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    Small pilotless plane
    181.
    发明专利
    Small pilotless plane 有权
    小型无人驾驶飞机

    公开(公告)号：JP2005067398A

    公开(公告)日：2005-03-17

    申请号：JP2003299869

    申请日：2003-08-25

    Applicant: Kawada Kogyo Kk ,  Masato Okamoto ,  正人 岡本 ,  川田工業株式会社

    Inventor： TANABE YASUTADA ,  TOTSUKA CHIHARU ,  AKASAKA TAKASHI ,  OKAMOTO MASATO

    IPC: B64C39/02 ,  B64C39/10

    CPC classification number: A63H27/02 ,  B64C39/028 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/165 ,  Y10S244/903

    Abstract: PROBLEM TO BE SOLVED: To realize miniaturization and light weight of a small pilotless plane suitable for hand throw staring or the like and portable by one person. SOLUTION: The small pilotless plane is provided with: all flying wing type main wing 1 being a camber wing type having an approximately flat lower surface, being thin toward a wing end in a tapered shape, having a wing front edge having a retreat angle and having a tailless type aerodynamincal surface of low aspect ratio; movable flaps 2 extending to both left and right sides at a rear edge part of the main wing over the approximately whole width and having a camber angle in at least horizontal flying; vertical stabilizer plates 3 arranged at both ends of the main wing; and two propellers 5 arranged on an upper surface of the main wing. COPYRIGHT: (C)2005,JPO&NCIPI

    Abstract translation: 要解决的问题：实现适合于手扔等的便携式的小型无人驾驶飞机的小型化和轻量化。

    解决方案：小型无人驾驶飞机设有：所有飞翼型主翼1是具有大致平坦的下表面的外倾翼型，朝向翼尖端呈锥形减薄，具有翼前边缘，其具有 具有低长宽比的无尾型气蚀表面; 在主翼翼的后边缘部分的大致整个宽度上延伸到左右两侧的活动翼片2和至少水平飞行的外倾角; 布置在主翼两端的垂直稳定板3; 以及布置在主翼的上表面上的两个螺旋桨5。 版权所有（C）2005，JPO＆NCIPI

    Unmanned helicopter and its take-off and landing method
    182.
    发明专利
    Unmanned helicopter and its take-off and landing method 有权

    公开(公告)号：JP2004130852A

    公开(公告)日：2004-04-30

    申请号：JP2002295174

    申请日：2002-10-08

    Applicant: Fuji Heavy Ind Ltd ,  富士重工業株式会社

    Inventor： YAMANE AKIHIRO

    IPC: B64C13/20 ,  B64C27/04 ,  B64C39/02 ,  G05D1/06 ,  G05D1/08

    CPC classification number: B64C13/20 ,  B64C39/024 ,  B64C2201/024 ,  B64C2201/108 ,  B64C2201/141 ,  B64C2201/165 ,  G05D1/0669 ,  G05D1/0676

    Abstract: PROBLEM TO BE SOLVED: To provide a take-off and landing method for an unmanned helicopter to fly autonomously without requiring any maneuver command from above, capable of accomplishing an automatic safe take-off and landing and suppressing the cost likely to increase for building a control system, whereby it is possible to achieve an automatic safe taking-off and an automatic safe landing.
    SOLUTION: The unmanned helicopter 20 is equipped with an altitude controlling means to control the altitude of the fuselage by giving a command for the collective pitch steering angle on the basis of an altitude change rate command etc., a take-off means which makes taking-off of the fuselage in the course of increasing the collective pitch steering angle without making the altitude control by the altitude controlling means upon receiving the take-off start command from the ground and starts the altitude control by the altitude control means after raising to the first altitude, and a descending means which descends the fuselage to the second altitude in the course of altering the descending rate command of the altitude controlling means and descends the fuselage from the second altitude to the ground by giving a descend rate command smaller than the descend rate command till the second altitude to the altitude controlling means.
    COPYRIGHT: (C)2004,JPO

    ROTATING PROPROTOR ARRANGEMENT FOR A TILTROTOR AIRCRAFT
    187.
    发明公开
    ROTATING PROPROTOR ARRANGEMENT FOR A TILTROTOR AIRCRAFT 审中-公开
    转向架飞行器的旋转传动装置

    公开(公告)号：EP3299290A1

    公开(公告)日：2018-03-28

    申请号：EP16206787.0

    申请日：2016-12-23

    Applicant: Bell Helicopter Textron Inc.

    Inventor： IVANS, Steven Ray ,  ROSS, Brent Chadwick

    IPC: B64C29/00

    CPC classification number: B64C29/0033 ,  B64C3/18 ,  B64C39/024 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/165 ,  B64D27/02 ,  B64D33/02 ,  B64D33/04 ,  B64D35/04 ,  B64D35/08 ,  F16H1/203 ,  F16H35/008

    Abstract: A propulsion system includes an engine (116) disposed within a fuselage (102), a first gearbox (130) coupled to the engine (116), a wing member having an upper wing skin and torque box formed by a first rib (172), a second rib (174), a first spar (176) and second spar (178), a drive shaft (132) coupled to the first gearbox (126) and disposed within the wing member, a second gear box (134) coupled to the drive shaft (132) and disposed outboard from the second rib (174) or inboard from the first rib (172), and a rotatable proprotor (106) coupled to the second gear box (134). The rotatable proprotor (106) includes a plurality of rotor blades (114), a rotor mast (140) having a mast axis of rotation (180), and a proprotor gearbox (136) coupled to the rotor mast (140). The proprotor gearbox (136) is rotatable about a conversion axis (156), which intersects with the mast axis of rotation (180) at a point within a central region of the torque box and above the upper wing skin.

    Abstract translation: 推进系统包括布置在机身（102）内的发动机（116），联接到发动机（116）的第一变速箱（130），具有上翼蒙皮和扭矩箱的翼构件，所述上翼蒙皮和扭矩箱由第一肋（172） ，第二肋（174），第一翼梁（176）和第二翼梁（178），联接到第一变速箱（126）并设置在翼构件内的驱动轴（132），联接第二齿轮箱 （132）并且设置在第二肋（174）的外侧或第一肋（172）的内侧，以及联接到第二齿轮箱（134）的可旋转的转速传感器（106）。 可旋转的旋翼桨叶（106）包括多个转子叶片（114），具有井架旋转轴线（180）的转子井架（140）以及联接到转子井架（140）的旋翼桨传动装置（136）。 推进器变速箱136可绕转换轴线156旋转，所述转换轴线156在转矩箱的中心区域内并且位于上机翼蒙皮上方的点处与转动轴线180相交。

    VEHICULE AERIEN LEGER SANS EQUIPAGE A DECOLLAGE VERTICAL
    190.
    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）。

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