Heat dissipation system of unmanned aerial vehicle airborne SAR central electronic device

Abstract

The application belongs to the technical field of electronic equipment heat dissipation, and particularly relates to a heat dissipation system of a central electronic device of a UAV airborne SAR, which comprises a single machine shell, a structural plate, a heat-conducting filler, a central electronic device single machine, a single machine surface thermal control coating and a heat dissipation fin; the central electronic device single machine comprises a digital single machine, an analog single machine and a data transmission single machine, each single machine is installed on the structural plate and filled with the heat-conducting filler between the structural plate, and the single machine surface thermal control coating is arranged on the remaining non-installed surfaces of each single machine except the upper and lower surfaces, and the heat dissipation fin is installed on the surface of the corresponding single machine shell away from the installed surface of each single machine. By filling the high-efficiency heat-conducting material between the single machine and the structural plate, the structural plate and the single machine shell, and the single machine and the heat dissipation fin, the heat transfer thermal resistance between each contact surface is greatly reduced, a continuous high-efficiency heat conduction path from the single machine to the structural plate, the single machine shell and the heat dissipation fin is formed, the rapid heat transfer is ensured, and the problem of low heat conduction efficiency of the traditional heat dissipation structure is solved.

Description

Technical Field

[0001] This invention belongs to the field of electronic device heat dissipation technology, specifically, it relates to a heat dissipation system for a UAV-borne SAR central electronic device. Background Technology

[0002] The UAV-borne SAR central electronic equipment is the core component of the UAV SAR system. It includes heat-generating units such as digital units, analog units, and data transmission units. Each unit continuously generates heat during operation. If the heat cannot be dissipated in time, it will cause the equipment temperature to rise, affecting the stability and service life of the equipment, and even causing damage to the components. Therefore, it is necessary to configure an efficient heat dissipation system for it.

[0003] Currently, the mainstream heat dissipation methods for airborne electronic devices are natural cooling and forced air cooling. Natural cooling has the advantages of simple structure and low manufacturing cost, but its heat dissipation efficiency is generally low. Forced air cooling has a complex structure and high requirements for heat dissipation layout. If a cooling fan is used, a separate power supply interface needs to be designed, and the cooling fan consumes additional power, which affects the drone's working time and makes it difficult to adapt to the lightweight and low power consumption design requirements of drones.

[0004] Various heat dissipation structures related to airborne radar have also been disclosed in the prior art, such as:

[0005] Southwest Institute of Electronic Engineering's patent CN110632561 discloses a thermal control structure for an airborne radar radio frequency unit, proposing a combined thermal control scheme based on "heat pipes, fins, and forced air cooling"; patent CN112638131 discloses an airborne radar heat dissipation structure, which uses an independent, enclosed finned heat dissipation structure for the TR component, which has a high heat flux density and relatively concentrated heat. The heat from the heat source devices on the wave control board is evenly distributed through a heat spreader and directed into the front cabin air duct, where a cooling fan draws the heat away; patent CN110446404 discloses... One radar heat dissipation structure utilizes a radar fan, heat pipes, and heat dissipation fins to achieve heat dissipation for the entire radar, including the TR component, wave controller, and power supply components. Patent CN109270495 discloses a radar internal and external circulation forced air cooling structure and radar, including internal and external circulation finned heat exchangers, internal and external circulation fans, etc. The internal circulation fan carries hot air generated at the heat source into the internal circulation duct, and the external circulation fan carries cold air from outside into the external circulation duct. The hot and cold air exchange heat within the internal circulation finned heat exchanger. All of the above technologies rely on forced air cooling, resulting in complex structures and additional power consumption.

[0006] Patent CN110082728 discloses a heat dissipation structure for an unmanned aerial vehicle (UAV)-borne SAR array system. The SAR array system is installed in the air duct on the side of the front fuselage of the UAV and is cooled by the natural wind generated during the flight of the UAV. However, the object of its heat dissipation is the SAR array system.

[0007] Therefore, there is an urgent need to design a heat dissipation system that is compatible with the central electronic equipment of UAV airborne SAR, taking into account the characteristics of high heat dissipation efficiency, simple structure, low manufacturing cost and no additional power consumption, so as to meet the long-term working requirements of the equipment in complex environments. Summary of the Invention

[0008] To address the shortcomings of existing technologies, the purpose of this invention is to provide a heat dissipation system for the central electronic equipment of an unmanned aerial vehicle (UAV) airborne SAR system.

[0009] A heat dissipation system for an airborne SAR central electronic device for unmanned aerial vehicles (UAVs) according to the present invention includes a single-unit shell, a structural plate, thermally conductive filler, a single central electronic device, a thermal control coating on the surface of the single-unit, and heat dissipation fins. The central electronic equipment unit includes a digital unit, an analog unit, and a data transmission unit. Each unit is mounted on a structural plate and filled with thermally conductive filler between itself and the structural plate. The non-mounting surfaces of each unit, except for the top and bottom surfaces, are provided with the thermal control coating. The heat dissipation fins are installed on the surface of the unit's outer shell that is away from the mounting surface. The single-unit shell has ventilation holes on the front and rear sides along the flight direction of the drone, and a heat dissipation air duct is formed inside the single-unit shell.

[0010] Preferably, the structural plate includes a first structural plate, a second structural plate, and a third structural plate arranged sequentially from top to bottom, and the first and second structural plates are fixedly connected by hangers, and the second and third structural plates are fixedly connected by hangers.

[0011] Preferably, the digital unit is disposed between the first structural plate and the second structural plate and installed at the bottom of the first structural plate, the analog unit is disposed between the second structural plate and the third structural plate and installed at the top of the third structural plate, and the data transmission unit is installed at the bottom front side of the second structural plate.

[0012] Preferably, the thermally conductive filler is a GapPad1500 thermal pad; the GapPad1500 thermal pad is attached between each unit and the structural plate, and between the surface of each unit's outer shell away from the mounting surface and the heat dissipation fins.

[0013] Preferably, a graphene thermal conductive film is installed between the unit housing and the structural plate, and the unit housing is made of aluminum alloy.

[0014] Preferably, the thermal control coating on the surface of the single unit is black paint, and the black paint is uniformly sprayed on the non-mounting surfaces of the digital single unit, analog single unit, and data transmission single unit, except for the top and bottom surfaces.

[0015] Preferably, the heat dissipation fins are made of aluminum alloy, and the groove direction of the heat dissipation fins is consistent with the flight direction of the UAV.

[0016] Preferably, the heat dissipation fins are installed on the bottom of the casing of the digital stand-alone unit, the bottom of the casing of the data transmission stand-alone unit, and the top of the casing of the analog stand-alone unit.

[0017] Preferably, the side of the drone fuselage is provided with an air inlet communicating with the heat dissipation duct, and the tail of the drone fuselage is provided with an air outlet communicating with the heat dissipation duct, with the air inlet facing forward in the direction of the drone's flight.

[0018] Preferably, the digital single unit, analog single unit, and data transmission single unit are all provided with a single unit shell for protection, and the heat generated by each single unit during operation can be transferred to the heat dissipation fins and structural plate in sequence through the thermally conductive filler.

[0019] Compared with the prior art, the present invention has the following beneficial effects: 1. This invention significantly reduces the thermal resistance between contact surfaces by filling the spaces between the unit and the structural plate, the structural plate and the unit's outer shell, and the unit and the heat dissipation fins with highly efficient thermally conductive materials. This forms a continuous and efficient heat conduction path from the unit to the structural plate, the unit's outer shell, and the heat dissipation fins, ensuring rapid heat transfer and solving the problem of low heat conduction efficiency in traditional heat dissipation structures.

[0020] 2. This invention utilizes the motion characteristics of drone flight. By opening ventilation holes along the flight direction on the single-shell and setting heat dissipation fins along the flight direction, it forms a heat dissipation air duct with the air inlet and outlet of the drone body. The relative airflow generated during drone flight creates a ram effect at the air inlet, driving the cool air to flow at high speed within the heat dissipation air duct. The heat is dissipated from the heat dissipation fins and structural plates through forced convection heat transfer. At the same time, the outer surface of the aluminum alloy single-shell is scourd by the high-speed airflow during drone flight, forming external forced convection heat transfer. This achieves the synergistic effect of internal air duct heat dissipation and external airflow cooling, resulting in high heat dissipation efficiency. Moreover, it does not require additional cooling fans or other power components, consumes no additional power, and does not shorten the drone's working time. Attached Figure Description

[0021] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings: Figure 1 This is a schematic diagram of the heat dissipation system of the present invention and its assembly with a drone; Figure 2This is a schematic diagram of the overall structure of the heat dissipation system of the present invention; Figure 3 This is a schematic diagram of the opening structure of the single-unit housing of the present invention.

[0022] The following are the labeling elements in the figure: 1. Unit casing; 2. Structural plate; 3. Thermally conductive filler; 4. Digital unit; 5. Analog unit; 6. Data transmission unit; 7. Thermal control coating on unit surface; 8. Heat dissipation fins. Detailed Implementation

[0023] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0024] like Figures 1-3 As shown, the present invention provides a heat dissipation system for an airborne SAR central electronic device of an unmanned aerial vehicle (UAV), comprising a single-unit shell 1, a structural plate 2, a thermally conductive filler 3, a single central electronic device, a thermal control coating 7 on the surface of the single-unit, and heat dissipation fins 8.

[0025] Structural panel 2 includes a first structural panel, a second structural panel, and a third structural panel arranged sequentially from top to bottom. The first and second structural panels, as well as the second and third structural panels, are fixedly connected by hangers.

[0026] The central electronic equipment unit includes a digital unit 4, an analog unit 5, and a data transmission unit 6. The digital unit 4 is located between the first structural plate and the second structural plate, and is installed at the bottom of the first structural plate. The analog unit 5 is located between the second structural plate and the third structural plate, and is installed at the top of the third structural plate. The data transmission unit 6 is installed on the bottom front side of the second structural plate. The mounting surfaces of each unit are screwed to the corresponding structural plate 2 to achieve a firm fixation of the unit, ensuring the stability of the connection and the integrity of the structure.

[0027] The outer sides of the digital single unit 4, the analog single unit 5, and the data transmission single unit 6 are all equipped with protective single unit shells 1, and the single unit shell 1 is connected to the structural plate by screws. The single unit shell 1 is made of aluminum alloy material, which has a high thermal conductivity and can quickly conduct internal heat to the outer surface. The single unit shell 1 has ventilation holes on the front and rear sides along the flight direction of the drone, with an opening rate of 70%. A heat dissipation channel is formed inside the single unit shell 1. The side of the drone fuselage is equipped with an air inlet connected to the heat dissipation channel, and the tail of the drone fuselage is equipped with an air outlet connected to the heat dissipation channel. The air inlet faces forward in the flight direction of the drone, and in conjunction with the flight of the drone, a ram effect is formed, driving the airflow to circulate in the heat dissipation channel.

[0028] Thermally conductive material 3 is filled between the digital single unit 4 and the first structural plate, between the analog single unit 5 and the third structural plate, and between the data transmission single unit 6 and the second structural plate to enhance the heat transfer effect between the single unit and the mounting plate.

[0029] In this embodiment, a graphene thermal conductive film is installed between the single-unit housing 1 and the structural plate 2 to reduce the thermal resistance between them; and a 1mm thick GapPad1500 thermal conductive pad is installed between the digital single-unit 4, analog single-unit 5, and data transmission single-unit 6 and the structural plate 2. At the same time, a 1mm thick GapPad1500 thermal conductive pad is also installed between the surface of the corresponding single-unit housing 1 away from the single-unit mounting surface and the heat dissipation fins 8. During the installation process, a tight contact without gaps is ensured to form a continuous heat conduction path.

[0030] Black paint is evenly sprayed onto the non-installation surfaces of the digital single unit 4, analog single unit 5, and data transmission single unit 6, except for the top and bottom surfaces, to form a thermal control coating 7 on the surface of the single unit, thereby enhancing the heat transfer effect between the single unit and the structural plate 2.

[0031] Aluminum alloy heat dissipation fins 8 are installed on the bottom of the casing of digital single-unit 4, the bottom of the casing of data transmission single-unit 6, and the top of the casing of analog single-unit 5. The bottom of the casing of digital single-unit 4 is equipped with heat dissipation fins with a size of 200mm×150mm, a substrate thickness of 2mm, a fin height of 10mm, a fin spacing of 6mm, and a fin width of 1mm. The top of the casing of analog single-unit 5 is equipped with heat dissipation fins with a size of 200mm×200mm, a substrate thickness of 2mm, a fin height of 15mm, a fin spacing of 6mm, and a fin width of 1mm. The bottom of the casing of data transmission single-unit 6 is equipped with heat dissipation fins with a size of 76mm×64mm, a substrate thickness of 2mm, a fin height of 10mm, a fin spacing of 6mm, and a fin width of 1mm. The slotted direction of the heat dissipation fins 8 is aligned with the flight direction of the UAV.

[0032] The heat dissipation system of this embodiment is adapted to drones with a flight speed of not less than 5m / s. The power consumption of the digital unit 4 is 40W, the power consumption of the analog unit 5 is 50W, and the power consumption of the data transmission unit 6 is 7W. In an ambient temperature of 40℃, after the drone carrying this system flies for 20 minutes, the temperature of the SAR central electronic equipment can be controlled below 45℃.

[0033] Working principle When the heat dissipation system of this embodiment is working, the heat generated by the digital single unit 4, analog single unit 5, and data transmission single unit 6 is first conducted to the housing of each single unit. The heat on the housing of the single unit is transferred to the heat dissipation fins 8 through the GapPad1500 thermal pad. The heat on the lower surface of the single unit is transferred to the structural plate 2 through the GapPad1500 thermal pad. Part of the heat on the structural plate 2 is transferred to the aluminum alloy single unit housing 1 through the graphene thermal conductive film, and the other part is directly exchanged with the airflow in the air duct.

[0034] As the drone flies forward, the oncoming airflow is obstructed at the air inlet, reducing its speed and converting kinetic energy into pressure energy, creating a ram effect with a pressure higher than the ambient air pressure. Driven by this pressure difference, external cold air flows into the air inlet and moves at high speed along the heat dissipation duct. The high-speed airflow sweeps over the surfaces of the heat dissipation fins 8 and the structural plate 2, and removes most of the heat through forced convection heat exchange. The air carrying the heat is finally discharged from the air outlet in the low-pressure area at the tail of the drone. At the same time, the high-speed airflow during the drone's flight continuously washes over the outer surface of the aluminum alloy single-shell shell 1, forming external forced convection heat exchange. The heat inside the single-shell shell 1 is quickly conducted to the outer surface and carried away by the airflow, achieving synergistic cooling of the internal air duct and external airflow.

[0035] The black thermal control coating 7 on the non-installation surface of each unit transfers some of the heat to the surrounding environment through thermal radiation, which, together with conduction and convection heat transfer, further improves the heat dissipation effect.

[0036] In the description of this application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.

[0037] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A heat dissipation system for a UAV-borne airborne SAR central electronic device, characterized in that, Includes single-unit casing (1), structural plate (2), thermally conductive filler (3), central electronic equipment unit, single-unit surface thermal control coating (7) and heat dissipation fins (8); The central electronic equipment unit includes a digital unit (4), an analog unit (5) and a data transmission unit (6). Each unit is mounted on a structural plate (2) and filled with thermally conductive filler (3) between itself and the structural plate (2). The non-mounting surfaces of each unit, except for the top and bottom surfaces, are provided with the heat control coating (7). The heat dissipation fins (8) are installed on the surface of the unit's outer shell (9) away from the mounting surface. The single-unit outer shell (1) has ventilation holes on the front and rear sides along the flight direction of the UAV, and a heat dissipation air duct is formed inside the single-unit outer shell (1).

2. The heat dissipation system of the UAV airborne SAR central electronic equipment according to claim 1, characterized in that, The structural plate (2) includes a first structural plate, a second structural plate and a third structural plate arranged sequentially from top to bottom. The first structural plate and the second structural plate, and the second structural plate and the third structural plate are fixedly connected by hangers.

3. The heat dissipation system of the UAV airborne SAR central electronic equipment according to claim 2, characterized in that, The digital single unit (4) is located between the first structural plate and the second structural plate and installed at the bottom of the first structural plate. The analog single unit (5) is located between the second structural plate and the third structural plate and installed at the top of the third structural plate. The data transmission single unit (6) is installed at the bottom front side of the second structural plate.

4. The heat dissipation system of the UAV airborne SAR central electronic equipment according to claim 1, characterized in that, The thermally conductive filler (3) is a GapPad1500 thermal pad; the GapPad1500 thermal pad is attached between each unit and the structural plate (2), and between the surface of each unit's corresponding unit shell (1) away from the mounting surface and the heat dissipation fins (8).

5. The heat dissipation system of the UAV airborne SAR central electronic equipment according to claim 1, characterized in that, A graphene thermal conductive film is installed between the single-unit housing (1) and the structural plate (2), and the single-unit housing (1) is made of aluminum alloy.

6. The heat dissipation system of the UAV airborne SAR central electronic equipment according to claim 1, characterized in that, The thermal control coating (7) on the surface of the single unit is black paint, which is uniformly sprayed on the non-installation surfaces of the digital single unit (4), analog single unit (5) and data transmission single unit (6) except for the top and bottom surfaces.

7. The heat dissipation system of the UAV airborne SAR central electronic equipment according to claim 1, characterized in that, The heat dissipation fins (8) are made of aluminum alloy, and the slotting direction of the heat dissipation fins (8) is consistent with the flight direction of the UAV.

8. The heat dissipation system of the UAV airborne SAR central electronic equipment according to claim 1, characterized in that, The heat dissipation fins (8) are installed on the bottom of the casing of the digital single machine (4), the bottom of the casing of the data transmission single machine (6), and the top of the casing of the analog single machine (5).

9. The heat dissipation system of the UAV airborne SAR central electronic equipment according to claim 1, characterized in that, The drone has an air inlet on its side that is connected to the cooling duct, and an air outlet at the tail that is connected to the cooling duct. The air inlet faces forward in the direction of the drone's flight.

10. The heat dissipation system of the UAV airborne SAR central electronic equipment according to claim 1, characterized in that, The digital single unit (4), analog single unit (5), and data transmission single unit (6) are all provided with a single unit shell (1) for protection. The heat generated by each single unit can be transferred to the heat dissipation fins (8) and the structural plate (2) in sequence through the heat-conducting filler (3).

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