An airborne radar antenna cover conformal heat dissipation structure and a control system thereof

Abstract

The application discloses an airborne radar antenna cover conformal heat dissipation structure and a control system thereof. The antenna cover conformal heat dissipation structure comprises an outer shell, a load, a driving unit, a liquid cooling pipeline, a first radiator and a second radiator which are arranged in the outer shell. The outer shell comprises an antenna cover surface and a metalized heat dissipation skin. The first radiator and the second radiator are attached to the inner wall of the metalized heat dissipation skin. The liquid cooling cavity of the load is communicated with the driving unit, the first radiator and the second radiator in sequence through the liquid cooling pipeline. The driving unit can drive the heat exchange working medium in the liquid cooling pipeline to circulate between the first radiator, the second radiator and the load to dissipate heat for the load. The antenna cover and the radiator are integrated, the equipment such as a rotary table and a water hinge is reduced, and the lightweight design of the heat dissipation system is realized. The control system can adjust the flow direction of the cooling liquid according to the flight direction of the aircraft, reduces the liquid supply temperature of the heat dissipation system and improves the system efficiency.

Description

Technical Field

[0001] This invention relates to the field of heat dissipation technology for airborne radar electronic equipment, and in particular to a conformal heat dissipation structure for an airborne radar radome, and a control system for the conformal heat dissipation structure for the airborne radar radome. Background Technology

[0002] Airborne cooling systems typically employ either air-liquid heat exchangers with air intakes or skin heat exchangers fixed to the fuselage to remove heat. Air-liquid heat exchangers are heavier, and the air intakes require vents for evacuation, which can negatively impact aircraft aerodynamics and hinder stealth and aerodynamic performance. In contrast, skin heat exchangers offer a superior, vent-free airborne cooling solution. However, in airborne radar systems, the antenna array cooling system is often independent of the aircraft and requires reorientation to different locations. In this case, the skin heat exchanger, fixed to the fuselage, must be connected to the rotating array electronics via water hinges, increasing system weight and reducing reliability. Summary of the Invention

[0003] To address the technical problems existing in the background art, the present invention proposes a conformal heat dissipation structure for an airborne radar radome, and a control system for the conformal heat dissipation structure for the airborne radar radome.

[0004] The present invention proposes a conformal heat dissipation structure for an airborne radar radome, comprising an outer shell and a load, a drive unit, liquid cooling pipes, a first heat sink, and a second heat sink installed inside the outer shell. The outer shell includes an antenna radome surface and a metallized heat dissipation skin. The first and second heat sinks are attached to the inner wall of the metallized heat dissipation skin. The liquid cooling cavity of the load is connected to the drive unit, the first heat sink, and the second heat sink in sequence through the liquid cooling pipes. The drive unit can drive the heat exchange medium in the liquid cooling pipes to circulate between the first heat sink, the second heat sink, and the load to dissipate heat from the load.

[0005] Preferably, the drive unit includes a water pump, a first solenoid three-way valve, a second solenoid three-way valve, and a controller. The controller is connected to the water pump, the first solenoid three-way valve, and the second solenoid three-way valve respectively to control the water pump, the first solenoid three-way valve, and the second solenoid three-way valve to be energized or de-energized.

[0006] The outlet end of the liquid cooling chamber of the load is connected to the water pump and the first electromagnetic three-way valve in sequence through the first-stage return liquid pipeline. The first electromagnetic three-way valve is connected to the first radiator through the second-stage return liquid pipeline A, and to the second radiator through the second-stage return liquid pipeline B.

[0007] The first radiator and the second radiator are connected to each other through connecting pipes;

[0008] The inlet of the liquid cooling chamber of the load is connected to the second solenoid three-way valve through the primary liquid supply line. The second solenoid three-way valve is connected to the second radiator through the secondary liquid supply line A, and to the first radiator through the secondary liquid supply line B.

[0009] Preferably, the first heat sink and the second heat sink are 90° apart in orientation in the circumferential direction of the metallized heat dissipation skin.

[0010] Preferably, there are two first radiators and two second radiators, with the two first radiators and the two second radiators arranged alternately.

[0011] Preferably, the first radiator and the second radiator have the same structure, both including two manifolds and multiple rows of pipes connecting the two manifolds.

[0012] Preferably, the outer wall of the metallized heat dissipation skin is provided with heat dissipation fins.

[0013] Preferably, the metallized heat dissipation skin and heat dissipation fins are made of aluminum alloy.

[0014] The present invention also provides a control system for the above-mentioned conformal heat dissipation structure of the airborne radar radome, wherein the controller controls the water pump to drive the heat exchange medium in the liquid cooling pipeline to circulate between the first radiator, the second radiator, and the load.

[0015] When the temperature of the first radiator is higher than that of the second radiator, the controller controls the first solenoid three-way valve to connect the secondary return liquid line A with the primary return liquid line, and controls the second solenoid three-way valve to connect the secondary supply liquid line A with the primary supply liquid line, so that the heat exchange medium flows through the first radiator and the second radiator in sequence.

[0016] When the temperature of the second radiator is higher than that of the first radiator, the controller controls the first solenoid three-way valve to connect the secondary return liquid line B with the primary return liquid line, and controls the second solenoid three-way valve to connect the secondary supply liquid line B with a section of the supply liquid line, so that the heat exchange medium flows through the second radiator and the first radiator in sequence.

[0017] Preferably, the controller circuit includes a power supply, a relay, a first thermistor, and a second thermistor. The first and second thermistors are connected in parallel in the main power supply circuit, and a fixed resistor is connected in series in each branch containing the first and second thermistors. A diode and a relay are connected between the branches containing the first and second thermistors. The relay is connected to the first solenoid three-way valve through control line A, and the relay is connected to the second solenoid three-way valve through control line B. The water pump is connected in series with the power supply.

[0018] Preferably, the positive terminal of the diode is connected to the branch where the first thermistor is located, and the negative terminal of the diode is connected to the branch where the second thermistor is located.

[0019] The conformal heat dissipation structure and control system of the airborne radar radome of the present invention integrates the heat sink with the radome, reducing equipment such as turntables and water hinges, and realizing a lightweight design of the heat dissipation system; the control system enables the coolant flow direction to be adjusted according to the flight direction of the aircraft, reducing the supply temperature of the heat dissipation system and improving system efficiency. Attached Figure Description

[0020] Figure 1 This is a perspective view of the airborne radar radome in the embodiment;

[0021] Figure 2 This is a cross-sectional view of the conformal heat dissipation structure of the airborne radar radome in the embodiment.

[0022] Figure 3 This is a perspective view of the conformal heat dissipation structure of the airborne radar radome in the embodiment.

[0023] Figure 4 This is a schematic diagram of the control system of the conformal heat dissipation structure of the airborne radar radome in the embodiment;

[0024] Figure 5 This is a controller circuit diagram of the control system in the embodiment;

[0025] Figure 6 This is a schematic diagram of the structure of the first heat sink of the antenna radome in the embodiment when it is located in the windward direction;

[0026] Figure 7 This is a schematic diagram of the structure of the second heat sink of the antenna radome in the embodiment when it is located in the windward direction. Detailed Implementation

[0027] Please refer to Figure 1-7 As shown, a conformal heat dissipation structure for an airborne radar radome according to an embodiment of the present invention includes an outer shell 1 and a load 2, a drive unit 3, a liquid cooling pipe 4, a first heat sink 5, and a second heat sink 6 installed inside the outer shell 1.

[0028] The outer casing 1 includes an antenna radome 11, a metallized heat dissipation skin 12, and a top cover 13. The antenna radome 11 and the metallized heat dissipation skin 12 are integrally formed. The antenna radome 11 is a hemispherical wave-transparent radome to ensure that the radar performance is not affected by the metallized heat dissipation skin 12. The metallized heat dissipation skin 12 is annular in shape and is a thin-walled structure with a thickness of 2mm made of aluminum alloy. The outer wall of the metallized heat dissipation skin 12 is also provided with heat dissipation fins 121, which are also made of aluminum alloy. The heat dissipation fins 121 are integrally formed with the metallized heat dissipation skin 12, which can improve the efficiency of heat exchange between the metallized heat dissipation skin 12 and the air. The metallized heat dissipation skin 12 is fixedly connected to the top cover 13, and a sealing ring is provided between the two to ensure the airtightness of the outer casing 1. The top cover 13 can be connected to the bottom of the aircraft and drives the entire outer casing 1 to rotate as needed according to the antenna polarization direction.

[0029] Load 2 is the electronic equipment of the radar. The housing of load 2 has a liquid-cooled cavity that can accommodate the heat exchange medium to dissipate heat from load 2. The first radiator 5 and the second radiator 6 are attached to the inner wall of the metallized heat dissipation skin 12. The first radiator 5 and the second radiator 6 have the same structure, each including two manifolds and multiple rows of pipes connecting the two manifolds. The rows of pipes are straight pipes, and the manifolds are arc-shaped pipes, so that the first radiator 5 and the second radiator 6 can be adapted to the shape and size of the metallized heat dissipation skin 12 to improve heat exchange efficiency. The liquid-cooled cavity of load 2 is connected to the drive unit 3, the first radiator 5, and the second radiator 6 in sequence through the liquid-cooled pipe 4. The drive unit 3 can drive the heat exchange medium in the liquid-cooled pipe 4 to circulate among the first radiator 5, the second radiator 6, and load 2 to dissipate heat from load 2.

[0030] It can be seen that the conformal heat dissipation structure of the airborne radar radome is integrated and installed on the radome surface 11 by the heat sink and the metallized heat dissipation skin 12. The heat on the surface of the metallized heat dissipation skin 12 is carried away by the air, and the load 2 can be cooled by air-liquid heat exchange. There is no need to use equipment such as turntables and water hinges, thus realizing the lightweight design of the heat dissipation system.

[0031] In this embodiment, the drive unit 3 includes a water pump 31, a first electromagnetic three-way valve 32, a second electromagnetic three-way valve 33, and a controller 34. The controller 34 is connected to the water pump 31, the first electromagnetic three-way valve 32, and the second electromagnetic three-way valve 33 respectively, and is used to control the water pump 31, the first electromagnetic three-way valve 32, and the second electromagnetic three-way valve 33 to be energized or de-energized.

[0032] The liquid cooling pipeline 4 includes a primary return pipeline 41, a primary supply pipeline 44, a secondary return pipeline A42, a secondary return pipeline B43, a secondary supply pipeline A45, and a secondary supply pipeline B46. The liquid cooling pipeline 4 system is equipped with a heat exchange medium, specifically No. 65 coolant, to ensure heat dissipation performance and antifreeze performance.

[0033] In the liquid cooling pipeline system 4, the outlet end of the liquid cooling chamber of load 2 is connected to the water pump 31 and the first solenoid three-way valve 32 in sequence through the primary return pipeline 41. The other two ends of the first solenoid three-way valve 32 are connected to the first radiator 5 and the second radiator 6, respectively. Specifically, the first solenoid three-way valve 32 is connected to the first radiator 5 through the secondary return pipeline A42 and to the second radiator 6 through the secondary return pipeline B43. The first radiator 5 and the second radiator 6 are interconnected through the connecting pipeline 7. The inlet end of the liquid cooling chamber of load 2 is connected to the second solenoid three-way valve 33 through the primary supply pipeline 44. The other two ends of the second solenoid three-way valve 33 are connected to the first radiator 5 and the second radiator 6, respectively. Specifically, the second solenoid three-way valve 33 is connected to the second radiator 6 through the secondary supply pipeline A45 and to the first radiator 5 through the secondary supply pipeline B46.

[0034] The first radiator 5 and the second radiator 6 are 90° apart in the circumferential direction of the metallized heat dissipation skin 12. Depending on the actual heat dissipation requirements, the number of the first radiator 5 and the second radiator 6 can be set to one or two. When the number of the first radiator 5 and the second radiator 6 is two, the first radiator 5 and the second radiator 6 are arranged alternately.

[0035] It is worth mentioning that if there are two first radiators 5 and two second radiators 6, the secondary return line A42 should be connected to the two first radiators 5 respectively, the secondary return line B43 should be connected to the two second radiators 6 respectively, the secondary supply line A45 should be connected to the two second radiators 6 respectively, and the secondary supply line B46 should be connected to the two first radiators 5 respectively.

[0036] Based on the above-described conformal heat dissipation structure for airborne radar radomes, this embodiment also provides a control system for the conformal heat dissipation structure for airborne radar radomes. The following content will provide a more detailed explanation of the control system and its working principle.

[0037] like Figure 5 As shown, the controller 34 circuit of the control system includes a power supply 341, a first thermistor 343, a second thermistor 344, a diode 346, a relay 342, and a resistor. The first thermistor 343 and the second thermistor 344 are connected in parallel with the power supply 341, and a fixed resistor 345 is connected in series in each branch containing the first thermistor 343 and the second thermistor 344. The resistance values ​​of the fixed resistors 345 in the two branches are equal. A diode 346 and a relay 342 are also connected between the two branches. The relay 342 is connected to the first electromagnetic three-way valve 32 through control line A347 and to the second electromagnetic three-way valve 33 through control line B348. The water pump 31 is connected in series with the power supply 341.

[0038] The anode of diode 346 is connected to the circuit of the first thermistor 343, and the cathode of diode 346 is connected to the circuit of the second thermistor 344. When the resistance of the first thermistor 343 is less than the resistance of the second thermistor 344, the voltage at the anode of the diode is less than the voltage at the cathode, diode 346 does not conduct, and relay 342 is in the closed state. When the resistance of the first thermistor 343 is greater than the resistance of the second thermistor 344, the voltage at the anode of the diode is greater than the voltage at the cathode, diode 346 conducts, relay 342 turns on, and power supply 341 energizes the first electromagnetic three-way valve 32 and the second electromagnetic three-way valve 33. Both the first thermistor 343 and the second thermistor 344 are negative temperature coefficient thermistors. The first electromagnetic three-way valve 32 and the second electromagnetic three-way valve 33 are preferably normally closed or normally open electromagnetic three-way valves with one inlet and one outlet.

[0039] The working principle of the control system is as follows: During operation, the controller 34 controls the water pump 31 to drive the heat exchange medium in the liquid cooling pipeline 4 to circulate between the first radiator 5, the second radiator 6, and the load 2.

[0040] When the temperature of the first radiator 5 is higher than that of the second radiator 6, the controller 34 controls the first solenoid three-way valve 32 to de-energize and connect the secondary return line A42 with the primary return line 41, and controls the second solenoid three-way valve 33 to de-energize and connect the secondary supply line A45 with the primary supply line 44, so that the coolant flows through the first radiator 5 and the second radiator 6 in sequence.

[0041] When the temperature of the second radiator 6 is higher than that of the first radiator 5, the controller 34 controls the first solenoid three-way valve 32 to be energized to connect the secondary return line B43 with the primary return line 41, and controls the second solenoid three-way valve 33 to be energized to connect the secondary supply line B46 with a section of the supply line, so that the coolant flows through the second radiator 6 and the first radiator 5 in sequence.

[0042] The design of this control system demonstrates good technical performance. Considering the influence of the atmosphere on the radome 11, when the aircraft carrying the radome is flying at high speed, the air compression on the radome surface generates aerodynamic heat, causing the radome surface temperature to rise. The temperatures on the windward side and the side facing the airflow are different, with the leeward side having the highest temperature, followed by the windward side, and the side surface having the lowest temperature. Therefore, when the first radiator 5 and the second radiator 6 are located on the windward side and the side facing the airflow, respectively, their temperatures differ. This control system adjusts the coolant flow path accordingly based on the temperature difference caused by the change in wind direction, maximizing the heat dissipation efficiency of both the first radiator 5 and the second radiator 6, thus ensuring good heat dissipation efficiency.

[0043] like Figure 6As shown, when the first radiator 5 is located in the windward direction of the radome, the second radiator 6 is located on the inflow side of the radome. The temperature of the first radiator 5 is higher than that of the second radiator 6. The resistance of the first thermistor 343 is lower than that of the second thermistor 344. At this time, the diode 346 is not conducting, the relay 342 is in the closed state, and the first electromagnetic three-way valve 32 and the second electromagnetic three-way valve 33 are not energized, and the state is 1. The flow direction of the coolant in state 1 is: load 2 → water pump 31 → primary return pipe → first electromagnetic three-way valve 32 → secondary return pipe A42 → first radiator 5 → connecting pipe 7 → second radiator 6 → secondary supply pipe A45 → second electromagnetic three-way valve 33 → primary supply pipe → load 2.

[0044] like Figure 7 As shown, when the second radiator 6 is located in the windward direction of the radome, the first radiator 5 is located on the inflow side of the radome. The temperature of the second radiator 6 is higher than that of the first radiator 5, and the resistance of the first thermistor 343 is higher than that of the second thermistor 344. At this time, the diode 346 is turned on, the relay 342 is in the open state, and the first electromagnetic three-way valve 32 and the second electromagnetic three-way valve 33 are energized, which is state 2. The flow direction of the coolant in state 2 is: load 2 → water pump 31 → primary return pipe → first electromagnetic three-way valve 32 → secondary return pipe B43 → second radiator 6 → connecting pipe 7 → first radiator 5 → secondary supply pipe B46 → second electromagnetic three-way valve 33 → primary supply pipe → load 2.

[0045] Since the first radiator 5 and the second radiator 6 are in close contact with the metallized heat dissipation skin 12 and have a large contact area, the temperature of the coolant after passing through the radiator is basically the same as that of the metallized heat dissipation skin 12. Therefore, by controlling the flow direction of the coolant, the high-temperature coolant flowing out of the liquid cooling chamber of the load 2 first enters the windward radiator and then flows out from the side radiator with a lower temperature. This can increase the heat exchange efficiency, effectively reduce the coolant temperature, improve the heat dissipation efficiency, and reduce the temperature of the radar electronic equipment.

[0046] The above description is only a preferred embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any equivalent substitutions or modifications made by those skilled in the art within the scope of the technology disclosed in the present invention, based on the technical solution and inventive concept of the present invention, should be covered within the scope of protection of the present invention.

Claims

1. A control system for a conformal heat dissipation structure of an airborne radar radome, characterized in that, The conformal heat dissipation structure of the airborne radar radome includes an outer shell (1) and a load (2), a drive unit (3), a liquid cooling pipeline (4), a first radiator (5), and a second radiator (6) installed inside the outer shell (1). The outer shell (1) includes an antenna radome (11) and a metallized heat dissipation skin (12). The first radiator (5) and the second radiator (6) are attached to the inner wall of the metallized heat dissipation skin (12). The liquid cooling cavity of the load (2) is connected to the drive unit (3), the first radiator (5), and the second radiator (6) in sequence through the liquid cooling pipeline (4). The drive unit (3) can drive the heat exchange medium in the liquid cooling pipeline (4) to circulate between the first radiator (5), the second radiator (6), and the load (2) to dissipate heat from the load (2). The drive unit (3) includes a water pump (31), a first electromagnetic three-way valve (32), a second electromagnetic three-way valve (33), and a controller (34). The controller (34) is connected to the water pump (31), the first electromagnetic three-way valve (32), and the second electromagnetic three-way valve (33) respectively to control the water pump (31), the first electromagnetic three-way valve (32), and the second electromagnetic three-way valve (33) to be energized or de-energized. The outlet end of the liquid cooling chamber of the load (2) is connected to the water pump (31) and the first electromagnetic three-way valve (32) in sequence through the first-stage return liquid pipeline (41). The first electromagnetic three-way valve (32) is connected to the first radiator (5) through the second-stage return liquid pipeline A (42) and to the second radiator (6) through the second-stage return liquid pipeline B (43). The first radiator (5) and the second radiator (6) are connected to each other through a connecting pipe (7); The inlet end of the liquid cooling chamber of the load (2) is connected to the second electromagnetic three-way valve (33) through the first-stage liquid supply pipeline (44). The second electromagnetic three-way valve (33) is connected to the second radiator (6) through the second-stage liquid supply pipeline A (45) and to the first radiator (5) through the second-stage liquid supply pipeline B (46). The control system, the controller (34) controls the water pump (31) to work and drive the heat exchange medium in the liquid cooling pipeline (4) to circulate between the first radiator (5), the second radiator (6), and the load (2); When the temperature of the first radiator (5) is higher than that of the second radiator (6), the controller (34) controls the first electromagnetic three-way valve (32) to connect the secondary return liquid pipeline A (42) with the primary return liquid pipeline (41), and controls the second electromagnetic three-way valve (33) to connect the secondary supply liquid pipeline A (45) with the primary supply liquid pipeline (44), so that the heat exchange medium flows through the first radiator (5) and the second radiator (6) in sequence. When the temperature of the second radiator (6) is higher than that of the first radiator (5), the controller (34) controls the first electromagnetic three-way valve (32) to connect the secondary return liquid pipeline B (43) with the primary return liquid pipeline (41), and controls the second electromagnetic three-way valve (33) to connect the secondary supply liquid pipeline B (46) with the primary supply liquid pipeline (44), so that the heat exchange medium flows through the second radiator (6) and the first radiator (5) in sequence.

2. The control system of the conformal heat dissipation structure for airborne radar radome according to claim 1, characterized in that, The first radiator (5) and the second radiator (6) are 90° apart in orientation around the metallized heat dissipation skin (12).

3. The control system of the conformal heat dissipation structure for airborne radar radome according to claim 2, characterized in that, There are two of each of the first radiator (5) and the second radiator (6), with the two first radiators (5) and the two second radiators (6) arranged alternately.

4. The control system for the conformal heat dissipation structure of the airborne radar radome according to any one of claims 1-3, characterized in that, The first radiator (5) and the second radiator (6) have the same structure, both including two manifolds and multiple pipes connected between the two manifolds.

5. The control system for the conformal heat dissipation structure of the airborne radar radome according to any one of claims 1-3, characterized in that, The outer wall of the metallized heat dissipation skin (12) is provided with heat dissipation fins (121).

6. The control system for the conformal heat dissipation structure of the airborne radar radome according to claim 5, characterized in that, The metallized heat dissipation skin (12) and heat dissipation fins (121) are made of aluminum alloy.

7. The control system for the conformal heat dissipation structure of the airborne radar radome according to claim 1, characterized in that, The circuit of the controller (34) includes a power supply (341), a relay (342), a first thermistor (343), and a second thermistor (344). The first thermistor (343) and the second thermistor (344) are connected in parallel in the main circuit of the power supply (341), and a fixed resistor (345) is connected in series in the branch where the first thermistor (343) and the second thermistor (344) are located. A diode (346) and a relay (342) are connected between the branch where the first thermistor (343) and the second thermistor (344) are located. The relay (342) is connected to the first electromagnetic three-way valve (32) through control line A (347), and the relay (342) is connected to the second electromagnetic three-way valve (33) through control line B (348). The water pump (31) is connected in series with the power supply (341).

8. The control system for the conformal heat dissipation structure of the airborne radar radome according to claim 7, characterized in that, The positive terminal of diode (346) is connected to the branch where the first thermistor (343) is located, and the negative terminal of diode (346) is connected to the branch where the second thermistor (344) is located.

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