Formation performance unmanned aerial vehicle

Abstract

The formation performance unmanned aerial vehicle comprises a vehicle body, a radiator and a lamp, the radiator comprises a heat conduction installation frame and a plurality of cooling fins arranged on the outer side of the heat conduction installation frame, the vehicle body is installed at the top of the heat conduction installation frame, the lamp is installed at the bottom of the heat conduction installation frame, and the cooling fins are located on the outer side of the vehicle body and the outer side of the lamp. A flow guide gap is formed between every two adjacent heat dissipation fins, and the extending direction of the flow guide gaps is the same as the height direction of the machine body. The formation performance unmanned aerial vehicle has the advantage of being good in heat dissipation performance, the heat conduction support is arranged between the lamp and the vehicle body to conduct heat, and the heat is dissipated out through the heat dissipation fins located on the outer side of the lamp and the outer side of the vehicle body. And the extending direction of the flow guide gap between every two adjacent heat dissipation fins is the same as the height direction of the machine body, so that the blocking of the heat dissipation fins to airflow is reduced, the flowing speed of the airflow in the flow guide gaps is increased, and the heat dissipation efficiency is improved.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicles, in particular to a formation performance unmanned aerial vehicle. Background Art

[0002] Drone formation performances usually consist of groups of drones carrying lights. The groups perform specific programs in the air to form a pleasing light show. Due to its cool spatial shape, it is gradually being promoted throughout the country and even the world. During the performance, the lighting effect on the drone will determine the overall performance effect. The greater the power of the light, the better the lighting effect. However, high power means high heat generation. Therefore, how to improve the heat dissipation performance of formation performance drones has become an urgent problem to be solved in this field. Utility Model Content

[0003] The technical problem to be solved by the utility model is to provide a formation performance UAV with good heat dissipation performance.

[0004] In order to solve the above technical problems, the technical solution adopted by the utility model is: a formation performance UAV, including a fuselage, a radiator and a lamp, the radiator including a heat-conducting mounting frame and a plurality of heat-dissipating fins arranged on the outside of the heat-conducting mounting frame, the fuselage is installed on the top of the heat-conducting mounting frame, the lamp is installed on the bottom of the heat-conducting mounting frame, the heat-dissipating fins are located on the outside of the fuselage and the lamp, and a guide gap is formed between two adjacent heat-dissipating fins, and the extension direction of the guide gap is the same as the height direction of the fuselage.

[0005] Furthermore, a columnar protrusion is provided at the bottom of the fuselage, a mounting groove is provided at the top of the heat-conducting mounting frame, and the columnar protrusion is installed in the mounting groove.

[0006] Furthermore, an outer side wall of the heat-conducting mounting frame is provided with a through hole communicating with the mounting groove.

[0007] Furthermore, a first extension portion extending outward is provided on the top of the heat-conducting mounting frame, the top of the first extension portion is connected to the fuselage, and the heat dissipation fins are installed on the first extension portion.

[0008] Furthermore, the first extension portion is connected to the fuselage via snaps and / or bolts.

[0009] Furthermore, a second extension portion is provided at one end of the first extension portion away from the heat-conducting mounting frame, the extension direction of the second extension portion is perpendicular to the extension direction of the first extension portion, and the heat dissipation fins are installed on the outer side wall of the second extension portion.

[0010] Furthermore, the second extension portion extends toward the bottom direction of the first extension portion, and the body is provided with a positioning protrusion, and the positioning protrusion abuts against a side of the second extension portion away from the heat dissipation fins.

[0011] Furthermore, the first extension portion is provided with a hollow hole.

[0012] The beneficial effect of the utility model is that the formation performance UAV provided by the utility model has the characteristic of good heat dissipation performance. Heat is conducted by arranging a heat-conducting bracket between the lamp and the fuselage, and the heat is dissipated through the heat dissipation fins located on the outside of the lamp and the fuselage. In addition, the extension direction of the guide gap between two adjacent heat dissipation fins is set to be the same as the height direction of the fuselage, thereby reducing the obstruction of the heat dissipation fins to the airflow, accelerating the flow speed of the airflow in the guide gap, and improving the heat dissipation efficiency. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] Figure 1 This is an assembly diagram of a formation performance UAV according to Embodiment 1 of the present utility model;

[0014] Figure 2 This is an exploded view of a formation performance drone according to Embodiment 1 of the present utility model.

[0015] Description of labels:

[0016] 1. Body; 11. Columnar protrusion; 12. Motor; 13. Blade; 2. Heat-conducting mounting frame; 21. First extension; 22. Second extension; 23. Through hole; 24. Mounting groove; 3. Heat dissipation fin; 31. Guide gap; 4. Side light panel; 5. Bottom light panel; 6. Lamp cover. DETAILED DESCRIPTION

[0017] In order to explain the technical content, achieved objectives and effects of the present invention in detail, the following is an explanation in conjunction with the implementation modes and the accompanying drawings.

[0018] Please refer to Figure 1 as well as Figure 2 A formation performance UAV comprises a fuselage 1, a radiator and a lamp, wherein the radiator comprises a heat-conducting mounting frame 2 and a plurality of heat-dissipating fins 3 arranged on the outside of the heat-conducting mounting frame 2, the fuselage 1 is mounted on the top of the heat-conducting mounting frame 2, the lamp is mounted on the bottom of the heat-conducting mounting frame 2, the heat-dissipating fins 3 are located on the outside of the fuselage 1 and the lamp, and a guide gap 31 is formed between two adjacent heat-dissipating fins 3, and the extension direction of the guide gap 31 is the same as the height direction of the fuselage 1.

[0019] From the above description, it can be seen that the beneficial effect of the utility model is that heat is conducted by arranging a heat-conducting bracket between the lamp and the body 1, and the heat is dissipated through the heat dissipation fins 3 located on the outside of the lamp and the body 1, and the extension direction of the guide gap 31 between two adjacent heat dissipation fins 3 is set to be the same as the height direction of the body 1, thereby reducing the obstruction of the heat dissipation fins 3 to the airflow, accelerating the flow speed of the airflow in the guide gap 31, and improving the heat dissipation efficiency.

[0020] Furthermore, a columnar protrusion 11 is provided at the bottom of the body 1 , and a mounting groove 24 is provided at the top of the heat-conducting mounting frame 2 , and the columnar protrusion 11 is installed in the mounting groove 24 .

[0021] It can be seen from the above description that by installing the columnar protrusion 11 in the installation groove 24 of the heat-conducting mounting frame 2, the contact area between the heat-conducting mounting frame 2 and the body 1 can be increased, which is beneficial to further improve the heat dissipation performance.

[0022] Furthermore, the outer wall of the heat-conducting mounting frame 2 is provided with a through hole 23 communicating with the mounting groove 24 .

[0023] It can be seen from the above description that the through hole 23 can reduce the weight of the heat-conducting mounting frame 2 .

[0024] Furthermore, a first extension portion 21 extending outward is provided on the top of the heat-conducting mounting frame 2 , and the top of the first extension portion 21 is connected to the body 1 , and the heat dissipation fins 3 are installed on the first extension portion 21 .

[0025] It can be seen from the above description that the first extension portion 21 is convenient for connection with the fuselage 1 , thereby ensuring the stability of the installation of the heat-conducting mounting frame 2 and the fuselage 1 .

[0026] Furthermore, the first extension portion 21 is connected to the fuselage 1 via snaps and / or bolts.

[0027] It can be seen from the above description that the connection method between the first extension portion 21 and the body 1 can be set according to actual application requirements.

[0028] Furthermore, a second extension portion 22 is provided at one end of the first extension portion 21 away from the heat-conducting mounting frame 2 . The extension direction of the second extension portion 22 is perpendicular to the extension direction of the first extension portion 21 . The heat dissipation fins 3 are mounted on the outer side wall of the second extension portion 22 .

[0029] It can be seen from the above description that the second extension portion 22 facilitates the arrangement of the heat dissipation fins 3 , thereby ensuring the structural stability of the heat dissipation fins 3 .

[0030] Furthermore, the second extension portion 22 extends toward the top of the first extension portion 21 , and the body 1 is provided with a positioning protrusion, which abuts against a side of the second extension portion 22 away from the heat dissipation fin 3 .

[0031] It can be known from the above description that the positioning protrusion is provided to cooperate with the second extension portion 22 to play a positioning role in the assembly of the heat-conducting mounting frame 2 and the fuselage 1 .

[0032] Furthermore, the first extension portion 21 is provided with a hollow hole.

[0033] It can be seen from the above description that the hollow hole can reduce the weight of the first extension portion 21 .

[0034] Please refer to Figure 1 and Figure 2 The first embodiment of the utility model is: a formation performance UAV, including a fuselage 1, a radiator and a lamp, the fuselage 1 is provided with a motor 12 and a propeller 13 connected to the output shaft of the motor 12, and the propeller 13 is driven by the motor 12 to rotate, thereby achieving take-off; the radiator includes a heat-conducting mounting frame 2 and a plurality of heat-dissipating fins 3 arranged on the outside of the heat-conducting mounting frame 2, the fuselage 1 is installed on the top of the heat-conducting mounting frame 2, the lamp is installed on the bottom of the heat-conducting mounting frame 2, and the heat-dissipating fins 3 are located between the fuselage 1 and the lamp. On the outside of the lamp, a guide gap 31 is formed between two adjacent heat sink fins 3, and the extension direction of the guide gap 31 is the same as the height direction of the fuselage 1. It can be understood that by arranging a heat-conducting bracket between the lamp and the fuselage 1 to conduct heat, the heat is dissipated through the heat sink fins 3 located on the outside of the lamp and the fuselage 1, and the extension direction of the guide gap 31 between two adjacent heat sink fins 3 is the same as the height direction of the fuselage 1, which reduces the obstruction of the heat sink fins 3 to the airflow, speeds up the flow of the airflow in the guide gap 31, and improves the heat dissipation efficiency.

[0035] Preferably, a columnar protrusion 11 is provided at the bottom of the fuselage 1, and a mounting groove 24 is provided at the top of the heat-conducting mounting frame 2, and the columnar protrusion 11 is installed in the mounting groove 24. The columnar protrusion 11 is arranged to be installed in the mounting groove 24 of the heat-conducting mounting frame 2, so that the contact area between the heat-conducting mounting frame 2 and the fuselage 1 can be increased, which is conducive to further improving the heat dissipation performance. Specifically, the outer wall of the heat-conducting mounting frame 2 is provided with a through hole 23 connected to the mounting groove 24, and the through hole 23 can reduce the weight of the heat-conducting mounting frame 2; more specifically, the top of the heat-conducting mounting frame 2 is provided with a first extension portion 21 extending toward the outside thereof, and the top of the first extension portion 21 is connected to the fuselage 1, and the heat dissipation fins 3 are installed on the first extension portion 21, and the first extension portion 21 is convenient for connection with the fuselage 1, thereby ensuring the stability of the installation of the heat-conducting mounting frame 2 and the fuselage 1.

[0036] Optionally, the first extension portion 21 is connected to the fuselage 1 by means of clips and / or bolts, and the connection method between the first extension portion 21 and the fuselage 1 can be set according to actual application requirements; further optionally, a hollow hole can be set in the first extension portion 21, so that the weight of the first extension portion 21 can be reduced.

[0037] In this embodiment, a second extension portion 22 is provided at one end of the first extension portion 21 away from the heat-conducting mounting frame 2, and an extension direction of the second extension portion 22 is perpendicular to an extension direction of the first extension portion 21. The heat dissipation fins 3 are installed on the outer side wall of the second extension portion 22. The second extension portion 22 is convenient for setting the heat dissipation fins 3, thereby ensuring the structural stability of the heat dissipation fins 3. Specifically, the second extension portion 22 extends toward the top direction of the first extension portion 21, and the fuselage 1 is provided with a positioning protrusion (not shown in the figure), and the positioning protrusion is in conflict with a side of the second extension portion 22 away from the heat dissipation fins 3. It is easy to understand that the positioning protrusion is provided to cooperate with the second extension portion 22, so as to play a positioning role in the assembly of the heat-conducting mounting frame 2 and the fuselage 1.

[0038] Preferably, the lamp includes a side light panel 4, a bottom light panel 5 and a lampshade 6, the lampshade 6 is provided with a light-emitting cavity, the thermal conductive mounting frame 2 is installed at the opening of the lampshade 6 and extends into the light-emitting cavity, the side light panel 4 is installed on the outer wall of the thermal conductive mounting frame 2 and is located in the light-emitting cavity, the bottom light panel 5 is installed on the bottom of the thermal conductive mounting frame 2 and is located in the light-emitting cavity, and the heat dissipation fins 3 are installed on the thermal conductive mounting frame 2 and are located on the outside of the lampshade 6.

[0039] In summary, the formation performance UAV provided by the utility model has the characteristics of good heat dissipation performance. Heat is conducted by arranging a heat-conducting bracket between the lamp and the fuselage, and the heat is dissipated through the heat dissipation fins located on the outside of the lamp and the fuselage. The extension direction of the guide gap between two adjacent heat dissipation fins is set to be the same as the height direction of the fuselage, which reduces the obstruction of the heat dissipation fins to the airflow, speeds up the flow speed of the airflow in the guide gap, and improves the heat dissipation efficiency.

[0040] The above description is only an embodiment of the present invention, and does not limit the patent scope of the present invention. Any equivalent transformations made using the contents of the specification and drawings of the present invention, or directly or indirectly applied in the relevant technical field, are also included in the patent protection scope of the present invention.

Claims

1. A formation performance drone, characterized in that: The invention comprises a body, a radiator and a lamp, wherein the radiator comprises a heat-conducting mounting frame and a plurality of heat-dissipating fins arranged on the outside of the heat-conducting mounting frame, the body is mounted on the top of the heat-conducting mounting frame, the lamp is mounted on the bottom of the heat-conducting mounting frame, the heat-dissipating fins are located on the outside of the body and the lamp, a flow-guiding gap is formed between two adjacent heat-dissipating fins, and the extension direction of the flow-guiding gap is the same as the height direction of the body.

2. The formation performance UAV according to claim 1, characterized in that: A columnar protrusion is provided at the bottom of the fuselage, and a mounting groove is provided at the top of the heat-conducting mounting frame, and the columnar protrusion is installed in the mounting groove.

3. The formation performance UAV according to claim 2, characterized in that: The outer side wall of the heat-conducting mounting frame is provided with a through hole communicating with the mounting groove.

4. The formation performance UAV according to claim 1, characterized in that: The top of the heat-conducting mounting frame is provided with a first extending portion extending toward the outside thereof, the top of the first extending portion is connected to the fuselage, and the heat dissipation fins are installed on the first extending portion.

5. The formation performance UAV according to claim 4, characterized in that: The first extension portion is connected to the fuselage via buckles and / or bolts.

6. The formation performance UAV according to claim 5, characterized in that: A second extension portion is disposed at one end of the first extension portion away from the heat-conducting mounting frame. The extension direction of the second extension portion is perpendicular to the extension direction of the first extension portion. The heat dissipation fins are mounted on an outer side wall of the second extension portion.

7. The formation performance UAV according to claim 6, characterized in that: The second extension portion extends toward the bottom of the first extension portion, and the body is provided with a positioning protrusion, which abuts against a side of the second extension portion away from the heat dissipation fins.

8. The formation performance UAV according to claim 4, characterized in that: The first extension portion is provided with a hollow hole.

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