High-temperature-resistant coating for unmanned aerial vehicle and unmanned aerial vehicle

Abstract

The invention discloses a high-temperature-resistant coating for an unmanned aerial vehicle and the unmanned aerial vehicle, and relates to the technical field of unmanned aerial vehicles, the high-temperature-resistant coating comprises a bottom layer, a middle layer and a top layer, the bottom layer comprises a modified polyimide resin and nanometer aluminum oxide compound, and the middle layer comprises hollow ceramic microbeads, boron nitride nanosheets and a phosphate binder; and the top layer comprises a silicon carbide composite ceramic sol layer. According to the invention, the multi-stage thermal barrier layer is constructed to prevent body parts, components and a flight control system of the unmanned aerial vehicle from losing efficacy in a high-temperature environment, so that the unmanned aerial vehicle is ensured to work stably and reliably in the high-temperature environment; a protection structure is arranged, so that the unmanned aerial vehicle body is protected through a parachute when the unmanned aerial vehicle is powered off or other sudden faults occur, and the unmanned aerial vehicle body is prevented from being damaged by high-altitude direct falling; and a release structure is arranged to release transported articles such as fire extinguishing agents, so that the overall weight of the unmanned aerial vehicle is reduced, and the damage to the unmanned aerial vehicle when the unmanned aerial vehicle falls due to overweight is effectively reduced.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicles (UAVs), and in particular to a high-temperature resistant coating for UAVs and the UAV. Background Art

[0002] Unmanned aerial vehicle (UAV) is an unmanned aircraft that is controlled by a radio remote control device and a self-contained program control device, or is operated completely or intermittently autonomously by an onboard computer.

[0003] Drones have been widely used in scenarios such as plant protection operations, crop monitoring, agricultural planning, aerial photography and film and television production, logistics and distribution, security and patrol, power inspection, environmental monitoring and protection, as well as scientific research and education. For example, drones can be equipped with medicine boxes and spraying equipment to accurately spray pesticides, fertilizers or herbicides on farmland; they can carry sensors or cameras to monitor the growth status and pest and disease conditions of crops in real time; in the field of aerial photography, they can capture high-altitude photos and videos, providing unique perspectives and images for urban planning, land resource surveys, disaster assessments, tourism promotion, as well as movies, TV series, variety shows, etc.

[0004] However, when used in emergency rescue scenarios, such as fire investigations, inspections, and even firefighting, existing drones face high temperatures that can cause components, devices, and flight control systems to fail, forcing them to fly farther from the fire source, impacting firefighting effectiveness and efficiency. Furthermore, the probability of drones crashing in emergency rescue scenarios is higher than in more general scenarios. Existing drones have relatively weak protection measures against crashes, resulting in high scrap rates and increased operating costs.

[0005] The above problems need to be solved urgently. Summary of the Invention

[0006] The object of the present invention is to provide a high-temperature resistant coating for a drone and a drone to solve the problems raised in the above-mentioned background technology.

[0007] To achieve the above object, the present invention provides the following technical solutions:

[0008] A high-temperature resistant coating for an unmanned aerial vehicle (UAV) includes a high-temperature resistant material, wherein the high-temperature resistant material includes a bottom layer, a middle layer, and a top layer. The bottom layer includes a modified polyimide resin and a nano-alumina composite, the middle layer includes hollow ceramic microbeads, boron nitride nanosheets, and a phosphate binder; and the top layer includes a silicon carbide composite ceramic sol layer.

[0009] As a further solution of the present invention: wherein, the modified polyimide resin has a content of 30-50, and a high temperature resistance of greater than or equal to 1300° C., and the nano-alumina composite has a content of 15-25.

[0010] As a further solution of the present invention, the hollow ceramic microspheres have a weight of 5-15, a diameter of 10-50 μm, a wall thickness of 1-3 μm, and account for 45%-55% of the total volume of the intermediate layer.

[0011] As a further solution of the present invention: wherein, the bottom layer, middle layer and top layer materials are all coated on the surface of the drone, and the high temperature resistant material is formed after the bottom layer, middle layer and top layer are cured.

[0012] A drone includes a drone body, wherein folding structures are provided on both sides of the drone body, and the folding structures facilitate storage of the drone body; a clamping structure is provided on the lower side of the drone body, and the clamping structure facilitates clamping of cargo; a protective structure is provided inside the drone body, and the protective structure protects the drone body; a release structure is provided between the protective structure and the clamping structure, and the release structure can release the cargo clamped by the drone body.

[0013] As a further solution of the present invention: wherein, the folding structure includes a mounting block, which is fixedly connected to the side of the drone body, and the interior of the mounting block is movably connected to a connecting rod through a rotating shaft, a wing is installed on the connecting rod, and a nut is sleeved on the rotating shaft.

[0014] As a further solution of the present invention: wherein, the clamping structure includes a fixing frame, the interior of the fixing frame is rotatably connected to a symmetrical threaded rod, and the threaded rod is threadedly connected to a clamping block.

[0015] As a further solution of the present invention: wherein, the protective structure includes a placement bin, the placement bin is opened on the drone body, an air inlet is opened on the bottom side of the drone body, a ventilation port is opened inside the placement bin, the ventilation port is communicated with the air inlet, the placement bin is hinged with a protective plate, a magnetic plate is installed on the protective plate, an electromagnet is installed inside the placement bin, the electromagnet is electrically connected to the battery of the drone body, the placement bin is rotatably connected to a rope winding shaft, a rope is wound around the rope winding shaft, and a parachute is tied to the rope.

[0016] As a further solution of the present invention: wherein, the release structure includes a first bevel gear, the first bevel gear is fixedly connected to the rope winding shaft, a second bevel gear is meshed with one side of the first bevel gear, the second bevel gear is rotatably connected to the inner wall of the drone body, two groups of third bevel gears are provided at the other end of the second bevel gear, a connecting rod is fixedly connected between the third bevel gears, the connecting rod is rotatably connected to the inner wall of the drone body, a fourth bevel gear is fixedly connected to the symmetrical threaded rod, and the fourth bevel gear and the second bevel gear are evenly meshed with the two groups of third bevel gears respectively.

[0017] As a further solution of the present invention: wherein, a fixed rod is fixedly connected to the threaded rod, a rotating ring is slidably connected to the fixed rod, a plurality of sliding grooves are opened on one side of the rotating ring, a sliding block is fixedly connected to one side of the fourth bevel gear, and the sliding block is slidably connected inside the sliding groove.

[0018] Compared with the prior art, the present invention has the following beneficial effects:

[0019] 1. By setting a high-temperature resistant coating on the surface of the drone body and constructing a multi-level thermal barrier layer, the drone body parts, components, and flight control system can be prevented from failing under high temperature conditions, ensuring that the drone can operate stably and reliably in high temperature environments.

[0020] 2. By providing a clamping structure, it is convenient for the drone to transport items during flight, thereby enhancing the functionality of the drone.

[0021] 3. By setting up a protective structure, the drone can be protected by a parachute in the event of a power outage or other sudden failure, avoiding damage when falling directly from a high altitude.

[0022] 4. By providing a release structure, when the drone falls, the drone body clamping structure cooperates with the protection structure to open the parachute at the same time, and the release structure releases the transported items such as fire extinguishing agents, etc., so that the overall weight of the drone is reduced, and the damage to the drone when it falls due to excessive weight is effectively reduced. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 It is a schematic diagram of the overall structure of the present invention;

[0024] Figure 2 Schematic diagram of the clamping structure in the present invention;

[0025] Figure 3 A schematic diagram of an embodiment of the present invention;

[0026] Figure 4 This is a schematic diagram of the parachute structure of the present invention;

[0027] Figure 5 Schematic diagram of the rotating ring structure in the present invention;

[0028] Figure 6 Schematic diagram of the structure of the fourth bevel gear in the present invention;

[0029] The corresponding relationship between the illustration labels and component names in the figure is as follows:

[0030] 1. UAV body; 2. Folding structure; 201. Mounting block; 202. Connecting rod; 203. Rotating shaft; 204. Wing; 3. Clamping structure; 301. Fixing frame; 302. Clamping block; 303. Threaded rod; 4. Protective structure; 401. Air inlet; 402. Storage compartment; 403. Ventilation port; 404. Rope; 405. Parachute; 406. Magnetic plate; 407. Protective plate; 408. Rope winding shaft; 5. Release structure; 501. First bevel gear; 502. Second bevel gear; 503. Third bevel gear; 504. Fourth bevel gear; 505. Fixing rod; 506. Rotating ring; 507. Slide groove; 508. Sliding block; 509. Connecting rod. DETAILED DESCRIPTION

[0031] See also Figures 1 to 6 :A high temperature resistant coating for drones, including high temperature resistant materials, which include a bottom layer, an intermediate layer and a top layer. The bottom layer includes a modified polyimide resin and a nano-alumina composite. The modified polyimide resin content of the bottom layer is between 30-50, and the high temperature resistance is greater than or equal to 1300°C. The high temperature resistance of the drone can be improved by modifying the polyimide resin. The nano-alumina composite content is between 15-25, the wall thickness is 1-3μm, and it accounts for 45%-55% of the total volume of the intermediate layer. The nano-alumina composite can improve the coating The adhesion of the drone can be improved to prevent paint peeling; the middle layer includes hollow ceramic microbeads, boron nitride nanosheets and phosphate binders. The weight of hollow ceramic microbeads is between 5-15 and the diameter is between 10-50μm. The hollow ceramic microbeads are easy to settle, which can improve the uniformity of paint application and play a role in heat insulation. The boron nitride nanosheets can play a role of lateral heat conduction and barrier, and the phosphate binder can achieve ultra-low thermal conductivity; the top layer includes a silicon carbide composite ceramic sol layer, which can play a role of wear resistance and erosion resistance, and can resist external erosion.

[0032] Specifically, the bottom layer, middle layer and top layer of high-temperature resistant materials are all coated on the surface of the drone, as well as the battery compartment, motor and circuit board. After the bottom layer, middle layer and top layer are cured, a high-temperature resistant material is formed. The curing is divided into three layers, where the bottom layer curing temperature is between 160-180 degrees Celsius (to avoid high temperature damage to the drone shell), the middle layer curing temperature is between 240-260 degrees Celsius (to activate the phosphate binder reaction), and the top layer curing temperature is between 440-460 degrees Celsius (to form a ceramic layer without damaging the bottom layer). When applying high-temperature resistant materials, drones need to undergo sandblasting, pickling and phosphating. Sandblasting can increase mechanical bonding strength, sandblasting can prevent the coating from peeling off under high-temperature vibration, acid treatment can eliminate weak boundary layers and avoid bubbles at the interface between the coating and the body; phosphating treatment plays an anti-corrosion role to prevent corrosion and expansion of the coated metal in a salt spray environment.

[0033] A drone includes a drone body 1. Folding structures 2 are provided on both sides of the drone body 1, and the folding structures 2 facilitate storage of the drone body 1. A clamping structure 3 is provided on the lower side of the drone body 1, and the clamping structure 3 facilitates clamping and processing of cargo. A protective structure 4 is provided inside the drone body 1, and the protective structure 4 protects the drone body 1. A release structure 5 is provided between the protective structure 4 and the clamping structure 3, and the release structure 5 can release the cargo clamped by the drone body 1.

[0034] like Figure 1 As shown, the folding structure 2 includes a mounting block 201, which is fixedly connected to the side of the drone body 1. The interior of the mounting block 201 is movably connected to a connecting rod 202 through a rotating shaft 203. Wings 204 are installed on the connecting rod 202, and a nut is sleeved on the rotating shaft 203. When the drone body 1 needs to be folded for storage, the wings 204 are bent through the connecting rod 202 so that the wings 204 fit into the side wall of the drone body 1, thereby reducing the space occupied by the drone body 1 and making the drone body 1 easy to carry.

[0035] like Figure 2 As shown, the clamping structure 3 includes a fixing frame 301, and the fixing frame 301 is internally rotatably connected to a symmetrical threaded rod 303, and the threaded rod 303 is threadedly connected to a clamping block 302. When it is necessary to carry items, the two threaded rods 303 can be rotated to make the two clamping blocks 302 move toward the middle direction of the drone body 1 at the same time, so that the items can be clamped, making it easier for the drone body 1 to carry items.

[0036] like Figure 3 and 4As shown, the protection structure 4 includes a placement compartment 402, which is opened on the drone body 1, and an air inlet 401 is opened on the bottom side of the drone body 1, and a vent 403 is opened inside the placement compartment 402, and the vent 403 is connected to the air inlet 401. The placement compartment 402 is hinged with a protection plate 407, and a magnetic plate 406 is installed on the protection plate 407. An electromagnet is installed inside the placement compartment 402, and the electromagnet is electrically connected to the battery of the drone body 1. The interior of the placement compartment 402 is rotatably connected to a rope shaft 408, and a rope 404 is wound around the rope shaft 408. A parachute 405 is tied to the rope 404. When the battery of the drone body 1 is cut off or there is no power, the electromagnet will also lose power, thereby making the magnetic plate 406 unable to attract the electromagnet, and a torsion spring is provided at the connection between the protection plate 407 and the placement compartment 402. In the case of power failure, the torsion spring resets and the protection plate 407 is in an expanded state ( Figure 3 ), at this time, the drone body 1 falls due to power outage. When the drone body 1 falls, wind will blow through the air inlet 401 to the vent 403 and the inside of the storage compartment 402, and the parachute 405 is in a flat state inside the storage compartment 402. After being blown by the wind, it will be in an unfolded state, thereby increasing the wind-exposed area of ​​the drone body 1, which can reduce the speed of the drone body 1 when falling, and play a protective role for the drone body 1.

[0037] like Figure 4 and 5 As shown, the release structure 5 includes a first bevel gear 501, which is fixedly connected to the rope winding shaft 408, a second bevel gear 502 is meshed with one side of the first bevel gear 501, and the second bevel gear 502 is rotatably connected to the inner wall of the drone body 1, and two groups of third bevel gears 503 are provided at the other end of the second bevel gear 502, and a connecting rod 509 is fixedly connected between the third bevel gears 503, and the connecting rod 509 is rotatably connected to the inner wall of the drone body 1, and a fourth bevel gear 504 is fixedly connected to the symmetrical threaded rod 303, and the fourth bevel gear 504 and the second bevel gear 502 are evenly meshed with the two groups of third bevel gears 503 respectively. When 05 is in the unfolded state, the rope 404 will be pulled. When the rope 404 is pulled, the rope winding shaft 408 will be driven to rotate. When the rope winding shaft 408 rotates, the second bevel gear 502 will be driven to rotate through the first bevel gear 501. The second bevel gear 502 drives the third bevel gear 503 to rotate. The third bevel gear 503 drives the fourth bevel gear 504 to rotate, and then drives the two threaded rods 303 to rotate. At this time, when the two threaded rods 303 rotate, the two clamping blocks 302 will move away from each other, so that the objects are no longer clamped, and the objects are discarded. This setting is to reduce the overall weight of the drone body 1 and prevent the drone body 1 from being too heavy and causing damage.

[0038] like Figure 4 、 5When the second gear 504 is engaged with the first gear 503, the wheel 504 is engaged with the wheel 506, and the wheel 506 is engaged with the first gear 504. When the second gear 504 is engaged with the wheel 506, the wheel 506 is engaged with the wheel 506, and the wheel 506 is engaged with the wheel 506. When the second gear 504 is engaged with the wheel 506, the wheel 506 is engaged with the wheel 506, and the wheel 506 is engaged with the wheel 506. 4 is close to the third bevel gear 503, wherein when the sliding block 508 is slidably connected to the inside of the sliding groove 507, there is a certain rotation angle (between 0-10 degrees). According to the pitch angle formula, if there are 36 teeth on the gear, the degree between the teeth is 5 degrees, that is, the meshing of the teeth on the gear can be completed by rotating 5 degrees. When the fourth bevel gear 504 is close to the third bevel gear 503, the fourth bevel gear 504 is rotated to allow the fourth bevel gear 504 to mesh with the third bevel gear 503. In order to prevent the rotating ring 506 from self-slipping when the third bevel gear 503 drives the fourth bevel gear 504, an anti-skid pattern or an anti-sliding block is provided on the fixed rod 505. That is, when the third bevel gear 503 drives the fourth bevel gear 504, in the absence of external force, the fourth bevel gear 504 cannot be translated on the fixed rod 505, that is, the position of the fourth bevel gear 504 is fixed, so that the third bevel gear 503 drives the fourth bevel gear 504 to rotate.

[0039] Working principle: When the drone body 1 needs to be folded for storage, the connecting rod 202 is used to bend the wing 204 so that the wing 204 fits the side wall of the drone body 1, reducing the space occupied by the drone body 1 and making the drone body 1 easy to carry. When it is necessary to carry items, the two threaded rods 303 can be rotated to move the two clamping blocks 302 toward the middle of the drone body 1 at the same time, thereby clamping the items and making it easier for the drone body 1 to carry items. When the parachute 405 is in the unfolded state, it will pull the rope 404, and the rope 405 will be pulled. When 04 is pulled, it will drive the rope winding shaft 408 to rotate. When the rope winding shaft 408 rotates, it drives the second bevel gear 502 to rotate through the first bevel gear 501. The second bevel gear 502 drives the third bevel gear 503 to rotate. The third bevel gear 503 drives the fourth bevel gear 504 to rotate, and then drives the two threaded rods 303 to rotate. At this time, when the two threaded rods 303 rotate, the two clamping blocks 302 will move away from each other, so that the objects are no longer clamped, and the objects are discarded. This setting is to reduce the overall weight of the drone body 1 and prevent the drone body 1 from being too heavy and causing damage.

[0040] The above is only a preferred specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any technician familiar with this technical field, within the technical scope disclosed by the present invention, who makes equivalent replacements or changes based on the technical solutions and inventive concepts of the present invention, should be covered by the scope of protection of the present invention.

Claims

1. A high temperature resistant coating for drones, characterized in that: The invention comprises a bottom layer, a middle layer and a top layer. The bottom layer comprises a modified polyimide resin and a nano-alumina composite. The middle layer comprises hollow ceramic microbeads, boron nitride nanosheets and a phosphate binder. The top layer comprises a silicon carbide composite ceramic sol layer.

2. The high temperature resistant coating for drone according to claim 1, characterized in that: The modified polyimide resin has a weight of 30-50 parts, and the nano-alumina composite has a weight of 15-25 parts.

3. The high temperature resistant coating for drone according to claim 1, characterized in that: The hollow ceramic microspheres have a weight of 5-15, a diameter of 10-50 μm, a wall thickness of 1-3 μm, and account for 45%-55% of the total volume of the middle layer.

4. The high temperature resistant coating for drone according to claim 1, characterized in that: The bottom layer, middle layer and top layer materials are all coated on the surface of the drone, and after the bottom layer, middle layer and top layer are cured, a high-temperature resistant material is formed.

5. A drone, characterized in that: A high-temperature resistant coating for a drone as claimed in any one of claims 1 to 4 comprises a drone body (1), wherein folding structures (2) are provided on both sides of the drone body (1), and the folding structures (2) facilitate storage of the drone body (1); a clamping structure (3) is provided on the lower side of the drone body (1), and the clamping structure (3) facilitates clamping of cargo; a protective structure (4) is provided inside the drone body (1), and the protective structure (4) protects the drone body (1); a release structure (5) is provided between the protective structure (4) and the clamping structure (3), and the release structure (5) can release the drone body (1) from clamping cargo.

6. The drone according to claim 5, characterized in that: The folding structure (2) comprises a mounting block (201), the mounting block (201) being fixedly connected to the side of the drone body (1), the interior of the mounting block (201) being movably connected to a connecting rod (202) via a rotating shaft (203), a wing (204) being mounted on the connecting rod (202), and a nut being sleeved on the rotating shaft (203).

7. The drone according to claim 6, characterized in that: The clamping structure (3) comprises a fixing frame (301), the fixing frame (301) is internally rotatably connected to a symmetrical threaded rod (303), and the threaded rod (303) is threadedly connected to a clamping block (302).

8. The drone according to claim 7, characterized in that: The protective structure (4) comprises a storage compartment (402), the storage compartment (402) is provided on the drone body (1), an air inlet (401) is provided on the bottom side of the drone body (1), a vent (403) is provided inside the storage compartment (402), the vent (403) is connected to the air inlet (401), the storage compartment (402) is hinged with a protection plate (407), a magnetic plate (406) is installed on the protection plate (407), an electromagnet is installed inside the storage compartment (402), the electromagnet is electrically connected to the battery of the drone body (1), a rope shaft (408) is rotatably connected inside the storage compartment (402), a rope (404) is wound around the rope shaft (408), and a parachute (405) is attached to the rope (404).

9. The drone according to claim 8, characterized in that: The release structure (5) comprises a first bevel gear (501), the first bevel gear (501) is fixedly connected to the rope winding shaft (408), a second bevel gear (502) is meshed with one side of the first bevel gear (501), the second bevel gear (502) is rotatably connected to the inner wall of the drone body (1), two groups of third bevel gears (503) are provided at the other end of the second bevel gear (502), a connecting rod (509) is fixedly connected between the third bevel gears (503), the connecting rod (509) is rotatably connected to the inner wall of the drone body (1), a fourth bevel gear (504) is fixedly connected to the symmetrical threaded rod (303), and the fourth bevel gear (504) and the second bevel gear (502) are evenly meshed with the two groups of third bevel gears (503) respectively.

10. The drone according to claim 9, characterized in that: A fixed rod (505) is fixedly connected to the threaded rod (303), a rotating ring (506) is slidably connected to the fixed rod (505), a plurality of sliding grooves (507) are provided on one side of the rotating ring (506), a sliding block (508) is fixedly connected to one side of the fourth bevel gear (504), and the sliding block (508) is slidably connected inside the sliding groove (507).

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