A natural convection heat dissipation structure of a case suitable for unmanned aerial vehicle detection

Abstract

The utility model belongs to the technical field of electronic product heat dissipation design, and relates to a case natural convection heat dissipation structure suitable for unmanned aerial vehicle detection, including case body, its upper installation has the air inlet, the shell is opened and has a plurality of air holes. The air duct formed by the two air inlets of the utility model is located at the maximum heat generation position of the acquisition card collection board and the control board, and the air duct formed by the two air inlet meshes is located at the upper surface of the industrial computer. When the case moves forward and backward in the air at the same speed, the airflow channel penetrating through the case can dissipate heat for the case. To ensure that the acquisition system maintains consistent working temperature when the unmanned aerial vehicle moves forward and backward, the balance of the heat dissipation performance of the case when moving in the two directions is considered. By optimizing the position of the ventilation hole and the airflow path, the heat dissipation capacity of the case when moving forward or backward is the same. This symmetrical design effectively reduces the temperature fluctuation caused by the change of the moving direction, thereby improving the temperature stability of the acquisition system.

Description

Technical Field

[0001] This utility model belongs to the field of heat dissipation design technology for electronic products, specifically relating to a natural convection heat dissipation structure for an aviation data acquisition system chassis, and particularly to a natural convection heat dissipation structure for a chassis suitable for UAV detection. Background Technology

[0002] In the field of drone detection, with the continuous improvement of electronic equipment performance, the power consumption and heat generation of the internal components of the electronic chassis carried by drones are also gradually increasing. Effective heat dissipation design is crucial for ensuring the stability of the electronic chassis, extending its service life, and maintaining performance. In the application scenario of drone-based aerospace magnetic surveying, the electronic chassis is mounted on a mobile platform. The drone has a small payload and limited space; therefore, it is necessary to minimize the size and weight of the chassis.

[0003] Currently, the main heat dissipation methods for electronic chassis include natural air cooling, forced air cooling, heat pipe cooling, thermoelectric cooling, and phase change cooling. Among these methods, forced air cooling uses fans to create airflow to improve heat dissipation efficiency, but the addition of fans increases the failure rate of the instrument and reduces the reliability of the system. Although heat pipe cooling has excellent thermal conductivity, its complex structure, large weight, and large volume make it unsuitable for drone chassis with limited space. While thermoelectric cooling can precisely control temperature, it has low energy efficiency, high power consumption, and requires an additional cooling mechanism to handle the heat released from the cold end. In contrast, natural air cooling relies on high-speed airflow outside the chassis to remove the heat generated inside, offering advantages such as simple structure, no need for external power supply, no space occupation within the chassis, and light weight.

[0004] Since drones have high airflow speeds during flight, it is essential to develop a heat dissipation structure for the chassis of an aerial data acquisition system that utilizes natural convection cooling. This structure can effectively improve the reliability and stability of the equipment in outdoor environments and has broad application prospects. Summary of the Invention

[0005] The purpose of this invention is to provide a natural air-cooled heat dissipation structure for the electronic chassis of a drone under a motion platform, so as to solve the problem of balanced heat dissipation when the electronic chassis moves in both the front and rear directions.

[0006] The objective of this utility model is achieved through the following technical solution:

[0007] A chassis natural convection heat dissipation structure suitable for UAV detection includes a chassis body 4, a rear air inlet 7 and a front air inlet 6 mounted on the chassis body 4; a front vent 5 is provided on the shell of the chassis body 4 below the front air inlet 6, and a rear vent 8 is provided on the shell of the chassis body 4 below the rear air inlet 7.

[0008] The chassis body 4 is composed of a front cover plate 13, a rear cover plate 19, a top plate 12, and a bottom plate 15. The front cover plate 13 is provided with a front positioning hole 22, and the rear cover plate 19 is provided with a rear positioning hole 23. The front cover plate 13 and the rear cover plate 19 are fixedly connected to the top plate 12 and the bottom plate 15, respectively. The front cover plate 13 has multiple through holes for connecting the switch 1, the aviation plug I 9, and the power interface 3. The rear cover plate 19 has multiple through holes for connecting the aviation plug II 21 and the data acquisition card power board 18. The top plate 12, the bottom plate 15, and the rear cover plate 19 are all provided with multiple mounting holes for mounting the industrial control computer 11, the main battery 14, the auxiliary battery 17, the data acquisition card board, the control board 16, and the transformer 20 inside the chassis body 4.

[0009] The chassis housing 4 is provided with mounting holes that match the rear air inlet 7 and the front air inlet 6. The chassis housing is also provided with multiple rear air inlet meshes 10 and multiple front air inlet meshes 2. When the chassis body 4 moves forward, air can enter the chassis body 4 through the front air inlet 6 and the front air inlet meshes 2, and be discharged through the rear air inlet meshes 10 and the rear air inlet 7. When the chassis body 4 moves backward, air can enter the chassis body 4 through the rear air inlet 7 and the rear air inlet meshes 10, and be discharged through the front air inlet meshes 2 and the rear air inlet 7. The air duct formed by the rear air inlet 7 and the front air inlet 6 is located at the maximum heat generation point of the data acquisition card board and the control board 16, and the air duct formed by the front air inlet meshes 2 and the rear air inlet meshes 10 is located on the upper surface of the industrial control computer 11.

[0010] Furthermore, the rear air inlet 7 is installed above the chassis body 4, and the opening of the rear air inlet 7 is a rectangle with a length of 50mm and a width of 50mm; the front air inlet 6 is installed on the side of the chassis body 4, and the opening of the front air inlet 6 is a rectangle with a length of 88mm and a width of 48mm.

[0011] Furthermore, the front positioning holes 22 and rear positioning holes 23 on the front cover plate 13 and the rear cover plate 19 are respectively fastened to the positioning holes on the top plate 12 and the bottom plate 15 by screws.

[0012] Furthermore, the front cover plate 13 and the rear cover plate 19 of the chassis body 4 are respectively connected to the bottom plate 15, and the front air inlet 6 is connected to both the top plate 12 and the bottom plate 15.

[0013] Furthermore, the top plate 12, bottom plate 15 and rear cover plate 19 are each provided with multiple mounting holes, and screws matching the electronic equipment are fixedly connected in the mounting holes for installing the industrial control computer 11, main battery 14, auxiliary battery 17, data acquisition card board, control board 16 and transformer 20 inside the chassis body 4.

[0014] Furthermore, the main battery 14 supplies power to the industrial control computer 11 via the transformer 20 and inputs the power to the data acquisition card power board 18, which in turn supplies power to the data acquisition card acquisition board and the control board 16. The auxiliary battery 17 supplies power to the fluxgate outside the chassis. The aviation plug I 9 is used to charge the auxiliary battery 17 inside the chassis. The aviation plug II 21 is used to transmit the UAV ESC data to the industrial control computer and the data acquired by the fluxgate to the data acquisition card acquisition board and the control board 16.

[0015] Furthermore, multiple front air intake meshes 2 and multiple rear air intake meshes 10 are respectively opened on the front and rear sides of the chassis body 4.

[0016] Furthermore, the diameter of the through holes of the rear air inlet mesh 7 and the front air inlet mesh 2 is 5mm, and the spacing between adjacent meshes is 10mm.

[0017] Compared with the prior art, the beneficial effects of this utility model are:

[0018] 1. The natural convection heat dissipation structure of this utility model forms an airflow channel inside the chassis that can cover the equipment with the greatest heat generation inside the chassis. Moreover, the airflow rate and path are the same when moving forward and backward, ensuring that the heat dissipation capacity of the chassis is the same in both movement states, reducing temperature fluctuations inside the chassis and improving the temperature stability of the acquisition system.

[0019] 2. Compared with forced air cooling, heat pipe cooling, thermoelectric cooling technology, etc., the natural air cooling solution adopted by this utility model does not require additional circuitry, thereby reducing power consumption and weight burden while ensuring functionality.

[0020] 3. This utility model does not require the installation of heat dissipation fins, heat pipes, cold conduction plates, etc. inside or outside the chassis; it saves the volume occupied by the drone's payload and reduces the weight of the drone's payload.

[0021] 4. When the chassis of the aerial data acquisition system designed with this utility model moves forward and backward at a speed of 2m / s, the heat dissipation capacity of the chassis is similar, and the temperature inside the chassis can be reduced by more than 20℃ after thermal design. Attached Figure Description

[0022] To more clearly illustrate the technical solutions of the embodiments of this utility model, the drawings used in the embodiments will be briefly introduced below. It should be understood that the following drawings only show some embodiments of this utility model and should not be regarded as a limitation on the scope. For those skilled in the art, other related drawings can be obtained based on these drawings without creative effort.

[0023] Figure 1 This is a schematic diagram of the front overall structure of the natural convection heat dissipation structure of the chassis for drone detection according to this utility model;

[0024] Figure 2 This is a schematic diagram of the rear overall structure of the natural convection heat dissipation structure of the chassis for UAV detection, which is applicable to the present invention.

[0025] Figure 3 This is an exploded structural diagram of a chassis with natural convection cooling structure suitable for drone detection.

[0026] In the diagram: 1. Switch 2. Front air intake mesh 3. Power interface 4. Chassis body 5. Front vent 6. Front air inlet 7. Rear air inlet 8. Rear vent 9. Aviation connector I 10. Rear air intake mesh 11. Industrial computer 12. Top plate 13. Front cover 14. Main battery 15. Bottom plate 16. Data acquisition card, acquisition board and control board 17. Auxiliary battery 18. Data acquisition card power board 19. Rear cover 20. Transformer 21. Aviation connector II 22. Front positioning hole 23. Rear positioning hole. Detailed Implementation

[0027] The present invention will be further described below with reference to embodiments:

[0028] The present invention will now be described in further detail with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the present invention and not intended to limit it. Furthermore, it should be noted that, for ease of description, the accompanying drawings show only the parts relevant to the present invention, not the entire structure.

[0029] It should be noted that similar reference numerals and letters in the following figures indicate similar items; therefore, once an item is defined in one figure, it does not need to be further defined and explained in subsequent figures. Furthermore, in the description of this utility model, terms such as "first," "second," etc., are used only to distinguish descriptions and should not be construed as indicating or implying relative importance.

[0030] This invention provides a natural air-cooling structure for an electronic chassis under a motion platform to dissipate heat from the electronic equipment inside the chassis. To ensure the data acquisition system maintains a consistent operating temperature during the forward and backward movement of the drone, the balance of heat dissipation performance in both directions is specifically considered. By optimizing the location of the ventilation holes and the airflow path, the heat dissipation capacity of the chassis is made the same whether moving forward or backward. This symmetrical design effectively reduces temperature fluctuations caused by changes in the direction of movement, thereby improving the temperature stability of the data acquisition system.

[0031] This utility model is applicable to the natural convection heat dissipation structure of the chassis for UAV detection, including chassis body 4, with a rear air inlet 7 installed on the top of the chassis body 4 and a front air inlet 6 installed on the left side. Multiple rear ventilation holes 8 and multiple front ventilation holes 5 are respectively opened below the rear air inlet 7 and the front air inlet 6.

[0032] The chassis body 4 consists of a front cover plate 13, a rear cover plate 19, a top plate 12, and a bottom plate 15. Four front positioning holes 22 are located on the left and right sides of the front cover plate 13, and four rear positioning holes 23 are located on the left and right sides of the rear cover plate 19. The front positioning holes 22 and rear positioning holes 23 on the front cover plate 13 and rear cover plate 19 are respectively fastened to the positioning holes on the top plate 12 and bottom plate 15 by screws. Multiple through holes are provided on the front cover plate 13 for connecting the switch 1, aviation plug I 9, and power interface 3.

[0033] The rear cover plate 19 has multiple through holes for connecting the aviation plug II 21 and the data acquisition card power board 18.

[0034] The top plate 12, bottom plate 15 and rear cover plate 19 are each provided with multiple mounting holes, and screws matching the electronic equipment are fixedly connected in the mounting holes for mounting the industrial control computer 11, main battery 14, auxiliary battery 17, data acquisition card, control board 16 and transformer 20 inside the chassis.

[0035] The chassis body 4 has mounting holes that match the front air inlet 6 and the rear air inlet 7. To prevent foreign objects from entering during flight due to excessively large chassis openings, multiple front air inlet meshes 2 and multiple rear air inlet meshes 10 are provided on the front and rear sides of the chassis body 4, respectively.

[0036] When the chassis body 4 moves forward, air enters the chassis body 4 through the front air intake mesh 2. Simultaneously, the installed triangular front air intake 6 guides a large amount of air into the chassis body 4. At this time, the rear air intake mesh 10 and rear air intake 7 are used to exhaust the air inside the chassis body 4. When the chassis body 4 moves backward, air enters the chassis body 4 through the rear air intake mesh 10. Simultaneously, the installed triangular rear air intake 7 guides a large amount of air into the chassis body 4. At this time, the front air intake mesh 2 and rear air intake 7 are used to exhaust the air inside the chassis body 4. When the chassis body 4 moves forward in the air, airflow enters the chassis body 4 through the front air intake 6 and front air intake mesh 2 and exits through the rear air intake 7 and rear air intake mesh 10; when moving backward, airflow enters the chassis body 4 through the rear air intake 7 and rear air intake mesh 10 and exits through the front air intake 6 and front air intake mesh 2. Both motion states can form an airflow channel through the chassis body 4 for chassis heat dissipation, and the chassis heat dissipation capacity is basically the same when moving in the two directions.

[0037] In this invention, the chassis is in motion during operation. Through a well-designed airflow path within the chassis body 4, formed by the front air inlet 4 and the rear air inlet 5, the airflow channels can cover the devices generating the most heat within the chassis, namely the data acquisition card and control board 16. Furthermore, the airflow rate and path are the same when moving forward and backward, ensuring consistent heat dissipation capacity in both motion states, reducing temperature fluctuations within the chassis, and improving the temperature stability of the data acquisition system. Since the chassis needs to be mounted on a drone platform, the design prioritizes minimizing instrument weight to improve drone battery life and reducing the amount of circuitry in the data acquisition system to maximize battery life. Compared to forced air cooling, heat pipe cooling, and thermoelectric cooling technologies, the natural air cooling method employed in this invention requires no additional circuitry, thus reducing power consumption and weight while maintaining functionality.

[0038] Furthermore, this invention eliminates the need for heat sinks, heat pipes, cooling plates, and other such devices inside and outside the chassis. This saves space occupied by the drone's payload and reduces its weight.

[0039] Thermal simulation was performed using Flotherm finite element simulation software to compare the highest temperature inside the chassis before and after the heat dissipation improvement. Compared to the improved thermal design, the chassis of the aerial data acquisition system before the thermal design lacked front air inlets 6 and rear air inlets 7, and also lacked front air intake mesh 2, rear air intake mesh 10, front vent 5, and rear vent 8. Other chassis designs remained unchanged. At ambient temperatures of 20℃, 25℃, and 30℃, the heat dissipation capacity of the aerial data acquisition system chassis designed according to this invention was similar when moving forward and backward at a speed of 2m / s. Furthermore, the internal temperature of the chassis could be reduced by more than 20℃ after the thermal design, as detailed in Tables 1 to 3.

[0040] Table 1 - Ambient Temperature 20 Degrees

[0041]

[0042] Table 2 - Ambient Temperature 25 Degrees

[0043]

[0044] Table 3 - Ambient Temperature 30 Degrees

[0045]

[0046] Example 1

[0047] like Figures 1-3 As shown, a natural convection cooling structure for a chassis suitable for UAV detection includes a chassis body 4, a rear air inlet 7 mounted on top of the chassis body 4, and a front air inlet 6 mounted on the side of the chassis body 4. The rear air inlet 7 has a rectangular opening of 50mm in length and 50mm in width, and the front air inlet 6 has a rectangular opening of 88mm in length and 48mm in width. A front vent 5 is provided on the chassis body 4 shell below the front air inlet 6, and a rear vent 8 is provided on the chassis body 4 shell below the rear air inlet 7.

[0048] The chassis body 4 consists of a front cover 13, a rear cover 19, a top plate 12, and a bottom plate 15. The front cover 13 and rear cover 19 are respectively fixedly connected to the top plate 12 and the bottom plate 15 via four screw holes on their sides. To facilitate disassembly and assembly of the chassis body 4, the front cover 13, rear cover 19, and bottom plate 15 are connected together, and the top plate 12 is removed to modify the internal equipment. When removing the top plate 12, it should be noted that the front air inlet 6 is connected to both the top plate 12 and the bottom plate 15; therefore, the front air inlet 6 must be removed before removing the top plate 12.

[0049] The front cover plate 13 has multiple through holes for connecting the switch 1, aviation connector I 9, and power interface 3. The switch 1 controls the main battery 14 to supply power to the industrial control computer 11, the data acquisition card board, the control board 16, and the data acquisition card power board 18. Two small aviation connectors in aviation connector I 9 are used to transmit UAV ESC data to the industrial control computer. The large aviation connector in aviation connector I 9 is used to transmit data acquired by the fluxgate magnetometer to the data acquisition card board and the control board 16. The rear cover plate 19 has multiple through holes for connecting aviation connector II 21 and the data acquisition card power board 18. Aviation connector II 21 is used to charge the auxiliary battery 17 inside the chassis.

[0050] The top plate 12, bottom plate 15, and rear cover plate 19 are all provided with multiple mounting holes, and screws matching the electronic equipment are fixedly connected in the mounting holes for mounting the industrial control computer 11, main battery 14, auxiliary battery 17, data acquisition card board, control board 16, and transformer 20 inside the chassis body 4. The industrial control computer 11 controls the data acquisition card board and control board 17 to acquire data through a program. The main battery 14 supplies power to the industrial control computer 11 via the transformer 20 and inputs the power to the data acquisition card power board 18, which in turn supplies power to the data acquisition card board and control board 16. To avoid introducing high-frequency noise and electromagnetic interference, the auxiliary battery 17 supplies power to the fluxgate magnetometer outside the chassis.

[0051] The chassis housing 4 is provided with mounting holes that match the air inlet. To prevent the chassis opening from being too large and foreign objects from entering during use, the chassis housing is also provided with a rear air inlet mesh 10 and a front air inlet mesh 2. The diameter of the through holes of the rear air inlet mesh 7 and the front air inlet mesh 2 is 5mm, and the spacing between adjacent meshes is 10mm.

[0052] Simulation analysis revealed that the main heat sources within the chassis are the industrial computer 11, the data acquisition card power board 18, the data acquisition card board, and the control board 16. Secondary heat sources include the main battery 14, the auxiliary battery 17, and the transformer 20. Heat is primarily concentrated above and below the data acquisition card board and control board 16, and at the industrial computer 11. Furthermore, the components are arranged on the PCB with a bias towards the rear of the chassis. Therefore, the airflow channels formed by the front air inlet 6 and the rear air inlet 7 designed in this invention are precisely located at the points of maximum heat generation on the data acquisition card board and control board 16. The airflow channels formed by the front air inlet mesh 2 and the rear air inlet mesh 10 are precisely located above the upper surface of the industrial computer 11. When the chassis moves forward and backward at the same speed in the air, the airflow channels forming through the chassis can dissipate heat, and the cooling capacity of the chassis is essentially the same in both directions of movement.

[0053] The parameters of the air inlet and vent in the above simulation model are embodiments of this utility model. For those skilled in the art, it will be understood that various changes, modifications, substitutions and variations can be made to these embodiments without departing from the principles and spirit of this utility model. The scope of this utility model is defined by the appended claims and their equivalents.

Claims

1. A chassis natural convection heat dissipation structure suitable for UAV detection, characterized in that: It includes a chassis body (4), a rear air inlet (7) and a front air inlet (6) mounted on the chassis body (4); a front vent (5) is provided on the chassis body (4) below the front air inlet (6), and a rear vent (8) is provided on the chassis body (4) below the rear air inlet (7); The casing of the main body (4) is composed of a front cover plate (13), a rear cover plate (19), a top plate (12), and a bottom plate (15); the front cover plate (13) is provided with a front positioning hole (22), and the rear cover plate (19) is provided with a rear positioning hole (23); the front cover plate (13) and the rear cover plate (19) are fixedly connected to the top plate (12) and the bottom plate (15), respectively; the front cover plate (13) has multiple through holes for connecting a switch (1). Aviation plug I (9) and power interface (3); multiple through holes are provided on the rear cover plate (19) for connecting aviation plug II (21) and data acquisition card power board (18); multiple mounting holes are provided on the top plate (12), bottom plate (15) and rear cover plate (19) for installing industrial control computer (11), main battery (14), auxiliary battery (17), data acquisition card acquisition board and control board (16) and transformer (20) inside the chassis body (4); The chassis body (4) is provided with mounting holes that match the rear air inlet (7) and the front air inlet (6). The chassis body is also provided with multiple rear air inlet meshes (10) and multiple front air inlet meshes (2). When the chassis body (4) moves forward, air can enter the chassis body (4) through the front air inlet (6) and the front air inlet mesh (2), and be discharged through the rear air inlet mesh (10) and the rear air inlet (7); When the chassis body (4) moves backward, air can enter the chassis body (4) through the rear air inlet (7) and the rear air inlet mesh (10), and be discharged through the front air inlet mesh (2) and the rear air inlet (7); the air duct formed by the rear air inlet (7) and the front air inlet (6) is located at the maximum heat generation point of the data acquisition card acquisition board and the control board (16), and the air duct formed by the front air inlet mesh (2) and the rear air inlet mesh (10) is located on the upper surface of the industrial computer (11).

2. The chassis natural convection heat dissipation structure suitable for UAV detection according to claim 1, characterized in that: The rear air inlet (7) is installed on the top of the chassis body (4), and the opening of the rear air inlet (7) is a rectangle with a length of 50mm and a width of 50mm; the front air inlet (6) is installed on the side of the chassis body (4), and the opening of the front air inlet (6) is a rectangle with a length of 88mm and a width of 48mm.

3. The chassis natural convection heat dissipation structure suitable for UAV detection according to claim 1, characterized in that: The front positioning holes (22) and rear positioning holes (23) on the front cover plate (13) and the rear cover plate (19) are respectively fastened to the positioning holes on the top plate (12) and the bottom plate (15) by screws.

4. A chassis natural convection heat dissipation structure suitable for UAV detection according to claim 3, characterized in that: The front cover (13) and rear cover (19) of the chassis body (4) are connected to the bottom plate (15) respectively, and the front air inlet (6) is connected to both the top plate (12) and the bottom plate (15).

5. A chassis natural convection heat dissipation structure suitable for UAV detection according to claim 1, characterized in that: The top plate (12), bottom plate (15) and rear cover plate (19) are each provided with multiple mounting holes, and screws matching the electronic equipment are fixedly connected in the mounting holes for installing the industrial control computer (11), main battery (14), auxiliary battery (17), data acquisition card, data acquisition board, control board (16) and transformer (20) inside the chassis body (4).

6. A chassis natural convection heat dissipation structure suitable for UAV detection according to claim 5, characterized in that: The main battery (14) supplies power to the industrial control computer (11) via the transformer (20) and inputs the power supply to the data acquisition card power board (18), which in turn supplies power to the data acquisition card acquisition board and the control board (16). The auxiliary battery (17) supplies power to the fluxgate outside the chassis. The aviation plug I (9) is used to charge the auxiliary battery (17) inside the chassis. The aviation plug II (21) is used to transmit the UAV ESC data to the industrial control computer and the data acquired by the fluxgate to the data acquisition card acquisition board and the control board (16).

7. A chassis natural convection heat dissipation structure suitable for UAV detection according to claim 1, characterized in that: The chassis body (4) has multiple front air intake meshes (2) and multiple rear air intake meshes (10) on its front and rear sides, respectively.

8. A chassis natural convection heat dissipation structure suitable for UAV detection according to claim 7, characterized in that: The diameter of the through holes of the rear air inlet mesh (10) and the front air inlet mesh (2) is 5mm, and the spacing between adjacent meshes is 10mm.

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