A drone and a method for waterproofing drones

Abstract

The utility model provides an unmanned plane and unmanned plane waterproof method, including unmanned plane shell, be used for unmanned plane whole machine support's unmanned plane support structure, be used for unmanned plane flight's unmanned plane flight structure, unmanned plane shell connects in unmanned plane support structure, unmanned plane flight structure is connected in unmanned plane shell outside unmanned plane support structure and drives, unmanned plane support structure is equipped with first unmanned plane support seat for unmanned plane shell connection, is equipped with second unmanned plane support seat for unmanned plane flight structure connection, and second unmanned plane support seat is equipped with second connection mounting position, and first unmanned plane support seat is equipped with first connection mounting position, second connection mounting position connects in first connection mounting position, makes second unmanned plane support seat detachable connection in first unmanned plane support seat, the structure design that the scheme adopts has reached the effect that effectively shortens unmanned plane fuselage's production time, improves unmanned plane production efficiency and expands second unmanned plane support seat production material's selection diversity.

Description

Technical Field

[0001] This invention belongs to the technical field of unmanned aerial vehicles (UAVs), and particularly relates to a UAV and a UAV waterproofing method applied to UAVs. Background Technology

[0002] In the prior art, 3D printing technology is mostly used to produce drones of specific shapes. However, 3D printing technology has low production efficiency, which makes it difficult to mass-produce drones and results in poor waterproof performance, which can reduce the lifespan of drones. Therefore, this invention proposes a new solution to the above-mentioned technical problems. Summary of the Invention

[0003] The purpose of this invention is to provide a drone that adopts a modular assembly structure for the drone fuselage, which effectively shortens the production time of the drone fuselage, improves the production efficiency of the drone, and expands the variety of materials available for the production of the second drone support.

[0004] Based on this, the present invention provides a drone, comprising:

[0005] The drone shell, the drone support structure for supporting the entire drone, and the drone flight structure for drone flight, wherein the drone shell is connected to the drone support structure, and the drone flight structure is connected to the outside of the drone support structure relative to the drone shell and is driven.

[0006] The drone support structure includes a first drone support base for connecting to the drone shell and a second drone support base for connecting to the drone flight structure. The second drone support base has a second connection mounting position, and the first drone support base has a first connection mounting position. The second connection mounting position is connected to the first connection mounting position, so that the second drone support base can be detachably connected to the first drone support base.

[0007] As described above, the first drone support base is provided with a first drone support plate one and a first drone support plate two. The first drone support plate one and the first drone support plate two are arranged opposite to each other to form the first connection mounting position, which is used for connection to the second connection mounting position.

[0008] As described above, the second drone support base includes a second drone support base one and a second drone support base two, which are connected to each other at the first connection mounting position for fastening.

[0009] As described above, in a drone, the second drone support base one and the second drone support base two are respectively provided with a second drone support base mounting position one and a second drone support base mounting position two. The second drone support base mounting position one and the second drone support base mounting position two are connected to the first connection mounting position to form the second connection mounting position.

[0010] As described above, the second drone support base one and the second drone support base two are respectively provided with flight structure mounting position one and flight structure mounting position two. The flight structure mounting position one is located at the other end of the second drone support base one, and the flight structure mounting position two is located at the other end of the second drone support base two, and the drone flight structure is connected to the flight structure mounting position one or the flight structure mounting position two for fastening.

[0011] As described above, the drone support structure further includes a first support stabilization structure and a second support stabilization structure. The second drone support base one and the second drone support base two are further provided with a support stabilization mounting part one and a support stabilization mounting part two, respectively. The first support stabilization structure and the second support stabilization structure are respectively connected to the support stabilization mounting part one and the support stabilization mounting part two to support the drone.

[0012] As described above, in a drone, the first support and stabilization structure is provided with a first support limiting slot and a first support stabilization protrusion. The first support limiting slot is provided with a first support limiting block. The first support and stabilization mounting part is provided with a first support and stabilization connection hole. The first support and stabilization structure is connected to the first support limiting block through the first support and stabilization connection hole, and then connected to the first support limiting slot and supported by the first support limiting block.

[0013] The second support and stabilizing structure is provided with a second support limiting slot and a second support and stabilizing protrusion. The second support limiting slot is provided with a second support limiting block. The second support and stabilizing mounting part is provided with a second support and stabilizing connecting hole. The second support and stabilizing structure is connected to the second support limiting block through the second support and stabilizing connecting hole, and then connected to the second support limiting slot and supported by the second support and stabilizing protrusion.

[0014] The drone described above further includes a main control module for controlling the drone's flight and a waterproof layer for waterproofing. The drone shell is connected to the first drone support plate and forms a control structure mounting cavity. The first drone support plate is disposed within the control structure mounting cavity. The main control module is connected to the first drone support plate and provides electrical connection to the drone's flight structure. The waterproof layer is disposed on the main control module and the drone's flight structure for waterproofing.

[0015] As described above, the second drone support base is further provided with connecting support members, and multiple connecting support members are respectively connected to the second drone support base one and the second drone support base two for support.

[0016] A method for waterproofing drones, used to produce the Piriline waterproofing layer as described above, the method comprising the following steps:

[0017] S1. Cleaning: Clean the main control module after SMT using any of the following cleaning agents: alcohol, ether, ester, or alkane.

[0018] S2. Shielding: Perform site shielding on the cleaned main control module, UAV flight structure, and other UAV components;

[0019] S3. Plasma treatment: Plasma treatment equipment is used to treat the shielded main control module and other UAV components with plasma.

[0020] S4. Coating: Plasma-treated main control module and other drone components are placed in a Perelin vacuum coating machine for coating to form a Perelin waterproof layer.

[0021] S5. Post-processing: Deshielding is performed on the main control module and other UAV components after coating.

[0022] Implementing the embodiments of the present invention has the following beneficial effects:

[0023] 1. This solution adopts a modular assembly structure for the drone fuselage, comprising a drone shell, a drone support base, and a drone flight structure. The drone support base includes a first drone support base and a second drone support base, each with a first and a second connection mounting position. The second drone support base is detachably connected to the first drone support base via the second connection mounting position. By connecting the drone shell to the first drone support base and the drone flight structure to the second drone support base relative to the second connection mounting position, modular assembly of the drone fuselage is achieved. Furthermore, the second drone support base can be manufactured separately using injection molding and then assembled onto the second drone support base. This effectively optimizes the drone production process, shortening the drone fuselage production time, improving drone production efficiency, and expanding the variety of materials available for the second drone support base. Attached Figure Description

[0024] To more clearly illustrate the technical solutions in the embodiments of this application, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the accompanying drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0025] Figure 1 This is a schematic diagram of the structure of an embodiment of the present invention;

[0026] Figure 2 For the corresponding Figure 1 A structural diagram from another direction;

[0027] Figure 3 For the corresponding Figure 2 A structural diagram from another direction;

[0028] Figure 4 For the corresponding Figure 3 A structural diagram from another direction;

[0029] Figure 5 This is an exploded view of the structure according to an embodiment of the present invention;

[0030] Figure 6 For the corresponding Figure 5 A structural diagram from another direction;

[0031] Figure 7 For the corresponding Figure 6 A structural diagram from another direction;

[0032] Figure 8 For the corresponding Figure 7 A structural diagram from another direction;

[0033] Figure 9 A schematic diagram showing the connection between the first and second support stabilizing structures and the second UAV support base;

[0034] Figure 10 For the corresponding Figure 9 Exploded view of the structure;

[0035] Figure 11 For the corresponding Figure 10 A schematic diagram of the structure from another direction.

[0036] In the diagram: 1-UAV shell, 11-UAV side panel, 12-GPS mounting position; 2-UAV support structure, 21-First UAV support base, 211-First connection mounting position, 212-First UAV support plate one, 213-First UAV support plate two, 22-Second UAV support base, 221-Second connection mounting position, 222-Second UAV support base one, 2221-Second UAV support base mounting position one, 2222-Flight structure mounting position one, 2223-Support and stabilization mounting part one, 22231-Support and stabilization connection hole one, 2224-Second UAV support base connection groove one, 223-Second UAV support base 2. 2231 - Second UAV support mounting position 2; 2232 - Flight structure mounting position 2; 2233 - Support and stabilization mounting part 2; 22331 - Support and stabilization connection hole 2; 2234 - Second UAV support connecting groove 2; 226 - Connecting support component; 23 - First support and stabilization structure; 231 - First support limiting slot; 2311 - First support limiting block; 232 - First support and stabilization protrusion; 24 - Second support and stabilization structure; 241 - Second support limiting slot; 2411 - Second support limiting block; 242 - Second support and stabilization protrusion; 3 - UAV flight structure; 31 - Flight structure connecting seat; 4 - Main control module. Detailed Implementation

[0037] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0038] like Figures 1 to 11 As shown, an embodiment of the present invention provides a drone, comprising:

[0039] The system comprises a drone shell 1, a drone support structure 2 for supporting the entire drone, and a drone flight structure 3 for drone flight. The drone shell 1 is connected to the drone support structure 2, and the drone flight structure 3 is connected to the outside of the drone support structure 2 relative to the drone shell 1, so as to provide sufficient lift and drop power to drive the drone. The drone support structure 2 has a first drone support base 21 for connecting the drone shell 1 and a second drone support base 22 for connecting the drone flight structure 3. The second drone support base 22 has a second connection mounting position 221, and the first drone support base 21 has a first connection mounting position 211. The second connection mounting position 221 is connected to the first connection mounting position 211, so that the second drone support base 22 can be detachably connected to the first drone support base 21 to improve the convenience of installation.

[0040] Specifically, the first UAV support base 21 is provided with a first UAV support plate 212 and a second UAV support plate 213. The first UAV support plate 212 and the second UAV support plate 213 are arranged opposite to each other to form the first connection mounting position 211 for connection with the second connection mounting position 221. The relative arrangement of the first UAV support plate 212 and the second UAV support plate 213 forms a precisely matched installation space between them, and the installation space is adapted to the shape and size of the second connection mounting position 221, thereby achieving a fast and accurate connection, effectively improving the efficiency and accuracy of UAV assembly, and reducing possible errors during the installation process.

[0041] Furthermore, the second drone support base 22 is provided with a second drone support base one 222 and a second drone support base two 223. The second drone support base one 222 and the second drone support base two 223 are connected to each other at the first connection mounting position 211 for fastening. In this embodiment of the invention, the second drone support base one 222 and the second drone support base two 223 are produced by injection molding. Preferably, each side of the drone is provided with one second drone support base one 222 and one second drone support base two 223. The two second drone support bases one 222 are diagonally connected at the first connection mounting positions 211 on both sides, and the two second drone support bases two 223 are diagonally connected at the first connection mounting positions 211 on both sides, so as to improve the stability of the drone during flight and improve the production convenience of the second drone support base one 222 and the second drone support base two 223.

[0042] Furthermore, the second UAV support base 1 222 and the second UAV support base 223 are respectively provided with second UAV support base mounting positions 1 2221 and 2231. The second UAV support base mounting positions 1 2221 and 2231 are connected to the first connecting mounting position 211 to form the second connecting mounting position 221. The second UAV support base mounting position 1 2221 is provided with a second UAV support base connecting half hole 1, and the second UAV support base mounting position 2231 is provided with a second UAV support base connecting half hole 2. The second UAV support base connecting half hole 1 and the second UAV support base connecting half hole 2 are connected to form a complete second UAV support base connecting hole 1, so that the second UAV support base 1 222 and the second UAV support base 223 can be connected through the second UAV support base connecting hole 1, improving the installation positioning accuracy and facilitating the fastening of the second UAV support base 22 to the first UAV support base 21 through the second connecting mounting position 221, thereby enhancing the stability after connection.

[0043] Furthermore, the second UAV support base 1 222 and the second UAV support base 223 are respectively provided with flight structure mounting positions 1 2222 and 2232. The flight structure mounting position 1 2222 is located at the other end of the second UAV support base 1 222, opposite to the second UAV support base mounting position 1 2221. The flight structure mounting position 2232 is located at the other end of the second UAV support base 223, opposite to the second UAV support base mounting position 2231. The UAV flight structure 3 is fastened to the flight structure mounting position 1 2222 or the flight structure mounting position 2232. This design allows the UAV flight structure 3 to be secured via the flight structure mounting positions 1 2222 and 2232. The drone flight structure 3 is securely connected to the second drone support 22, thereby stably mounting the drone flight structure 3 on the drone support 2, ensuring power transmission and control precision during flight, and improving flight stability and reliability. The flight structure mounting position 2222 is provided with a first flight structure connection hole and a second flight structure connection hole, with the second flight structure connection hole equidistantly surrounding the first flight structure connection hole. The drone flight structure 3 is provided with a flight structure connection seat 31, which has flight structure mating holes corresponding to the second flight structure connection holes, so as to secure the drone flight structure 3 to the flight structure mounting position 2222 through a first threaded connector, thereby improving the tightness of the connection of the drone flight structure 3.

[0044] The second flight structure mounting position 2232 is provided with a third flight structure connection hole and a fourth flight structure connection hole. The fourth flight structure connection hole is equidistantly arranged around the third flight structure connection hole, and the four flight structure connection holes correspond one-to-one with the flight structure mating holes, so as to fasten the UAV flight structure 3 to the second flight structure mounting position 2232 through the second threaded connector, thereby improving the tightness of the connection of the UAV flight structure 3.

[0045] Furthermore, the UAV support structure 2 is also provided with a first support stabilization structure 23 and a second support stabilization structure 24. The second UAV support base 1 222 and the second UAV support base 223 are also provided with a first support stabilization mounting part 2223 and a second support stabilization mounting part 2233. The first support stabilization structure 23 and the second support stabilization structure 24 are respectively connected to the first support stabilization mounting part 2223 and the second support stabilization mounting part 2233 to support the UAV, so as to ensure that the UAV can be stably docked on the ground after the flight, avoiding damage to the UAV by direct docking and improving the safety of UAV docking. At the same time, it ensures the levelness of the second UAV support base 1 222 and the second UAV support base 223 after connection, so as to reduce wear on the connection of the second UAV support base 1 222 and the second UAV support base 223, thereby extending the service life of the UAV.

[0046] Furthermore, the first support and stabilizing structure 23 is provided with a first support limiting groove 231 and a first support and stabilizing protrusion 232. The first support limiting groove 231 is provided with a first support limiting block 2311, and the support and stabilizing mounting part 2223 is provided with a support and stabilizing connecting hole 22231. The first support and stabilizing structure 23 is connected to the first support limiting block 2311 through the support and stabilizing connecting hole 22231, and then connected within the first support limiting groove 231 and supported by the first support limiting block 2311. This provides double limiting for the first support and stabilizing structure 23 through the first support limiting groove 231 and the first support limiting block 2311, thereby ensuring that the grounding stability of the first support and stabilizing structure 23 is enhanced when the first support and stabilizing protrusion 232 abuts against the ground. The contact area between the first support and stabilizing protrusion 232 and the ground is designed as a plane to increase the contact area between the first support and stabilizing protrusion 232 and the ground, thereby enhancing the grounding stability of the first support and stabilizing structure 23.

[0047] The second support and stabilizing structure 24 is provided with a second support limiting groove 241 and a second support and stabilizing protrusion 242. The second support limiting groove 241 is provided with a second support limiting block 2411. The second support and stabilizing mounting part 2233 is provided with a second support and stabilizing connecting hole 22331. The second support and stabilizing structure 24 is connected to the second support limiting block 2411 through the second support and stabilizing connecting hole 22331, and then connected in the second support limiting groove 241. It is supported by the second support and stabilizing protrusion 242, so that the second support and stabilizing structure 24 is doubly limited by the second support limiting groove 241 and the second support limiting block 2411, thereby ensuring that the second support and stabilizing protrusion 242 abuts the ground, thus enhancing the grounding stability of the second support and stabilizing structure 24. The contact area between the second support and stabilizing protrusion 242 and the ground is designed as a plane to increase the contact area between the second support and stabilizing protrusion 242 and the ground, thereby enhancing the grounding stability of the second support and stabilizing structure 24.

[0048] Furthermore, the drone provided in this embodiment of the invention also includes a main control module 4 for controlling the drone's flight and a waterproof layer for waterproofing. The drone shell 1 is connected to the first drone support plate 213 and forms a control structure mounting cavity. The first drone support plate 212 is disposed within the control structure mounting cavity. The second drone support base 222 and the second drone support base 223 are also provided with a second drone support base connecting groove 2224 and a second drone support base connecting groove 2234, which are respectively connected to the first flight structure connecting hole and the third flight structure connecting hole. The main control module 4 is connected to the first UAV support plate 212. The UAV flight structure 3, which is set on the second UAV support base 222 and the second UAV support base 223, is connected to the main control module 4 through connecting lines installed in the second UAV support base connecting cable grooves 2224 and 2234, respectively. The main control module 4 controls the rotation of the UAV flight structure 3, thereby driving the UAV to fly. This design, with the connecting lines installed in the second UAV support base connecting cable grooves 2224 and 2234, effectively improves the stability and safety of the UAV during operation.

[0049] The Pirilin waterproof layer is installed on the main control module 4 and the UAV flight structure 3 for waterproofing. In this embodiment of the invention, the Pirilin waterproof layer is vacuum coated using a Pirilin vacuum coating machine. Pirilin vacuum coating technology is an advanced process that uses parylene material for coating. Pirilin vacuum coating technology deposits and generates a polymer film on the surface of an object through chemical vapor deposition. The specific process includes three steps: vaporization, pyrolysis and polymerization. First, the raw material of Pirilin is vaporized at 150°C, then pyrolyzed into monomers at 650°C, and finally uniformly covered on the surface of the coated object by vapor deposition at room temperature. The entire Parylene vacuum coating process must be carried out under vacuum conditions to ensure uniform coating without dead corners, covering all parts of the object to be coated, including sharp edges, inside gaps, and extremely fine pinholes. This provides waterproof, moisture-proof, dustproof, and insulating protection for electronic components, thereby improving the reliability and lifespan of electronic products. In this embodiment of the invention, the main control module 4, the UAV flight structure 3, and the connecting lines are coated with a nano- to micron-sized Parylene waterproof layer using Parylene vacuum coating technology to enhance applicability to different UAV models, thereby improving the overall waterproof performance of the UAV and extending its lifespan.

[0050] Furthermore, the second drone support base 22 is also provided with connecting support members 226, and both the second drone support base 1 222 and the second drone support base 223 adopt an integral molding structure design to improve the convenience of separately producing the second drone support base 1 222 and the second drone support base 223 using injection molding process; the multiple connecting support members 226 are respectively connected to the second drone support base 1 222 and the second drone support base 223 for support, so as to avoid damage to the second drone support base 1 222 and the second drone support base 223 due to excessive local stress, thereby extending the service life of the second drone support base 1 222 and the second drone support base 223; in this embodiment of the invention, the connecting support members 226 are connected to the second drone support base 1 222 and the second drone support base 223 by glue connection to improve the convenience of connection.

[0051] In this embodiment of the invention, the drone shell 1 is provided with a drone side panel 11 and a GPS mounting position 12. The drone side panel 11 adopts a laser-engraved light-transmitting process, which can enhance the aesthetics and technological feel of the drone, thereby enhancing its market competitiveness. The GPS mounting position 12 is used to install a GPS device. The GPS device is electrically connected to the main control module 4 and is coated with a nano- to micron-level waterproof layer. The origin information can be preset through the main control module 4, so that the drone can automatically return to its home location through GPS positioning in case of an accident, thereby reducing losses.

[0052] The present invention also provides a method for waterproofing drones, for producing the Piriton waterproofing layer as described above, the method comprising the following steps:

[0053] S1. Cleaning: After SMT, the circuit board on the main control module 4 usually has residues such as flux and ink. These residues will affect the adhesion of the phenelzine. Therefore, the circuit board on the main control module 4 after SMT can be cleaned with any of the following cleaning agents: alcohol (such as methanol, ethanol, isopropanol, n-butanol), ether (such as tert-methyl ether, isopropyl ether, ethylene glycol monomethyl ether, ethylene glycol dimethyl ether), ester (such as ethyl acetate, isopropyl acetate, n-butyl acetate), or alkane (n-hexane, n-heptane, n-pentane) to improve the adhesion of the phenelzine during the coating process.

[0054] S2. Shielding: During the coating process, the pads and connectors on the circuit board of the main control module 4, the drone flight structure 3, drone components, connectors and interfaces will be covered, which may lead to poor connection or increased contact resistance. Before coating, one of the following should be used to shield the pads and connectors on the circuit board of the main control module 4, the drone flight structure 3, drone components, connectors and interfaces after cleaning, to ensure that the normal function and performance of all drone components are not affected after coating, and to enhance the connection stability of the drone after coating.

[0055] S3. Plasma Treatment: After shielding all components of the UAV, in order to effectively change the surface state of all components and increase the adhesion of the P-coating on their surfaces, the pads and connectors on the circuit board of the shielded main control module 4, the UAV flight structure 3, UAV components, connectors and interfaces are subjected to plasma treatment using a plasma treatment device. In this invention, argon, oxygen, hydrogen or a combination of argon / oxygen or argon / hydrogen is preferably used for plasma treatment. The treatment power is 300-600W and the treatment time is 100-600S to increase the adhesion of the P-coating on the surface of all components of the UAV.

[0056] S4. Coating: The solder pads and connectors on the circuit board of the plasma-treated main control module 4, the drone flight structure 3, drone components, connectors, and interfaces are placed in a Perylene vacuum coating machine for coating to form a nano- to micron-scale Perylene waterproof layer. In this embodiment of the invention, depending on the usage scenario of the drone under different conditions, the Perylene material can be selected as type C, type F, or type AF4, and the coating thickness can be selected as 10μm-30μm to enhance the applicability of the drone in different environments. Perylene type C: Perylene type C contains chlorine atoms, which gives it better moisture-proof and chemical corrosion-proof properties, effectively preventing moisture from penetrating the drone, and also resisting various chemical substances. With good tolerance, it helps extend the service life of drones in humid environments; Parylene F type: Parylene F type contains fluorine atoms, which gives it better chemical resistance and high temperature resistance, ensuring that drones maintain stable performance at higher temperatures, while also having excellent tolerance to a variety of chemicals, which helps extend the service life of drones in high-temperature environments; Parylene AF4 type: Parylene AF4 type contains fluorine and aromatic ring structures, which gives it even higher high temperature resistance and chemical resistance, ensuring that drones maintain stable performance at higher temperatures, while also having excellent tolerance to a variety of chemicals, which helps extend the service life of drones in high-temperature and harsh environments.

[0057] S5. Post-processing: Deshield the pads and connectors on the circuit board of the main control module 4, the UAV flight structure 3, the UAV components, connectors and interfaces after coating. Preferably, laser cutting, laser etching, or robotic adhesive removal is used for deshielding to ensure that the normal function and performance of the pads and connectors on the circuit board of the main control module 4, the UAV flight structure 3, the UAV components, connectors and interfaces after coating are not affected.

[0058] It should be understood that the terms "first," "second," etc., are used in this invention to describe various information, but this information should not be limited to these terms. These terms are only used to distinguish information of the same type from each other. For example, without departing from the scope of this invention, "first" information can also be referred to as "second" information, and similarly, "second" information can also be referred to as "first" information. In addition, the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this invention.

[0059] The above description represents the preferred embodiments of the present invention. It should be noted that those skilled in the art can make various improvements and modifications without departing from the principles of the present invention, and these improvements and modifications are also considered to be within the scope of protection of the present invention.

Claims

1. A drone, characterized in that, The utility model relates to a kind of unmanned aerial vehicle, including: Unmanned aerial vehicle shell (1), unmanned aerial vehicle support structure (2) for unmanned aerial vehicle whole machine support, unmanned aerial vehicle flight structure (3) for unmanned aerial vehicle flight, the unmanned aerial vehicle shell (1) is connected in the unmanned aerial vehicle support structure (2), the unmanned aerial vehicle flight structure (3) is connected in the unmanned aerial vehicle support structure (2) outside relative to the unmanned aerial vehicle shell (1) and is driven; The unmanned aerial vehicle support structure (2) is provided with first unmanned aerial vehicle support seat (21) for the connection of the unmanned aerial vehicle shell (1), second unmanned aerial vehicle support seat (22) for the connection of the unmanned aerial vehicle flight structure (3), the second connection mounting position (221) is arranged in the second unmanned aerial vehicle support seat (22), and the first connection mounting position (211) is arranged in the first unmanned aerial vehicle support seat (21);The second connection mounting position (221) is connected in the first connection mounting position (211), so that the second unmanned aerial vehicle support seat (22) can be detachably connected in the first unmanned aerial vehicle support seat (21).

2. The unmanned aerial vehicle of claim 1, wherein, The first unmanned aerial vehicle support seat (21) is provided with first unmanned aerial vehicle support plate one (212) and first unmanned aerial vehicle support plate two (213), and the first unmanned aerial vehicle support plate one (212) and the first unmanned aerial vehicle support plate two (213) are oppositely arranged to form the first connection mounting position (211) for the connection of the second connection mounting position (221).

3. The unmanned aerial vehicle of claim 1, wherein, The second unmanned aerial vehicle support seat (22) is provided with second unmanned aerial vehicle support seat one (222) and second unmanned aerial vehicle support seat two (223), and the second unmanned aerial vehicle support seat one (222) and the second unmanned aerial vehicle support seat two (223) are oppositely connected in the first connection mounting position (211) to be fastened.

4. The unmanned aerial vehicle of claim 3, wherein, The second unmanned aerial vehicle support seat one (222) and the second unmanned aerial vehicle support seat two (223) are respectively provided with second unmanned aerial vehicle support seat mounting position one (2221) and second unmanned aerial vehicle support seat mounting position two (2231), and the second unmanned aerial vehicle support seat mounting position one (2221) and the second unmanned aerial vehicle support seat mounting position two (2231) are connected in the first connection mounting position (211) to form the second connection mounting position (221).

5. The unmanned aerial vehicle of claim 4, wherein, The second unmanned aerial vehicle support seat one (222) and the second unmanned aerial vehicle support seat two (223) are respectively provided with flight structure mounting position one (2222) and flight structure mounting position two (2232), and the flight structure mounting position one (2222) is arranged at the other end of the second unmanned aerial vehicle support seat one (222) relative to the second unmanned aerial vehicle support seat mounting position one (2221), the flight structure mounting position two (2232) is arranged at the other end of the second unmanned aerial vehicle support seat two (223) relative to the second unmanned aerial vehicle support seat mounting position two (2231), and the unmanned aerial vehicle flight structure (3) is connected in the flight structure mounting position one (2222) or flight structure mounting position two (2232) to be fastened.

6. The unmanned aerial vehicle of claim 4, wherein, The unmanned aerial vehicle support structure (2) is further provided with a first support stabilizing structure (23) and a second support stabilizing structure (24), the second unmanned aerial vehicle support seat one (222) and the second unmanned aerial vehicle support seat two (223) are further provided with a support stabilizing mounting part one (2223) and a support stabilizing mounting part two (2233), and the first support stabilizing structure (23) and the second support stabilizing structure (24) are connected to the support stabilizing mounting part one (2223) and the support stabilizing mounting part two (2233) respectively to support the unmanned aerial vehicle.

7. The unmanned aerial vehicle of claim 6, wherein, The first support stabilizing structure (23) is provided with a first support limiting slot (231) and a first support stabilizing protrusion (232), the first support limiting slot (231) is provided with a first support limiting block (2311), and the support stabilizing mounting part one (2223) is provided with a support stabilizing connecting hole one (22231); the first support stabilizing structure (23) is connected to the first support limiting block (2311) through the support stabilizing connecting hole one (22231), and then is connected in the first support limiting slot (231) and supported through the first support limiting block (2311); The second support stabilizing structure (24) is provided with a second support limiting slot (241) and a second support stabilizing protrusion (242), the second support limiting slot (241) is provided with a second support limiting block (2411), and the support stabilizing mounting part two (2233) is provided with a support stabilizing connecting hole two (22331); the second support stabilizing structure (24) is connected to the second support limiting block (2411) through the support stabilizing connecting hole two (22331), and then is connected in the second support limiting slot (241) and supported through the second support stabilizing protrusion (242).

8. The unmanned aerial vehicle of claim 2, wherein, Further comprising a main control module (4) for controlling the flight of the unmanned aerial vehicle and a Parry waterproof layer for waterproofing, the unmanned aerial vehicle shell (1) is connected to the first unmanned aerial vehicle support plate two (213) and surrounds a control structure mounting cavity, and the first unmanned aerial vehicle support plate one (212) is arranged in the control structure mounting cavity; the main control module (4) is connected to the first unmanned aerial vehicle support plate one (212) and is electrically connected to the unmanned aerial vehicle flight structure (3); and the Parry waterproof layer is arranged on the main control module (4) and the unmanned aerial vehicle flight structure (3) for waterproofing.

9. The unmanned aerial vehicle of claim 3, wherein, The second unmanned aerial vehicle support seat (22) is further provided with a connecting support (226), and a plurality of connecting supports (226) are connected to the second unmanned aerial vehicle support seat one (222) and the second unmanned aerial vehicle support seat two (223) respectively for support. 10.A method for waterproofing a drone, the method comprising: A method for producing the Parry waterproof layer as claimed in claim 8, the method comprising the following steps: S1, cleaning: cleaning the main control module (4) after SMT by using any one of alcohol, ether, ester or alkane as a cleaning agent; S2, shielding: shielding the main control module (4), the unmanned aerial vehicle flight structure (3) and other unmanned aerial vehicle components after cleaning; S3, plasma treatment: using plasma treatment equipment to shield the main control module (4), the unmanned aerial vehicle flight structure (3) and other unmanned aerial vehicle components are treated by plasma; S4, coating: the main control module (4), the unmanned aerial vehicle flight structure (3) and other unmanned aerial vehicle components after plasma treatment are placed in the parylene vacuum coating machine for coating, forming parylene waterproof layer; S5, post-processing: the main control module (4), the unmanned aerial vehicle flight structure (3) and other unmanned aerial vehicle components after coating are deshielded.

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