Heat dissipation device for microwave radar antenna cabin single machine

Abstract

The application provides a heat dissipation device for a microwave radar antenna cabin single machine, and relates to the technical field of spacecraft thermal control, which comprises a heat dissipation plate arranged between single machines, a heat pipe arranged in the heat dissipation plate, and a graphene film arranged on the effective heat dissipation surface of the heat dissipation plate, and the outer surface of the graphene film is sprayed with a thermal control coating. The heat on the single machine is first transferred to the heat dissipation plate, then to the effective heat dissipation surface of the heat dissipation plate through the heat pipe, and then radiated to the cold space through the graphene film, thereby meeting the heat dissipation requirement of the high-power single machine of the microwave radar antenna after being moved from the cabin to the bottom of the antenna, and solving the problem of insufficient heat dissipation capacity caused by the single machine being blocked by the antenna. The whole device is a passive thermal control measure, and does not have the problems of system start, termination and failure, and has high reliability.

Description

Technical Field

[0001] This invention relates to the field of spacecraft thermal control technology, specifically to a heat dissipation device for a single external unit of a microwave radar antenna. Background Technology

[0002] Microwave radar antennas are a major form of spaceborne radar. In traditional microwave radar antennas, high-power components such as the transmitter are located inside the satellite cabin, and their heat dissipation is provided by the satellite's overall heat dissipation surface, which is relatively simple. Due to increasing demands, microwave radar antennas require higher precision and response rates. Currently, high-power components of microwave radar antennas are moved outside the cabin and directly connected to the antenna via short waveguides. While this improves precision and response rate, it also severely degrades heat dissipation conditions. Without effective heat dissipation measures, the temperature of high-power components can rise sharply, leading to performance degradation or even failure. Furthermore, due to requirements for anti-static properties, wave transmission, and external heat flow, the antenna cannot serve as a direct heat dissipation channel.

[0003] A Chinese patent application with publication number CN114865267A discloses a phased array antenna TR assembly and an active phased array antenna, relating to the field of active phased array thermal control technology, to improve the heat dissipation efficiency of the TR module. The phased array antenna TR assembly includes a TR module, a mounting structure, a heat pipe, and heat sinks. The mounting structure is located on one side of the TR module. The evaporation section of the heat pipe is fixed to the mounting structure, and the condensation section of the heat pipe is located on the outside of the mounting structure. Several heat sinks are installed on the condensation section of the heat pipe. The heat pipe transfers heat to the heat sinks, which dissipate heat under the action of an external fan. Most of the heat is carried into the air, thus achieving air cooling.

[0004] Existing heat dissipation devices operate in an atmospheric environment, which is difficult to adapt to spaceborne requirements. Currently, there is an urgent need for a high-power single-unit heat dissipation device for microwave radar antennas that can adapt to the spaceborne environment. Summary of the Invention

[0005] In view of the deficiencies in the prior art, the purpose of this invention is to provide a heat dissipation device for a stand-alone unit outside the microwave radar antenna compartment.

[0006] According to the present invention, a heat dissipation device for an external single unit of a microwave radar antenna compartment includes a heat dissipation plate disposed between the antennas of the single unit, heat pipes are arranged inside the heat dissipation plate, a graphene film is disposed on the effective heat dissipation surface of the heat dissipation plate, and a thermal control coating is sprayed on the outer surface of the graphene film.

[0007] Preferably, the unit is connected to the lower surface of the heat sink, and an indium foil is disposed between the unit and the heat sink.

[0008] Preferably, the effective heat dissipation surface of the heat sink includes the area on the heat sink that extends beyond the area of ​​the antenna's orthographic projection on the heat sink.

[0009] Preferably, the solar absorptivity of the thermal control coating is αs = 0.3 ± 0.04; the infrared emissivity of the thermal control coating is εh = 0.9 ± 0.04; and the thermal control coating comprises ACR-1g white paint.

[0010] Preferably, a fiberglass heat insulation pad is provided between the antenna and the heat sink, and the gap between the antenna and the heat sink is filled with a multi-layer heat insulation component.

[0011] Preferably, multiple fiberglass heat insulation pads are arranged in an array between the antenna and the heat sink, and the plane where the antenna is located is parallel to the upper surface of the heat sink.

[0012] Preferably, the heat pipe connects the area where the heat sink is installed and the effective heat dissipation surface of the heat sink; the heat generated by the heat sink is first transferred to the heat sink, then transferred to the effective heat dissipation surface of the heat sink through the heat pipe, and then radiated to the cold space through the graphene film.

[0013] Preferably, the heat sink comprises a honeycomb plate.

[0014] Preferably, both the heat sink and the heat pipe are made of lightweight materials.

[0015] Preferably, the on-orbit temperature is -10°C to 37°C.

[0016] Compared with the prior art, the present invention has the following beneficial effects:

[0017] 1. This invention first transfers the heat from the single unit to the heat sink, then through the heat pipe to the effective heat dissipation surface of the heat sink, and then through the graphene film to the cold space. This satisfies the heat dissipation requirements of high-power single units of current microwave radar antennas after they are moved from inside the cabin to the bottom of the antenna, and solves the problem of insufficient heat dissipation capacity of the single unit when it is blocked by the antenna.

[0018] 2. The present invention, by using a fiberglass heat insulation pad placed between the heat sink and the antenna, helps to reduce the impact of drastic temperature changes on the device and individual unit.

[0019] 3. By using lightweight materials and lightweight design, the present invention is lightweight and low in cost. Moreover, the entire device uses passive thermal control measures, so there are no problems with system start-up, termination and failure, and the reliability is high. Attached Figure Description

[0020] 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:

[0021] Figure 1 This is a top view illustrating the overall structure of the heat dissipation device in this invention.

[0022] Figure 2 This is a side view that mainly illustrates the overall structure of the heat dissipation device in this invention;

[0023] Figure 3 This invention primarily reflects the actual test temperature curve of high-power equipment;

[0024] Figure 4 This invention primarily reflects the actual on-orbit temperature curve of high-power equipment.

[0025] The diagram shows: 1. Heat sink; 2. Heat pipe; 3. Graphene film; 4. Thermal control coating; 5. Fiberglass heat insulation pad; 6. Antenna; 7. Standalone unit. Detailed Implementation

[0026] 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.

[0027] like Figure 1 and Figure 2 As shown, a heat dissipation device for an external unit of a microwave radar antenna according to the present invention includes a heat dissipation plate 1 disposed between seven antennas 6 of the unit. Heat pipes 2 are arranged inside the heat dissipation plate 1. A graphene film 3 is disposed on the effective heat dissipation surface of the heat dissipation plate 1, and a thermal control coating 4 is sprayed onto the outer surface of the graphene film 3. The heat dissipation device can ensure an on-orbit temperature of -10°C to 37°C.

[0028] Specifically, the effective heat dissipation surface of the heat sink 1 includes the area on the heat sink 1 that extends beyond the area projected onto the heat sink 1 by the antenna 6. The heat sink 1 includes a honeycomb panel, with heat pipes 2 arranged inside the honeycomb panel. A graphene film 3 is adhered to the effective heat dissipation surface of the heat sink 1, thereby ensuring that the heat from the single unit 7 can be transferred to the entire heat dissipation device. This effectively solves the problem of insufficient heat dissipation capacity of the single unit 7 due to being blocked by the antenna 6, and also features high adaptability and high reliability.

[0029] More specifically, the single unit 7 is connected to the lower surface of the heat sink 1, and an indium foil is disposed between the single unit 7 and the heat sink 1. The single unit 7 generates high heat loss during operation, and the high-purity indium foil can quickly transfer the heat from the single unit 7 to the heat sink 1. The graphene film 3 disposed on the effective heat dissipation surface of the heat sink 1 can improve the temperature uniformity of the heat sink 1 and increase heat dissipation efficiency.

[0030] A low-absorptivity, high-emissivity thermal control coating 4 is sprayed onto the outer surface of the graphene film for heat dissipation. The solar absorptivity of the thermal control coating 4 is αs = 0.3 ± 0.04, and the infrared emissivity of the thermal control coating 4 is εh = 0.9 ± 0.04. The thermal control coating 4 includes ACR-1g white paint.

[0031] A fiberglass heat insulation pad 5 is disposed between the antenna 6 and the heat sink 1, and the gap between the antenna 6 and the heat sink 1 is filled with a multi-layer heat insulation component. Multiple fiberglass heat insulation pads 5 are arrayed between the antenna 6 and the heat sink 1, with the plane of the antenna 6 parallel to the upper surface of the heat sink 1. One feasible implementation is to array nine fiberglass heat insulation pads 5 between the heat sink 1 and the antenna 6, with the remaining gaps filled with a multi-layer heat insulation component, thereby reducing heat exchange between the heat sink 1 and the antenna 6 and preventing temperature changes in the antenna 6 from affecting the temperature of the unit 7. It should be further noted that the multi-layer heat insulation component of this application is any type of heat insulation component suitable for spaceborne environments in the prior art.

[0032] Furthermore, heat pipe 2 connects the area where the single unit 7 is mounted on heat sink 1 to the effective heat dissipation surface of heat sink 1. The heat transfer path is as follows: the heat generated by the single unit 7 is first transferred to heat sink 1, then transferred to the effective heat dissipation surface of heat sink 1 through heat pipe 2, and then radiated to the cold space through graphene film 3.

[0033] Furthermore, both the heat sink 1 and the heat pipe 2 are made of lightweight materials to reduce the overall weight of the heat dissipation device. Preferably, the heat sink 1 is made of a 10mm honeycomb structure, weighing 1.5kg per square meter, the heat pipe 2 weighs 0.7kg per meter, and the graphene film weighs 0.5kg per square meter. The entire device adopts a lightweight design.

[0034] It should be further noted that the heat dissipation device of this application is a passive thermal control measure, and there are no issues with system startup, termination, or failure. It has a simple and reliable structure, is easy to manufacture, has low cost, and is lightweight.

[0035] Based on the above heat dissipation device, the temperature of the high-power unit 7 of a satellite microwave radar antenna 6 was tested and verified in orbit. The test used a heater to simulate the heat flow outside the orbit, and the microwave radar antenna 6 operated according to the actual working mode.

[0036] like Figure 3 and Figure 4 The figure shows the temperature curve of the high-power single unit 7. From the above test results, it can be seen that the test temperature of the high-power single unit 7 is kept below 35℃ when it is turned on. This is because thermal grease is placed between the high-power single unit 7 and the heat dissipation device, and heat pipes 2 are pre-embedded in the heat dissipation plate 1. Graphene film is pasted on the effective heat dissipation surface of the honeycomb plate to ensure that the heat of the high-power transmitter is transferred to the entire heat dissipation device. A thermal control coating 4 with low absorptivity and high emissivity is sprayed on the surface of the graphene film to ensure the heat dissipation effect of the device.

[0037] The on-orbit temperature was maintained between -10°C and 37°C, which is consistent with the experimental results, providing a good guarantee for the operation of the microwave radar.

[0038] As demonstrated by the above embodiments, the microwave radar antenna 6 external high-power single unit 7 heat dissipation device of the present invention has the characteristics of stable temperature control, low energy demand, high adaptability, good reliability and flexible design.

[0039] 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.

[0040] 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 device for a single unit outside a microwave radar antenna compartment, characterized in that, It includes a heat sink (1) disposed between the single unit (7) and the antenna (6), a heat pipe (2) is arranged inside the heat sink (1), a graphene film (3) is disposed on the effective heat dissipation surface of the heat sink (1), and a thermal control coating (4) is sprayed on the outer surface of the graphene film (3). The heat pipe (2) connects the area where the heat sink (1) is installed with the single unit (7) and the effective heat dissipation surface of the heat sink (1); The heat generated by the single machine (7) is first transferred to the heat sink (1), then transferred to the effective heat dissipation surface of the heat sink (1) through the heat pipe (2), and then radiated to the cold space through the graphene film (3).

2. The heat dissipation device for a single unit outside the microwave radar antenna compartment as described in claim 1, characterized in that, The single unit (7) is connected to the lower surface of the heat sink (1), and an indium foil is provided between the single unit (7) and the heat sink (1).

3. The heat dissipation device for a single external unit of a microwave radar antenna compartment as described in claim 1, characterized in that, The effective heat dissipation surface of the heat sink (1) includes the area on the heat sink (1) that extends beyond the orthographic projection area of ​​the antenna (6) on the heat sink (1).

4. The heat dissipation device for a single external unit of a microwave radar antenna compartment as described in claim 1, characterized in that, The solar absorptivity of the thermal control coating (4) is αs = 0.3 ± 0.04; The infrared emissivity of the thermal control coating (4) is εh = 0.9 ± 0.04; The thermal control coating (4) includes ACR-1g white paint.

5. The heat dissipation device for a single external unit of a microwave radar antenna compartment as described in claim 1, characterized in that, A fiberglass heat insulation pad (5) is provided between the antenna (6) and the heat sink (1), and the gap between the antenna (6) and the heat sink (1) is filled with a multi-layer heat insulation component.

6. The heat dissipation device for a single external unit of a microwave radar antenna compartment as described in claim 5, characterized in that, Multiple fiberglass heat insulation pads (5) are arranged in an array between the antenna (6) and the heat sink (1), and the plane where the antenna (6) is located is parallel to the upper surface of the heat sink (1).

7. The heat dissipation device for an external unit of a microwave radar antenna as described in claim 1, characterized in that, The heat sink (1) includes a honeycomb panel.

8. The heat dissipation device for an external unit of a microwave radar antenna as described in claim 1, characterized in that, Both the heat sink (1) and the heat pipe (2) are made of lightweight materials.

9. The heat dissipation device for a single external unit of a microwave radar antenna compartment as described in claim 1, characterized in that, The on-orbit temperature ranges from -10°C to 37°C.

Images