An aircraft

Abstract

The present invention discloses an aircraft, comprising: a body, comprising a receiving cavity with an opening; a motor assembly, comprising a motor installed in the receiving cavity from the opening and a rotor connected to the output shaft of the motor, the output shaft extending out of the body; and a sealing structure connected to the body, used to seal the opening of the receiving cavity. By placing the motor in the receiving cavity of the body so that the motor is not exposed, and using the sealing structure to seal the opening of the receiving cavity, the purpose of reducing the flying wind resistance and improving the flight efficiency of the aircraft can be achieved, and the interference of the outside world on the motor can be reduced, and the dustproof and waterproof performance of the aircraft can be improved.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft, and in particular to an aircraft. Background Art

[0002] In recent years, with the improvement of science and technology and people's living standards, the application of unmanned aerial vehicles has become increasingly popular around the world, especially in agriculture, transportation, public safety, mining, film and television entertainment, and competition. The demand for unmanned aerial vehicles has gradually increased.

[0003] In the prior art, conventional UAV motors are of two types: exposed and open. Exposed motors will increase the wind resistance of the UAV during flight, affecting flight efficiency; while existing open motors are directly installed in the accommodating cavity of the body, which cannot meet the requirements of dust and water resistance.

[0004] Therefore, there is an urgent need for an aircraft with low wind resistance and dustproof and waterproof functions. Summary of the invention

[0005] Therefore, the technical problem to be solved by the present invention is to overcome the problems of large wind resistance during flight of drones with exposed motor structures in the prior art and poor dust and water resistance of drones with open and built-in motors, thereby providing an aircraft.

[0006] In order to solve the above technical problems, the technical solution of the present invention is as follows:

[0007] An aircraft, comprising:

[0008] A body, comprising a receiving cavity having an opening;

[0009] a motor assembly, comprising a motor installed in the accommodating cavity through the opening and a rotor connected to an output shaft of the motor, wherein the output shaft extends out of the body; and

[0010] A sealing structure is connected to the body and is used to seal the opening of the accommodating cavity.

[0011] Furthermore, 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.

[0012] Furthermore, the adapter plate has a through hole for the output shaft to pass through.

[0013] Furthermore, 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 arranged around the through hole.

[0014] Furthermore, the adapter plate is provided with a second mounting hole for mounting the motor, and the second mounting hole is arranged around the through hole.

[0015] Furthermore, the adapter plate is provided with a second mounting hole for mounting the motor.

[0016] Furthermore, the adapter plate is located in the accommodating cavity and is connected to the body.

[0017] Furthermore, the adapter plate is located outside the accommodating cavity and is connected to the body.

[0018] Furthermore, the adapter plate is made of heat-conducting material.

[0019] Furthermore, the adapter plate and the body are integrally formed.

[0020] Furthermore, the sealing structure is a portion of the machine body corresponding to a side of the motor having an output shaft.

[0021] Furthermore, a sealing gasket is provided between the motor and the machine body.

[0022] Furthermore, the machine body includes a body and an arm connected to the body, and the accommodating cavity is arranged on at least one of the body and the arm.

[0023] The technical solution of the present invention has the following advantages:

[0024] 1. The aircraft provided by the present invention has the motor built into the accommodating cavity of the aircraft body so that the motor is not exposed, thereby reducing the wind resistance during the flight of the aircraft and improving the flight efficiency of the aircraft.

[0025] 2. The aircraft provided by the present invention uses an adapter plate to seal the opening of the body accommodating cavity, which can reduce external interference with the motor and has better dustproof and waterproof functions.

[0026] 3. In the aircraft provided by the present invention, the adapter plate is made of heat-conducting material and is fixedly connected to the motor, which facilitates the heat dissipation of the motor and overcomes the problem of poor heat dissipation performance of aircraft with a closed motor structure.

[0027] 4. In the aircraft provided by the present invention, during the process of installing the motor on the fuselage, the motor and the adapter plate can be assembled first, and then the adapter plate can be assembled on the fuselage. The entire installation process can be performed in the same direction. Compared with the common method of assembling the motor to the fuselage through the bottom, there is no need to turn the fuselage over for installation during the motor installation process, and the operation is more convenient. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] In order to more clearly illustrate the specific implementation methods of the present invention or the technical solutions in the prior art, the drawings required for use in the specific implementation methods or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are some implementation methods of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0029] Figure 1 This is a schematic diagram of the structure in which the motor is installed behind the machine body in the first embodiment of the present invention;

[0030] Figure 2 It is a partial cross-sectional view of the motor installed in the machine body in the first embodiment of the present invention;

[0031] Figure 3 An exploded view of the motor, rotor and body in the first embodiment of the present invention;

[0032] Figure 4 It is a schematic diagram of the installation structure of the motor and the adapter plate in the first embodiment of the present invention;

[0033] Figure 5 An exploded view of the motor and the adapter plate in the first embodiment of the present invention;

[0034] Figure 6 An exploded view of the motor, rotor and body in the second embodiment of the present invention;

[0035] Figure 7 It is a partial cross-sectional view of the motor after being installed in the machine body in the second embodiment of the present invention;

[0036] Figure 8 It is a schematic diagram of the structure of the accommodation compartment on the first aircraft arm in an embodiment of the present invention;

[0037] Fig. 9 It is a schematic diagram of the structure of a storage compartment on a component of a second type of aircraft arm in an embodiment of the present invention.

[0038] Explanation of the accompanying drawings: 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

[0039] The technical solution of the present invention will be described clearly and completely below in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0040] In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., indicating the orientation or positional relationship, are based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the present invention. In addition, the terms "first", "second", and "third" are used for descriptive purposes only, and cannot be understood as indicating or implying relative importance.

[0041] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0042] In addition, the technical features involved in the different embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other.

[0043] like Figure 1 An aircraft shown in Figure 2 comprises a body 1, a motor assembly and a sealing structure. The body 1 comprises a receiving cavity with an opening; the motor assembly comprises a motor 1 installed in the receiving cavity from the opening and a rotor 5 assembled with the output shaft of the motor 1, the main body of the motor 2 is placed in the receiving cavity of the body 1, and the output shaft of the motor 2 extends out of the body 1; the sealing structure is connected to the body 1 and is used to close the opening of the receiving cavity.

[0044] The motor 2 is built into the housing cavity of the body 1 so that the motor 2 is not exposed, which can reduce the wind resistance of the aircraft during flight and improve the flight efficiency of the aircraft. The opening of the housing cavity is sealed with a sealing structure, which can reduce the interference of the outside world on the motor 2 and has better dustproof and waterproof functions.

[0045] In one implementation of this embodiment, the opening of the accommodating cavity is set at the top of the body 1, and the sealing structure is an adapter plate 3, which is connected to the top surface of the motor 2, wherein the top surface of the motor 2 is the surface with the output shaft. Here, the connection between the adapter plate 3 and the body 1 can be inside the accommodating cavity of the body 1, or outside the accommodating cavity of the body 1, or installed at a position flush with the opening of the accommodating cavity.

[0046] In the process of installing the motor 2 on the body 1, the motor 2 can be assembled with the adapter plate 3 first, and then the adapter plate 3 can be assembled on the body 1. The entire installation process can be performed in the same direction. Compared with the common method of assembling the motor 2 with the body 1 through the bottom, there is no need to turn the body 1 over during the installation of the motor 2, and the operation is more convenient.

[0047] Specifically, Figure 3 As shown, the adapter plate 3 is provided with a through hole 31 in the middle for the output shaft of the power supply machine 2 to pass through, and the adapter plate 3 is also provided with four first mounting holes 32 for mounting the adapter plate 3 on the machine body 1, and the four first mounting holes 32 are evenly spaced around the central axis direction of the through hole 31. Such an arrangement can improve the tightness of the mounting structure of the adapter plate 3 and the machine body 1, and prevent moisture from entering the accommodating cavity from the gap at the connection between the adapter plate 3 and the machine body 1 in all directions.

[0048] The body 1 is provided with a mounting plane 11 for mounting the adapter plate 3, and the mounting plane 11 is correspondingly provided with a first threaded hole, and the adapter plate 3 is detachably fixed to the body 1 by four screws passing through the first mounting hole 32 and the first threaded hole respectively. After the adapter plate 3 is mounted on the mounting plane 11 of the body 1, the adapter plate 3 fits tightly with the mounting plane 11, 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 an arc surface or a stepped surface, as long as the contact surfaces between the adapter plate 3 can fit tightly after the adapter plate 3 is mounted on the body 1.

[0049] like Figure 4 and Figure 5 As shown, the adapter plate 3 is also 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 direction of the through hole 31. A second threaded hole is correspondingly provided on the top surface of the motor 2. The adapter plate 3 and the motor 2 are fixed by four screws passing through the second mounting holes 33 and the second threaded holes respectively. Such an arrangement can improve the stability of the mounting structure of the motor 2 and the adapter plate 3 and is easy to operate.

[0050] Furthermore, 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 dust-proof and waterproof role, but also facilitate the heat dissipation of the motor 2, overcoming the problem of poor heat dissipation performance of aircraft with closed motor structure.

[0051] In the second implementation of this embodiment, Figure 6As shown, the sealing structure can also be a portion of the machine body 1 corresponding to the side of the motor 2 having the output shaft, that is, the sealing structure is formed integrally with the machine body 1. In this embodiment, the sealing structure also has a mounting plane 11, and the top of the motor 2 is directly fixed to the mounting plane 11 by screws. In this case, the storage compartment should also be provided with another opening in other parts of the machine body for the power supply 2 to enter the storage compartment. In this way of directly mounting the motor 2 on the machine body 1, since the sealing structure and the machine body 1 are an integral structure, the sealing performance of the machine body 1 is better, and correspondingly has better waterproof, windproof and other properties.

[0052] Based on the second implementation method of this embodiment, Figure 7 As shown, a sealing gasket 4 arranged around the output shaft of the motor 2 is provided at the position where the top of the motor 2 and the body 1 are installed, which can further improve the waterproof level between the output shaft of the motor 2 and the body 2. It is easy to imagine that the sealing gasket 4 can also be arranged 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 of this embodiment.

[0053] Based on the above implementation of this embodiment, the machine body includes a machine body and an arm connected to the machine body. The accommodating cavity can be set on the machine body 1 or the arm. The installation structure of the accommodating cavity on the machine body 1 is described in detail. Figure 1 -7, the installation structure diagram of the accommodating chamber set on the machine arm is shown in Figure 8 As shown in FIG. 9 , of course, the accommodating cavity can also be arranged on a detachable component of the fuselage or the arm.

[0054] The aircraft provided in this embodiment has the motor 2 built into the accommodating cavity of the body 1 so that the motor 2 is not exposed, thereby reducing the wind resistance during the flight of the aircraft and improving the flight efficiency of the aircraft; the adapter plate 3 is used to close the opening of the accommodating cavity of the body 1, which can reduce external interference with the motor 2 and has better dustproof and waterproof functions; in the process of installing the motor 2 on the body 1, the motor 2 can be assembled with the adapter plate 3 first, and then the adapter plate 3 can be assembled on the body 1. The entire installation process can be installed in the same direction. Compared with the common method of assembling the motor 2 with the body 1 through the bottom, there is no need to turn the body 1 over before installing the motor 2 during the installation process, which is more convenient to operate.

[0055] Obviously, the above embodiments are merely examples for the purpose of clear explanation, and are not intended to limit the implementation methods. For those skilled in the art, other different forms of changes or modifications can be made based on the above description. It is not necessary and impossible to list all the implementation methods here. The obvious changes or modifications derived therefrom are still within the scope of protection of the invention.

Claims

1. An aircraft, characterized in that: include: A body (1) comprising a receiving cavity having an opening; a motor assembly, comprising a motor (2) installed in the accommodating cavity through the opening and a rotor (5) connected to an output shaft of the motor (2), wherein the output shaft extends out of the body (1); and a sealing structure connected to the machine body (1) and used to seal the opening of the accommodating cavity; the sealing structure is a portion of the machine body (1) corresponding to a side of the motor (2) having an output shaft; 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 a surface having the output shaft; the adapter plate (3) is made of a heat-conducting material; and the adapter plate (3) is used to dissipate heat for the motor (2).

2. The aircraft according to claim 1, characterized in that The adapter plate (3) has a through hole (31) for the output shaft to pass through.

3. The aircraft according to claim 2, characterized in that: The adapter plate (3) is also provided with a first mounting hole (32) for mounting the adapter plate (3) to the machine body (1); the first mounting hole (32) is arranged around the through hole (31).

4. The aircraft according to claim 3, characterized in that The adapter plate (3) is provided with a second mounting hole (33) for mounting the motor (2), and the second mounting hole (33) is arranged around the through hole (31).

5. The aircraft according to any one of claims 1 to 4, characterized in that: The adapter plate (3) is located in the accommodating cavity and is connected to the machine body (1).

6. The aircraft according to any one of claims 1 to 4, characterized in that: The adapter plate (3) is located outside the accommodating cavity and is connected to the machine body (1).

7. The aircraft according to any one of claims 1 to 2, characterized in that: The adapter plate (3) and the machine body (1) are integrally formed.

8. The aircraft according to any one of claims 1 to 4, characterized in that: A sealing gasket (4) is provided between the motor (2) and the machine body (1).

9. The aircraft according to any one of claims 1 to 4, characterized in that: The machine body (1) comprises a body and an arm connected to the body, and the accommodating cavity is arranged on at least one of the body and the arm.

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