身（119）相对于所述第一轴线或所述第一和第二轴线转动飞机。 此外，飞机质量的不少于35％但不多于85％适于在起飞和/或着陆期间位于所述主螺旋桨的螺旋桨管线（108）的后侧（109）上 相对于飞机的鼻子（111）。

    SENKRECHTSTARTFÄHIGES FLUGGERÄT
    192.
    发明公开
    SENKRECHTSTARTFÄHIGES FLUGGERÄT 审中-公开
    SENKRECHTSTARTFÄHIGESFLUGGERÄT

    公开(公告)号：EP3038913A1

    公开(公告)日：2016-07-06

    申请号：EP14756074.2

    申请日：2014-08-29

    Applicant: Airbus Defence and Space GmbH ,  Steinbeis Flugzeug- und Leichtbau GmbH

    Inventor： JUDAS, Michael ,  STRATENBERG, Friederike ,  VAN TOOR, Jan ,  SCHOLZ, Werner ,  KARRAIS, Berthold ,  STANGL, Wolfgang

    IPC: B64C29/00

    CPC classification number: B64C29/0025 ,  B64C3/38 ,  B64C5/08 ,  B64C27/08 ,  B64C27/473 ,  B64C39/024 ,  B64C39/08 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/165 ,  B64D27/02 ,  B64D27/24 ,  B64D2027/026

    Abstract: The invention relates to an aircraft (1) which can both take off and land vertically and can hover and also fly horizontally at a high cruising speed. The aircraft (1) has a support structure (27), a wing structure (15), at least three and preferably at least four lifting rotors (5) and at least one thrust drive (9). The wing structure (15) is designed to generate a lifting force for the aircraft during horizontal motion. To achieve this the wing structure (15) has at least one mainplane (3) provided with a profile that generates dynamic lift. The wing structure (15) is preferably designed as a tandem wing structure. Each of the lifting rotors (5) is fixed to the support structure (27), has a propeller (7) and is designed to generate a lifting force for the aircraft (1) by means of a rotation of the propeller (7), said force acting in a vertical direction. The thrust drive (9) is designed to generate a thrust force on the support structure (27), said force acting in a horizontal direction. The lifting rotors (5) can have a simple construction, i.e. they can have a simple rigid propeller for example, and a vertical take-off or hovering of the aircraft can be controlled, in a similar manner to quadcopters, by a simple control of the speeds of the lifting rotors. High cruising speeds can be achieved as a result of the additional horizontally acting thrust drive (9).

    Abstract translation: 本发明涉及一种能够垂直起降的飞机（1），并且能够以高巡航速度悬停和水平飞行。 飞机（1）具有支撑结构（27），机翼结构（15），至少三个，优选至少四个升力转子（5）和至少一个推力驱动器（9）。 机翼结构（15）被设计成在水平运动期间为飞机产生提升力。 为了实现这一点，机翼结构（15）具有至少一个主平面（3），该主平面设有产生动态升力的轮廓。 机翼结构（15）优选设计为串联机翼结构。 每个提升转子5固定在支撑结构27上并具有螺旋桨7并且设计成通过螺旋桨7的旋转产生用于飞机1的提升力， 所述力沿垂直方向作用。 推力驱动器（9）被设计成在支撑结构（27）上产生推力，所述力沿水平方向作用。 提升转子（5）可以具有简单的构造，即例如它们可以具有简单的刚性螺旋桨，并且可以通过简单地控制飞行器的类似方式来控制飞行器的垂直起飞或悬停，这与四轴飞行器类似 提升转子的速度。 由于额外的水平作用推力驱动（9），可实现较高的巡航速度。

    CONVERTIPLANE WITH NEW AERODYNAMIC AND TECHNICAL SOLUTIONS WHICH MAKE THE AIRCRAFT SAFE AND USABLE
    193.
    发明公开
    CONVERTIPLANE WITH NEW AERODYNAMIC AND TECHNICAL SOLUTIONS WHICH MAKE THE AIRCRAFT SAFE AND USABLE 审中-公开
    新的空气动力学和安全性和易用性的技术解决方案可换股PLANE

    公开(公告)号：EP3033272A1

    公开(公告)日：2016-06-22

    申请号：EP14784533.3

    申请日：2014-08-07

    Applicant: UNIT 1SRL

    Inventor： GIOVENGA, Pietro

    IPC: B64C29/00 ,  B64D27/08 ,  B64C3/38 ,  B64C3/54

    CPC classification number: B64C29/0033 ,  B64C3/385 ,  B64C3/54 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/162 ,  B64D27/08 ,  Y02T50/14

    Abstract: A convertiplane has the ability to take off like a helicopter and then fly horizontally like a conventional aircraft. The aircraft includes a variable incidence front wing of variable span located below the fuselage and mounted on a structure in the form of a venturi tube, a rear wing having two propellers for controlling the stability of the vehicle in pitch and roll installed therein, two counter-rotating, pivotally mounted ducted propellers equipped with four flaps orthogonal to each other provided on the sides of the cockpit, engines placed behind the cockpit close to the center of gravity, a static balancing system for controlling the center of gravity of the aircraft consisting of a weight placed in the lower part of the fuselage, self-propelled on the track rack longitudinally to the fuselage, and a digital flight control system.

    Vertically landing aircraft
    194.
    发明公开
    Vertically landing aircraft 审中-公开
    Vertikal地产Flugzeug

    公开(公告)号：EP2927122A1

    公开(公告)日：2015-10-07

    申请号：EP15151731.5

    申请日：2015-01-20

    Applicant: The Boeing Company

    Inventor： Newman, Daniel Ira ,  Lacy, Roger W. ,  Preator, Robin M. ,  Gianopulos, Elia N. ,  Ziegenbein, Perry

    IPC: B64C29/00

    CPC classification number: B64C27/26 ,  B64C27/28 ,  B64C29/0008 ,  B64C29/0025 ,  B64C29/0033 ,  B64C2201/021 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/162

    Abstract: An aircraft (10) takes off, lands, or hovers with at least one wing-mounted thrust-producing device (12) attached to at least one wing (16) of the aircraft and at least two fuselage-mounted thrust-producing devices (18) attached to a fuselage of the aircraft both providing vertical thrust. The aircraft (10) is flown while the at least one wing-mounted thrust-producing device (12) provides horizontal thrust and with the at least two fuselage-mounted thrust-producing devices (18) not providing any thrust.

    Abstract translation: 飞机（10）起飞，降落或悬停，其中至少有一个安装在飞行器的至少一个翼（16）上的机翼安装推力产生装置（12）和至少两个机身安装的推力产生装置 18）附在机身的机身上，提供垂直推力。 飞行器（10）飞行，而至少一个机翼安装的推力产生装置（12）提供水平推力并且至少两个机身安装的推力产生装置（18）不提供任何推力。

    AIRCRAFT WITH DETACHABLE WINGS
    195.
    发明公开
    AIRCRAFT WITH DETACHABLE WINGS 有权
    FLUGZEUG MIT ABNEHMBARENFLÜGELN

    公开(公告)号：EP2903892A1

    公开(公告)日：2015-08-12

    申请号：EP13763040.6

    申请日：2013-09-13

    Applicant: Sensefly S.A.

    Inventor： BEYELER, Antoine ,  KLAPTOCZ, Adam ,  ROBERTS, James F. ,  ZIMMERMANN, Loic ,  ZUFFEREY, Jean-Christophe ,  LAZZARATTO-PINÖSCH, Andreas

    IPC: B64C1/26

    CPC classification number: B64C1/26 ,  B64C39/024 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/086 ,  B64C2201/104 ,  B64C2201/162 ,  B64C2201/187 ,  B64C2201/20

    Abstract: This invention relates to a connection set that is used to attach and transfer force and torque between a wing (2a, 2b), comprising a lifting surface and a control surface (9) connected together by a hinge, and the central body (1) of an aircraft, which contains a servo-motor (10) used for actuating said control surface (9). The wing (2a, 2b) is connected to the central body (1) using a connection set comprised of two components. First, an attachment mechanism (3, 4, 5, 6) is used to align the wings (2a, 2b) relative to the central body (1) and to transfer the aerodynamic forces acting on the wing (2a, 2b) to the central body (1), preventing the wing (2a, 2b) from bending at its connection point. Second, a torque coupling mechanism (7, 8) is used to actuate the control surfaces that are present on the wings using servomotors (10) that are embedded within the central body (1). The connection set is engaged and disengaged using a single motion and does not require additional connection of electrical cables or mechanical fixations.

    Abstract translation: 本发明涉及一种用于在包括提升表面和通过铰链连接在一起的控制表面（9）的翼（2a，2b）之间附接和传递力和扭矩的连接组，以及中心体（1） 其包含用于致动所述控制表面（9）的伺服电动机（10）。 翼（2a，2b）使用由两个部件组成的连接组件连接到中心体（1）。 首先，使用附接机构（3,4,5,6）来相对于中心体（1）对准翼（2a，2b）并将作用在机翼（2a，2b）上的空气动力传递到 中心体（1），防止机翼（2a，2b）在其连接点处弯曲。 第二，扭矩联接机构（7,8）用于使用嵌入在中心体（1）内的伺服电动机（10）致动存在于机翼上的控制表面。 连接组使用单一动作进行接合和分离，不需要额外连接电缆或机械固定。

    Unmanned aerial vehicle
    196.
    发明公开
    Unmanned aerial vehicle 审中-公开
    Unbemanntes Luftfahrzeug

    公开(公告)号：EP2902319A1

    公开(公告)日：2015-08-05

    申请号：EP14382029.8

    申请日：2014-01-30

    Applicant: The Boeing Company

    Inventor： Criado, Alfredo ,  Kawiecki, Grzegorz M. ,  Valero, Omar

    IPC: B64C39/02 ,  B64C39/10

    CPC classification number: B64C39/024 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/165 ,  G01R31/021 ,  G06K9/00637 ,  H04N7/185 ,  Y02T50/12

    Abstract: An unmanned aerial vehicle adapted for hover and short/vertical take-off and landing (S/VTOL) is disclosed. The vehicle comprises: a body having an aspect-ratio less than two and having therein a payload volume, at least one propeller located forward of the body, at least one rudder. The body may have an inverse Zimmerman planform which provides lift as air flows across the body in horizontal flight/fixed wing mode, and further adapted such that during hover and/or short/vertical take-off and landing (S/VTOL) the vehicle operates as a rotorcraft with the body oriented with the at least one propeller substantially above the body. The vehicle is suited to a method of inspection, such as power line inspection where large distances can be analysed efficiently by flying in fixed wing mode, but by transitioning to hover mode allows detailed inspection of selected areas.

    Abstract translation: 公开了适用于悬停和短/垂直起降的无人驾驶飞行器（S / VTOL）。 该车辆包括：具有小于2的长宽比并且具有有效载荷体积的主体，位于身体前方的至少一个螺旋桨，至少一个舵。 身体可以具有逆Zimmerman平面图，其在水平飞行/固定翼模式中随着空气流过身体而提供电梯，并且还适于使得在悬停和/或短/垂直起飞和着陆期间（S / VTOL），车辆 作为旋翼航空器运行，其中身体以至少一个螺旋桨取向，大致在身体上方。 该车辆适用于检查方法，例如电力线检查，其中通过以固定翼模式飞行可以有效地分析大距离，但是通过转换到悬停模式允许对所选区域进行详细检查。

    UNMANNED AERIAL VEHICLE AND METHOD OF LAUNCHING
    197.
    发明公开
    UNMANNED AERIAL VEHICLE AND METHOD OF LAUNCHING 有权
    UNBEMANNTES LUFTFAHRZEUG UND ABSCHUSSVERFAHRENDAFÜR

    公开(公告)号：EP2874875A1

    公开(公告)日：2015-05-27

    申请号：EP13742690.4

    申请日：2013-07-19

    Applicant: Elson, Andrew Charles

    Inventor： Elson, Andrew Charles

    IPC: B64D5/00 ,  B64C39/02

    CPC classification number: B64D5/00 ,  B64B1/40 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/066 ,  B64C2201/082 ,  B64C2201/104 ,  B64C2201/122 ,  B64C2201/123 ,  B64C2201/162 ,  B64C2201/187 ,  B64D2211/00

    Abstract: A method of launching a powered unmanned aerial vehicle, the method comprising lifting the vehicle by attachment to a lighter-than-air carrier from a substantially ground-level location to an elevated altitude, wherein the vehicle is prevented from entering its flight mode during ascent, causing the vehicle to detach from the carrier while the velocity of the vehicle relative to the carrier is substantially zero, the vehicle thereafter decreasing in altitude as it accelerates to a velocity where it is capable of preventing any further descent and can begin independent sustained flight.

    Abstract translation: 一种在至少13000米的高度上发射供电的无人驾驶飞行器的方法，所述方法包括通过将空载承载器从基本上地平面的位置附近提升到升高的高度，使得车辆 当车辆相对于承运人的速度基本上为零时，车辆离开载体，然后车辆随着其高度减小到能够防止任何进一步下降并且可以开始独立的持续飞行的速度。

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