Unmanned aerial vehicle and unmanned aerial vehicle waterproof method

Abstract

The unmanned aerial vehicle comprises an unmanned aerial vehicle shell, an unmanned aerial vehicle supporting structure used for supporting the whole unmanned aerial vehicle and an unmanned aerial vehicle flying structure used for flying of the unmanned aerial vehicle, the unmanned aerial vehicle shell is connected to the unmanned aerial vehicle supporting structure, and the unmanned aerial vehicle flying structure is connected to the outer side of the unmanned aerial vehicle supporting structure relative to the unmanned aerial vehicle shell for driving; the unmanned aerial vehicle supporting structure is provided with a first unmanned aerial vehicle supporting seat for connecting an unmanned aerial vehicle shell and a second unmanned aerial vehicle supporting seat for connecting an unmanned aerial vehicle flight structure, the second unmanned aerial vehicle supporting seat is provided with a second connecting mounting position, and the first unmanned aerial vehicle supporting seat is provided with a first connecting mounting position; the second connecting mounting position is connected to the first connecting mounting position, so that the second unmanned aerial vehicle supporting seat is detachably connected to the first unmanned aerial vehicle supporting seat. According to the structural design adopted by the scheme, the effects of effectively shortening the production time of the unmanned aerial vehicle body, improving the production efficiency of the unmanned aerial vehicle and expanding the selection diversity of production materials of the second unmanned aerial vehicle supporting seat are achieved.

Description

Technical Field

[0001] The present invention belongs to the technical field of unmanned aerial vehicles (UAVs), and in particular relates to a UAV and a UAV waterproofing method applied to the UAV. Background Art

[0002] In the existing technology, in order to produce drones of specific shapes, 3D printing technology is mostly used for production. However, 3D printing technology has low production efficiency, which easily leads to the inability to mass-produce drones and poor waterproof performance of drones, which easily leads to a shortened lifespan of drones. Therefore, the present invention proposes a new solution to the above technical problems. Summary of the Invention

[0003] The purpose of the present invention is to provide a drone that adopts a structural design of split assembly of the drone fuselage, thereby effectively shortening the production time of the drone fuselage, improving the production efficiency of the drone, and expanding the diversity of choices for the production materials of the second drone support base.

[0004] Based on this, the present invention provides a drone, comprising: A drone housing, a drone support structure for supporting the entire drone, and a drone flight structure for flying the drone, wherein the drone housing 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 housing for driving; The drone support structure is provided with a first drone support seat for connecting the drone shell and a second drone support seat for connecting the drone flight structure. The second drone support seat is provided with a second connection mounting position, and the first drone support seat is provided with a first connection mounting position; the second connection mounting position is connected to the first connection mounting position, so that the second drone support seat can be detachably connected to the first drone support seat.

[0005] As described above, the first drone support seat is provided with a first drone support plate 1 and a first drone support plate 2. The first drone support plate 1 and the first drone support plate 2 are arranged relative to each other to form the first connection installation position for connection to the second connection installation position.

[0006] In the drone as described above, the second drone support seat is provided with a second drone support seat 1 and a second drone support seat 2, and the second drone support seat 1 and the second drone support seat 2 are relatively connected and fastened at the first connection and installation position.

[0007] As described above, the second drone support seat 1 and the second drone support seat 2 are respectively provided with a second drone support seat installation position 1 and a second drone support seat installation position 2, and the second drone support seat installation position 1 and the second drone support seat installation position 2 are cooperatively connected to the first connection installation position to form the second connection installation position.

[0008] As described above, the second UAV support seat 1 and the second UAV support seat 2 are further provided with a flight structure mounting position 1 and a flight structure mounting position 2, respectively. The flight structure mounting position 1 is arranged at the other end of the second UAV support seat 1 relative to the second UAV support seat mounting position 1, and the flight structure mounting position 2 is arranged at the other end of the second UAV support seat 2 relative to the second UAV support seat mounting position 2. The UAV flight structure is connected to the flight structure mounting position 1 or the flight structure mounting position 2 for fastening.

[0009] As described above, the drone support structure is further provided with a first supporting stabilizing structure and a second supporting stabilizing structure. The second drone support seat one and the second drone support seat two are further provided with a supporting stabilizing mounting part one and a supporting stabilizing mounting part two. The first supporting stabilizing structure and the second supporting stabilizing structure are respectively connected to the supporting stabilizing mounting part one and the supporting stabilizing mounting part two to support the drone.

[0010] In the drone described above, the first support stabilizing structure is provided with a first support limiting slot and a first support stabilizing protrusion, the first support limiting slot is provided with a first support limiting block, and the first support stabilizing mounting portion is provided with a first support stabilizing connecting hole; the first support stabilizing structure is connected to the first support limiting block through the first support stabilizing connecting hole, and is further connected to the first support limiting slot and supported by the first support limiting block; The second support stabilization structure is provided with a second support limit slot and a second support stabilization protrusion. The second support limit slot is provided with a second support limit block. The second support stabilization installation part is provided with a second support stabilization connection hole. The second support stabilization structure is connected to the second support limit block through the second support stabilization connection hole, and then connected to the second support limit slot and supported by the second support stabilization protrusion.

[0011] The drone described above further includes a main control module for controlling the drone's flight and a parylene waterproof layer for waterproofing. The drone housing is connected to the first drone support plate 2 and encloses a control structure mounting cavity. The first drone support plate 1 is disposed within the control structure mounting cavity. The main control module is connected to the first drone support plate 1 and provides electrical connection to the drone's flight structure. The parylene waterproof layer is disposed on the main control module and the drone's flight structure for waterproofing.

[0012] In the drone as described above, the second drone support seat is further provided with a connecting support member, and a plurality of the connecting support members are respectively connected to the second drone support seat 1 and the second drone support seat 2 for support.

[0013] A method for waterproofing a drone, for producing the above-mentioned parylene waterproof layer, comprising the following steps: S1. Cleaning: Clean the main control module after SMT with any cleaning agent such as alcohol, ether, ester or alkane; S2. Shielding: Shield the cleaned main control module, UAV flight structure, and other UAV components; S3. Plasma treatment: Plasma treatment equipment is used to perform plasma treatment on the shielded main control module and other UAV components; S4, Coating: Place the plasma-treated main control module and other drone components in the Parylene vacuum coating machine for coating to form a Parylene waterproof layer; S5. Post-processing: Deshielding the coated main control module and other UAV components.

[0014] The implementation of the embodiments of the present invention has the following beneficial effects: 1. This solution adopts a structural design of split assembly of the UAV fuselage, which is provided with a UAV shell, a UAV support seat, and a UAV flight structure. The UAV support seat is provided with a first UAV support seat and a second UAV support seat. The first UAV support seat and the second UAV support seat are respectively provided with a first connection mounting position and a second connection mounting position. The second UAV support seat is connected to the first connection mounting position through the second connection mounting position and can be detachably connected to the first UAV support seat. By connecting the UAV shell to the first UAV support seat and connecting the UAV flight structure to the second UAV support seat relative to the second connection mounting position, the split assembly of the UAV body is realized. Then, the second UAV support seat can be produced separately through the injection molding process and then assembled to the second UAV support seat, which effectively optimizes the production method of the UAV, achieves the effect of effectively shortening the production time of the UAV fuselage, improving the production efficiency of the UAV, and expanding the diversity of production materials for the second UAV support seat. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the following briefly introduces the drawings required for use in the description of the embodiments. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without any creative work.

[0016] Figure 1 Schematic diagram of the structure of an embodiment of the present invention; Figure 2 To correspond Figure 1 Structural diagram of the other direction; Figure 3 To correspond Figure 2 Structural diagram of the other direction; Figure 4 To correspond Figure 3 Structural diagram of the other direction; Figure 5 An exploded diagram of the structure of an embodiment of the present invention; Figure 6 To correspond Figure 5 Structural diagram of the other direction; Figure 7 To correspond Figure 6 Structural diagram of the other direction; Figure 8 To correspond Figure 7 Structural diagram of the other direction; Figure 9 A schematic diagram of the structure in which the first supporting and stabilizing structure and the second supporting and stabilizing structure are connected to the second UAV supporting base; Figure 10 To correspond Figure 9 Structural explosion diagram; Figure 11 To correspond Figure 10 Schematic diagram of the structure in another direction.

[0017] In the figure: 1-UAV shell, 11-UAV side panel, 12-GPS installation position; 2-UAV support structure, 21-first UAV support seat, 211-first connection installation position, 212-first UAV support plate 1, 213-first UAV support plate 2, 22-second UAV support seat, 221-second connection installation position, 222-second UAV support seat 1, 2221-second UAV support seat installation position 1, 2222-flight structure installation position 1, 2223-support stabilization installation part 1, 22231-support stabilization connection hole 1, 2224-second UAV support seat connection wire groove 1, 223-second UAV support seat 2. 2231-Second UAV support seat installation position 2, 2232-Flight structure installation position 2, 2233-Support stabilization installation part 2, 22331-Support stabilization connection hole 2, 2234-Second UAV support seat connection wire groove 2, 226-Connecting support, 23-First support stabilization structure, 231-First support limit slot, 2311-First support limit block, 232-First support stabilization protrusion, 24-Second support stabilization structure, 241-Second support limit slot, 2411-Second support limit block, 242-Second support stabilization protrusion; 3-UAV flight structure, 31-Flight structure connection seat; 4-Main control module. DETAILED DESCRIPTION

[0018] The following will clearly and completely describe the technical solutions in the embodiments of the present invention 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. All other embodiments obtained by ordinary technicians in this field based on the embodiments of the present invention without making any creative efforts shall fall within the scope of protection of the present invention.

[0019] like Figures 1 to 11 As shown, an embodiment of the present invention provides a drone, comprising: 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 lifting power to drive the drone through the drone flight structure 3; the drone support structure 2 is provided with a first drone support seat 21 for connecting the drone shell 1, and a second drone support seat 22 for connecting the drone flight structure 3, the second drone support seat 22 is provided with a second connection mounting position 221, and the first drone support seat 21 is provided with 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 seat 22 can be detachably connected to the first drone support seat 21 to improve the convenience of installation.

[0020] Specifically, the first UAV support seat 21 is provided with a first UAV support plate 1 212 and a first UAV support plate 2 213. The first UAV support plate 1 212 and the first UAV support plate 2 213 are relatively arranged to form the first connection installation position 211 for connection to the second connection installation position 221; the relative arrangement of the first UAV support plate 1 212 and the first UAV support plate 213 forms a precisely matched installation space therebetween, and the installation space is adapted to the shape and size of the second connection installation position 221, thereby achieving fast and accurate connection, effectively improving the efficiency and accuracy of UAV assembly, and reducing errors that may occur during the installation process.

[0021] Furthermore, the second UAV support seat 22 is provided with a second UAV support seat 1 222 and a second UAV support seat 2 223, and the second UAV support seat 1 222 and the second UAV support seat 2 223 are relatively connected to the first connection installation position 211 for fastening; in an embodiment of the present invention, the second UAV support seat 1 222 and the second UAV support seat 2 223 are produced by injection molding process, and preferably, one second UAV support seat 1 222 and one second UAV support seat 2 223 are provided on each side of the UAV, and the two second UAV support seats 1 222 are diagonally connected to the first connection installation position 211 provided on both sides, and the two second UAV support seats 223 are diagonally connected to the first connection installation position 211 provided on both sides, so as to improve the stability of the UAV during flight, and at the same time improve the production convenience of the second UAV support seat 1 222 and the second UAV support seat 2 223.

[0022] Furthermore, the second drone support seat 1 222 and the second drone support seat 2 223 are respectively provided with a second drone support seat installation position 1 2221 and a second drone support seat installation position 2 2231, and the second drone support seat installation position 1 2221 and the second drone support seat installation position 2 2231 are cooperated and connected to the first connection installation position 211 to form the second connection installation position 221; the second drone support seat installation position 1 2221 is provided with a second drone support seat connection half hole 1, and the second drone support seat installation position 2 2231 is provided with a second drone support seat connection half hole 2, and the second drone support seat connection half hole 1 and the second drone support seat connection half hole 2 are connected to form a complete second drone support seat connection hole 1, so that the second drone support seat 1 222 and the second drone support seat 2 223 can be connected through the second drone support seat connection hole 1, thereby improving the installation positioning accuracy, and facilitating that the second drone support seat 22 can be fastened to the first drone support seat 21 through the second connection installation position 221, thereby enhancing the stability after connection.

[0023] Furthermore, the second UAV support seat 1 222 and the second UAV support seat 2 223 are further provided with a flight structure mounting position 1 2222 and a flight structure mounting position 2 2232, respectively. The flight structure mounting position 1 2222 is arranged at the other end of the second UAV support seat 1 222 relative to the second UAV support seat mounting position 1 2221, and the flight structure mounting position 2 2232 is arranged at the other end of the second UAV support seat 2 2231 relative to the second UAV support seat mounting position 2 2231. The UAV flight structure 3 is connected to the flight structure mounting position 1 2222 or the flight structure mounting position 2 2232 for fastening. With such a design, the UAV flight structure 3 can be fastened to the flight structure mounting position 1 2222 and the flight structure mounting position 2 2232. It is fastened to the second UAV support seat 22, so that the UAV flight structure 3 is stably installed on the UAV support structure 2, ensuring power transmission and control accuracy during flight, and improving flight stability and reliability; the flight structure mounting position 1 2222 is provided with a first flight structure connection hole and a second flight structure connection hole, and the second flight structure connection holes are equidistantly arranged around the first flight structure connection hole; the UAV flight structure 3 is provided with a flight structure connection seat 31, and the flight structure connection seat 31 is provided with a flight structure matching hole corresponding to the second flight structure connection hole one by one, so that the UAV flight structure 3 is fastened to the flight structure mounting position 1 2222 through a first threaded connector, thereby improving the fastness of the connection of the UAV flight structure 3; The second flight structure mounting position 2232 is provided with a third flight structure connecting hole and a fourth flight structure connecting hole. The fourth flight structure connecting hole is arranged equidistantly around the third flight structure connecting hole, and the four flight structure connecting holes correspond one-to-one with the flight structure matching holes, so that the UAV flight structure 3 can be fastened to the second flight structure mounting position 2232 through a second threaded connection, thereby improving the tightness of the connection of the UAV flight structure 3.

[0024] Furthermore, the UAV support structure 2 is also provided with a first supporting stabilizing structure 23 and a second supporting stabilizing structure 24. The second UAV support seat 1 222 and the second UAV support seat 2 223 are also provided with a supporting stabilizing mounting part 1 2223 and a supporting stabilizing mounting part 2 2233. The first supporting stabilizing structure 23 and the second supporting stabilizing structure 24 are respectively connected to the supporting stabilizing mounting part 1 2223 and the supporting stabilizing mounting part 2 2233 to support the UAV, so as to ensure that the UAV can be stably docked on the ground after the flight, avoid direct docking to cause damage to the UAV, and improve the safety of the UAV docking; at the same time, ensure the horizontality of the second UAV support seat 1 222 and the second UAV support seat 2 223 after connection, so as to reduce the wear on the connection between the second UAV support seat 1 222 and the second UAV support seat 2 223, thereby extending the service life of the UAV.

[0025] Furthermore, the first supporting and stabilizing structure 23 is provided with a first supporting and limiting slot 231 and a first supporting and stabilizing protrusion 232. The first supporting and limiting slot 231 is provided with a first supporting and limiting block 2311. The supporting and stabilizing mounting portion 1 2223 is provided with a supporting and stabilizing connecting hole 1 22231. The first supporting and stabilizing structure 23 is connected to the first supporting and limiting block 2311 through the supporting and stabilizing connecting hole 1 22231, and then connected to the first supporting and limiting slot 231 and supported by the first supporting and limiting block 2311, so as to perform a dual position limitation on the first supporting and stabilizing structure 23 by the first supporting and limiting slot 231 and thereby ensure that when the first supporting and stabilizing protrusion 232 abuts against the ground, the grounding stability of the first supporting and stabilizing structure 23 is enhanced. The first supporting and stabilizing protrusion 232 is designed to be flat at the point where it contacts the ground, so as to expand the contact area between the first supporting and stabilizing protrusion 232 and the ground, thereby enhancing the grounding stability of the first supporting and stabilizing structure 23. 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. The second support stabilizing mounting part 2233 is provided with a second support stabilizing connecting hole 22331. The second support stabilizing structure 24 is connected to the second support limiting block 2411 through the second support stabilizing connecting hole 22331, and then connected to the second support limiting slot 241 and supported by the second support stabilizing protrusion 242, so as to perform doubly limiting on the second support stabilizing structure 24 by the second support limiting slot 241 and the second support limiting block 2411, thereby ensuring that when the second support stabilizing protrusion 242 abuts against the ground, the stability of the second support stabilizing structure 24 grounding is enhanced. The second support stabilizing protrusion 242 contacting the ground is designed to be flat, so as to expand the contact area between the second support stabilizing protrusion 242 and the ground, thereby enhancing the stability of the second support stabilizing structure 24 grounding.

[0026] Furthermore, an embodiment of the present invention provides a drone, further comprising a main control module 4 for controlling drone flight and a parylene waterproof layer for waterproofing. The drone housing 1 is connected to the first drone support plate 213 and encloses a control structure installation cavity, wherein the first drone support plate 1 212 is disposed within the control structure installation cavity. The second drone support seat 1 222 and the second drone support seat 223 are further provided with a second drone support seat connection wire groove 1 2224 and a second drone support seat connection wire groove 2 2234, wherein the second drone support seat connection wire groove 1 2224 and the second drone support seat connection wire groove 2 2234 are connected to the first flight structure connection hole and the third flight structure connection hole, respectively. The main control module 4 is connected to the first UAV support plate 1 212; the UAV flight structure 3 set on the second UAV support seat 1 222 and the second UAV support seat 2 223 is connected to the main control module 4 through the connecting wires installed in the second UAV support seat connecting wire groove 1 2224 and the second UAV support seat connecting wire groove 2 2234, respectively, so as to control the rotation of the UAV flight structure 3 through the main control module 4, thereby driving the UAV to fly; with this design, the connecting wires are respectively installed in the second UAV support seat connecting wire groove 1 2224 and the second UAV support seat connecting wire groove 2 2234, which effectively improves the stability and safety of the UAV during operation.

[0027] The parylene waterproof layer is provided on the main control module 4 and the UAV flight structure 3 for waterproofing. In the embodiment of the present invention, the parylene waterproof layer is vacuum-coated using a parylene vacuum coating machine. Parylene vacuum coating technology is an advanced process for coating polyparaxylene materials. Parylene vacuum coating technology deposits polymer films on the surface of an object through chemical vapor deposition. The specific process includes three steps: vaporization, cracking, and polymerization. First, the parylene raw material is vaporized at 150°C, then cracked into monomers at 650°C, and finally uniformly coated on the surface of the coating object by vapor deposition at room temperature. The entire Parylene vacuum coating process must be performed under vacuum conditions to ensure uniform coating without blind spots, covering every part of the object to be coated, including sharp edges, inside gaps, and extremely fine pinholes. This provides waterproof, moisture-proof, dust-proof, and insulating protection for electronic components, thereby improving the reliability and service life of electronic products. In this embodiment of the present invention, the main control module 4, drone flight structure 3, and connecting cables are coated with a nano- to micron-scale Parylene waterproof layer using Parylene vacuum coating technology to enhance applicability to different drone models, thereby improving the drone's overall waterproof performance and extending its service life.

[0028] Furthermore, a connecting support 226 is provided on the second UAV support seat 22, and the second UAV support seat 1 222 and the second UAV support seat 2 223 both adopt an integrally formed structural design to improve the convenience of the second UAV support seat 1 222 and the second UAV support seat 2 223 being produced separately by injection molding process; multiple connecting supports 226 are respectively connected to the second UAV support seat 1 222 and the second UAV support seat 2 223 for support to avoid damage to the second UAV support seat 1 222 and the second UAV support seat 2 223 due to excessive local stress, thereby extending the service life of the second UAV support seat 1 222 and the second UAV support seat 2 223; in an embodiment of the present invention, the connecting support 226 is connected to the second UAV support seat 1 222 and the second UAV support seat 2 223 by glue connection to improve the convenience of connection.

[0029] In the embodiment of the present invention, the drone housing 1 is provided with a drone side panel 11 and a GPS installation position 12. The drone side panel 11 adopts a laser engraving and light-transmitting process, which can enhance the drone's aesthetics and sense of technology, thereby enhancing the drone's market competitiveness; the GPS installation position 12 is used to install a GPS, which is electrically connected to the main control module 4 and is coated with a nano- to micron-level parylene waterproof layer. The origin information can be preset by the main control module 4, so that the drone can automatically return through GPS positioning in the event of an accident, thereby reducing losses.

[0030] The present invention also provides a method for waterproofing a drone, which is used to produce the above-mentioned parylene waterproof layer. The method for waterproofing a drone comprises the following steps: 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 parylene. Therefore, the circuit board on the main control module 4 after SMT can be cleaned with any cleaning agent such as alcohol (such as methanol, ethanol, isopropyl alcohol, and n-butanol), ether (such as tertiary methyl ether, isopropyl ether, ethylene glycol monomethyl ether, and ethylene glycol dimethyl ether), ester (such as ethyl acetate, isopropyl acetate, and n-butyl acetate), or alkane (n-hexane, n-heptane, and n-pentane) to improve the adhesion of parylene during the coating process. S2. Shielding: The Parylene coating process will cover the pads and connectors on the circuit board of the main control module 4, the UAV flight structure 3, the UAV components, the contact points of the connectors and the plug interfaces, resulting in poor connection or increased contact resistance. Before coating, it is necessary to use one of the following: adhesive tape, solder mask, UV glue, silicone, or metal plugs to shield the pads and connectors on the circuit board of the cleaned main control module 4, the UAV flight structure 3, the UAV components, the connectors and the plug interfaces to ensure that the normal functions and performance of all UAV components are not affected after coating, thereby enhancing the connection stability of the UAV after coating; S3. Plasma Treatment: After all components of the drone are shielded, plasma treatment is performed on the solder pads and connectors on the circuit board of the shielded main control module 4, the drone flight structure 3, the drone components, connectors, and plug interfaces using a plasma treatment device to effectively change the surface condition of all components of the drone and increase the adhesion of the parylene coating on their surfaces. In the present invention, the plasma treatment is preferably performed using one of argon, oxygen, hydrogen, or a combination of argon / oxygen or argon / hydrogen. The treatment power is 300-600 W, and the treatment time is 100-600 seconds to increase the adhesion of the parylene coating on the surfaces of all components of the drone. S4. Coating: Place the pads and connectors on the circuit board of the main control module 4 after plasma treatment, the UAV flight structure 3, the UAV components, connectors and plug interfaces in a parylene vacuum coating machine for coating to form a parylene waterproof layer of nanometer to micrometer level. In the embodiment of the present invention, according to the usage scenarios of the UAV in different states, the parylene material can be selected from C type, F type, and AF4 type, and the coating thickness can be selected from 10μm to 30μm to enhance the applicability of the UAV in different environments. Parylene C type: Parylene C type contains chlorine atoms, which makes it have better moisture resistance and chemical corrosion resistance, and can effectively prevent moisture from invading the UAV, while being resistant to various chemicals. It has good tolerance, which helps to extend the service life of drones in humid environments; Parylene F type: Parylene F type contains fluorine atoms, which makes it have better chemical resistance and high temperature resistance, which can ensure that the drone maintains stable performance at higher temperatures, and has excellent tolerance to a variety of chemicals, which helps to extend the service life of drones in high temperature environments; Parylene AF4 type: Parylene AF4 type contains fluorine and aromatic ring structure, which makes it have higher high temperature resistance and chemical resistance, which can ensure that the drone maintains stable performance at higher temperatures, and has excellent tolerance to a variety of chemicals, which helps to extend the service life of drones in high temperature and harsh environments.

[0031] S5. Post-processing: Deshielding the pads and connectors on the circuit board of the main control module 4 after coating, the UAV flight structure 3, the UAV components, connectors and plug interfaces. Preferably, the deshielding process is performed by one of laser cutting, laser etching, and robotic glue tearing to ensure that the normal functions and performances 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 plug interfaces after coating are not affected.

[0032] It should be understood that the terms "first", "second", etc. are used in the present invention to describe various information, but such information should not be limited to these terms, which are only used to distinguish the same type of information from each other. For example, without departing from the scope of the present invention, "first" information may also be referred to as "second" information, and similarly, "second" information may also be referred to as "first" information. In addition, the orientations or positional relationships indicated by the terms "center", "up", "down", "left", "right", "vertical", "horizontal", "inside", "outside", etc. are 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 device or element referred to must have a specific orientation, be constructed and operate in a specific orientation, and therefore should not be understood as limiting the present invention.

[0033] The above is a preferred embodiment of the present invention. It should be pointed out that for ordinary technicians in this technical field, several improvements and modifications can be made without departing from the principles of the present invention. 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: include: A drone housing (1), a drone support structure (2) for supporting the entire drone, and a drone flight structure (3) for flying the drone, wherein the drone housing (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 housing (1) for driving; The UAV support structure (2) is provided with a first UAV support seat (21) for connecting the UAV housing (1), and a second UAV support seat (22) for connecting the UAV flight structure (3), wherein the second UAV support seat (22) is provided with a second connection mounting position (221), and the first UAV support seat (21) is provided with 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 UAV support seat (22) can be detachably connected to the first UAV support seat (21).

2. The drone according to claim 1, characterized in that: The first UAV support seat (21) is provided with a first UAV support plate 1 (212) and a first UAV support plate 2 (213), wherein the first UAV support plate 1 (212) and the first UAV support plate 2 (213) are arranged relative to each other to form the first connection installation position (211) for connection to the second connection installation position (221).

3. The drone according to claim 1, wherein: The second UAV support seat (22) is provided with a second UAV support seat 1 (222) and a second UAV support seat 2 (223), and the second UAV support seat 1 (222) and the second UAV support seat 2 (223) are relatively connected to the first connection installation position (211) for fastening.

4. The drone according to claim 3, characterized in that: The second UAV support seat 1 (222) and the second UAV support seat 2 (223) are respectively provided with a second UAV support seat installation position 1 (2221) and a second UAV support seat installation position 2 (2231); the second UAV support seat installation position 1 (2221) and the second UAV support seat installation position 2 (2231) are cooperatively connected to the first connection installation position (211) to form the second connection installation position (221).

5. The drone according to claim 4, characterized in that: The second UAV support seat 1 (222) and the second UAV support seat 2 (223) are further provided with a flight structure mounting position 1 (2222) and a flight structure mounting position 2 (2232), respectively. The flight structure mounting position 1 (2222) is provided at the other end of the second UAV support seat 1 (2221) relative to the second UAV support seat mounting position 1 (2221), and the flight structure mounting position 2 (2232) is provided at the other end of the second UAV support seat 2 (2231) relative to the second UAV support seat mounting position 2 (2231). The UAV flight structure (3) is connected to the flight structure mounting position 1 (2222) or the flight structure mounting position 2 (2232) for fastening.

6. The drone according to claim 4, characterized in that: The UAV support structure (2) is further provided with a first supporting stabilizing structure (23) and a second supporting stabilizing structure (24); the second UAV support seat 1 (222) and the second UAV support seat 2 (223) are further provided with a supporting stabilizing mounting portion 1 (2223) and a supporting stabilizing mounting portion 2 (2233); the first supporting stabilizing structure (23) and the second supporting stabilizing structure (24) are respectively connected to the supporting stabilizing mounting portion 1 (2223) and the supporting stabilizing mounting portion 2 (2233) to support the UAV.

7. The drone according to claim 6, characterized in that: The first supporting and stabilizing structure (23) is provided with a first supporting and limiting slot (231) and a first supporting and stabilizing protrusion (232); the first supporting and limiting slot (231) is provided with a first supporting and limiting block (2311); the first supporting and stabilizing mounting portion (2223) is provided with a supporting and stabilizing connecting hole (22231); the first supporting and stabilizing structure (23) is connected to the first supporting and limiting block (2311) through the supporting and stabilizing connecting hole (22231), and is further connected to the first supporting and limiting slot (231) and supported by the first supporting and 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); the second support stabilizing mounting portion (2233) is provided with a second support stabilizing connecting hole (22331); the second support stabilizing structure (24) is connected to the second support limiting block (2411) through the second support stabilizing connecting hole (22331), and is further connected to the second support limiting slot (241) and supported by the second support stabilizing protrusion (242).

8. The drone according to claim 2, characterized in that: The invention also includes a main control module (4) for controlling the flight of the UAV and a Parylene waterproof layer for waterproofing. The UAV housing (1) is connected to the first UAV support plate 2 (213) and is surrounded by a control structure installation cavity. The first UAV support plate 1 (212) is arranged in the control structure installation cavity. The main control module (4) is connected to the first UAV support plate 1 (212) and is electrically connected to the UAV flight structure (3). The Parylene waterproof layer is arranged on the main control module (4) and the UAV flight structure (3) for waterproofing.

9. The drone according to claim 3, characterized in that: The second UAV support seat (22) is further provided with a connecting support member (226), and a plurality of the connecting support members (226) are respectively connected to the second UAV support seat 1 (222) and the second UAV support seat 2 (223) for support.

10. A method for waterproofing a drone, characterized in that: For producing the Parylene waterproof layer as claimed in claim 8, the drone waterproofing method comprises the following steps: S1. Cleaning: Clean the main control module (4) after SMT by using any one of alcohol, ether, ester or alkane cleaning agents; S2, shielding: performing site shielding on the cleaned main control module (4), the UAV flight structure (3) and other UAV components; S3, plasma treatment: using plasma treatment equipment to perform plasma treatment on the shielded main control module (4), the UAV flight structure (3) and other UAV components; S4, coating: Plating the plasma-treated main control module (4), the UAV flight structure (3) and other UAV components in a Parylene vacuum coating machine for coating to form a Parylene waterproof layer; S5, post-processing: deshielding the coated main control module (4), the UAV flight structure (3) and other UAV components.

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