WO2020135793A1

WO2020135793A1 - Aerial vehicle

Info

Publication number: WO2020135793A1
Application number: PCT/CN2019/129557
Authority: WO
Inventors: 梁智颖
Original assignee: 深圳市道通智能航空技术有限公司
Priority date: 2018-12-28
Filing date: 2019-12-28
Publication date: 2020-07-02
Also published as: CN109573063A

Abstract

Provided is an aerial vehicle, comprising: a fuselage (1), comprising an accommodating cavity with an opening; a motor assembly, comprising a motor (2) with an opening installed in the accommodating cavity and a rotor (5) connected to the output shaft of the motor, the output shaft extending out of the fuselage; and a sealing structure connected with the fuselage, which is used to close the opening of the accommodating cavity. The motor is built into the accommodating cavity of the fuselage, and the opening of the accommodating cavity is sealed with the sealing structure, thus the flight wind resistance is reduced, the flight efficiency of the aerial vehicle is improved, external interference to the motor is reduced, and the dustproof and waterproof performances of the aerial vehicle are improved.

Description

An aircraft

Technical field

The present invention relates to the technical field of aircraft, and in particular to an aircraft.

Background technique

In recent years, with the improvement of science and technology and people's living standards, the application of unmanned aerial vehicles in the world has become increasingly popular, especially in the fields of agriculture, transportation, public safety, mining, film and television entertainment, and sports. The demand is gradually increasing.

In the prior art, 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.

Therefore, there is an urgent need for an aircraft and an aircraft with low wind resistance, dustproof and waterproof functions.

Summary of the invention

Therefore, 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.

To solve the above technical problems, the technical solutions of the present invention are as follows:

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.

Further, 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.

Further, the adapter plate has a through hole for the output shaft to pass through.

Further, 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.

Further, 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.

Further, the adapter plate is provided with a second mounting hole for mounting the motor.

Further, the adapter plate is located in the accommodating cavity and is connected to the body.

Further, the adapter plate is located outside the accommodating cavity, and is connected to the body.

Further, the adapter plate is made of thermally conductive material.

Further, the adapter plate is integrally formed with the body.

Further, the sealing structure is a part corresponding to a side of the machine body and the motor having an output shaft.

Further, a sealing gasket is provided between the motor and the body.

Further, 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 technical solution of the present invention has the following advantages:

1. In the aircraft provided by the present invention, 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.

2. 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.

3. In the aircraft provided by the present invention, 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.

4. In the process of installing the motor on the fuselage, 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.

BRIEF DESCRIPTION

In order to more clearly explain the specific embodiments of the present invention or the technical solutions in the prior art, the following will briefly introduce the drawings required in the specific embodiments or the description of the prior art. Obviously, the appended The drawings are some embodiments of the present invention. For those of ordinary skill in the art, without paying any creative labor, other drawings can also be obtained based on these drawings.

FIG. 1 is a schematic structural diagram of a motor after being installed in a body in a first embodiment of the present invention;

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;

3 is an exploded view of the motor, rotor, and airframe in the first embodiment of the present invention;

4 is a schematic diagram of the installation structure of the motor and the adapter plate in the first embodiment of the present invention;

5 is an exploded view of the motor and the adapter plate in the first embodiment of the present invention;

6 is an exploded view of the motor, rotor, and airframe in the second embodiment of the present invention;

7 is a partial cross-sectional view of the second embodiment of the present invention after the motor is installed in the body;

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.

DESCRIPTION OF REFERENCE NUMERALS: 1. Body; 11. Mounting plane; 2. Motor; 3. Adapter plate; 31, through hole; 32, first mounting hole; 33, second mounting hole; 4. Sealing gasket; 5 , Rotor.

detailed description

The technical solutions of the present invention will be described clearly and completely below with reference to the drawings. Obviously, the described embodiments are part of the embodiments of the present invention, but not all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by a person of ordinary skill in the art without creative work fall within the protection scope of the present invention.

In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. The indicated orientation or positional relationship is based on the orientation or positional relationship shown in the drawings, just to facilitate the description of the present invention and simplify the description, rather than to indicate or imply that the device or element referred to must have a specific orientation, a specific orientation The construction and operation cannot be understood as a limitation of the present invention. In addition, the terms "first", "second", and "third" are for descriptive purposes only, and cannot be understood as indicating or implying relative importance.

In the description of the present invention, it should be noted that, unless otherwise clearly specified and defined, the terms "installation", "connection", and "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. For those of ordinary skill in the art, the specific meaning of the above terms in the present invention can be understood in specific situations.

In addition, the technical features involved in the different embodiments of the present invention described below can be combined as long as they do not conflict with each other.

As shown in Figure 1-2, 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.

In an implementation of this embodiment, 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. Here, 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.

In the process of installing the motor 2 on the body 1, you can first assemble the motor 2 with the adapter plate 3, and then assemble the adapter plate 3 on the body 1, the entire installation process can be installed in the same direction, and common Compared with the method of assembling the body 1 through the bottom of the motor 2, it is not necessary to turn the body 1 over and install it during the installation of the motor 2, and the operation is more convenient.

Specifically, as shown in FIG. 3, 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. It can be understood that 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.

As shown in FIGS. 4 and 5, 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.

Further, 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.

In the second implementation manner of this embodiment, as shown in FIG. 6, 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. In this embodiment, 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. In this case, a power supply unit 2 should also be provided in other parts of the housing to enter the housing Other openings in the warehouse. In this way of directly mounting the motor 2 on the body 1, since the sealing structure and the body 1 are an integrated structure, the sealing performance of the body 1 is better, and correspondingly has better waterproof, windproof and other properties.

On the basis of the second implementation mode based on this example, as shown in FIG. 7, 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.

Based on the above-mentioned implementation mode 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, and the installation structure of the accommodating cavity provided on the fuselage 1 is shown in detail As shown in Figure 1-7, the installation structure of the accommodating cavity on the arm is shown in Figure 8-9. Of course, the accommodating cavity can also be installed on a detachable part of the fuselage or the arm.

In the aircraft provided in this embodiment, 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. During the process of installing the motor 2 on the body 1, 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.

Obviously, the above examples are only examples for clear explanation, and are not limitations on the implementation. For those of ordinary skill in the art, based on the above description, other different forms of changes or changes can also be made. There is no need to exhaustively list all implementations. The obvious changes or changes derived from this are still within the protection scope created by the present invention.

Claims

An aircraft, characterized in that it includes:

The body (1) includes a containing cavity with an opening;

Motor assembly, including a motor (2) installed in the accommodating cavity from the opening and a rotor (5) connected to an output shaft of the motor (2), the output shaft extends out of the body (1) ;as well as,

The sealing structure is connected with the body (1) and is used for closing the opening of the accommodating chamber.
The aircraft according to claim 1, characterized in that the sealing structure is an adapter plate (3), the adapter plate (3) is connected to the top surface of the motor (2), wherein the motor (2) The top surface is the surface having the output shaft.
The aircraft according to claim 2, characterized in that the adapter plate (3) has a through hole (31) through which the output shaft passes.
The aircraft according to claim 3, characterized in that the adapter plate (3) is further provided with a first mounting hole (32) for mounting the adapter plate (3) to the airframe (1) ), the first mounting hole (32) is disposed around the through hole (31).
The aircraft according to claim 3 or 4, characterized in that the adapter plate (3) is provided with a second mounting hole (33) for mounting the motor (2), the second mounting hole (33) 33) Around the through hole (31).
The aircraft according to any one of claims 2-5, characterized in that the adapter plate (3) is located in the accommodating cavity and is connected to the airframe (1).
The aircraft according to any one of claims 2-5, characterized in that the adapter plate (3) is located outside the receiving cavity and connected to the airframe (1).
The aircraft according to any one of claims 2-7, characterized in that the adapter plate (3) is made of a thermally conductive material.
The aircraft according to any one of claims 1-3, 6-8, characterized in that the adapter plate (3) is integrally formed with the airframe (1).
The aircraft according to claim 1, characterized in that the sealing structure is a portion corresponding to a side of the airframe (1) and the motor (2) having an output shaft.
The aircraft according to any one of claims 1-10, characterized in that a sealing gasket (4) is provided between the motor (2) and the airframe (1).
The aircraft according to any one of claims 1-11, characterized in that the airframe (1) includes a fuselage and an arm connected to the fuselage, and the accommodating cavity is provided in the fuselage and On at least one of the arms.