WO2018049720A1 - 一种飞行器的机臂组件以及飞行器 - Google Patents

一种飞行器的机臂组件以及飞行器 Download PDF

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Publication number
WO2018049720A1
WO2018049720A1 PCT/CN2016/104593 CN2016104593W WO2018049720A1 WO 2018049720 A1 WO2018049720 A1 WO 2018049720A1 CN 2016104593 W CN2016104593 W CN 2016104593W WO 2018049720 A1 WO2018049720 A1 WO 2018049720A1
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Prior art keywords
opening
arm
air guiding
aircraft
arm housing
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English (en)
French (fr)
Inventor
冯建刚
王震
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SZ DJI Technology Co Ltd
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SZ DJI Technology Co Ltd
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/08—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
    • 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
    • B64U10/14—Flying platforms with four distinct rotor axes, e.g. quadcopters
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U20/00—Constructional aspects of UAVs
    • B64U20/90—Cooling

Definitions

  • the present invention relates to the field of aircraft, and more particularly to an arm assembly and an aircraft to which the arm assembly is applied.
  • the technical problem to be solved by the present invention is to provide an arm assembly of an aircraft and an aircraft, which can improve the heat dissipation capability of the aircraft.
  • a technical solution adopted by the present invention is to provide an arm assembly of an aircraft, the arm assembly including an arm housing and a wind guiding mechanism, and a cavity is formed in the arm housing.
  • the arm housing is provided with an opening, the opening is in communication with the cavity, and the air guiding mechanism is disposed on the arm housing and corresponds to the opening to pass the arm The air flow of the housing is guided.
  • the arm assembly is for supporting a propeller
  • the opening is formed at a lower side of the arm assembly to allow the external airflow generated by the propeller during rotation to pass through the opening and the machine
  • the cavities of the arm housing are in communication.
  • the air guiding mechanism is embedded in the opening.
  • the arm housing comprises an upper arm housing and a lower arm housing.
  • the air guiding mechanism includes at least one air guiding plate, and two ends of the air guiding plate are connected to the opening.
  • the opening has a length direction, the length direction is consistent with the length direction of the arm assembly, the air deflector has at least two, and the at least two air deflectors are spaced along the length direction. .
  • the opening comprises a first opening and a second opening, the first opening and the second opening are spaced apart, and the first opening and the second opening are along the middle of the arm
  • the air guiding mechanism includes a first air guiding portion and a second air guiding portion, the first air guiding portion is mounted on the first opening, and the second air guiding portion is mounted on On the second opening.
  • the air deflector is disposed obliquely with respect to a cross section of the opening.
  • the arm housing and the air guiding mechanism are provided with a fitting mechanism that cooperates with each other, and the air guiding mechanism is fixed to the arm housing.
  • the assembly mechanism includes a mounting hole and a mounting post, the mounting hole is disposed on the air guiding mechanism, the mounting post is disposed on the arm housing, and the mounting post is inserted into the mounting hole Further, the air guiding mechanism is fixed to the arm housing.
  • the present invention also provides an aircraft comprising a body, a propeller and the arm assembly according to any one of claims 1 to 10, wherein the body forms a cavity, the arm An assembly is coupled to the body, the cavity is in communication with the cavity, and the propeller is disposed at an end of the arm assembly.
  • the propeller is disposed on an upper side of the arm housing, and the air guiding mechanism is disposed on a lower side of the arm housing.
  • the air guiding mechanism is located between the propeller and the body.
  • the aircraft is a multi-rotor unmanned aerial vehicle.
  • the invention has the beneficial effects that the invention is different from the prior art, and the invention provides an arm housing and an air guiding mechanism on the arm assembly, wherein the arm housing is provided with an opening, and the air guiding mechanism is connected to the opening By guiding the external airflow entering the inside of the arm housing, the heat dissipation capability of the aircraft can be effectively improved.
  • FIG. 1 is a schematic view showing the assembly of a boom assembly according to a first embodiment of the present invention
  • FIG. 2 is a schematic exploded view of a boom assembly according to a first embodiment of the present invention
  • FIG. 3 is a schematic structural view of an air guiding mechanism in an arm assembly according to a first embodiment of the present invention
  • Figure 4 is a partial perspective view of the arm housing in the arm assembly according to the first embodiment of the present invention.
  • Figure 5 is an enlarged view of A of Figure 2;
  • Figure 6 is a schematic structural view of an aircraft according to a second embodiment of the present invention.
  • Figure 7 is a schematic diagram of airflow analysis of an aircraft in accordance with a second embodiment of the present invention.
  • FIG. 1 is a schematic view showing the assembly of the arm assembly 10 according to the first embodiment of the present invention
  • FIG. 2 is a disassembled schematic view of the arm assembly 10 according to the first embodiment of the present invention
  • the arm assembly 10 includes an arm housing 12 and an air guiding mechanism 14 (see FIG. 2) disposed inside the arm housing 12, and a cavity 121 is formed in the arm housing 12, and the arm housing is formed.
  • the body 12 is provided with an opening 122, and the opening 122 communicates with the cavity 121.
  • the arm assembly 10 is for supporting the propeller 20, and the opening 122 is opened on the lower side of the arm assembly 10 to allow the external airflow generated by the propeller 20 during the rotation to communicate with the cavity 121 of the arm housing 12 through the opening 122.
  • an external lower temperature airflow may enter the cavity 121 to reduce the temperature in the cavity 121, or an internal higher temperature airflow exiting the cavity 121, also causing the temperature in the cavity 121. Can be reduced.
  • the arm housing 12 includes an upper arm housing 124 and a lower arm housing 126 that cooperate with each other.
  • the upper arm housing 124 and the lower arm housing 126 abut each other to form a cavity 121.
  • the opening 122 is disposed on the lower arm housing 126 and located within the cavity 121.
  • FIG. 2 in order to clearly show the configuration inside the arm assembly 10, the upper arm housing 124 is removed.
  • an opening 122 is defined in the lower arm housing 126 to allow the screw
  • the external airflow generated by the propeller 20 during the rotation enters the inside of the arm housing 12 through the opening 122.
  • the propeller 20 and the opening 122 are respectively located on both sides of the arm housing 12.
  • the air guiding mechanism 14 is disposed inside the arm housing 12, optionally embedded in the hole wall of the opening 122, thereby guiding the external airflow entering the arm housing 12 through the opening 122. Specifically, the air guiding mechanism 14 is disposed at the opening 122 of the lower arm housing 126 and is located in the cavity 121 formed by the upper arm housing 124 and the lower arm housing body 126 abutting each other.
  • the heat dissipation capability of the aircraft can be effectively improved.
  • FIG. 3 is a schematic structural view of the air guiding mechanism 14 in the arm assembly 10 according to the first embodiment of the present invention
  • FIG. 4 is a machine in the arm assembly 10 according to the first embodiment of the present invention.
  • the air guiding mechanism 14 includes at least one air guiding plate 142. As can be seen in FIG. 3, two sets of air guiding plates 142 are disposed in the air guiding mechanism 14, and correspondingly on the lower arm housing 126. Two openings 122 are provided (refer to a partial perspective view of the arm housing of FIG. 4).
  • the opening 122 has a longitudinal direction, and the longitudinal direction is consistent with the longitudinal direction of the arm assembly.
  • the air deflector 142 has at least two, and at least two air guiding plates 142 are spaced apart in the longitudinal direction.
  • the opening 122 includes a first opening 1222 and a second opening 1224.
  • the first opening 1222 and the second opening 1224 are spaced apart, and the first opening 1222 and the second opening 1224 are axisymmetric.
  • the air guiding mechanism 14 includes a first air guiding portion 146 and a second air guiding portion 147, and a connecting portion 148 connecting the first air guiding portion 146 and the second air guiding portion 147.
  • the first air guiding portion 146 is mounted.
  • the second air guiding portion 147 is disposed on the second opening 1224.
  • the first air guiding portion 146 includes a first peripheral wall 1462 and a first air guiding plate 1422, and both ends of the first air guiding plate 1422 are connected to the first peripheral wall 1462.
  • the second air guiding portion 147 includes a second peripheral wall 1472 and a second air guiding plate 1424, and both ends of the second air guiding plate 1424 are connected to the second peripheral wall 1462.
  • Figure 5 is an enlarged view of A of Figure 2 .
  • the arm shell The body 12 and the air guiding mechanism 14 are provided with mutually fitting mounting mechanisms, and the air guiding mechanism 14 is fixed to the arm housing 12.
  • the assembly mechanism includes an assembly hole 144 and an assembly post 128.
  • the fitting hole 144 is disposed on the connecting portion 148 of the air guiding mechanism 14, and the mounting post 128 is disposed on the lower arm housing 126.
  • the specific connection between the air guiding mechanism 14 and the opening 122 is such that the first peripheral wall 1462 of the first air guiding portion 146 is embedded inside the hole wall of the first opening 1222, and the second peripheral wall 1472 of the second air guiding portion 147 is embedded.
  • the inner side of the hole wall of the second opening 1224 is disposed, and the mounting post 128 is inserted into the mounting hole 144, and the air guiding mechanism 14 is fixed to the lower arm housing body 126.
  • the number of air deflectors 142 and the number of openings 122 may be set according to specific use conditions, and are not limited by the above examples.
  • the air deflector 142 is disposed obliquely with respect to the cross section of the opening 122, and the angle of inclination is between 0 and 90 degrees.
  • the inclination angle of the air deflector 142 can be adjusted according to the external environment: when the external ambient temperature is high, for example, in a low latitude region, the tilt angle can be appropriately adjusted to increase the introduced air volume; and the external ambient temperature is higher. At low altitudes, such as high latitudes, the tilt angle can be appropriately adjusted to reduce the amount of air introduced, and even the air deflector 142 can be closed to avoid internal heat dissipation and the machine is at a good operating temperature.
  • FIG. 6 is a schematic structural view of an aircraft according to a second embodiment of the present invention
  • FIG. 7 is a schematic diagram of airflow analysis of an aircraft according to a second embodiment of the present invention.
  • the aircraft may be a drone or other aircraft and includes a body 30, a propeller 20A, and an arm assembly 10A.
  • a cavity 32 is formed in the body 30, the arm assembly 10A is connected to the body 30, the cavity 32 is in communication with the cavity 121A, the propeller 20A is disposed on the arm assembly 10A, and the arm assembly 10A is provided with an opening 122A for guiding the wind.
  • the mechanism 14A is arranged to direct the external airflow entering the interior of the arm housing 12A through the opening 122A toward the body 30 (as specifically shown in Figure 7).
  • the propeller 20A is disposed on the upper side of the arm housing 12A
  • the air guiding mechanism 14A is disposed on the lower side of the arm housing 12A
  • the air guiding mechanism 14A is disposed in the middle of the arm assembly 10A and located at the propeller 20A and the body. Between 30.
  • the lower arm housing 126A on the lower side of the arm housing 12A is provided with an opening 122A and is engaged with the air guiding mechanism 14A.
  • the airflow enters the arm housing 12A through the opening 122A of the lower arm housing body 126A, and flows to the cavity 32 inside the body 30 through the air guiding mechanism 14A, and then the air body 30 is driven by the propeller 20A.
  • the internal components achieve the effect of heat dissipation.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Remote Sensing (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Manipulator (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

一种飞行器的机臂组件以及飞行器，该飞行器的机臂组件（10）包括机臂壳体（12）和导风机构（14），机臂壳体（12）内形成空腔（121），机臂壳体（12）上设置有开孔（122），开孔（122）与空腔（121）连通，导风机构（14）设置于机臂壳体（12）上并与开孔（122）对应以对经过机臂壳体（12）的气流进行导向；通过导风机构（14）连接于开孔（122）以对进入机臂壳体（12）内部的外部气流进行导向，能够有效提高飞行器的散热能力。

Description

一种飞行器的机臂组件以及飞行器 技术领域
本发明涉及飞行器领域，尤其涉及一种机臂组件及应用该机臂组件的飞行器。
背景技术
在现有的飞行器的设计中，为了降低飞行器的体积，一般需要将飞行器的结构设计得相对紧凑，飞行控制板、各部分感测组件以及锂电池等都集中在飞行器的主体部分舱室内。但是，结构的紧凑必然导致散热不佳。例如，在外界环境温度较低的情况下，锂电池在舱室内产生的热量很容易传导到外部环境，但是在外界环境温度较高的情况下，舱室内的热量无法有效地传导到外部环境，会导致飞行器的内部运行环境温度较高，出现异常状况，严重时会导致飞行器计算出“错误”的飞行姿态，大大影响到飞行器的安全性能。
发明内容
本发明主要解决的技术问题是提供一种飞行器的机臂组件以及飞行器，能够提高飞行器的散热能力。
为解决上述技术问题，本发明采用的一个技术方案是：提供一种飞行器的机臂组件，所述机臂组件包括机臂壳体和导风机构，所述机臂壳体内形成空腔，所述机臂壳体上设置有开孔，所述开孔与所述空腔连通，所述导风机构设置于所述机臂壳体上并与所述开孔对应以对经过所述机臂壳体的气流进行导向。
其中，所述机臂组件用于支撑螺旋桨，所述开孔开设于所述机臂组件的下侧以允许所述螺旋桨在旋转过程中产生的所述外部气流经所述开孔与所述机臂壳体的所述空腔相通。
其中，所述导风机构嵌设于所述开孔中。
其中，所述机臂壳体包括上机臂壳体和下机臂壳体。
其中，所述导风机构包括至少一个导风板，所述导风板的两端连接于所述开孔。
其中，所述开孔具有长度方向，所述长度方向与所述机臂组件的长度方向一致，所述导风板至少有二个，所述至少二个导风板沿所述长度方向间隔设置。
其中，所述开孔包括第一开孔和第二开孔，所述第一开孔和第二开孔间隔设置，且所述第一开孔和第二开孔沿所述机臂的中轴轴对称，所述导风机构包括第一导风部和第二导风部，所述第一导风部装设于所述第一开孔上，所述第二导风部装设于所述第二开孔上。
其中，所述导风板相对于所述开孔的截面倾斜设置。
其中，所述机臂壳体与所述导风机构设置有相互配合的装配机构，进而将所述导风机构固定于所述机臂壳体上。
其中，所述装配机构包括装配孔和装配柱，所述装配孔设置于所述导风机构上，所述装配柱设置于所述机臂壳体上，所述装配柱插入于所述装配孔内，进而所述导风机构固定于所述机臂壳体上。
为了解决上述问题，本发明还提供了一种飞行器，所述飞行器包括机体、螺旋桨和如权利要求1-10任意一项所述的机臂组件，所述机体内形成腔体，所述机臂组件与所述机体连接，所述腔体与所述空腔连通，所述螺旋桨设置于所述机臂组件的末端。
其中，所述螺旋桨设置于所述机臂壳体的上侧，所述导风机构设置于所述机臂壳体的下侧。
其中，所述导风机构位于所述螺旋桨和所述机体之间。
其中，所述飞行器为多旋翼无人飞行器。
本发明的有益效果是：区别于现有技术的情况，本发明通过在机臂组件上设置机臂壳体和导风机构，机臂壳体上设置有开孔，导风机构连接于开孔以对进入机臂壳体内部的外部气流进行导向，能够有效提高飞行器的散热能力。
附图说明
图1是根据本发明第一实施例的机臂组件的组装示意图；
图2是根据本发明第一实施例的机臂组件的拆解示意图；
图3是根据本发明第一实施例的机臂组件中的导风机构的结构示意图；
图4是根据本发明第一实施例的机臂组件中的机臂壳体的局部立体图；
图5是图2的A处放大视图；
图6是根据本发明第二实施例的飞行器的结构示意图；
图7是根据本发明第二实施例的飞行器的气流分析示意图。
具体实施方式
为更进一步阐述本发明所采取的技术手段及其效果，以下结合本发明的实施例及其附图进行详细描述。
参照图1和图2，图1是根据本发明第一实施例的机臂组件10的组装示意图，图2是根据本发明第一实施例的机臂组件10的拆解示意图。在本实施例中，机臂组件10包括机臂壳体12以及设置于机臂壳体12内部的导风机构14(参见图2)，机臂壳体12内形成空腔121，机臂壳体12上设有开孔122，开孔122和空腔121连通。
机臂组件10用于支撑螺旋桨20，开孔122开设于机臂组件10的下侧以允许螺旋桨20在旋转过程中产生的外部气流经开孔122与机臂壳体12的空腔121相通，在这里可以是外部的温度较低的气流进入空腔121，以使得空腔121内的温度得到降低，也可以是内部的温度较高的气流排出空腔121，同样使得空腔121内的温度得以降低。
机臂壳体12包括彼此配合的上机臂壳体124和下机臂壳体126。上机臂壳体124和下机臂壳体126相互对接形成空腔121。开孔122设置于下机臂壳体126上并位于空腔121内。在图2中，为了清楚表示机臂组件10内部的构造，将上机臂壳体124去除。
在本实施例中，在下机臂壳体126上开设有开孔122，以允许螺 旋桨20在旋转过程中产生的外部气流经开孔122进入机臂壳体12内部。螺旋桨20与开孔122分别位于机臂壳体12的两侧。
导风机构14设置于机臂壳体12内部，可选的是嵌在开孔122孔壁内，由此对经开孔122进入机臂壳体12内部的外部气流进行导向。具体的，导风机构14装设于下机臂壳体126上的开孔122处，并位于上机臂壳体124和下机臂壳体体126相互对接形成的空腔121中。
在本实施例中，通过在机臂壳体12上设置有开孔122，并配合导风机构14来对进入机臂壳体12内部的外部气流进行导向，能够有效提高飞行器的散热能力。
参照图3和图4，图3是根据本发明第一实施例的机臂组件10中的导风机构14的结构示意图，图4是根据本发明第一实施例的机臂组件10中的机臂壳体12的局部立体图。
在本实施例中，导风机构14包括至少一个导风板142，在图3中可以看到，导风机构14中设置了两组导风板142，且对应地在下机臂壳体126上设置有两个开孔122(参照图4的机臂壳体的局部立体图)。
进一步的，开孔122具有长度方向，该长度方向与机臂组件的长度方向一致，上述导风板142至少有二个，至少二个导风板142沿长度方向间隔设置。
参照图4，开孔122包括第一开孔1222和第二开孔1224，第一开孔1222和第二开孔1224间隔设置，且第一开孔1222和第二开孔1224为轴对称。继续参照图3，导风机构14包括第一导风部146和第二导风部147以及连接第一导风部146和第二导风部147的连接部148，第一导风部146装设于第一开孔1222上，第二导风部147装设于第二开孔1224上。第一导风部146包括第一周壁1462和第一导风板1422，第一导风板1422的两端与第一周壁1462相连接。同样的，第二导风部147包括第二周壁1472和第二导风板1424，第二导风板1424的两端与第二周壁1462相连接。
参照图5，图5是图2的A处放大视图。在本实施例中，机臂壳 体12与导风机构14设置有相互配合的装配机构，进而将导风机构14固定于机臂壳体12上。装配机构包括装配孔144和装配柱128。
具体来说，装配孔144设置于导风机构14的连接部148上，装配柱128设置于下机臂壳体126上。
导风机构14与开孔122的具体连接方式为第一导风部146的第一周壁1462嵌设在第一开孔1222的孔壁内侧，第二导风部147的第二周壁1472嵌设在第二开孔1224的孔壁内侧，装配柱128插入于装配孔144内，进而导风机构14固定于下机臂壳体体126上。
当然，本领域技术人员也可以根据实际需要设置其他的装配机构。
在其他实施例中，导风板142的数量以及开孔122的数量可以根据具体使用情况进行设置，并不以上述举例为限制。
继续参照图3，导风板142相对于开孔122的截面倾斜设置，倾斜角度在0度到90度之间。
在实际使用过程中，导风板142的倾斜角度可以根据外部环境进行调节：在外部环境温度较高时，例如低纬度地区，可以适当调整倾斜角度，增加导入的风量；而在外部环境温度较低时，例如高纬度地区，可以适当调整倾斜角度，减少导入的风量，甚至可以关闭导风板142，避免内部热量的逸散，使机器处于较好的工作温度。
参见图6和图7，图6是根据本发明第二实施例的飞行器的结构示意图；图7是根据本发明第二实施例的飞行器的气流分析示意图。
在本实施例中，飞行器可以是无人机或其他飞行器，且包括机体30、螺旋桨20A和机臂组件10A。机体30内形成腔体32，机臂组件10A与机体30连接，腔体32与空腔121A连通，螺旋桨20A设置于机臂组件10A的上，机臂组件10A上设置有开孔122A，导风机构14A设置成将经开孔122A进入机臂壳体12A内部的外部气流朝机体30进行导向(具体如图7所示)。
具体来说，螺旋桨20A设置于机臂壳体12A的上侧，导风机构14A设置于机臂壳体12A的下侧，导风机构14A设置于机臂组件10A的中部且位于螺旋桨20A和机体30之间。
在本实施例中，机臂壳体12A的下侧的下机臂壳体126A上设置有开孔122A，并与导风机构14A配合。
参照图7，气流在螺旋桨20A的带动下经下机臂壳体体126A上的开孔122A进入机臂壳体12A，并经过导风机构14A流向机体30内部的腔体32，进而对机体30的内部组件达到散热的效果。
以上所述仅为本发明的实施方式，并非因此限制本发明的专利范围，凡是利用本发明说明书及附图内容所作的等效结构或等效流程变换，或直接或间接运用在其他相关的技术领域，均同理包括在本发明的专利保护范围内。

Claims (14)

  1. 一种飞行器的机臂组件，其特征在于，所述机臂组件包括机臂壳体和导风机构，所述机臂壳体内形成空腔，所述机臂壳体上设置有开孔，所述开孔与所述空腔连通，所述导风机构设置于所述机臂壳体上并与所述开孔对应以对经过所述机臂壳体的气流进行导向。
  2. 根据权利要求1所述的机臂组件，其特征在于，所述机臂组件用于支撑螺旋桨，所述开孔开设于所述机臂组件的下侧以允许所述螺旋桨在旋转过程中产生的所述外部气流经所述开孔与所述机臂壳体的所述空腔相通。
  3. 根据权利要求2所述的机臂组件，其特征在于，所述导风机构嵌设于所述开孔中。
  4. 根据权利要求2所述的机臂组件，其特征在于，所述机臂壳体包括上机臂壳体和下机臂壳体，所述上机臂壳体和所述下机臂壳体对接形成所述空腔，所述开孔设置于所述下机臂壳体上，所述导风机构位于所述空腔内。
  5. 根据权利要求1所述的机臂组件，其特征在于，所述导风机构包括至少一个导风板，所述导风板的两端连接于所述开孔。
  6. 根据权利要求5所述的机臂组件，其特征在于，所述开孔具有长度方向，所述长度方向与所述机臂组件的长度方向一致，所述导风板至少有二个，所述至少二个导风板沿所述长度方向间隔设置。
  7. 根据权利要求5所述的机臂组件，其特征在于，所述开孔包括第一开孔和第二开孔，所述第一开孔和第二开孔间隔设置，且所述第一开孔和第二开孔沿所述机臂的中轴轴对称，所述导风机构包括第一导风部和第二导风部，所述第一导风部装设于所述第一开孔上，所述第二导风部装设于所述第二开孔上。
  8. 根据权利要求5所述的机臂组件，其特征在于，所述导风板相对于所述开孔的截面倾斜设置。
  9. 根据权利要求1所述的机臂组件，其特征在于，所述机臂壳体与所述导风机构设置有相互配合的装配机构，进而将所述导风机构固定于所述机臂壳体上。
  10. 根据权利要求9所述的机臂组件，其特征在于，所述装配机构包括装配孔和装配柱，所述装配孔设置于所述导风机构上，所述装配柱设置于所述机臂壳体上，所述装配柱插入于所述装配孔内，进而所述导风机构固定于所述机臂壳体上。
  11. 一种飞行器，其特征在于，所述飞行器包括机体、螺旋桨和如权利要求1-10任意一项所述的机臂组件，所述机体内形成腔体，所述机臂组件与所述机体连接，所述腔体与所述空腔连通，所述螺旋桨设置于所述机臂组件上。
  12. 根据权利要求11所述的飞行器，其特征在于，所述螺旋桨设置于所述机臂壳体的上侧，所述导风机构设置于所述机臂壳体的下侧。
  13. 根据权利要求11所述的飞行器，其特征在于，所述导风机构位于所述螺旋桨和所述机体之间。
  14. 根据权利要求10所述的飞行器，其特征在于，所述飞行器为多旋翼无人飞行器。
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CN108995818A (zh) * 2017-06-07 2018-12-14 深圳光启合众科技有限公司 涵道风扇
WO2019127390A1 (zh) * 2017-12-29 2019-07-04 深圳市大疆创新科技有限公司 无人机的机臂组件及无人机
CN113093188B (zh) * 2021-04-02 2022-01-11 滁州学院 一种基于无人机遥感的农作物种类识别系统
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