WO2020135793A1 - 一种飞行器 - Google Patents

一种飞行器 Download PDF

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Publication number
WO2020135793A1
WO2020135793A1 PCT/CN2019/129557 CN2019129557W WO2020135793A1 WO 2020135793 A1 WO2020135793 A1 WO 2020135793A1 CN 2019129557 W CN2019129557 W CN 2019129557W WO 2020135793 A1 WO2020135793 A1 WO 2020135793A1
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Prior art keywords
motor
adapter plate
accommodating cavity
aircraft according
output shaft
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PCT/CN2019/129557
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English (en)
French (fr)
Inventor
梁智颖
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Autel Robotics Co Ltd
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Autel Robotics Co Ltd
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Publication date
Application filed by Autel Robotics Co Ltd filed Critical Autel Robotics Co Ltd
Publication of WO2020135793A1 publication Critical patent/WO2020135793A1/zh
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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
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/02—Aircraft characterised by the type or position of power plants
    • 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
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/02—Aircraft characterised by the type or position of power plants
    • B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
    • 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
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/40—Arrangements for mounting power plants in aircraft

Definitions

  • the present invention relates to the technical field of aircraft, and in particular to an aircraft.
  • the motors of conventional UAVs are exposed and open.
  • the motors installed in the exposed type will cause the wind resistance during the flight of the drone to increase, which affects the flight efficiency; while the existing open-mounted motors Directly installed in the accommodating cavity of the machine body, it can not meet the requirements of dustproof and waterproof.
  • the technical problem to be solved by the present invention is to overcome the problems of large wind resistance during the flight of the drone with the exposed structure of the motor in the prior art, and the built-in motor with built-in drone has poor dustproof and waterproof performance, thereby providing a Kind of aircraft.
  • An aircraft including:
  • the body includes a containing cavity with an opening
  • the motor assembly includes a motor installed in the accommodating cavity from the opening and a rotor connected to an output shaft of the motor, the output shaft extending out of the body; and,
  • the sealing structure is connected with the body and used for closing the opening of the accommodating cavity.
  • the sealing structure is an adapter plate, and the adapter plate is connected to the top surface of the motor, wherein the top surface of the motor is a surface having the output shaft.
  • the adapter plate has a through hole for the output shaft to pass through.
  • the adapter plate is also provided with a first mounting hole for mounting the adapter plate to the body, and the first mounting hole is provided around the through hole.
  • a second mounting hole for mounting the motor is provided on the adapter plate, and the second mounting hole is disposed around the through hole.
  • the adapter plate is provided with a second mounting hole for mounting the motor.
  • the adapter plate is located in the accommodating cavity and is connected to the body.
  • the adapter plate is located outside the accommodating cavity, and is connected to the body.
  • the adapter plate is made of thermally conductive material.
  • the adapter plate is integrally formed with the body.
  • sealing structure is a part corresponding to a side of the machine body and the motor having an output shaft.
  • a sealing gasket is provided between the motor and the body.
  • the body includes a fuselage and an arm connected to the fuselage, and the accommodating cavity is provided on at least one of the fuselage and the arm.
  • the motor is built into the accommodating cavity of the airframe, so that the motor is not exposed, the wind resistance during the flight of the aircraft is reduced, and the flight efficiency of the aircraft is improved.
  • the aircraft provided by the present invention adopts an adapter plate to close the opening of the body cavity, which can reduce the interference of the outside world to the motor, and has good dustproof and waterproof functions.
  • the adapter plate is made of a thermally conductive material and fixedly connected to the motor, which facilitates the heat dissipation of the motor and overcomes the problem of poor heat dissipation performance of the aircraft with a closed motor structure.
  • the aircraft provided by the present invention can first assemble the motor and the adapter plate, and then assemble the adapter plate on the fuselage.
  • the entire installation process can be installed in the same direction. Compared with the way that the common motor is assembled with the body through the bottom, there is no need to turn the body over and install it during the motor installation process, and the operation is more convenient.
  • FIG. 1 is a schematic structural diagram of a motor after being installed in a body in a first embodiment of the present invention
  • FIG. 2 is a partial cross-sectional view of the motor after being installed in the machine body in the first embodiment of the present invention
  • FIG. 3 is an exploded view of the motor, rotor, and airframe in the first embodiment of the present invention
  • FIG. 4 is a schematic diagram of the installation structure of the motor and the adapter plate in the first embodiment of the present invention
  • FIG. 6 is an exploded view of the motor, rotor, and airframe in the second embodiment of the present invention.
  • FIG. 7 is a partial cross-sectional view of the second embodiment of the present invention after the motor is installed in the body;
  • FIG. 8 is a schematic view of the structure of the accommodating bin on the arm of the first aircraft according to the embodiment of the present invention.
  • FIG. 9 is a schematic structural view of a receiving bin on a component of an arm of a second type aircraft in an embodiment of the present invention.
  • connection should be understood in a broad sense, for example, it can be fixed connection or detachable Connected, or connected integrally; either mechanically or electrically; directly connected, or indirectly connected through an intermediary, or internally connected between two components.
  • installation should be understood in a broad sense, for example, it can be fixed connection or detachable Connected, or connected integrally; either mechanically or electrically; directly connected, or indirectly connected through an intermediary, or internally connected between two components.
  • an aircraft includes an airframe 1, a motor assembly, and a sealing structure.
  • the body 1 includes an accommodating cavity with an opening;
  • the motor assembly includes a motor 1 installed in the accommodating cavity from the opening and a rotor 5 assembled with the output shaft of the motor 1, the main part of the motor 2 is placed in the accommodating cavity of the body 1, the motor 2
  • the output shaft extends from the body 1;
  • the sealing structure is connected to the body 1 for closing the opening of the containing cavity.
  • the motor 2 is built in the accommodating cavity of the airframe 1 so that the motor 2 is not exposed, which can reduce the wind resistance during the flight of the aircraft and improve the flight efficiency of the aircraft.
  • the sealing structure is used to seal the opening of the accommodating cavity, which can reduce the interference of the outside world to the motor 2 and has good dustproof and waterproof functions.
  • the opening of the accommodating cavity is provided at the top of the body 1, the sealing structure is an adapter plate 3, and the adapter plate 3 is connected to the top surface of the motor 2, wherein the top surface of the motor 2 is One side with output shaft.
  • the connection between the adaptor plate 3 and the body 1 may be in the accommodating cavity of the body 1 or outside the accommodating cavity of the body 1, or may be installed at a position flush with the opening of the accommodating cavity.
  • the adapter plate 3 is provided with a through hole 31 through which the output shaft of the power supply machine 2 passes, and the adapter plate 3 is further provided with four for mounting the adapter plate 3 on the body 1
  • the first mounting holes 32 and the four first mounting holes 32 are evenly spaced around the central axis of the through hole 31. This arrangement can improve the tightness of the mounting structure of the adapter plate 3 and the body 1 and prevent moisture from entering the accommodating cavity from the gap between the adapter plate 3 and the body 1 in all directions.
  • the body 1 is provided with a mounting plane 11 for the adapter plate 3 to be installed.
  • the mounting plane 11 is correspondingly provided with a first threaded hole.
  • the adapter plate 3 can pass through four screws that respectively pass through the first mounting hole 32 and the first threaded hole Removably fixed on the body 1. After the adaptor plate 3 is installed on the installation plane 11 of the body 1, the adaptor plate 3 and the installation plane 11 are closely attached to each other, which can improve the waterproof performance of the connection.
  • the mounting surface of the body 1 and the adapter plate 3 can also be a curved surface or a stepped surface, as long as the adapter plate 3 is installed in the body 1, the contact surface between the two can closely fit can.
  • the adapter plate 3 is further provided with four second mounting holes 33 for mounting the motor 2.
  • the four second mounting holes 33 are evenly spaced around the central axis of the through hole 31, and the motor
  • the top surface of 2 is correspondingly provided with a second threaded hole, the adapter plate 3 and the motor 2 are fixed by four screws that respectively pass through the second mounting hole 33 and the second threaded hole, so the arrangement can improve the motor 2 and the adapter plate 3
  • the stability of the installation structure, and the operation is simple.
  • the adapter plate 3 is made of pure copper sheet, aluminum sheet or other materials with high thermal conductivity, so that the adapter plate 3 can not only play a role of dustproof and waterproof, but also facilitate the heat dissipation of the motor 2 and overcome the closed type The problem of poor heat dissipation performance of aircraft with motor structure.
  • the sealing structure may also be a portion corresponding to the side of the body 1 and the motor 2 having the output shaft, that is, the sealing structure is integrally formed with the body 1.
  • the sealing structure also has a mounting plane 11, and the top of the motor 2 is directly fixed on the mounting plane 11 by screws.
  • a power supply unit 2 should also be provided in other parts of the housing to enter the housing Other openings in the warehouse.
  • a gasket 4 is provided around the output shaft of the motor 2 at the position where the top of the motor 2 and the body 1 are installed, which can further improve the motor 2Waterproof grade between output shaft and body 2. It is easy to think that the sealing gasket 4 can also be disposed between the top surface of the motor 2 and the adapter plate 3 and around the output shaft of the motor 2 based on the first implementation manner of this embodiment.
  • the body includes a fuselage and an arm connected to the fuselage
  • the accommodating cavity may be provided on the fuselage 1 or the arm
  • the installation structure of the accommodating cavity provided on the fuselage 1 is shown in detail
  • the installation structure of the accommodating cavity on the arm is shown in Figure 8-9.
  • the accommodating cavity can also be installed on a detachable part of the fuselage or the arm.
  • the motor 2 is built into the accommodating cavity of the airframe 1, so that the motor 2 is not exposed, the wind resistance during the flight of the aircraft is reduced, and the flight efficiency of the aircraft is improved; the adapter plate 3 is used to close the airframe 1 to accommodate
  • the opening of the cavity can reduce the external interference to the motor 2 and has good dustproof and waterproof functions.
  • the motor 2 and the adapter plate 3 can be assembled first, and then Assemble the adapter plate 3 on the body 1.
  • the entire installation process can be installed in the same direction. Compared with the way that the common motor 2 is assembled with the body 1 through the bottom, there is no need to turn the body 1 upside down during the installation of the motor 2 Installation and operation are more convenient.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Motor Or Generator Frames (AREA)
  • Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)

Abstract

一种飞行器，包括：机体（1），包括具有开口的容纳腔；电机组件，包括开口安装于容纳腔内的电机（2）和与电机的输出轴相连的旋翼（5），输出轴伸出机体；以及，密封结构，与机体连接，用于封闭容纳腔的开口。通过将电机内置在机体的容纳腔内，并采用密封结构密封容纳腔的开口，减少了飞行风阻、提高了飞行器的飞行效率，减少了外界对电机的干扰，提高了飞行器的防尘、防水性能。

Description

一种飞行器 技术领域
本发明涉及飞行器技术领域，具体涉及一种飞行器。
背景技术
近年来，随着科技水平以及人们生活水平的提高，无人飞行器在全球范围内的应用日益普及，特别是在农业、运输、公共安全、采矿、影视娱乐以及竞技等领域，对无人飞行器的需求逐步增加。
现有技术中，常规无人机的电机有外露式和开放式的，外露式安装的电机会导致无人机飞行过程中的风阻变大，影响飞行效率；而现有的开放式安装的电机直接安装在机体的容纳腔内，达不到防尘、防水的要求。
因此，亟需一种风阻小、具备防尘防水功能的飞行器及飞行器。
发明内容
因此，本发明要解决的技术问题在于克服现有技术中的电机外露结构的无人机飞行过程中的风阻大，电机开放式内置的无人机防尘、防水性能差的问题，从而提供一种飞行器。
为解决上述技术问题，本发明的技术方案如下：
一种飞行器，包括：
机体，包括具有开口的容纳腔；
电机组件，包括自所述开口安装于所述容纳腔内的电机和与所述电机的输出轴相连的旋翼，所述输出轴伸出所述机体；以及，
密封结构，与所述机体连接，用于封闭所述容纳腔的所述开口。
进一步地，所述密封结构为转接板，所述转接板与所述电机的顶面连接，其中，所述电机的顶面为具有所述输出轴的一面。
进一步地，所述转接板具有供所述输出轴穿出的通孔。
进一步地，所述转接板上还设有用于将所述转接板安装至所述机体的第一安装孔，所述第一安装孔环绕所述通孔设置。
进一步地，所述转接板上设有用于安装所述电机的第二安装孔，所述第二安装孔环绕所述通孔设置。
进一步地，所述转接板上设有用于安装所述电机的第二安装孔。
进一步地，所述转接板位于所述容纳腔内，并与所述机体相连。
进一步地，所述转接板位于所述容纳腔外，并与所述机体相连。
进一步地，所述转接板由导热材料制成。
进一步地，所述转接板与所述机体一体成型。
进一步地，所述密封结构为所述机体与所述电机具有输出轴的一面对应的部分。
进一步地，所述电机和所述机体之间设有密封垫片。
进一步地，所述机体包括机身和与所述机身相连的机臂，所述容纳腔设置在所述机身和所述机臂中的至少一个上。
本发明技术方案，具有如下优点：
1.本发明提供的飞行器，将电机内置在机体的容纳腔内，使电机不外露，减少了飞行器飞行过程中的风阻，提高了飞行器的飞行效率。
2.本发明提供的飞行器，采用转接板封闭机体容纳腔的开口，可以减少外界对电机的干扰，具备较好的防尘、防水等功能。
3.本发明提供的飞行器，转接板采用导热材料制成，并与电机固定连接，方便电机散热，克服了封闭式电机结构的飞行器散热性能差的问题。
4.本发明提供的飞行器，在将电机安装在机体上的过程中，可以先将电机与转接板装配，再将转接板装配在机体上，整个安装过程可以采用相同的方向 进行安装，与常见电机通过底部与机体装配的方式相比，电机安装过程中无需将机体倒翻过来再安装，操作更加方便。
附图说明
为了更清楚地说明本发明具体实施方式或现有技术中的技术方案，下面将对具体实施方式或现有技术描述中所需要使用的附图作简单地介绍，显而易见地，下面描述中的附图是本发明的一些实施方式，对于本领域普通技术人员来讲，在不付出创造性劳动的前提下，还可以根据这些附图获得其他的附图。
图1为本发明第一种实施方式中电机安装在机体后的结构示意图；
图2为本发明第一种实施方式中电机安装在机体后的局部剖视图；
图3为本发明第一种实施方式中电机、旋翼和机体的爆炸图；
图4为本发明第一种实施方式中电机和转接板的安装结构示意图；
图5为本发明第一种实施方式中电机和转接板的爆炸图；
图6为本发明第二种实施方式中电机、旋翼和机体的爆炸图；
图7为本发明第二种实施方式中电机安装在机体后的局部剖视图；
图8为本发明实施例中容纳仓在第一种飞行器机臂上的结构示意图；
图9为本发明实施例中容纳仓在第二种飞行器机臂的一个部件上的结构示意图。
附图标记说明：1、机体；11、安装平面；2、电机；3、转接板；31、通孔；32、第一安装孔；33、第二安装孔；4、密封垫片；5、旋翼。
具体实施方式
下面将结合附图对本发明的技术方案进行清楚、完整地描述，显然，所描述的实施例是本发明一部分实施例，而不是全部的实施例。基于本发明中的实施例，本领域普通技术人员在没有做出创造性劳动前提下所获得的所有其他实施例，都属于本发明保护的范围。
在本发明的描述中，需要说明的是，术语“中心”、“上”、“下”、“左”、“右”、“竖直”、“水平”、“内”、“外”等指示的方位或位置关系为基于附图所示的方位或位置关系，仅是为了便于描述本发明和简化描述，而不是指示或暗示所指的装置或元件必须具有特定的方位、以特定的方位构造和操作，因此不能理解为对本发明的限制。此外，术语“第一”、“第二”、“第三”仅用于描述目的，而不能理解为指示或暗示相对重要性。
在本发明的描述中，需要说明的是，除非另有明确的规定和限定，术语“安装”、“相连”、“连接”应做广义理解，例如，可以是固定连接，也可以是可拆卸连接，或一体地连接；可以是机械连接，也可以是电连接；可以是直接相连，也可以通过中间媒介间接相连，可以是两个元件内部的连通。对于本领域的普通技术人员而言，可以具体情况理解上述术语在本发明中的具体含义。
此外，下面所描述的本发明不同实施方式中所涉及的技术特征只要彼此之间未构成冲突就可以相互结合。
如图1-2所示的一种飞行器，包括机体1、电机组件以及密封结构。机体1包括具有开口的容纳腔；电机组件包括自开口安装于容纳腔内的电机1和与电机1输出轴相装配的旋翼5，电机2的主体部分置于机体1的容纳腔内，电机2的输出轴伸出机体1；密封结构与机体1连接，用于封闭容纳腔的开口。
将电机2内置在机体1的容纳腔内，使电机2不外露，可以减少飞行器飞行过程中的风阻，提高了飞行器的飞行效率。采用密封结构密封容纳腔的开口，可以减少外界对电机2的干扰，具备较好的防尘、防水等功能。
在本实施例的一种实施方式中，容纳腔的开口设置在机体1的顶部，密封结构为转接板3，转接板3与电机2的顶面连接，其中，电机2的顶面为具有输出轴的一面。此处转接板3与机体1的连接，可以在机体1的容纳腔内，也可以是在机体1的容纳腔外，还可以是安装在与容纳腔的开口齐平的位置处。
在将电机2安装在机体1上的过程中，可以先将电机2与转接板3装配，再将转接板3装配在机体1上，整个安装过程可以采用相同的方向进行安装， 与常见电机2通过底部与机体1装配的方式相比，电机2安装过程中无需将机体1倒翻过来再安装，操作更加方便。
具体的，如图3所示，转接板3中间设有供电机2输出轴穿出的通孔31，转接板3上还设有用于将转接板3安装在机体1上的四个第一安装孔32，四个第一安装孔32环绕通孔31的中心轴线方向均匀间隔布置。如此设置可以提高转接板3与机体1安装结构的紧密性，在各个方向上防止水分从转接板3与机体1连接处的缝隙进入容纳腔内。
机体1上设有供转接板3安装的安装平面11，安装平面11对应设有第一螺纹孔，转接板3通过四个分别穿过第一安装孔32和第一螺纹孔的螺钉可拆卸式固定在机体1上。当转接板3安装在机体1的安装平面11之后，转接板3与安装平面11紧密贴合，可以提高连接处的防水性能。可以理解的是，机体1与转接板3的安装面还可以是弧形面或阶梯状的表面，只要转接板3安装在机体1后，两两之间的接触面能紧密贴合即可。
如图4和图5所示，转接板3上还设有用于安装电机2的四个第二安装孔33，四个第二安装孔33环绕通孔31的中心轴线方向均匀间隔布置，电机2的顶面对应设有第二螺纹孔，转接板3与电机2通过四个分别穿过第二安装孔33和第二螺纹孔的螺钉固定，如此设置可以提高电机2和转接板3安装结构的稳定性，而且操作简单。
进一步的，转接板3采用纯铜片、铝片或其他导热性高的材料制成，这样转接板3既可以起到防尘、防水作用，又可以方便电机2散热，克服了封闭式电机结构的飞行器散热性能差的问题。
在本实施例的第二种实施方式中，如图6所示，密封结构还可以为机体1与电机2具有输出轴的一面对应的部分，即密封结构与机体1一体成型。该实施方式中，密封结构也具有安装平面11，电机2的顶部通过螺钉直接固定在安装平面11上，在这种情况下，容纳仓在机体的其它部位还应设置有一个供电机2进入容纳仓内的其它开口。这种直接将电机2安装在机体1上的方式，由于 密封结构与机体1为一体结构，机体1的密封性能更好，相应的具备较好的防水、防风等性能。
在基于本实施例的第二种实施方式的基础上，如图7所示，在电机2顶部与机体1安装的位置垫设有环绕电机2输出轴设置的密封垫片4，可以进一步提高电机2输出轴与机体2之间的防水等级。容易想到的是，密封垫片4还可以基于本实施例的第一种实施方式的基础上，设置在电机2的顶面和转接板3之间并环绕电机2输出轴设置。
在基于本实施例上述实施方式的基础上，机体包括机身和与机身连接的机臂，容纳腔可以设置在机体1或机臂上，容纳腔设置在机体1上的安装结构详见图1-7所示，容纳腔设置在机臂上的安装结构示意图详见图8-9所示，当然，容纳腔还可以是设置在机身或机臂的一个可拆卸安装的部件上。
本实施例提供的飞行器，将电机2内置在机体1的容纳腔内，使电机2不外露，减少了飞行器飞行过程中的风阻，提高了飞行器的飞行效率；采用转接板3封闭机体1容纳腔的开口，可以减少外界对电机2的干扰，具备较好的防尘、防水等功能；在将电机2安装在机体1上的过程中，可以先将电机2与转接板3装配，再将转接板3装配在机体1上，整个安装过程可以采用相同的方向进行安装，与常见电机2通过底部与机体1装配的方式相比，电机2安装过程中无需将机体1倒翻过来再安装，操作更加方便。
显然，上述实施例仅仅是为清楚地说明所作的举例，而并非对实施方式的限定。对于所属领域的普通技术人员来说，在上述说明的基础上还可以做出其它不同形式的变化或变动。这里无需也无法对所有的实施方式予以穷举。而由此所引伸出的显而易见的变化或变动仍处于本发明创造的保护范围之中。

Claims (12)

  1. 一种飞行器，其特征在于，包括：
    机体(1)，包括具有开口的容纳腔；
    电机组件，包括自所述开口安装于所述容纳腔内的电机(2)和与所述电机(2)的输出轴相连的旋翼(5)，所述输出轴伸出所述机体(1)；以及，
    密封结构，与所述机体(1)连接，用于封闭所述容纳腔的所述开口。
  2. 根据权利要求1所述的飞行器，其特征在于，所述密封结构为转接板(3)，所述转接板(3)与所述电机(2)的顶面连接，其中，所述电机(2)的顶面为具有所述输出轴的一面。
  3. 根据权利要求2所述的飞行器，其特征在于，所述转接板(3)具有供所述输出轴穿出的通孔(31)。
  4. 根据权利要求3所述的飞行器，其特征在于，所述转接板(3)上还设有用于将所述转接板(3)安装至所述机体(1)的第一安装孔(32)，所述第一安装孔(32)环绕所述通孔(31)设置。
  5. 根据权利要求3或4所述的飞行器，其特征在于，所述转接板(3)上设有用于安装所述电机(2)的第二安装孔(33)，所述第二安装孔(33)环绕所述通孔(31)设置。
  6. 根据权利要求2-5中任一项所述的飞行器，其特征在于，所述转接板(3)位于所述容纳腔内，并与所述机体(1)相连。
  7. 根据权利要求2-5中任一项所述的飞行器，其特征在于，所述转接板(3)位于所述收容腔外，并与所述机体(1)相连。
  8. 根据权利要求2-7中任一项所述的飞行器，其特征在于，所述转接板(3)由导热材料制成。
  9. 根据权利要求1-3,6-8中任一项所述的飞行器，其特征在于，所述转接板(3)与所述机体(1)一体成型。
  10. 根据权利要求1所述的飞行器，其特征在于，所述密封结构为所述机体(1)与所述电机(2)具有输出轴的一面对应的部分。
  11. 根据权利要求1-10中任一项所述的飞行器，其特征在于，所述电机(2)和所述机体(1)之间设有密封垫片(4)。
  12. 根据权利要求1-11中任一项所述的飞行器，其特征在于，所述机体(1)包括机身和与所述机身相连的机臂，所述容纳腔设置在所述机身和所述机臂中的至少一个上。
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