Fairing and multi-rotor aircraft with same

Abstract

The utility model provides a fairing and a multi-rotor aircraft with the fairing, the fairing is used for the multi-rotor aircraft, the multi-rotor aircraft comprises a radiator and two motors, the fairing comprises a shell, an installation cavity is formed in the shell, the installation cavity is used for containing wire harnesses of the radiator and the motors, and the two motors are arranged in the shell. A lampshade hole is formed in the shell; and the lampshade is connected with the shell, and the lampshade seals and covers the lampshade hole. According to the fairing, the lampshade is arranged, the lamp body can be prevented from being impacted by objects such as broken stones, then the lamp body can be effectively protected, the service life of the lamp body can be prolonged, meanwhile, the fairing covers the wiring harness of the motor in the mounting cavity, the use safety of the multi-rotor aircraft can be guaranteed, and the reliability of the multi-rotor aircraft can be improved.

Description

Technical Field

[0001] The utility model relates to the technical field of multi-rotor aircraft manufacturing, in particular to a fairing and a multi-rotor aircraft having the same. Background Art

[0002] In the existing multi-rotor aircraft, in order to facilitate the identification of other flying equipment, luminous objects such as lamps are usually set up for easy identification. However, the existing lamps are generally set on the outside of the multi-rotor aircraft, and the fairing cannot protect the lamp body. The lamp body is easily damaged by impact from other objects, thereby reducing the service life of the lamp body. Utility Model Content

[0003] The utility model aims to solve at least one of the technical problems existing in the prior art. To this end, the utility model proposes a fairing which can effectively protect the lamp body.

[0004] The utility model also provides a multi-rotor aircraft with the fairing.

[0005] The fairing according to the embodiment of the utility model is used for a multi-rotor aircraft, which includes a radiator and two motors. The fairing includes: a shell, a mounting cavity is formed in the shell, the mounting cavity is used to accommodate the wiring harness of the radiator and the motor, and a lampshade hole is formed on the shell; and a lampshade is connected to the shell and covers the lampshade hole.

[0006] According to the fairing of the utility model, a lampshade is provided to prevent the lamp body from being hit by objects such as gravel, thereby effectively protecting the lamp body and increasing the service life of the lamp body. At the same time, the fairing sets the wiring harness cover of the motor in the installation cavity, which can ensure the safe use of the multi-rotor aircraft and improve the reliability of the multi-rotor aircraft.

[0007] According to some embodiments of the utility model, the shell includes: a first shell and a second shell, the first shell and the second shell are arranged along a first direction, the first shell and the second shell are both boxes with one side open, the open sides of the first shell and the second shell are arranged facing each other and docked to define the installation cavity, and the first shell and the second shell are detachably connected.

[0008] According to some optional embodiments of the present utility model, the lampshade is connected to one end of the first shell and / or the second shell in a second direction, and the second direction intersects with the first direction.

[0009] According to some embodiments of the present invention, a heat dissipation hole penetrating the shell along a first direction is formed on one of the first shell and the second shell, and the heat dissipation hole is suitable for exposing the radiator at the position of the heat dissipation hole.

[0010] According to some optional embodiments of the present invention, a reinforcement edge is provided on the periphery of the heat dissipation hole, the reinforcement edge surrounds the periphery of the heat dissipation hole to form a ring, and the reinforcement edge extends obliquely toward the installation cavity.

[0011] According to some embodiments of the utility model, a first notch and a second notch are formed on the first shell, and the first notch and the second notch are respectively arranged on both side walls of the first shell in a third direction, and the first notch and the second notch penetrate the first shell along the third direction; a third notch and a fourth notch are formed on the second shell, and the third notch and the fourth notch are respectively arranged on both side walls of the second shell in the third direction, and the third notch and the fourth notch penetrate the second shell along the third direction; the first notch and the third notch cooperate to form a first through hole, and the first through hole is suitable for one of the motors to extend from the fairing; the second notch and the fourth notch cooperate to form a second through hole, and the second through hole is suitable for the other motor to extend from the fairing.

[0012] According to some embodiments of the utility model, one of the first shell and the second shell is provided with a clip and the other is provided with a clip hole, a plurality of the clips are arranged around the circumference of the first shell, and the number of the clips corresponds to the number of the clips and the clip holes. The clips are inserted into the clip holes to connect the first shell and the second shell.

[0013] The multi-rotor aircraft according to the embodiment of the second aspect of the utility model includes: a fairing according to the first aspect of the utility model; a strut, one end of which extends into the fairing; a motor, the motor is connected to the end of the strut extending into the fairing, at least part of the motor is located outside the fairing, and the number of the motors is two; a wiring harness, the wiring harness is electrically connected to the motor, and the wiring harness is arranged in the fairing; a radiator, the radiator is connected to the end of the strut extending into the fairing, and the number of the radiators is two.

[0014] According to the multi-rotor aircraft of the utility model, by setting the fairing of the first embodiment and the lampshade, the lamp body can be prevented from being hit by objects such as gravel, thereby effectively protecting the lamp body and prolonging the service life of the lamp body. At the same time, the fairing sets the wiring harness cover of the motor in the installation cavity, which can ensure the safety of the use of the multi-rotor aircraft and improve the reliability of the multi-rotor aircraft. In addition, the support rod can provide a connection position for the motor, the radiator and the wiring harness, so that the structural layout of the multi-rotor aircraft can be reasonable.

[0015] According to some optional embodiments of the utility model, the support rod includes: a rod body, the fairing is provided with a connecting hole at the end facing away from the lampshade, one end of the rod body passes through the connecting hole and is connected to the motor; a mounting seat, the mounting seat is located in the fairing and connected to the rod body, and the motor is fixed on the mounting seat.

[0016] According to some embodiments of the present utility model, the multi-rotor aircraft includes: a circuit board, the circuit board is located in the fairing and connected to the support rod, and the circuit board is electrically connected to the wiring harness.

[0017] Additional aspects and advantages of the present invention will be given in part in the following description, and in part will become apparent from the following description, or will be learned through the practice of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 is a schematic diagram of a multi-rotor aircraft according to an embodiment of the second aspect of the utility model;

[0019] Figure 2 yes Figure 1 The aircraft shown in the diagram does not include the fairing;

[0020] Figure 3 is a schematic diagram of the brace shown in 2;

[0021] Figure 4 yes Figure 1 An exploded view of the fairing is shown in;

[0022] Figure 5 yes Figure 4 A schematic diagram of a first housing shown in ;

[0023] Figure 6 yes Figure 4 Schematic diagram of the second shell shown in .

[0024] Reference numerals:

[0025] 100. Fairing;

[0026] 10. Shell; 11. First shell; 111. Buckle; 112. First notch; 113. Second notch; 12. Second shell; 121. Clamp hole; 122. Third notch; 123. Fourth notch; 13. Heat dissipation hole; 14. Reinforced edge; 15. Connection hole; 16. Lampshade hole; 17. Bracket structure;

[0027] 20. Lampshade;

[0028] 200, support rod; 210, rod body; 2101, joint; 220, mounting seat; 230, cable harness;

[0029] 300, motor;

[0030] 400, wiring harness;

[0031] 500, radiator;

[0032] 600, circuit board;

[0033] 1000. Multi-rotor aircraft. DETAILED DESCRIPTION

[0034] The embodiments of the present invention are described in detail below, and examples of the embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are intended to be used to explain the present invention, and should not be construed as limiting the present invention.

[0035] Please refer to the following Figure 1-6 A fairing 100 according to an embodiment of the present invention is described.

[0036] Reference Figure 1 , Figure 2 and Figure 4 According to an embodiment of the utility model, the fairing 100 is used for a multi-rotor aircraft 1000. The multi-rotor aircraft 1000 includes a radiator 500 and two motors 300. The fairing 100 includes: a shell 10 and a lampshade 20.

[0037] Specifically, a mounting cavity is formed in the shell 10 for accommodating the heat sink 500 and the wiring harness 400 of the motor 300 . A lampshade 20 hole is formed on the shell 10 ; the lampshade 20 is connected to the shell 10 , and the lampshade 20 covers the lampshade hole 16 .

[0038] For example, Figure 1 , Figure 2 and Figure 4 As shown, the radiator 500 is used to dissipate heat for the motor 300, and the motor 300 is used to connect a propeller (not shown in the figure). An installation cavity is formed inside the shell 10, and a wiring harness 400 of the motor 300 is installed in the installation cavity. A lamp body is provided on the multi-rotor aircraft 1000, and the lamp body is arranged in the installation cavity.

[0039] The fairing 100 of the utility model is provided with a lampshade 20, which can protect the lamp body in the installation cavity, thereby preventing the lamp body from being hit by objects such as gravel, and further effectively protecting the lamp body and prolonging the service life of the lamp body. At the same time, the fairing 100 covers the wiring harness 400 of the motor 300 in the installation cavity, which can effectively prevent the wiring harness 400 from being exposed and entangled with the propeller, thereby ensuring the safe use of the multi-rotor aircraft 1000 and improving the reliability of the multi-rotor aircraft 1000.

[0040] According to the fairing 100 of the embodiment of the utility model, a lampshade 20 is provided to prevent the lamp body from being hit by objects such as gravel, thereby effectively protecting the lamp body and increasing the service life of the lamp body. At the same time, the fairing 100 covers the wiring harness 400 of the motor 300 in the installation cavity, which can ensure the safe use of the multi-rotor aircraft 1000 and improve the reliability of the multi-rotor aircraft 1000.

[0041] According to some embodiments of the present invention, referring to Figure 4 , Figure 5 and Figure 6 The housing 10 includes a first housing 11 and a second housing 12. The first housing 11 and the second housing 12 are arranged along a first direction (eg Figure 4 The first shell 11 and the second shell 12 are arranged in the left and right direction, and both of them are box bodies with one side open. The open sides of the first shell 11 and the second shell 12 are arranged opposite to each other and docked to define an installation cavity. The first shell 11 and the second shell 12 are detachably connected.

[0042] In this way, the first shell 11 and the second shell 12 cooperate to form the shell 10, which can facilitate the assembly of the shell 10 and improve the assembly efficiency of the shell 10. At the same time, it can facilitate the installation of components such as the wiring harness 400 in the installation cavity of the shell 10, thereby saving the time for installing components such as the wiring harness 400 in the installation cavity. Furthermore, an installation cavity is formed in the first shell 11 and the second shell 12, and there is no need to set up an additional installation cavity, so that the structural design of the shell 10 is reasonable. In addition, the first shell 11 and the second shell 12 are detachably connected, which is convenient for the maintenance and replacement of the first shell 11 and the second shell 12, and can also facilitate the inspection of components such as the wiring harness 400 in the installation cavity.

[0043] For example, Figure 4 , Figure 5 and Figure 6 As shown, the first shell 11 and the second shell 12 are arranged along the left-right direction, the first shell 11 is a box body with an open left side, and the second shell 12 is a box body with an open right side. The left side of the first shell 11 and the right side of the second shell 12 are spliced ​​to form the shell 10, so that an installation cavity is formed in the first shell 11 and the second shell 12.

[0044] According to some optional embodiments of the present invention, referring to Figure 1 and Figure 4 The lampshade 20 is connected to the first housing 11 and / or the second housing 12 in the second direction (eg Figure 4 one end of the vertical direction shown in FIG. Figure 4 The upper end of the first shell 11 and / or the second shell 12 shown in FIG. 1 ), the second direction is parallel to the first direction (such as Figure 4Thus, the lampshade 20 is connected to the end of the first shell 11 and / or the second shell 12, and the position of the lampshade 20 corresponds to the lamp body, so that the lampshade 20 can cover the lamp body in the installation cavity, thereby ensuring the protective effect of the lampshade 20 on the lamp body.

[0045] For example, Figure 1 and Figure 4 As shown, the lampshade 20 is connected to the first shell 11 and the second shell 12 at the upper end, and the second direction is perpendicular to the first direction. Preferably, the lampshade 20 is made of a transparent material, so that the light of the lamp body can pass through the lampshade 20 and emit the fairing 100, so that other aircraft can identify the multi-rotor aircraft 1000.

[0046] According to some embodiments of the present invention, referring to Figure 2 , Figure 4 , Figure 5 and Figure 6 At least one of the first shell 11 and the second shell 12 is formed with a plurality of Figure 4 The heat dissipation hole 13 (in the left and right direction as shown) penetrates the housing 10, and the heat dissipation hole 13 is suitable for exposing the radiator 500 at the position of the heat dissipation hole 13. Therefore, the heat dissipated by the radiator 500 can be conveniently dissipated to the outside of the installation cavity through the heat dissipation hole 13, thereby improving the heat dissipation efficiency of the radiator 500.

[0047] For example, Figure 2 , Figure 4 , Figure 5 and Figure 6 As shown, the first shell 11 is provided with a heat dissipation hole 13 penetrating the first shell 11 along the left-right direction, and the second shell 12 is provided with a heat dissipation hole 13 penetrating the second shell 12 along the left-right direction. The heat dissipation hole 13 is rectangular, and the radiator 500 is exposed outside the installation cavity from the heat dissipation hole 13.

[0048] According to some optional embodiments of the present invention, referring to Figure 4 , Figure 5 and Figure 6 A reinforcing edge 14 is provided on the periphery of the heat dissipation hole 13. The reinforcing edge 14 surrounds the periphery of the heat dissipation hole 13 to form a ring, and the reinforcing edge 14 extends obliquely toward the installation cavity. Thus, the reinforcing edge 14 can strengthen the periphery of the heat dissipation hole 13, avoid the periphery of the heat dissipation hole 13 from breaking, and thus ensure the strength of the periphery of the heat dissipation hole 13.

[0049] Furthermore, if Figure 4 , Figure 5 and Figure 6As shown, a support structure 17 is provided on the reinforcing edge 14, and the support structure 17 extends in the left-right direction toward the installation cavity. Thus, the support structure 17 can provide support and limit for components such as the radiator 500 in the installation cavity, thereby effectively preventing the radiator 500 from shaking relative to the fairing 100.

[0050] According to some embodiments of the present invention, referring to Figure 4 , Figure 5 and Figure 6 The first shell 11 is formed with a first notch 112 and a second notch 113, and the first notch 112 and the second notch 113 are respectively arranged on the first shell 11 in the third direction (such as Figure 4 The first notch 112 and the second notch 113 penetrate the first shell 11 along the third direction, and the second shell 12 is formed with a third notch 122 and a fourth notch 123. The third notch 122 and the fourth notch 123 are respectively arranged on the side walls of the second shell 12 in the third direction, and the third notch 122 and the fourth notch 123 penetrate the second shell 12 along the third direction.

[0051] Further, the first notch 112 cooperates with the third notch 122 to form a first through hole, and the first through hole is suitable for one of the motors 300 to extend from the fairing 100. The second notch 113 cooperates with the fourth notch 123 to form a second through hole, and the second through hole is suitable for the other motor 300 to extend from the fairing 100. In this way, the two motors 300 can extend from the first through hole and the second through hole respectively to connect with the propeller, thereby facilitating the connection between the propeller and the motor 300.

[0052] For example, Figure 4 , Figure 5 and Figure 6 As shown, a first semicircular notch 112 is formed on the front side wall of the first shell 11, a second semicircular notch 113 is formed on the rear side wall of the first shell 11, a third semicircular notch 122 is formed on the front side wall of the second shell 12, and a fourth semicircular notch 123 is formed on the rear side wall of the second shell 12. The first notch 112 and the third notch 122 cooperate to form a first arc-shaped through hole, and a motor 300 extends from the first through hole. The second notch 113 and the fourth notch 123 cooperate to form a second arc-shaped through hole, and another motor 300 extends from the second through hole.

[0053] According to some embodiments of the present invention, referring to Figure 4 , Figure 5 and Figure 6One of the first shell 11 and the second shell 12 is provided with a buckle 111 and the other is provided with a locking hole 121, that is, the first shell 11 can be provided with a buckle 111 and the second shell 12 is provided with a locking hole 121, or the second shell 12 can be provided with a buckle 111 and the first shell 11 is provided with a locking hole 121. A plurality of buckles 111 are arranged around the circumference of the first shell 11, that is, two, three or four or more buckles 111 can be arranged around the circumference of the first shell 11, and the number of buckles 111 and the number of locking holes 121 correspond one to one. The buckle 111 is snapped into the locking hole 121 to connect the first shell 11 with the second shell 12.

[0054] In this way, the connection between the buckle 111 and the hole 121 has a simple structure and is convenient for connection, thereby improving the connection efficiency between the first shell 11 and the second shell 12. At the same time, multiple buckles 111 and holes 121 are provided to ensure the clamping strength between the first shell 11 and the second shell 12, thereby effectively preventing the first shell 11 from separating from the second shell 12.

[0055] For example, Figure 4 , Figure 5 and Figure 6 As shown, a plurality of buckles 111 are provided on the periphery of the first shell 11, and a buckle hole 121 corresponding to the buckle 111 is provided on the periphery of the second shell 12. When each buckle 111 is snapped into the corresponding buckle hole 121, the first shell 11 and the second shell 12 are snap-connected.

[0056] The multi-rotor aircraft 1000 according to the second embodiment of the utility model, referring to Figure 1 , Figure 2 and Figure 3 , comprising: a fairing 100 of the first aspect of this embodiment, a strut 200, a motor 300, a wiring harness 400 and a radiator 500. One end of the strut 200 (such as Figure 1 The upper end of the support rod 200 shown in the figure extends into the fairing 100; the motor 300 is connected to one end of the support rod 200 extending into the fairing 100, and at least part of the motor 300 is located outside the fairing 100, that is, part of the motor 300 can be located outside the fairing 100, or the whole of the motor 300 can be located outside the fairing 100, and the number of motors 300 is two; the wiring harness 400 is electrically connected to the motor 300, and the wiring harness 400 is arranged in the fairing 100; the radiator 500 is connected to one end of the support rod 200 extending into the fairing 100, and the number of radiators 500 is two.

[0057] The support rod 200 can provide a fixed position for the motor 300, thereby facilitating the arrangement of the motor 300. The radiator 500 is connected to the upper end of the support rod 200, thereby facilitating the radiator 500 to dissipate heat for the motor 300. The wiring harness 400 is disposed in the fairing 100 to prevent the wiring harness 400 from being exposed and entangled with the propeller.

[0058] For example, Figure 1 , Figure 2 and Figure 3 As shown, the strut 200 is arranged in the up-down direction, the upper end of the strut 200 extends into the fairing 100, the motor 300 is connected to the upper end of the strut 200, and the motor 300 is located outside the fairing 100 as a whole, two motors 300 are arranged on the front and rear sides of the strut 200, the wiring harness 400 is arranged in the fairing 100 as a whole, and two radiators 500 are arranged, and the two radiators 500 are arranged on the left and right sides of the strut 200. Preferably, the fairing 100 is bolted to the strut 200, and this connection form has a simple structure, low cost, and is convenient for connecting the fairing 100 and the strut 200.

[0059] According to the multi-rotor aircraft 1000 of the embodiment of the utility model, by providing the fairing 100 of the first embodiment and the lampshade 20, the lamp body can be prevented from being hit by objects such as gravel, thereby effectively protecting the lamp body and improving the service life of the lamp body. At the same time, the fairing 100 covers the wiring harness 400 of the motor 300 in the installation cavity, which can ensure the safety of the use of the multi-rotor aircraft 1000 and improve the reliability of the multi-rotor aircraft 1000. In addition, the support rod 200 can provide a connection position for the motor 300, the radiator 500 and the wiring harness 400, so that the structural layout of the multi-rotor aircraft 1000 can be reasonable.

[0060] According to some embodiments of the present invention, referring to Figure 1 and Figure 3 The support rod 200 includes a rod body 210 and a mounting seat 220. The fairing 100 is at one end away from the lampshade 20 (such as Figure 1 The end of the fairing 100 shown in the figure is provided with a connecting hole 15, and one end of the rod body 210 (such as Figure 3 The upper end of the rod body 210 shown in the figure passes through the connecting hole 15 to connect with the motor 300; the mounting seat 220 is located in the fairing 100 and connected to the rod body 210, and the motor 300 is fixed on the mounting seat 220. Therefore, the connecting hole 15 can facilitate the rod body 210 to extend into the installation cavity to connect with the motor 300 and other components, so that the motor 300 and other components can be connected with the rod body 210 in the installation cavity. At the same time, the mounting seat 220 can provide a fixed position for the motor 300, which is convenient for the installation of the motor 300.

[0061] For example, Figure 1 and Figure 3 As shown, the rod body 210 extends in the up-down direction, the lower end of the fairing 100 is provided with a connecting hole 15, the upper end of the rod body 210 extends into the connecting hole 15 and is connected to the motor 300, and two mounting seats 220 are provided at the upper end of the rod body 210, and the two mounting seats 220 are respectively arranged on the left and right sides of the rod body 210, and the two motors 300 are respectively fixed on the corresponding mounting seats 220.

[0062] Furthermore, if Figure 1 and Figure 3 As shown, the upper end of the rod body 210 is provided with a wire harness 230, and the wire harness 400 passes through the wire harness 230 and is connected to the motor 300. The lower end of the rod body 210 is provided with a connector 2101. Thus, the wire harness 230 can arrange the wire harness 400 in an orderly manner, which is convenient for the maintenance of the wire harness 400. At the same time, the connector 2101 can facilitate the connection of the rod body 210 with other components, thereby improving the assembly efficiency of the rod body 210 and other components.

[0063] According to some embodiments of the present invention, referring to Figure 2 The multi-rotor aircraft 1000 may include: a circuit board 600, the circuit board 600 is located in the fairing 100 and connected to the strut 200, and the circuit board 600 is electrically connected to the wire harness 400. Thus, the circuit board 600 controls the operation of the motor 300 through the wire harness 400, thereby ensuring the normal operation of the multi-rotor aircraft 1000.

[0064] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise", "axial", "radial", "circumferential" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present invention.

[0065] In addition, the terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" and "second" may explicitly or implicitly include one or more of the features. In the description of the present utility model, the meaning of "plurality" is two or more, unless otherwise clearly and specifically defined.

[0066] In the present invention, unless otherwise clearly specified and limited, the terms "install", "connect", "connect", "fix" and the like 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, an electrical connection, or a communication; it can be a direct connection, or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0067] In the description of this specification, the description with reference to the terms "one embodiment", "some embodiments", "example", "specific example", or "some examples" etc. means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the utility model. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described may be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art may combine and combine the different embodiments or examples described in this specification and the features of the different embodiments or examples, without contradiction.

[0068] Although the embodiments of the present invention have been shown and described, those skilled in the art will appreciate that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the claims and their equivalents.

Claims

1. A fairing for a multi-rotor aircraft, the multi-rotor aircraft comprising a radiator and two motors, characterized in that: include: A housing, wherein a mounting cavity is formed in the housing, the mounting cavity is used to accommodate the heat sink and the wiring harness of the motor, and a lampshade hole is formed on the housing; A lampshade is connected to the housing and covers the lampshade hole.

2. The fairing according to claim 1, characterized in that: The shell includes: a first shell and a second shell, the first shell and the second shell are arranged along a first direction, the first shell and the second shell are both boxes with one side open, the open sides of the first shell and the second shell are arranged facing each other and docked to define the installation cavity, and the first shell and the second shell are detachably connected.

3. The fairing according to claim 2, characterized in that: The lampshade is connected to one end of the first shell and / or the second shell in a second direction, and the second direction intersects with the first direction.

4. The fairing according to claim 2, characterized in that: A heat dissipation hole penetrating the shell along a first direction is formed on one of the first shell and the second shell, and the heat dissipation hole is suitable for exposing the radiator at the position of the heat dissipation hole.

5. The fairing according to claim 4, characterized in that: A reinforcement edge is provided on the periphery of the heat dissipation hole, the reinforcement edge surrounds the periphery of the heat dissipation hole to form a ring, and the reinforcement edge extends obliquely toward the inside of the installation cavity.

6. The fairing according to claim 2, characterized in that: The first shell has a first notch and a second notch formed thereon. The first notch and the second notch are respectively arranged on two side walls of the first shell in a third direction. The first notch and the second notch penetrate the first shell along the third direction. A third notch and a fourth notch are formed on the second shell, and the third notch and the fourth notch are respectively arranged on the side walls of the second shell in the third direction, and the third notch and the fourth notch penetrate the second shell along the third direction. The first notch cooperates with the third notch to form a first through hole, which is suitable for one of the motors to extend from the fairing. The second notch cooperates with the fourth notch to form a second through hole, which is suitable for the other motor to extend from the fairing.

7. The fairing according to claim 2, characterized in that: One of the first shell and the second shell is provided with a buckle and the other is provided with a clamping hole. A plurality of the buckles are arranged around the circumference of the first shell, and the number of the buckles corresponds to the number of the buckles and the buckle holes. The buckles are inserted into the buckle holes to connect the first shell with the second shell.

8. A multi-rotor aircraft, characterized in that: include: A fairing according to any one of claims 1 to 7; A support rod, one end of which extends into the fairing; A motor, the motor being connected to one end of the strut extending into the fairing, at least part of the motor being located outside the fairing, and the number of the motors being two; A wiring harness, the wiring harness is electrically connected to the motor, and the wiring harness is arranged in the fairing; A radiator is connected to one end of the support rod extending into the fairing, and the number of the radiators is two.

9. The multi-rotor aircraft according to claim 8, characterized in that: The support rod comprises: A rod body, wherein the fairing is provided with a connecting hole at an end away from the lampshade, and one end of the rod body passes through the connecting hole and is connected to the motor; A mounting seat is located in the fairing and connected to the rod body, and the motor is fixed on the mounting seat.

10. The multi-rotor aircraft according to claim 8, characterized in that: include: A circuit board is located in the fairing and connected to the support rod, and the circuit board is electrically connected to the wiring harness.

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