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    AIRCRAFT HAVING A VERSATILE PROPULSION SYSTEM
    142.
    发明公开
    AIRCRAFT HAVING A VERSATILE PROPULSION SYSTEM 审中-公开
    飞机具有多功能推进系统

    公开(公告)号：EP3263456A1

    公开(公告)日：2018-01-03

    申请号：EP17179010.8

    申请日：2017-06-30

    Applicant: Bell Helicopter Textron Inc.

    Inventor： OLDROYD, Paul K ,  McCULLOUGH, John Richard

    IPC: B64C39/02 ,  B64C29/00 ,  B64D27/06 ,  B64D27/24 ,  B64D31/00 ,  B64D35/08 ,  B64D27/02 ,  B64D27/26

    CPC classification number: B64D27/12 ,  B64C11/46 ,  B64C29/0033 ,  B64C39/024 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/086 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2211/00 ,  B64D27/06 ,  B64D27/24 ,  B64D27/26 ,  B64D31/00 ,  B64D35/08 ,  B64D2027/026 ,  B64D2027/262 ,  Y02T50/62

    Abstract: An aircraft (10) having a vertical takeoff and landing fight mode and a forward flight mode. The aircraft (10) includes an airframe (12) and a versatile propulsion system attached to the airframe (12). The versatile propulsion system includes a plurality of propulsion assemblies (26a-d). A flight control system (40) is operable to independently control the propulsion assemblies (26a-d). The propulsion assemblies (26a-d) are interchangeably attachable to the airframe (12) such that the aircraft (10) has a liquid fuel flight mode and an electric flight mode. In the liquid fuel flight mode, energy is provided to each of the propulsion assemblies (26a-d) from a liquid fuel. In the electric flight mode, energy is provided to each of the propulsion assemblies (26a-d) from an electric power source.

    Abstract translation: 一种具有垂直起降战斗模式和向前飞行模式的飞机（10）。 飞机（10）包括机身（12）和附接到机身（12）的多功能推进系统。 多功能推进系统包括多个推进组件（26a-d）。 飞行控制系统（40）可操作以独立地控制推进组件（26a-d）。 推进组件（26a-d）可互换地附连到机身（12），使得飞机（10）具有液体燃料飞行模式和电动飞行模式。 在液体燃料飞行模式中，能量从液体燃料提供给每个推进组件（26a-d）。 在电动飞行模式中，能量从电源被提供给每个推进组件（26a-d）。

    VEHICULE AERIEN LEGER SANS EQUIPAGE A DECOLLAGE VERTICAL
    144.
    发明公开
    VEHICULE AERIEN LEGER SANS EQUIPAGE A DECOLLAGE VERTICAL 审中-公开

    公开(公告)号：EP3230161A1

    公开(公告)日：2017-10-18

    申请号：EP15808600.9

    申请日：2015-12-11

    Applicant: Université Pierre et Marie Curie - UPMC ,  Centre National de la Recherche Scientifique

    Inventor： MORIN, Pascal ,  GASTE, Olivier ,  PHUNG, Duc-Kien

    IPC: B64C3/38 ,  B64C27/22 ,  B64C29/00

    CPC classification number: B64C29/0025 ,  B64C3/385 ,  B64C13/28 ,  B64C27/26 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/165 ,  Y02T50/14

    Abstract: The disclosure thus relates to a light unmanned vertical takeoff aerial vehicle (1) which comprises at least two fixed coplanar propulsion devices (7) and at least one wing (3) providing the drone (1) with lift. The coplanar propulsion devices (7) and the wing (3) are each arranged on the framework (10) of the drone (1) such that the plane of the chord of the profile of the wing (3) is substantially parallel to the plane defined by the two coplanar propulsion devices (7). The wing (3) is capable of a pivoting movement with respect to the framework (10) about an axis parallel to the pitch axis of the drone (1). The disclosure also relates to a method for controlling a light unmanned aerial vehicle (1) like the one described hereinabove, which involves a step of controlling the orientation of the wing (3), which uses at least one parameter pertaining to the flight of the drone (1).

    Abstract translation: 因此，本公开涉及一种轻型无人垂直起飞架空飞行器（1），其包括至少两个固定共面推进装置（7）和至少一个提供无人驾驶飞机（1）的升降机翼（3）。 共面推进装置（7）和机翼（3）分别布置在无人驾驶飞机（1）的框架（10）上，使得机翼（3）的轮廓翼弦的平面基本平行于平面 由两个共面推进装置（7）限定。 机翼（3）能够围绕平行于无人机（1）的俯仰轴线的轴线相对于框架（10）枢转运动。 本公开还涉及一种用于控制如上文所述的轻型无人驾驶飞行器（1）的方法，其包括控制机翼（3）的方位的步骤，该方法使用至少一个与飞行器 无人机（1）。

    HIGH SPEED MULTI-ROTOR VERTICAL TAKEOFF AND LANDING AIRCRAFT
    145.
    发明公开
    HIGH SPEED MULTI-ROTOR VERTICAL TAKEOFF AND LANDING AIRCRAFT 审中-公开
    高速多转子垂直起飞和着陆飞机

    公开(公告)号：EP3224140A1

    公开(公告)日：2017-10-04

    申请号：EP15862818.0

    申请日：2015-10-28

    Applicant: Xcraft Enterprises, LLC

    Inventor： CLARIDGE, Jerry, Daniel ,  MANNING, Charles, Fischer

    IPC: B64C29/02

    CPC classification number: B64C29/02 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/104 ,  B64C2201/108

    Abstract: This disclosure is generally directed to a High Speed vertical takeoff and landing (VTOL) aircraft that includes fixed wing flight capabilities. The High Speed VTOL aircraft may include at least two thrust producing rotors located equidistant from a longitudinal axis of the aircraft on a main wing, and at least two thrust producing rotors located equidistant from a longitudinal axis of the aircraft on a vertical wing. The rotors may be driven by electric motors. However, other power sources may be used such as combustion or hybrid engines. By adjusting the speed and/or the pitch of the rotors, the aircraft can transition from a vertical flight configuration to a horizontal flight configuration and back.

    Abstract translation: 本公开总体上针对包括固定机翼飞行能力的高速垂直起飞和降落（VTOL）飞行器。 高速VTOL飞机可以包括至少两个与主飞行器上的飞行器的纵向轴线等距离的推力产生转子，以及至少两个与飞行器的纵向轴线在垂直翼上等距的推力产生转子。 转子可以由电动机驱动。 但是，可以使用其他动力源，例如燃烧或混合动力发动机。 通过调整转子的速度和/或俯仰角，飞机可以从垂直飞行形态转变为水平飞行形态并返回。

    PROPULSION SYSTEM
    146.
    发明公开
    PROPULSION SYSTEM 审中-公开
    推进系统

    公开(公告)号：EP3174787A1

    公开(公告)日：2017-06-07

    申请号：EP15827418.3

    申请日：2015-07-28

    Applicant: Israel Aerospace Industries Ltd.

    Inventor： REGEV, Eyal

    IPC: B64C27/00 ,  B64C27/02 ,  B64C29/00 ,  F02B73/00

    CPC classification number: B64C29/0033 ,  B64C27/28 ,  B64C39/024 ,  B64C2201/042 ,  B64C2201/104 ,  B64C2201/108 ,  B64D27/24 ,  B64D35/02 ,  B64D35/08 ,  B64D2027/026 ,  F02B61/04 ,  F02B73/00 ,  Y02T50/64

    Abstract: A propulsion system is provided, including a first propulsion unit, a second propulsion unit, a rotor, a first coupling and a second coupling. The first propulsion unit is configured for being fixedly mounted to an airframe. The rotor is configured for being pivotably mounted with respect to the first propulsion unit to allow selectively pivoting of the rotor from a horizontal mode to a vertical mode. The first coupling is configured for selectively coupling and decoupling the rotor with respect to the first propulsion unit. The second coupling is configured for selectively coupling and decoupling the rotor with respect to the second propulsion unit, independently of the first coupling.

    Abstract translation: 提供推进系统，其包括第一推进单元，第二推进单元，转子，第一联接件和第二联接件。 第一推进单元构造成用于固定地安装到机身。 转子构造成相对于第一推进单元可枢转地安装，以允许转子从水平模式选择性地枢转到垂直模式。 第一联接器构造成用于选择性地将转子相对于第一推进单元联接和脱开。 第二联接器构造成独立于第一联接器选择性地将转子相对于第二推进单元联接和分离。

    AN UNMANNED AERIAL VEHICLE
    148.
    发明公开
    AN UNMANNED AERIAL VEHICLE 有权
    UNBEMANNTES LUFTFAHRZEUG

    公开(公告)号：EP3087003A1

    公开(公告)日：2016-11-02

    申请号：EP13900333.9

    申请日：2013-12-24

    Applicant: Singapore Technologies Aerospace Ltd

    Inventor： CHAN, Keen Ian

    IPC: B64C27/08 ,  B64C27/10 ,  B64C29/02 ,  B64C25/32 ,  B64C39/10 ,  B64C11/46 ,  B64C39/02 ,  A63H27/127 ,  A63H27/133 ,  A63H27/18

    CPC classification number: B64C29/02 ,  A63H27/12 ,  B64C11/48 ,  B64C27/08 ,  B64C27/10 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/122 ,  B64C2201/141

    Abstract: An unmanned aerial vehicle (UAV) capable of vertical and horizontal flight modes, a method of assembling a UAV, and a kit of parts for assembling a UAV. The UAV comprises an elongated wing structure having an elongated axis along the longest dimension of the elongated wing structure, the elongated wing structure having a middle location at a substantially halfway point; a connecting structure extending substantially perpendicularly from the elongated wing structure, the connecting structure being offset from the middle location of the elongated wing structure at a first position along the elongated axis; and at least three sets of propellers, wherein at least two sets of propellers are mounted on the connecting structure, and wherein at least one set of propellers is mounted at a second position offset from the middle location in an opposite direction away from the connecting structure.

    Abstract translation: 一种能够进行垂直和水平飞行模式的无人驾驶飞行器（UAV），组装无人机的方法以及组装无人机的零件套件。 无人机包括细长机翼结构，其具有沿着细长机翼结构的最长尺寸的细长轴线，细长机翼结构在大致中途点处具有中间位置; 所述连接结构从所述细长翼结构基本上垂直延伸，所述连接结构在所述细长轴线的第一位置处从所述细长翼结构的中间位置偏移; 和至少三组螺旋桨，其中至少两组螺旋桨安装在连接结构上，并且其中至少一组螺旋桨安装在远离连接结构的相反方向偏离中间位置的第二位置 。

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