Integrated lighting unmanned aerial vehicle

Abstract

The utility model relates to the technical field of unmanned aerial vehicles, in particular to an integrated lighting unmanned aerial vehicle which comprises a lighting unmanned aerial vehicle body, the lighting unmanned aerial vehicle body comprises a main vehicle body, rotors are arranged on the periphery of the main vehicle body in a matched mode, vehicle body supporting rods are arranged between the main vehicle body and the rotors, and rotating shafts are arranged on the vehicle body supporting rods in a matched mode. The integrated lighting unmanned aerial vehicle comprises a main vehicle body and a vehicle body supporting rod, the vehicle body supporting rod is connected with the main vehicle body through a rotating shaft, a lighting assembly is arranged in the vehicle body supporting rod in an embedded mode, a locking mechanism is arranged between the lighting assembly and the vehicle body supporting rod, and the locking mechanism comprises a limiting protrusion and a limiting buckle connected with the limiting protrusion. According to the lighting unmanned aerial vehicle, the lighting lamp set is embedded into the fuselage supporting rod, a lighting lamp set connector does not need to be exposed, the lighting function is achieved on the basis that the overall aerodynamic shape of the unmanned aerial vehicle is not affected, the lamp set heat dissipation plate and the supporting rod are fused, and the rotor wing air volume is effectively used for dissipating heat of the lighting lamp set.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicles, in particular to an integrated lighting unmanned aerial vehicle. Background Art

[0002] With the rapid development of science and technology, drone technology has penetrated into all areas of our lives and work. From aerial photography to agricultural spraying, from logistics distribution to disaster relief, drones are used more and more widely. In these applications, the outdoor lighting function of drones has gradually become an indispensable part. However, traditional drone lighting systems mostly use independent lighting modules installed under the fuselage, which not only increases the size and weight of the drone, but also requires frequent disassembly during use and transportation, which is extremely inconvenient. Utility Model Content

[0003] In order to solve some problems existing in the above-mentioned prior art, the utility model provides an integrated lighting drone to solve the deficiencies existing in the prior art.

[0004] To achieve the above-mentioned purpose, the utility model provides an integrated lighting drone, including a lighting drone body, the lighting drone body including a main body, the main body is cooperated with rotors arranged around, a fuselage support rod is arranged between the main body and the rotor, the fuselage support rod is cooperated with a rotating shaft, the fuselage support rod is connected to the main body through the rotating shaft, a lighting component is embedded in the fuselage support rod, a locking mechanism is arranged between the lighting component and the fuselage support rod, and the locking mechanism includes a limiting protrusion and a limiting buckle connected to the limiting protrusion.

[0005] As a further improvement of the utility model, in order to ensure the installation effect of the fuselage support rod and the lighting lamp group, a fixing groove is arranged inside the fuselage support rod, and the opening of the fixing groove is arranged downward. The fixing groove is arranged in cooperation with the locking mechanism, and the limiting protrusion is arranged to protrude from the fuselage support rod, and limiting hooks are arranged on both sides of the limiting protrusion, and a plurality of groups of heat dissipation holes are arranged on the other side of the fuselage support rod.

[0006] As a further improvement of the present invention, in order to ensure the structural stability of the lighting assembly, the lighting assembly includes a fixed connecting member and a lighting lamp group arranged below the fixed connecting member, a limiting groove is arranged in the middle of the fixed connecting member, and the limiting buckle is arranged inside the limiting groove.

[0007] As a further improvement of the utility model, in order to ensure that the limit buckle can be stably docked with the limit protrusion and avoid docking failure, the limit buckle includes a buckle shell, the middle of the buckle shell is hollowed out, a compression spring is arranged inside the buckle shell, one end of the compression spring is connected to the bottom of the buckle shell, and the other end is provided with a compression block, limiting ribs are arranged on both sides of the compression block, and connecting blocks are arranged on both sides of the buckle shell.

[0008] As a further improvement of the present invention, in order to ensure stable and reliable operation of the rotor, the main body is provided with an onboard power supply, a motion motor is provided between the rotor and the fuselage support rod, and the rotor is electrically connected to the onboard power supply through the motion motor.

[0009] As a further improvement of the present invention, in order to facilitate the use of the air volume generated by the rotor to dissipate the heat of the lighting lamp group, lamp group heat dissipation plates are respectively arranged on both sides of the limiting groove.

[0010] When the utility model works, rotors are arranged around the main body, a fuselage support rod is arranged between the main body and the rotor, a rotating shaft is arranged in cooperation with the fuselage support rod, the fuselage support rod is connected to the main body through the rotating shaft, a lighting assembly is embedded in the fuselage support rod, a limiting groove is arranged in the middle of the fixed connection piece, a limiting buckle is arranged in the limiting groove, heat dissipation plates of the lamp group are arranged on both sides of the limiting groove, a locking mechanism is arranged between the lighting assembly and the fuselage support rod, the locking mechanism includes a limiting protrusion and a limiting buckle connected to the limiting protrusion, and the machine A fixing groove is arranged inside the body support rod, and the opening of the fixing groove is arranged downward, and the fixing groove is arranged in cooperation with the locking mechanism, and a limiting protrusion is arranged to protrude from the body support rod, and limiting hooks are arranged on both sides of the limiting protrusion, and a plurality of groups of heat dissipation holes are arranged on the other side of the body support rod. The limiting buckle includes a buckle shell, and the middle of the buckle shell is hollowed out. A compression spring is arranged inside the buckle shell, one end of the compression spring is connected to the bottom of the buckle shell, and a compression block is arranged at the other end. Limiting ribs are arranged on both sides of the compression block, and clamping blocks are arranged on both sides of the buckle shell.

[0011] The beneficial effects of the utility model are as follows: the utility model provides an integrated lighting UAV, which embeds the lighting lamp group into the fuselage support rod, integrates the wiring harness internally, does not need to expose the lighting lamp group connector, has a simple and beautiful appearance, and integrates the heat dissipation plate of the lamp group with the fuselage support rod, effectively utilizes the air volume generated by the rotor to dissipate the heat of the lighting lamp group, and improves the heat dissipation efficiency. Due to the integrated design of the lighting lamp group and the fuselage support rod, the UAV does not need to frequently disassemble the lighting module during use and transportation, which not only reduces the operating difficulty and damage risk, but also improves the use efficiency and convenience of the UAV. BRIEF DESCRIPTION OF THE DRAWINGS

[0012] In order to facilitate the understanding of those skilled in the art, the present invention is further described below in conjunction with the accompanying drawings:

[0013] Figure 1 It is a structural diagram of the utility model.

[0014] Figure 2 It is a side view of the utility model.

[0015] Figure 3 This is the installation structure diagram of the lighting component and the limit buckle.

[0016] Figure 4 This is a bottom structure diagram of the utility model.

[0017] Among them, 1 main body, 101 onboard power supply, 102 motion motor, 2 rotor, 3 fuselage support rod, 301 fixed groove, 302 heat dissipation hole, 4 rotating shaft, 5 lighting assembly, 501 fixed connector, 502 lighting lamp group, 503 limiting groove, 504 lamp group heat dissipation plate, 6 locking mechanism, 7 limiting protrusion, 701 limiting hook, 8 limiting buckle, 801 buckle shell, 802 compression spring, 803 compression block, 804 limiting rib, 805 snap block. DETAILED DESCRIPTION

[0018] In order to enable those skilled in the art to better understand the technical solution in this application, Figure 1-4 The utility model is further described. The following embodiments are only used to more clearly illustrate the technical solution of the utility model, and cannot be used to limit the protection scope of the utility model.

[0019] like Figure 1-4 An integrated lighting drone is shown, including a lighting drone body, the lighting drone body including a main body 1, the main body 1 is cooperated with rotors 2 arranged around it, a fuselage support rod 3 is arranged between the main body 1 and the rotor 2, the fuselage support rod 3 is cooperated with a rotating shaft 4, the fuselage support rod 3 is connected to the main body 1 through the rotating shaft 4, a lighting component 5 is embedded in the fuselage support rod 3, a locking mechanism 6 is arranged between the lighting component 5 and the fuselage support rod 3, the locking mechanism 6 includes a limiting protrusion 7 and a limiting buckle 8 connected to the limiting protrusion 7.

[0020] A fixing groove 301 is arranged inside the fuselage support rod 3, and the opening of the fixing groove 301 is arranged downward. The fixing groove 301 is arranged in cooperation with the locking mechanism 6. The limiting protrusion 7 is arranged to protrude from the fuselage support rod 3, and limiting hooks 701 are arranged on both sides of the limiting protrusion 7. A plurality of heat dissipation holes 302 are arranged on the other side of the fuselage support rod 3.

[0021] The lighting assembly 5 includes a fixed connection member 501 and a lighting lamp group 502 arranged below the fixed connection member 501 . A limiting groove 503 is arranged in the middle of the fixed connection member 501 , and the limiting buckle 8 is arranged inside the limiting groove 503 .

[0022] The limiting buckle 8 includes a buckle shell 801, which is hollow in the middle. A compression spring 802 is arranged inside the buckle shell 801. One end of the compression spring 802 is connected to the bottom of the buckle shell 801, and the other end is provided with a compression block 803. Limiting ribs 804 are arranged on both sides of the compression block 803, and clamping blocks 805 are arranged on both sides of the buckle shell 801.

[0023] The main body 1 is provided with an onboard power supply 101 , a motion motor 102 is provided between the rotor 2 and the fuselage support rod 3 , and the rotor 2 is electrically connected to the onboard power supply 101 via the motion motor 102 .

[0024] Lamp group heat dissipation plates 504 are respectively arranged on both sides of the limiting groove 503 .

[0025] When the utility model is working, the main body 1 is cooperated with the rotor 2 around, the main body 1 and the rotor 2 are provided with a fuselage support rod 3, the fuselage support rod 3 is cooperated with the rotating shaft 4, the fuselage support rod 3 is connected to the main body 1 through the rotating shaft 4, the fuselage support rod 3 is embedded with a lighting assembly 5, a locking mechanism 6 is arranged between the lighting assembly 5 and the fuselage support rod 3, the locking mechanism 6 includes a limiting protrusion 7 and a limiting buckle 8 connected with the limiting protrusion 7; a fixing groove 301 is arranged inside the fuselage support rod 3, the fixing groove 301 is opened downward, the fixing groove 301 is arranged in cooperation with the locking mechanism 6, and the limiting protrusion 7 protrudes from the fuselage support rod 3.

[0026] When the lighting component 5 is embedded in the fuselage support rod 3, the clamping block 805 is pressed, the limiting protrusion 7 is docked with the limiting buckle 8 set in the limiting groove 503, the compression block 803 slides downward, the compression spring 802 is compressed, and the limiting ribs 804 on both sides of the compression block 803 slowly swing toward the center at the same time, and the limiting ribs 804 are clamped with the limiting hooks 701 on both sides of the limiting protrusion 7. After the clamping is completed, the lighting component 5 is clamped with the fuselage support rod 3, and the lighting lamp group 502 is embedded in the fuselage support rod 3. Through the internal integration of the wiring harness, there is no need to expose the connector of the lighting lamp group 502. The heat sink 504 of the lamp group is in contact with the inside of the fuselage support rod 3. The heat sink 504 of the lamp group is integrated with the fuselage support rod 3, and the air volume generated by the rotor 2 is effectively used to dissipate the heat of the lighting lamp group 502, thereby improving the heat dissipation efficiency.

[0027] The present utility model is not limited to the above-mentioned embodiments. On the basis of the technical solution disclosed in the present utility model, technicians in this field can make some substitutions and deformations to some technical features therein according to the disclosed technical content without creative labor, and these substitutions and deformations are all within the protection scope of the present utility model.

Claims

1. An integrated lighting drone, comprising a lighting drone body, characterized in that: The lighting drone body comprises a main body (1), the main body (1) is provided with rotors (2) around its periphery, a fuselage support rod (3) is provided between the main body (1) and the rotors (2), the fuselage support rod (3) is provided with a rotating shaft (4), the fuselage support rod (3) is connected to the main body (1) via the rotating shaft (4), a lighting component (5) is embedded in the fuselage support rod (3), a locking mechanism (6) is provided between the lighting component (5) and the fuselage support rod (3), the locking mechanism (6) comprises a limiting protrusion (7) and a limiting buckle (8) connected to the limiting protrusion (7).

2. The integrated lighting drone according to claim 1, characterized in that: A fixing groove (301) is arranged inside the fuselage support rod (3), the fixing groove (301) is arranged with its opening facing downward, the fixing groove (301) is arranged in cooperation with a locking mechanism (6), the limiting protrusion (7) is arranged to protrude from the fuselage support rod (3), limiting hooks (701) are arranged on both sides of the limiting protrusion (7), and a plurality of groups of heat dissipation holes (302) are arranged on the other side of the fuselage support rod (3).

3. The integrated lighting drone according to claim 1, characterized in that: The lighting assembly (5) comprises a fixed connection piece (501) and a lighting lamp group (502) arranged below the fixed connection piece (501); a limiting groove (503) is arranged in the middle of the fixed connection piece (501); and the limiting buckle (8) is arranged inside the limiting groove (503).

4. The integrated lighting drone according to claim 3, characterized in that: The limit buckle (8) comprises a buckle shell (801), the middle of the buckle shell (801) is hollowed out, a compression spring (802) is arranged inside the buckle shell (801), one end of the compression spring (802) is connected to the bottom of the buckle shell (801), and the other end is provided with a compression block (803), limiting ribs (804) are arranged on both sides of the compression block (803), and clamping blocks (805) are arranged on both sides of the buckle shell (801).

5. The integrated lighting drone according to claim 1, characterized in that: The main body (1) is provided with an onboard power supply (101), a motion motor (102) is provided between the rotor (2) and the fuselage support rod (3), and the rotor (2) is electrically connected to the onboard power supply (101) via the motion motor (102).

6. The integrated lighting drone according to claim 3, characterized in that: Lamp group heat dissipation plates (504) are respectively arranged on both sides of the limiting groove (503).

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