WO2019015129A1 - 一种便携式多旋翼无人机 - Google Patents

一种便携式多旋翼无人机 Download PDF

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Publication number
WO2019015129A1
WO2019015129A1 PCT/CN2017/105230 CN2017105230W WO2019015129A1 WO 2019015129 A1 WO2019015129 A1 WO 2019015129A1 CN 2017105230 W CN2017105230 W CN 2017105230W WO 2019015129 A1 WO2019015129 A1 WO 2019015129A1
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Prior art keywords
arm
arms
frame
portable multi
blade
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PCT/CN2017/105230
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English (en)
French (fr)
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袁泽昊
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袁泽昊
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Publication of WO2019015129A1 publication Critical patent/WO2019015129A1/zh

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U30/00—Means for producing lift; Empennages; Arrangements thereof
    • B64U30/20—Rotors; Rotor supports
    • B64U30/29—Constructional aspects of rotors or rotor supports; Arrangements thereof
    • B64U30/293—Foldable or collapsible rotors or rotor supports
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U10/00—Type of UAV
    • B64U10/10—Rotorcrafts
    • B64U10/13—Flying platforms
    • B64U10/16—Flying platforms with five or more distinct rotor axes, e.g. octocopters

Definitions

  • the utility model relates to the technical field of drones, in particular to a portable multi-rotor drone.
  • Unmanned Aerial Vehicle refers to an aircraft that does not carry an operator who can fly autonomously or remotely.
  • the multi-rotor drone is a special unmanned helicopter with three or more rotor shafts that rotates by the motor on each axle to drive the rotor to generate lift thrust by changing the relative speed between the different rotors.
  • the uniaxial propulsion force can be changed to control the trajectory of the aircraft.
  • the rotors of multi-rotor UAVs are mostly umbrella-folded. After the rotor is folded, the height of the aircraft is still limited by the length of the arm and the size of the center plate, resulting in a large volume after folding, which is not convenient to carry; the motor is at the lower end after the rotor is folded, and the motor and the blade easily touch the ground. It is easy to cause wear during transportation.
  • the object of the present invention is to provide a folding multi-rotor UAV, which solves the problem that the center plate of the existing multi-rotor UAV is large and the arm is long by using the technical solution provided by the utility model. It is not easy to carry, and the technical problem that the motor is located below when the motor is folded and the blade and the blade are easily worn during transportation.
  • a portable multi-rotor UAV comprising a frame mounted with a main control board and a plurality of arms uniformly mounted on the frame,
  • the end of the arm is provided with a motor and a blade
  • the arm includes a first arm, a second arm and a Y-shaped connecting member; one end of the first arm is pivotally connected to the frame And being foldable downward relative to a plane in which the frame is located, and the other end is fixed on one end of the connecting member; the number of the second arm is two, respectively pivoted to the connecting member
  • the motor is fixed to the end of the second arm; the two second arms can be folded back to each other, and the folding direction is directed toward the first arm.
  • the distance between the ends of the two adjacent second arms is greater than the diameter of the circle generated when the blade rotates.
  • the plane in which the first arm is folded is perpendicular to the plane generated by the rotation of the blade; the plane in which the second arm is folded is parallel to the plane generated by the rotation of the blade.
  • one end of the connecting member pivotally connected to the two second arms respectively forms a limiting block;
  • the limiting block has a tubular shape with a notch in the axial direction; the width of the notch is larger than the The width of the second arm; the limiting block is sleeved outside the deployed second arm.
  • an inner threaded sleeve is included; and an outer thread matching the inner thread sleeve is formed on an outer side wall of the limiting block.
  • the utility model changes the adjacent arm to the Y-folding machine arm through the Y-shaped connecting member, thereby solving the existing multi-rotor unmanned
  • the mechanical center plate is larger and the arm is longer, which is not convenient to carry.
  • the motor and the frame are at the same height after folding, the motor and the blade are not in contact with the ground, and the motor and the blade are solved during transportation.
  • Wear problems; and the connectors reduce the number of arms attached to the rack to half that of existing multi-rotor drones, increasing the effective electronics placement space and further reducing the size of the rack.
  • Figure 1 is a schematic structural view of an embodiment
  • Figure 2 is an enlarged view of a portion A of Figure 1;
  • Figure 3 is a schematic view showing the structure of the arm of the embodiment.
  • the multi-rotor UAV with folding structure after the rotor is folded, the height of the drone is still limited by the length of the arm and the size of the center plate, resulting in a large volume after folding, which is not convenient to carry; the motor is in the rotor after the rotor is folded At the lower end, the motor and the blade easily touch the ground and are prone to wear during transportation.
  • the present embodiment provides a portable multi-rotor UAV including a rack 10 mounted with a main control board and a plurality of arms 20 uniformly mounted on the rack 10 .
  • a motor 30 and a paddle 40 are provided at the end of the arm 20.
  • the three arms 20 are preferred embodiments, but the number of the arms 20 can be increased or decreased according to user requirements or processing requirements, as long as the number of the arms 20 is greater than or equal to two, and is evenly set in the machine.
  • the motor 30 at the end of the arm can be evenly distributed around the frame 10.
  • the arm 20 includes a first arm 21, a second arm 22, and a Y-shaped connecting member 23.
  • One end of the first arm 21 is pivotally connected to the frame 10 and can be folded downward relative to the plane in which the frame 10 is located; the other end is fixed to one end of the connecting member 23.
  • the number of the second arms 22 is two, which are respectively pivotally connected to the other ends of the connecting member 23.
  • the motor 30 is fixed to the end of the second arm 22.
  • the two second arms 22 can be folded back toward each other with the folding direction facing the first arm 21. Specifically, the plane in which the first arm 21 is folded is perpendicular to the plane generated by the rotation of the blade 40; the plane in which the second arm 22 is folded is parallel to the plane generated by the rotation of the blade 40.
  • the two second arms 22 are folded back and folded toward the first arm 21.
  • the motor 30 is close to the pivot point between the first arm 22 and the frame 10, and then The first arm 21 is folded downward, and after the folding, the connecting member 23 is under the frame 10 and is in contact with the ground, and the motor 30 is located above the connecting member 23 in a plane with the frame 10.
  • the portable multi-rotor UAV converts the adjacent arm into a Y-folding arm through the Y-shaped connecting member 23, thereby solving the problem that the existing multi-rotor UAV center plate is large and the arm is long.
  • the connector 23 reduces the number of arms connected to the rack to half that of the existing multi-rotor drone, increasing the effective electronic equipment placement space and further reducing the size of the rack.
  • the embodiment provides a portable multi-rotor UAV including a frame 10 on which a main control board is mounted and a plurality of arms 20 uniformly mounted on the frame 10, in the arm 20 A motor 30 and a paddle 40 are provided at the end.
  • the arm 20 also includes a first arm 21, a second arm 22, and a Y-shaped connector 23.
  • One end of the first arm 21 is pivotally connected to the frame 10 and can be folded downward relative to the plane in which the frame 10 is located; the other end is fixed to one end of the connecting member 23.
  • the number of the second arms 22 is two, which are respectively pivotally connected to the other ends of the connecting member 23.
  • the motor 30 is fixed to the end of the second arm 22.
  • the two second arms 22 can be folded back toward each other with the folding direction facing the first arm 21.
  • the present embodiment is different from the first embodiment in that the first arm 21 and the second machine are After the arms 22 are deployed, the distance between the ends of the adjacent two second arms 22 is greater than the diameter of the circle produced when the blades 40 rotate.
  • the embodiment provides a portable multi-rotor UAV including a frame 10 on which a main control board is mounted and a plurality of arms 20 uniformly mounted on the frame 10, in the arm 20 A motor 30 and a paddle 40 are provided at the end.
  • the arm 20 also includes a first arm 21 and a second arm 22 And a connecting member 23 in the shape of a Y.
  • One end of the first arm 21 is pivotally connected to the frame 10 and can be folded downward relative to the plane in which the frame 10 is located; the other end is fixed to one end of the connecting member 23.
  • the number of the second arms 22 is two, which are respectively pivotally connected to the other ends of the connecting member 23.
  • the motor 30 is fixed to the end of the second arm 22.
  • the two second arms 22 can be folded back toward each other with the folding direction facing the first arm 21.
  • the embodiment is different from the above embodiment in that the end of the connecting member 23 pivotally connected to the two second arms 22 respectively form a limiting block 231 .
  • the limiting block 231 has a tubular shape with a notch 232 in the axial direction, and the width of the notch 232 is larger than the width of the second arm 22 .
  • the limiting block 231 is sleeved outside the deployed second arm 22 . This configuration can limit the deployment angle of the second arm 22, thereby ensuring that the distance between the ends of the two second arms 22 is less than the diameter of the circle produced when the blade 40 is rotated.
  • an inner threaded sleeve 50 is sleeved on the outer side of the second arm 22, on the outer side wall of the limiting block 231.
  • An external thread 233 matching the inner threaded sleeve 50 is formed thereon.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Remote Sensing (AREA)
  • Toys (AREA)

Abstract

一种便携式多旋翼无人机，包括机架（10）以及若干个机臂（20），在机臂（20）的末端设置有电机（30）和桨叶（40），机臂（20）包括第一机臂（21）、第二机臂（22）和呈Y字形的连接件（23）；第一机臂（21）的一端枢接于机架（10）上，可相对于机架（10）所处的平面向下折叠；第二机臂（22）的数量为两根，分别枢接于连接件（23）的另外两端；电机（30）固定于第二机臂（22）的末端；两根第二机臂（22）可相互背向折叠，且折叠方向均朝向第一机臂（21）。该折叠式多旋翼无人机解决了现有多旋翼无人机中心板较大和机臂较长导致的不便于携带，以及折叠后电机位于下方导致电机和桨叶容易在运输过程中磨损的技术问题。

Description

一种便携式多旋翼无人机 技术领域
本实用新型涉及无人机技术领域，尤其涉及一种便携式多旋翼无人机。
背景技术
无人机简称UAV(Unmanned Aerial Vehicle)，指不载有操作人员可以自主飞行或遥控驾驶的飞行器。多旋翼无人机是一种具有三个及以上旋翼轴的特殊的无人驾驶直升机，其通过每个轴上的电动机转动，带动旋翼，从而产生升推力，通过改变不同旋翼之间的相对转速，可以改变单轴推进力的大小，从而控制飞行器的运行轨迹。
为了提高多旋翼无人机的便携性，多旋翼无人机的旋翼多采用伞型折叠结构。旋翼折叠后，飞行器高度仍受限于机臂的长度和中心板的大小，导致折叠后体积仍旧较大，不便于携带；旋翼折叠后电机处于下端，电机和桨叶容易触碰到地面，在运输过程中容易造成磨损。
实用新型内容
本实用新型的发明目的在于提供一种折叠式多旋翼无人机，采用本实用新型提供的技术方案解决了现有多旋翼无人机中心板较大和机臂较长导致的 不便于携带，以及折叠后电机位于下方导致电机和桨叶容易在运输过程中磨损的技术问题。
为了达到以上发明目的，本实用新型采用的技术方案为:一种便携式多旋翼无人机，包括安装有主控板的机架以及若干个均匀安装于所述机架上的机臂，在所述机臂的末端设置有电机和桨叶，所述机臂包括第一机臂、第二机臂和呈Y字形的连接件；所述第一机臂的一端枢接于所述机架上，可相对于所述机架所处的平面向下折叠，另一端固定于所述连接件的一端上；所述第二机臂的数量为两根，分别枢接于所述连接件的另外两端；所述电机固定于所述第二机臂的末端；两根所述第二机臂可相互背向折叠，且折叠方向均朝向所述第一机臂。
优选的，所述第一机臂和第二机臂展开后，相邻的两根所述第二机臂的末端之间的距离大于所述桨叶旋转时产生的圆的直径。
优选的，所述第一机臂折叠所处的平面与所述桨叶旋转产生的平面垂直；所述第二机臂折叠所处的平面与所述桨叶旋转产生的平面平行。
优选的，在所述连接件上与两根所述第二机臂枢接的一端分别形成有限位块；所述限位块呈沿轴向具有缺口的管状；所述缺口的宽度大于所述第二机臂的宽度；所述限位块套接于展开后的所述第二机臂外。
优选的，包括内螺纹套；在所述限位块的外侧壁上形成有与所述内螺纹套匹配的外螺纹。
由上可见，采用本实用新型实施例提供的技术方案具有以下有益效果，本实用新型通过Y字形的连接件将相邻的机臂改成Y型折叠机臂，解决了现有多旋翼无人机中心板较大和机臂较长导致的不便于携带的技术问题；同时由于折叠后电机与机架处于同一高度，使得电机与桨叶不与地面接触，解决了电机和桨叶在运输过程中磨损的问题；并且连接件使得与机架连接的机臂的数量减少为现有多旋翼无人机的一半，提升了有效的电子设备放置空间，进一步减小了机架的体积。
附图说明
为了更清楚地说明本实用新型实施例或现有技术中的技术方案，下面将对本实用新型实施例或现有技术的描述中所需要使用的附图作简单地介绍。显而易见地，下面描述中的附图仅仅是本实用新型的一部分实施例，对于本领域普通技术人员来讲，在不付出创造性劳动性的前提下，还可以根据这些附图获得其他的附图。
图1为实施例结构示意图；
图2为实施例图1中A处放大图；
图3为实施例机臂结构示意图。
具体实施方式
下面将结合本实用新型实施例中的附图，对本实用新型实施例中的技术方案进行清楚、完整地描述。显然，所描述的实施例仅仅是本实用新型一部分实施例，而不是全部的实施例。基于本实用新型中的实施例，本领域普通技术人员在没有作出创造性劳动前提下所获得的所有其他实施例，都属于本实用新型保护的范围。
实施例1
采用折叠结构的多旋翼无人机，旋翼折叠后，无人机的高度仍受限于机臂的长度和中心板的大小，导致折叠后体积仍旧较大，不便于携带；旋翼折叠后电机处于下端，电机和桨叶容易触碰到地面，在运输过程中容易造成磨损。
请参见图1，本实施例提供一种便携式多旋翼无人机，该便携式多旋翼无人机包括安装有主控板的机架10以及若干个均匀安装于机架10上的机臂20，在机臂20的末端设置有电机30和桨叶40。在本实施例中以3个机臂20为优选实施方式，但机臂20的数量可以根据用户要求或加工要求进行增减，只要机臂20的数量大于或等于2个，且均匀设于机架10上，使机臂末端的电机30能够均匀分布于机架10的四周即可。
请参见图2，为了解决上述技术问题，机臂20包括第一机臂21、第二机臂22和呈Y字形的连接件23。其中第一机臂21的一端枢接于机架10上，可相对于机架10所处的平面向下折叠；另一端固定于连接件23的一端上。第二机臂22的数量为两根，分别枢接于连接件23的另外两端。电机30固定于第二机臂22的末端。两根第二机臂22可相互背向折叠，且折叠方向均朝向第一机臂21。具体的，第一机臂21折叠所处的平面与桨叶40旋转产生的平面垂直；第二机臂22折叠所处的平面与桨叶40旋转产生的平面平行。
需要对机臂20进行折叠时，将两根第二机臂22相背且朝向第一机臂21折叠，折叠后电机30靠近第一机臂22与机架10之间的枢接点，再将第一机臂21向下折叠，折叠后连接件23处于机架10的下方，并与地面接触，电机30则与机架10成一平面位于连接件23的上方。
本实施例提供的便携式多旋翼无人机通过Y字形的连接件23将相邻的机臂改成Y型折叠机臂，解决了现有多旋翼无人机中心板较大和机臂较长导致的不便于携带的技术问题；同时由于折叠后电机30与机架10处于同一高度，使得电机30与桨叶40不与地面接触，解决了电机30和桨叶在运输过程中磨损的问题；并且连接件23使得与机架连接的机臂的数量减少为现有多旋翼无人机的一半，提升了有效的电子设备放置空间，进一步减小了机架的体积。
实施例2
本实施例提供一种便携式多旋翼无人机，该便携式多旋翼无人机包括安装有主控板的机架10以及若干个均匀安装于机架10上的机臂20，在机臂20的末端设置有电机30和桨叶40。机臂20同样包括第一机臂21、第二机臂22和呈Y字形的连接件23。其中第一机臂21的一端枢接于机架10上，可相对于机架10所处的平面向下折叠；另一端固定于连接件23的一端上。第二机臂22的数量为两根，分别枢接于连接件23的另外两端。电机30固定于第二机臂22的末端。两根第二机臂22可相互背向折叠，且折叠方向均朝向第一机臂21。
为了避免机臂20展开后，相邻两个桨叶40运转时会相互碰撞产生损坏，作为技术方案的进一步改进，本实施例与实施例1不同的是，第一机臂21和第二机臂22展开后，相邻的两根第二机臂22的末端之间的距离大于桨叶40旋转时产生的圆的直径。
实施例3
本实施例提供一种便携式多旋翼无人机，该便携式多旋翼无人机包括安装有主控板的机架10以及若干个均匀安装于机架10上的机臂20，在机臂20的末端设置有电机30和桨叶40。机臂20同样包括第一机臂21、第二机臂22 和呈Y字形的连接件23。其中第一机臂21的一端枢接于机架10上，可相对于机架10所处的平面向下折叠；另一端固定于连接件23的一端上。第二机臂22的数量为两根，分别枢接于连接件23的另外两端。电机30固定于第二机臂22的末端。两根第二机臂22可相互背向折叠，且折叠方向均朝向第一机臂21。
请参见图3，作为技术方案的进一步改进，本实施例与上述实施例不同的是，在连接件23上与两根第二机臂22枢接的一端分别形成有限位块231。限位块231呈沿轴向具有缺口232的管状，缺口232的宽度大于第二机臂22的宽度。限位块231套接于展开后的第二机臂22外。该结构能够对第二机臂22的展开角度起到限制作用，从而确保两个第二机臂22端部之间的距离小于桨叶40旋转时产生的圆的直径。
为了避免第二机臂22在无人机运转时产生松动，造成桨叶40之间发生碰撞，还在第二机臂22的外侧套接有内螺纹套50，在限位块231的外侧壁上形成有与内螺纹套50匹配的外螺纹233。第二机臂22展开后，内螺纹套50旋进限位块231的外螺纹233上，将缺口232填补完整，使第二机臂22固定在连接件23的端部。
以上所述的实施方式，并不构成对该技术方案保护范围的限定。任何在 上述实施方式的精神和原则之内所作的修改、等同替换和改进等，均应包含在该技术方案的保护范围之内。

Claims (5)

  1. 一种便携式多旋翼无人机，包括安装有主控板的机架以及若干个均匀安装于所述机架上的机臂，在所述机臂的末端设置有电机和桨叶，其特征在于：所述机臂包括第一机臂、第二机臂和呈Y字形的连接件；所述第一机臂的一端枢接于所述机架上，可相对于所述机架所处的平面向下折叠，另一端固定于所述连接件的一端上；所述第二机臂的数量为两根，分别枢接于所述连接件的另外两端；所述电机固定于所述第二机臂的末端；两根所述第二机臂可相互背向折叠，且折叠方向均朝向所述第一机臂。
  2. 根据权利要求1所述的一种便携式多旋翼无人机，其特征在于：所述第一机臂和第二机臂展开后，相邻的两根所述第二机臂的末端之间的距离大于所述桨叶旋转时产生的圆的直径。
  3. 根据权利要求2所述的一种便携式多旋翼无人机，其特征在于：所述第一机臂折叠所处的平面与所述桨叶旋转产生的平面垂直；所述第二机臂折叠所处的平面与所述桨叶旋转产生的平面平行。
  4. 根据权利要求3所述的一种便携式多旋翼无人机，其特征在于：在所述连接件上与两根所述第二机臂枢接的一端分别形成有限位块；所述限位块呈沿轴向具有缺口的管状；所述缺口的宽度大于所述第二机臂的宽度；所述限位块套接于展开后的所述第二机臂外。
  5. 根据权利要求4所述的一种便携式多旋翼无人机，其特征在于：包括内螺纹套；在所述限位块的外侧壁上形成有与所述内螺纹套匹配的外螺纹。
PCT/CN2017/105230 2017-07-18 2017-10-01 一种便携式多旋翼无人机 WO2019015129A1 (zh)

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CN204895844U (zh) * 2015-06-01 2015-12-23 深圳市大疆创新科技有限公司 多旋翼无人机
CN205738077U (zh) * 2016-05-05 2016-11-30 上海东古航空科技有限公司 一种用于折叠式多旋翼无人机的折叠机构
WO2016192021A1 (en) * 2015-06-01 2016-12-08 SZ DJI Technology Co., Ltd. Systems and methods for foldable arms
CN205837172U (zh) * 2016-07-13 2016-12-28 江苏数字鹰科技发展有限公司 无人机用折叠机构以及具有折叠机构的无人机
CN206125436U (zh) * 2016-08-31 2017-04-26 长沙拓航农业科技有限公司 异型多旋翼植保无人机
CN106741841A (zh) * 2017-01-25 2017-05-31 东莞产权交易中心 一种植保无人机

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CN204895844U (zh) * 2015-06-01 2015-12-23 深圳市大疆创新科技有限公司 多旋翼无人机
WO2016192021A1 (en) * 2015-06-01 2016-12-08 SZ DJI Technology Co., Ltd. Systems and methods for foldable arms
CN205738077U (zh) * 2016-05-05 2016-11-30 上海东古航空科技有限公司 一种用于折叠式多旋翼无人机的折叠机构
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CN106741841A (zh) * 2017-01-25 2017-05-31 东莞产权交易中心 一种植保无人机

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