Airborne product constant-temperature liquid cooling system and method

Abstract

The invention discloses an airborne product constant-temperature liquid cooling system and method, and belongs to the technical field of equipment heat dissipation. According to the airborne product constant-temperature liquid cooling system, airborne cooling liquid is divided into two paths through the three-way electromagnetic valve, one path flows through a constant-temperature object refrigerated by the thermoelectric refrigerating unit, the other path flows through the high-heat-consumption device, flow distribution of the electromagnetic valve and input current and voltage of the thermoelectric refrigerating unit are regulated and controlled through the control module, and control over one path of constant temperature and one path of heat dissipation is achieved. According to the constant-temperature liquid cooling system, onboard liquid cooling resources are reasonably utilized, the constant-temperature liquid cooling system is not affected by the large temperature change amplitude of onboard cooling liquid, constant-temperature control over a constant-temperature object in an onboard product can be achieved, and meanwhile the heat dissipation requirement of the other path for a high-heat-consumption device is met.

Description

Technical Field

[0001] The present invention belongs to the technical field of equipment heat dissipation, and in particular relates to a constant temperature liquid cooling system and method for airborne products. Background Art

[0002] The external thermal environment in which airborne optoelectronic products operate is relatively harsh, and temperature changes often directly affect product performance. As the new generation of airborne optoelectronic products has more and more functions and higher performance indicators, the heat consumption of the electronic devices inside the products continues to increase, and the problem of product performance indicators declining due to temperature factors is becoming increasingly prominent. Therefore, it is necessary to develop technical requirements for thermal control design of airborne optoelectronic systems to control the temperature distribution and uniformity of the system, especially for optoelectronic products that need to work at a constant temperature, which requires them to work under constant temperature conditions in the best working state. At the same time, with the continuous development of electronic components, the power density of airborne components has been greatly improved, and the volumetric thermal power of the equipment has been greatly increased when it is working. For some precision equipment, it is of great significance to the reliability of the equipment to dissipate the heat generated by the electronic components in the equipment into the environment in a timely manner to keep the equipment at a normal operating temperature.

[0003] At present, liquid cooling is a widely used heat dissipation method for medium and high power density equipment. It can quickly remove the heat generated by various components in electronic equipment and has high working reliability and stability.

[0004] Airborne optoelectronic products are one of the aircraft mission systems. With the increasing power density of avionics equipment, the traditional air-controlled air cooling system can no longer meet the heat dissipation requirements. The liquid cooling resources of airborne optoelectronic products are supplied by the aircraft. Due to the different flight altitudes, regions and flight attitudes of aircraft when performing missions, the temperature of the coolant in the aircraft liquid cooling system changes with the flight state in the air, causing the coolant temperature on the aircraft to change greatly (the temperature range is about 0℃-60℃). The coolant in the aircraft liquid cooling system is the input source of the airborne optoelectronic product liquid cooling system. The temperature change of the coolant supplied by the aircraft has a great impact on the airborne optoelectronic product environmental control system. In the past, the use of onboard liquid cooling resources by airborne optoelectronic products was mainly to directly introduce coolant, and there was no way to respond to the changes in the onboard coolant temperature. How to reasonably use the onboard liquid cooling resources can not only realize the constant temperature control of the constant temperature objects that need to work at a constant temperature in airborne optoelectronic products, but also realize the liquid cooling and heat dissipation of high heat consumption devices in airborne optoelectronic products, which is worthy of our study. Summary of the invention

[0005] Technical issues to be solved:

[0006] In order to avoid the shortcomings of the prior art, the present invention provides a constant temperature liquid cooling system for airborne products, which divides the airborne coolant into two paths through a three-way solenoid valve, one path flows through the constant temperature object cooled by the thermoelectric cooler, and the other path flows through the high heat consumption device. The control module regulates the flow distribution of the solenoid valve and the input current and voltage of the thermoelectric cooler to achieve one path of constant temperature and one path of heat dissipation. The problem in the prior art that the temperature of the airborne coolant varies greatly, making it difficult to perform constant temperature control on the constant temperature control object in the airborne optoelectronic product, and the high heat consumption device needs to be dissipated in time, is solved.

[0007] The technical solution of the present invention is: a constant temperature liquid cooling system for airborne products, comprising a coolant circulation module, the coolant circulation module is a coolant circulation system of the aircraft itself, and is used to provide coolant; it also includes a solenoid valve, a thermoelectric cooler, a first liquid cooling plate, a second liquid cooling plate, a control module and a temperature acquisition module;

[0008] The solenoid valve is a three-way solenoid valve, the inlet of the solenoid valve is connected to the coolant, the first outlet of the solenoid valve is connected to the inlet of the first liquid cooling plate through a pipeline, and the outlet of the first liquid cooling plate is connected to the coolant circulation module through a pipeline; the second outlet of the solenoid valve is connected to the inlet of the second liquid cooling plate through a pipeline, and the outlet of the second liquid cooling plate is connected to the coolant circulation module through a pipeline;

[0009] The first liquid cooling plate is installed at the hot end of the thermoelectric cooler to dissipate heat from the hot end of the thermoelectric cooler; the cold end of the thermoelectric cooler is connected to a constant temperature object, and the thermoelectric cooler is used to control the temperature of the constant temperature object; the second liquid cooling plate is installed at a high heat consumption device to dissipate heat from the high heat consumption device;

[0010] The temperature acquisition module is used to collect the temperature of the coolant, the temperature of the constant temperature object and the temperature of the high heat consumption device, and feed the collected data back to the control module;

[0011] The control module is electrically connected to the electromagnetic valve and the thermoelectric cooler, and is used to control the opening and closing degree of the first outlet of the electromagnetic valve and the input current and voltage of the thermoelectric cooler.

[0012] A further technical solution of the present invention is: the temperature acquisition module includes a first temperature sensor, a second temperature sensor and a third temperature sensor; the first temperature sensor is installed at the inlet of the solenoid valve, and is used to monitor the temperature of the coolant entering the solenoid valve; the second temperature sensor is installed on the constant temperature object to be regulated, and is used to monitor the temperature of the constant temperature object; the third temperature sensor is installed on the high heat consumption device, and is used to monitor the temperature of the high heat consumption device; the three temperature sensors are electrically connected to the control module respectively, and transmit the monitored temperature to the control module in real time for processing.

[0013] A further technical solution of the present invention is: the constant temperature liquid cooling system also includes a three-way joint, a first inlet of the three-way joint is connected to the outlet of the first liquid cooling plate through a pipeline; the second inlet of the three-way joint is connected to the outlet of the second liquid cooling plate through a pipeline; the outlet of the three-way joint is connected to the coolant circulation module through a pipeline.

[0014] A further technical solution of the present invention is: a target temperature is set for the constant temperature object in the control module, and the control module automatically adjusts the flow of the first outlet of the solenoid valve and the voltage and current of the thermoelectric cooler after comparing the temperature data transmitted by the temperature acquisition module with the target temperature.

[0015] A further technical solution of the present invention is: the thermoelectric cooler is installed on the constant temperature object through a structural gasket, the structural gasket is fixed above the constant temperature object, a through recessed portion is provided in the center of the structural gasket, and the shape of the recessed portion is consistent with the shape of the thermoelectric cooler; the thermoelectric cooler is embedded in the recessed portion, its cold end contacts the constant temperature object for cooling the constant temperature object, and its hot end contacts the first liquid cooling plate, and the heat of the hot end is taken away by the coolant flowing through the first liquid cooling plate.

[0016] A further technical solution of the present invention is: the solenoid valve includes a valve seat and a stepper motor integrated in the valve seat; the valve seat is provided with an inlet, a first outlet and a second outlet that are interconnected; the stepper motor has a retractable motor rod, the motor rod is located inside the valve seat, and the stepper motor drives the motor rod to retract to adjust the opening and closing degree of the first outlet, thereby adjusting the flow of coolant entering the first liquid cooling plate; the stepper motor is electrically connected to the control module and receives control instructions from the control module.

[0017] A further technical solution of the present invention is: the solenoid valve is equipped with a regulating valve controller, the regulating valve controller is installed in the control module and electrically connected to the control module; the stepper motor is electrically connected to the regulating valve controller and receives working instructions from the control module through the regulating valve controller.

[0018] A method for constant temperature liquid cooling of an airborne product using a constant temperature liquid cooling system, the steps are as follows:

[0019] Step 1: Set the target temperature of the constant temperature object in the control module;

[0020] Step 2: The aircraft control system starts the coolant circulation module, and the temperature acquisition module collects the coolant temperature, the temperature of the constant temperature object and the temperature of the high heat consumption device in real time, and feeds the collected information back to the control module. The control module determines whether the constant temperature object needs to be heated or cooled according to the target temperature requirement;

[0021] Step 3, the control module sends a control signal to the solenoid valve and the thermoelectric cooler at the same time according to the determination result of step 2; the control module controls the stepper motor to move, so that the motor rod is extended and retracted to adjust the flow rate of the coolant flowing out of the first outlet; the control module adjusts the voltage and current at both ends of the thermoelectric cooler according to the difference between the actual temperature of the constant temperature object and the target temperature; until the constant temperature object reaches the set target temperature;

[0022] Step 4: The coolant flowing out of the second outlet of the solenoid valve flows through the second liquid cooling plate to cool down the high heat consumption components.

[0023] Beneficial Effects

[0024] The beneficial effects of the present invention are as follows: the present invention provides a constant temperature liquid cooling system for airborne products, which uses a thermoelectric cooler to cool the constant temperature object, and introduces the coolant circulation system of the aircraft to provide a coolant source to dissipate heat for the airborne products. The coolant is divided into two paths, one for dissipating heat at the hot end of the thermoelectric cooler, and the other for dissipating heat for high heat consumption devices inside the product. Since the temperature of the liquid cooling resource of the onboard coolant circulation system changes with the flight state of the carrier aircraft, the temperature changes greatly, and the temperature range is about 0°C-60°C. In order to cope with different temperature conditions, the present invention rationally utilizes the onboard liquid cooling resources and designs a controllable liquid cooling flow distribution system. The constant temperature liquid cooling system can monitor the coolant temperature and the temperature of the constant temperature object in real time. The control module controls the coolant flow of the first outlet of the solenoid valve according to the monitoring data results, and controls the voltage and current at both ends of the thermoelectric cooler, so as to realize the constant temperature control of the constant temperature object in the airborne product, and at the same time ensure the heat dissipation demand of the other path for high heat consumption devices.

[0025] The constant temperature liquid cooling system for airborne products of the present invention has a simple structure, is easy to operate and implement, can effectively utilize the aircraft cooling liquid source, is not affected by the temperature change of the airborne cooling liquid source, and has a significant temperature control effect. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] Figure 1 is a system block diagram of the constant temperature liquid cooling system of the present invention;

[0027] Figure 2 This is a control principle diagram of the constant temperature liquid cooling system of the present invention;

[0028] Figure 3 It is a structural schematic diagram of the solenoid valve of the present invention;

[0029] Figure 4 It is a schematic diagram of the internal structure of the solenoid valve of the present invention;

[0030] Figure 5 It is a schematic diagram of the installation structure of the first liquid cooling plate, the thermoelectric cooler and the constant temperature object of the present invention;

[0031] Figure 6It is an exploded schematic diagram of the installation structure of the first liquid cooling plate, the thermoelectric cooler and the constant temperature object of the present invention.

[0032] Explanation of the accompanying drawings: 1. solenoid valve, 11. solenoid valve inlet, 12. first outlet, 13. second outlet, 14. valve seat, 15. stepper motor, 16. motor rod, 2. thermoelectric cooler, 21. cold end, 22. hot end, 3. first liquid cooling plate, 31. inlet of first liquid cooling plate, 32. outlet of first liquid cooling plate, 4. second liquid cooling plate, 5. constant temperature object, 6. high heat consumption device, 7. first temperature sensor, 8. three-way joint, 9. structural gasket, 10. screw. DETAILED DESCRIPTION

[0033] The embodiments described below with reference to the accompanying drawings are exemplary and are intended to be used to explain the present invention, but should not be construed as limiting the present invention.

[0034] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the present invention.

[0035] Embodiment 1:

[0036] See also Figure 1 This embodiment provides a constant temperature liquid cooling system for airborne products, which includes a coolant circulation module, which is a coolant circulation system of the aircraft, and is used to provide a coolant source for the constant temperature liquid cooling system. The coolant circulation module can deliver a coolant of a certain flow rate (flow rate range is 1-10L / min), temperature (temperature range is 0-60℃) and pressure to the constant temperature liquid cooling system of the present invention.

[0037] The constant temperature liquid cooling system for airborne products of the present invention further comprises a solenoid valve 1, a thermoelectric cooler 2, a first liquid cooling plate 3, a second liquid cooling plate 4, a three-way connector 8, a control module and a temperature acquisition module.

[0038] See also Figure 1 , 34, the solenoid valve 1 is a three-way solenoid valve, including a valve seat 14 and a stepper motor 15 integrated in the valve seat 14. The valve seat 14 is provided with three interlinked valve ports, including a solenoid valve inlet 11, a first outlet 12 and a second outlet 13. The solenoid valve inlet 11 is connected to the coolant of the coolant circulation module, the first outlet 12 of the solenoid valve 1 is connected to the inlet 31 of the first liquid cooling plate 3 through a pipeline, and the outlet 32 ​​of the first liquid cooling plate 3 is connected to the first inlet of the three-way joint 8 through a pipeline. The second outlet 13 of the solenoid valve is connected to the inlet of the second liquid cooling plate 4 through a pipeline, and the outlet of the second liquid cooling plate is connected to the second inlet of the three-way joint 8 through a pipeline. The three-way joint 8 is a universal three-way joint, and its outlet is connected to the coolant circulation module through a pipeline to form a circulation loop. The coolant from the solenoid valve inlet 11 is divided into two paths by the solenoid valve 1, one path flows through the first liquid cooling plate 3 and then enters the coolant circulation module, and the other path flows through the second liquid cooling plate 4 and then enters the coolant circulation module.

[0039] The stepper motor 15 has a retractable motor rod 16, which is located inside the valve seat 14. The stepper motor 15 drives the motor rod 16 to retract, so that the motor rod 16 can block the first outlet 12 to varying degrees, thereby adjusting the opening and closing degree of the first outlet 12, and then adjusting the flow of the coolant entering the first liquid cooling plate 3, and realizing the flow adjustment of the two branches. The stepper motor 15 is electrically connected to the control module and receives the control command of the control module.

[0040] See also Figure 1 , 5 , 6. The first liquid cooling plate 3 is installed on the hot end 22 of the thermoelectric cooler 2 (ie, TEC) to dissipate heat for the hot end 22 of the thermoelectric cooler 2. The cold end 21 of the thermoelectric cooler 2 is connected to the constant temperature object 5, and the thermoelectric cooler 2 is used to control the temperature of the constant temperature object 5. After the thermoelectric cooler 2 is powered on, the cold end 21 cools down and the hot end 22 heats up to achieve temperature regulation. The cooling capacity of the thermoelectric cooler 2 is determined by the heat dissipation capacity of the hot end 22 and the input voltage and current. The second liquid cooling plate 4 is fixedly installed on the high heat consumption device 6 to dissipate heat for the high heat consumption device 6. The present invention enhances the heat dissipation capacity of the two liquid cooling plates within a given spatial range by optimizing the design of the internal flow channel structure of the first liquid cooling plate 3 and the second liquid cooling plate 4. The thermoelectric cooler 2 is electrically connected to the control module, and the voltage and current at both ends of the thermoelectric cooler 2 are controlled by the control module to achieve temperature control.

[0041] Specifically, the thermoelectric cooler 2 is installed on the thermostatic object 5 through the structural gasket 9. In this embodiment, the thermostatic object 5 is specifically an optical lens barrel. The structural gasket 9 is fixed above the thermostatic object 5 by screws 10. The center of the structural gasket 9 is provided with a through inner concave portion, and the shape of the inner concave portion is consistent with the shape of the thermoelectric cooler 2. The thermoelectric cooler 2 is embedded in the inner concave portion, and the cold end 21 of the thermoelectric cooler 2 is in contact with the thermostatic object 5. The cold end 21 cools down and is used to cool the thermostatic object 5. Its hot end 22 is in contact with the first liquid cold plate 3. The hot end 22 heats up, and the heat of the hot end 22 is taken away by the coolant flowing through the first liquid cold plate 3. The first liquid cold plate 3 is installed above the thermoelectric cooler 2. The four corners of the first liquid cold plate 3 are provided with screw holes that match the four corners of the structural gasket 9. The screws pass through the first liquid cold plate 3, the structural gasket 9 and the upper end surface of the optical lens barrel of the thermostatic object 5 in sequence to be fixedly connected.

[0042] The temperature acquisition module in this embodiment is specifically three temperature sensors, and the temperature acquisition module is used to acquire the temperature of the coolant, the temperature of the constant temperature object 5 and the temperature of the high heat consumption component 6, and feed the acquired data back to the control module.

[0043] Specifically, the temperature acquisition module includes a first temperature sensor 7, a second temperature sensor and a third temperature sensor. The first temperature sensor 7 is integrated and installed at the inlet 11 of the solenoid valve 1, and is used to monitor the temperature of the coolant entering the solenoid valve 1 in real time. The second temperature sensor is installed on the constant temperature object 5 to be regulated, and is used to monitor the temperature of the constant temperature object 5 in real time. The third temperature sensor is installed on the high heat consumption device 6 (such as laser components, circuit board components, etc.), and is used to monitor the temperature of the high heat consumption device 6 in real time. The three temperature sensors are electrically connected to the control module respectively, and the monitored temperature is transmitted to the control module in real time for data processing.

[0044] The control module sets a target temperature for the thermostatic object 5. The control module compares the real-time temperature data of the thermostatic object 5 with the target temperature according to the temperature data collected by the temperature acquisition module, and refers to the current coolant temperature and the temperature of the high heat consumption device 6 to automatically adjust the flow of the first outlet 12 of the solenoid valve to distribute the coolant flow, and adjust the voltage and current of the thermoelectric cooler 2 to adjust the cooling capacity of the thermoelectric cooler 2 to achieve temperature control of the thermostatic object 5. The control module is electrically connected to the solenoid valve 1 and the thermoelectric cooler 2, and is used to control the opening and closing degree of the first outlet 12 of the solenoid valve 1 and the input current and voltage of the thermoelectric cooler 2 to achieve temperature control of the thermostatic object 5.

[0045] In this embodiment, the solenoid valve 1 is equipped with a regulating valve controller, which is installed in the control module and electrically connected to the control module. The stepper motor 15 is electrically connected to the regulating valve controller, and receives the working instructions of the control module through the regulating valve controller, controls the stepper motor 15 to drive the motor rod 16 to extend and retract, and realizes the flow regulation of the first outlet 12 of the solenoid valve.

[0046] The control module is specifically a control circuit board with a control algorithm inside. The control module can realize data acquisition and storage of the temperature acquisition module, compare the acquired temperature data with the target temperature, and send control instructions to the solenoid valve 1 and the thermoelectric cooler 2 according to the calculation results to control the temperature of the constant temperature object 5.

[0047] Embodiment 2:

[0048] This embodiment provides a method for performing constant temperature liquid cooling on an airborne product using the constant temperature liquid cooling system in Embodiment 1, and the steps are as follows:

[0049] Step 1: Set the target temperature of the constant temperature object 5 in the control module.

[0050] Step 2: The aircraft control system starts the coolant circulation module. The temperature acquisition module collects the coolant temperature, the temperature of the constant temperature object 5 and the temperature of the high heat consumption device 6 in real time, and feeds the collected information back to the control module. The control module determines whether the constant temperature object 5 needs to be heated or cooled according to the target temperature requirement.

[0051] Step 3: The control module sends a control signal to the solenoid valve 1 and the thermoelectric cooler 2 at the same time according to the determination result of step 2. The control module controls the stepper motor 15 to move, so that the motor rod 16 can be extended and retracted to adjust the flow rate of the coolant flowing out of the first outlet 12. The control module adjusts the voltage and current at both ends of the thermoelectric cooler 2 according to the difference between the measured temperature of the thermostatic object 5 and the target temperature. The temperature of the thermostatic object 5 is controlled by adjusting the flow rate of the coolant at the first outlet 12 and the current and voltage input to the thermoelectric cooler 2 until the thermostatic object 5 reaches the set target temperature.

[0052] Specifically, when the monitored temperature of the thermostatic object 5 is lower than the target temperature, it needs to be heated, and the control module controls the stepper motor 15 to reduce the opening and closing degree of the first outlet 12, reducing the flow rate of the coolant flowing out of the first outlet 12, that is, reducing the heat dissipation capacity of the first liquid cold plate 3 to the hot end of the thermoelectric cooler 2. Then, according to the difference from the target temperature, the voltage and current at both ends of the thermoelectric cooler 2 are adjusted to reduce the cooling capacity of the thermoelectric cooler 2, so that the thermostatic object 5 is heated.

[0053] When the monitored temperature of the thermostatic object 5 is higher than the target temperature, it is necessary to increase the cooling. The control module controls the stepper motor 15 to increase the opening and closing degree of the first outlet 12, increase the flow rate of the coolant flowing out of the first outlet 12, and accelerate the heat dissipation of the hot end of the thermoelectric cooler 2 by the first liquid cold plate 3. Then, according to the difference from the target temperature, the voltage and current at both ends of the thermoelectric cooler 2 are adjusted to improve the cooling capacity of the thermoelectric cooler 2 and cool down the thermostatic object 5. The input current and voltage of the thermoelectric cooler 2 are adjusted according to the temperature reduction range.

[0054] Step 4: The coolant flowing out of the second outlet 13 of the solenoid valve flows through the second liquid cooling plate 4 to cool down the high heat consumption component 6. It should be noted that it is only necessary to control the coolant flow rate entering the first liquid cooling plate 3 from the first outlet 12, and the coolant flowing into the second liquid cooling plate 4 from the second outlet 13 is sufficient to meet the heat dissipation requirements of the high heat consumption component 6.

[0055] The present invention rationally utilizes the aircraft liquid cooling resources and proposes a controllable liquid cooling flow distribution system. According to the temperature change of the coolant supplied on board, the constant temperature control of the constant temperature object 5 inside the airborne optoelectronic product and the liquid cooling heat dissipation of the high heat consumption device 6 are realized, thereby ensuring the normal operation of the airborne optoelectronic product.

[0056] Although the embodiments of the present invention have been shown and described above, it is to be understood that the above embodiments are exemplary and are not to be construed as limitations on the present invention. A person skilled in the art may change, modify, replace and modify the above embodiments within the scope of the present invention without departing from the principles and intent of the present invention.

Claims

1. A constant temperature liquid cooling system for airborne products, comprising a coolant circulation module, wherein the coolant circulation module is a coolant circulation system of the aircraft itself, and is used to provide coolant; characterized in that: It also includes a solenoid valve, a thermoelectric cooler, a first liquid cooling plate, a second liquid cooling plate, a control module and a temperature acquisition module; The solenoid valve is a three-way solenoid valve, the inlet of the solenoid valve is connected to the coolant, the first outlet of the solenoid valve is connected to the inlet of the first liquid cooling plate through a pipeline, and the outlet of the first liquid cooling plate is connected to the coolant circulation module through a pipeline; the second outlet of the solenoid valve is connected to the inlet of the second liquid cooling plate through a pipeline, and the outlet of the second liquid cooling plate is connected to the coolant circulation module through a pipeline; the first liquid cooling plate is installed at the hot end of the thermoelectric cooler, and is used to dissipate heat from the hot end of the thermoelectric cooler; the cold end of the thermoelectric cooler is connected to a constant temperature object, and the thermoelectric cooler is used to control the temperature of the constant temperature object; the second liquid cooling plate is installed on a high heat consumption device, and is used to dissipate heat from the high heat consumption device; The temperature acquisition module is used to collect the temperature of the coolant, the temperature of the constant temperature object and the temperature of the high heat consumption device, and feed the collected data back to the control module; The control module is electrically connected to the electromagnetic valve and the thermoelectric cooler, and is used to control the opening and closing degree of the first outlet of the electromagnetic valve and the input current and voltage of the thermoelectric cooler.

2. The constant temperature liquid cooling system for airborne products according to claim 1, characterized in that: The temperature acquisition module includes a first temperature sensor, a second temperature sensor and a third temperature sensor; the first temperature sensor is installed at the inlet of the solenoid valve to monitor the temperature of the coolant entering the solenoid valve; the second temperature sensor is installed on the constant temperature object to be regulated to monitor the temperature of the constant temperature object; the third temperature sensor is installed on the high heat consumption device to monitor the temperature of the high heat consumption device; the three temperature sensors are electrically connected to the control module respectively, and transmit the monitored temperature to the control module for processing in real time.

3. The constant temperature liquid cooling system for airborne products according to claim 1, characterized in that: The constant temperature liquid cooling system also includes a three-way joint, a first inlet of the three-way joint is connected to the outlet of the first liquid cooling plate through a pipeline; a second inlet of the three-way joint is connected to the outlet of the second liquid cooling plate through a pipeline; and the outlet of the three-way joint is connected to the coolant circulation module through a pipeline.

4. The constant temperature liquid cooling system for airborne products according to claim 1, characterized in that: The control module sets a target temperature for the constant temperature object. After comparing the temperature data transmitted by the temperature acquisition module with the target temperature, the control module automatically adjusts the flow rate of the first outlet of the solenoid valve and the voltage and current of the thermoelectric cooler.

5. The constant temperature liquid cooling system for airborne products according to claim 1, characterized in that: The thermoelectric cooler is installed on the constant temperature object through a structural gasket, and the structural gasket is fixed above the constant temperature object. A through recessed portion is provided in the center of the structural gasket, and the shape of the recessed portion is consistent with the shape of the thermoelectric cooler; the thermoelectric cooler is embedded in the recessed portion, and its cold end contacts the constant temperature object for cooling the constant temperature object, and its hot end contacts the first liquid cooling plate, and the heat of the hot end is taken away by the coolant flowing through the first liquid cooling plate.

6. The constant temperature liquid cooling system for airborne products according to claim 1, characterized in that: The solenoid valve includes a valve seat and a stepper motor integrated in the valve seat; the valve seat is provided with an inlet, a first outlet and a second outlet that are interconnected; the stepper motor has a retractable motor rod, which is located inside the valve seat. The stepper motor drives the motor rod to retract to adjust the opening and closing degree of the first outlet, thereby adjusting the flow of coolant entering the first liquid cooling plate; the stepper motor is electrically connected to the control module and receives control instructions from the control module.

7. The constant temperature liquid cooling system for airborne products according to claim 6, characterized in that: The solenoid valve is equipped with a regulating valve controller, which is installed in the control module and electrically connected to the control module; the stepper motor is electrically connected to the regulating valve controller and receives the working instructions of the control module through the regulating valve controller.

8. A method for constant temperature liquid cooling of an airborne product using the constant temperature liquid cooling system of claim 7, characterized in that: Here are the steps: Step 1: Set the target temperature of the constant temperature object in the control module; Step 2: The aircraft control system starts the coolant circulation module, and the temperature acquisition module collects the coolant temperature, the temperature of the constant temperature object and the temperature of the high heat consumption device in real time, and feeds the collected information back to the control module. The control module determines whether the constant temperature object needs to be heated or cooled according to the target temperature requirement; Step 3, the control module sends a control signal to the solenoid valve and the thermoelectric cooler at the same time according to the determination result of step 2; the control module controls the stepper motor to move, so that the motor rod is extended and retracted to adjust the flow rate of the coolant flowing out of the first outlet; the control module adjusts the voltage and current at both ends of the thermoelectric cooler according to the difference between the actual temperature of the constant temperature object and the target temperature; until the constant temperature object reaches the set target temperature; Step 4: The coolant flowing out of the second outlet of the solenoid valve flows through the second liquid cooling plate to cool down the high heat consumption components.

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