A thermal vacuum test system and test method for a temperature control pump of a spacecraft

Abstract

The present invention provides a thermal vacuum test system and a test method for a spacecraft temperature control pump. The test system includes a thermal vacuum chamber, a temperature control component, a control box, a computer, and a heating sheet power supply device. Inside the thermal vacuum chamber, a first heating cage and a second heating cage are placed. The temperature control pump assembly is placed in the first heating cage, and the temperature control component is placed in the second heating cage. The temperature control pump assembly and the temperature control component are connected into a loop through a medium inlet pipe and a medium outlet pipe. The control box, the computer, and the heating sheet power supply device are placed outside the thermal vacuum chamber and are connected to the temperature control pump assembly and the temperature control component inside the thermal vacuum chamber through a number of cables. The present invention solves the problems that the conventional thermal vacuum test system cannot fully simulate the space usage conditions and cannot achieve rapid and effective temperature rise and fall under vacuum conditions.

Description

Technical Field

[0001] The present invention belongs to the technical field of thermal control fluid loop systems, and particularly relates to a thermal vacuum test system and method for a temperature control pump of a spacecraft. Background Art

[0002] The temperature control pump of a spacecraft (hereinafter referred to as the temperature control pump) is a core component in the thermal control fluid loop of a spacecraft. Its function is to drive the cooling medium in the system to circulate in the pipeline, thereby playing a role in controlling the temperature and dissipating heat of the spacecraft. The temperature control pump works in a vacuum environment in space, and is accompanied by frequent high and low temperature (-25°C to 65°C) cycles. Therefore, during the early development process of the temperature control pump, it is necessary to conduct sufficient and realistic thermal vacuum environment tests on the ground to avoid problems such as structural fatigue, interface leakage, and component failure of the temperature control pump in space due to the vacuum and high and low temperature cycle environmental conditions after it is launched into orbit.

[0003] Currently, the existing ground test systems and methods for temperature control pumps place the temperature control pump inside a vacuum chamber and the auxiliary devices outside the vacuum chamber. Such test systems and methods cannot achieve effective temperature rise and fall within the specified time, and cannot guarantee the required rate of temperature rise and fall. The main reason is that the temperature control pump and the controller are of an integrated structure, and the temperature control point of the temperature control pump is located on the surface of the controller. The temperature control pump continuously generates heat during operation, and the heat capacity of the working medium in the entire test system is very large, resulting in the inability of the temperature control pump to form temperature rise and fall on the basis of the interference of the internal heat capacity of the system without convective heat transfer during the thermal vacuum test. At the same time, the working medium circulates outside the vacuum chamber and then circulates back into the temperature control pump. Only the temperature control pump experiences the vacuum environment, and the medium does not follow the environment for temperature rise and fall, and cannot effectively simulate the actual working state of the temperature control pump in space. Summary of the Invention

[0004] The problem to be solved by the present invention is: The present invention provides a thermal vacuum test system and test method for a temperature control pump of a spacecraft, which solves the problems that the conventional thermal vacuum test system cannot fully simulate the space usage conditions and cannot achieve rapid and effective temperature rise and fall under vacuum conditions.

[0005] The technical solution adopted by the present invention is: A thermal vacuum test system for a temperature control pump of a spacecraft includes a thermal vacuum chamber, a temperature control component, a control box, a computer, and a heating sheet power supply device; inside the thermal vacuum chamber, a first heating cage and a second heating cage are placed. The temperature control pump assembly is placed in the first heating cage, and the temperature control component is placed in the second heating cage. The temperature control pump assembly and the temperature control component are connected into a loop through a medium inlet pipe and a medium outlet pipe; the control box, the computer, and the heating sheet power supply device are placed outside the thermal vacuum chamber and are connected to the temperature control pump assembly and the temperature control component inside the thermal vacuum chamber through a plurality of cables.

[0006] Further, the temperature control component includes: a heat exchange plate, a first insulating heat conducting pad, a heat conducting plate, a second insulating heat conducting pad, a liquid nitrogen cold plate, and a liquid nitrogen metal hose; the heat exchange plate is respectively connected to the medium inlet pipe and the medium outlet pipe, forms a medium loop with the temperature control pump component, and is installed on the first insulating heat conducting pad; the first insulating heat conducting pad is installed on the heat conducting plate, and the heat conducting plate is installed on the second insulating heat conducting pad; the second insulating heat conducting pad is installed on the liquid nitrogen cold plate, and the liquid nitrogen cold plate is respectively connected to the liquid nitrogen metal hose, and external liquid nitrogen enters the liquid nitrogen cold plate through the liquid nitrogen metal hose.

[0007] Further, a plurality of grooves and wire grooves are provided on one side of the heat conducting plate in contact with the second insulating heat conducting pad, a plurality of heating sheets are pasted in the grooves, the heating sheet wires are connected to each heating sheet, and the heating sheet wires pass through the wire grooves and are connected to the heating sheet power supply device outside the thermal vacuum chamber.

[0008] Further, the temperature control pump component includes:

[0009] The pump controller, the temperature control pump, the filter, the filter bracket, the regulating valve, the pressure sensor at the pump outlet, the temperature control pump inlet pipe, and the temperature control pump outlet pipe are all in parallel with three units as backups for each other; the pump controller and the temperature control pump are of an integrated structure, and the pump controller is fixed on the tooling base plate; the filter bracket is fixed to the tooling base plate; the filter is fixed to the filter bracket by a clamp, one end is connected to one end of the pump inlet pipe, and the other end is connected to one of the branches of the inlet main pipe through a pipeline; one end of the pump inlet pipe is connected to the inlet of the temperature control pump, and one end is connected to the outlet of the filter; one end of the regulating valve is connected to the pump outlet pipe, and one end is connected to one of the branches of the outlet main pipe; one end of the pump outlet pipe is connected to the outlet of the temperature control pump, and one end is connected to the regulating valve; the pressure sensor at the pump outlet is installed on the pump outlet pipe for monitoring the pressure at the pump outlet; the three branches of the inlet main pipe are respectively connected to the inlet end of the filter, and the main path is connected to one port of the four-way valve; the three branches of the outlet main pipe are respectively connected to the regulating valve, and the main path is connected to the medium outlet pipe; the pressure compensator bracket is fixed to the tooling base plate; the pressure compensator is fixed to the pressure compensator bracket by a clamp and is connected to one port of the four-way valve through a pipeline; the addition and drainage service valve is connected to one port of the four-way valve through a pipeline; the medium inlet pipe is connected to one end of the four-way valve.

[0010] According to the above test method for the thermal vacuum test system of the spacecraft temperature control pump, it includes:

[0011] The temperature control pump assembly and the heat exchange plate form a closed loop through the medium inlet pipe and the medium outlet pipe; before the test, at room temperature, the inlet main pipe pressure sensor, the pump outlet pressure sensor, and the outlet main pipe pressure sensor are powered by the control box and the computer to display the pressure value in the loop; the entire closed loop is evacuated through the addition and evacuation service valve, and the closed loop is filled with the medium through the addition and evacuation service valve until the filling is stopped when the pressure in the loop cavity rises to the set value;

[0012] Through the control box and the computer, the pump controller and the temperature control pump in the temperature control pump assembly are powered to drive the pump controller and the temperature control pump to work, so that the medium in the closed loop circulates; the medium passes through the inlet main pipe, and the inlet main pipe pressure sensor monitors the pressure in the inlet main pipe. The medium passes through three branches of the inlet main pipe, and the medium is filtered through three filters respectively, and then enters three temperature control pumps respectively. The pump outlet pressure sensor monitors the outlet pressure of each temperature control pump. The medium passes through the regulating valve, and the medium flow rate of each branch is changed by the opening degree of the regulating valve. The medium passes through three branches of the outlet main pipe and converges to the main path. The outlet main pipe pressure sensor is used to monitor the pressure of the outlet main pipe;

[0013] The medium flows through the medium outlet pipe to the heat exchange plate, and heat exchange occurs in the heat exchange plate, and then flows into the four-way valve in the temperature control pump assembly through the medium inlet pipe to form a cycle.

[0014] Furthermore, the test method further includes:

[0015] Control the temperature in the thermal vacuum chamber to make the internal temperature cycle between -25°C and 65°C;

[0016] When the temperature decreases, the medium in the closed loop contracts due to cooling, resulting in a pressure drop. At this time, the medium in the pressure compensator passes through the four-way valve to compensate the pressure of the closed loop, so that the internal pressure of the system remains relatively balanced; conversely, when the temperature increases, the medium in the closed loop expands due to heating, resulting in a pressure increase. At this time, the medium in the closed loop flows through the four-way valve to the pressure compensator, so that the internal pressure of the system remains relatively balanced.

[0017] Furthermore, the test method further includes:

[0018] The temperature of the medium is controlled by a temperature control component. When it is necessary to increase the temperature of the medium, the heating sheet power supply device is powered on, and the heating sheet attached to the heat conduction plate starts to work. The temperature of the heat conduction plate rises, and the heat is transferred to the heat exchange plate through the first insulating heat conduction pad. The medium in the heat exchange plate realizes heat exchange through heat conduction;

[0019] When it is necessary to reduce the temperature of the medium, the heating sheet power supply device is de-energized, and external liquid nitrogen is introduced into the liquid nitrogen cold plate through the liquid nitrogen metal hose. The temperature of the liquid nitrogen cold plate drops rapidly, and the low temperature is transferred to the heat conduction plate through the second insulating heat conduction pad, and then transferred to the heat exchange plate through the first insulating heat conduction pad. The medium in the heat exchange plate realizes heat exchange through heat conduction.

[0020] The advantages of the present invention compared with the prior art are as follows:

[0021] (1) The present invention changes the external circulation mode of the traditional test system to an integrated in-tank circulation mode. In this way, the working medium can undergo vacuum and high and low temperature environment tests, which is closer to the actual use environment.

[0022] (2) The present invention utilizes components such as a heat exchange plate, a pressure compensator, a heat conduction plate, a heating sheet, and a temperature sensor. The heat exchanger can increase the heat exchange efficiency of the working medium in the thermal vacuum environment and solve the problem that the working medium cannot effectively increase or decrease the temperature in the vacuum environment. The pressure compensator is used to compensate for the volume change caused by the high and low temperatures of the working medium, thereby ensuring the stability of the test system pressure and enabling continuous and reliable operation.

[0023] (3) The present invention adopts a zoning temperature control mode, that is, the temperature control pump and the working medium are controlled separately, so that the working medium does not interfere with the temperature of the temperature control pump itself and can play an auxiliary role in increasing or decreasing the temperature of the temperature control pump.

[0024] (4) The present invention adopts an intelligent temperature acquisition and control system, which can collect the temperatures of the temperature control points in the system in real time and feedback and adjust to ensure the heat balance of the system during the high and low temperature stable stages of the temperature control pump.

[0025] (5) All components of the system of the present invention are integrated on the bottom plate and all are placed in the thermal vacuum chamber, so that the test working medium can rise and fall in temperature with the environment together. The temperature increase and decrease of the medium can be used to assist the temperature control pump in increasing or decreasing the temperature, enabling the temperature control pump to fully meet the requirements of the test temperature increase and decrease rate. Such a test system can fully simulate the on-orbit working state of the temperature control pump. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] Figure 1 It is a schematic diagram of the overall structure of the thermal vacuum system provided by the present invention.

[0027] Figure 2 It is a schematic diagram of the structure of the temperature control pump assembly provided by the present invention.

[0028] Figure 3 It is a schematic diagram of the structure of the temperature control component provided by the present invention.

[0029] Figure 4 It is a schematic diagram of the structure of the heat transfer plate provided by the present invention. DETAILED DESCRIPTION OF THE INVENTION

[0030] The present invention will be further described in detail below with reference to the accompanying drawings:

[0031] The present invention provides a thermal vacuum test system and a test method for a spacecraft temperature control pump. The system adopts a zone temperature control technology, a heat conduction and radiation heat exchange method, and combines a pressure compensation device, an intelligent acquisition and control system, which can solve the problem of the influence of the heat capacity of the working medium on the heating and cooling rates of the temperature control pump, achieve the requirements of the heating and cooling rates for both the temperature control pump and the working medium, meet the test requirements of temperature stability, and can fully simulate the actual working state of the temperature control pump in orbit.

[0032] As Figure 1 , a thermal vacuum test system for a spacecraft temperature control pump mainly includes a thermal vacuum chamber 1, a temperature control pump assembly 2, a temperature control assembly 3, a control box 5, a computer 6, a heating sheet power supply device 7, etc. Inside the thermal vacuum chamber 1, a first heating cage 8 and a second heating cage 9 are placed. Among them, the temperature control pump assembly 2 is placed in the first heating cage 8, and the temperature control assembly 3 is placed in the second heating cage 9. The temperature control pump assembly 2 and the temperature control assembly 3 are connected into a loop through a medium inlet pipe 41 and a medium outlet pipe 42, and the flow direction of the medium is as shown by the arrow on the metal hose. The control box 5, the computer 6, and the heating sheet power supply device 7 are placed outside the thermal vacuum chamber 1 and are connected to the temperature control pump assembly 2 and the temperature control assembly 3 inside the thermal vacuum chamber 1 through several cables.

[0033] As Figure 2It is a schematic structural diagram of a temperature-controlled pump assembly. Taking the tooling base plate 21 as the base body, there are several threaded holes on the tooling base plate 21; the pump controller 26, the temperature-controlled pump 27, the filter 23, the filter bracket 231, the regulating valve 24, the pressure sensor 252 at the pump outlet, the temperature-controlled pump inlet pipe 271, and the temperature-controlled pump outlet pipe 272 are all in parallel in three units and backup each other; the pump controller 26 and the temperature-controlled pump 27 are of an integrated structure, and the pump controller 26 is fixed to the tooling base plate 21 by means of bolt connection; the filter bracket 231 is fixed to the tooling base plate by bolts, and the filter 23 is fixed to the filter bracket 231 by a clamp, with one end connected to one end of the pump inlet pipe 271 and the other end connected to one of the branches of the inlet main pipe 291 through a pipeline; one end of the pump inlet pipe 271 is connected to the inlet of the temperature-controlled pump 27 and the other end is connected to the outlet of the filter 23; one end of the regulating valve 24 is connected to the pump outlet pipe 272 and the other end is connected to one of the branches of the outlet main pipe 292 through a pipeline; one end of the pump outlet pipe 272 is connected to the outlet of the temperature-controlled pump 27 and the other end is connected to the regulating valve 24; the pressure sensor 252 at the pump outlet is installed on the pump outlet pipe 272 to monitor the pressure at the pump outlet; the three branches of the inlet main pipe 291 are respectively connected to the inlet end of the filter 23 through pipelines, and the main path is connected to one port of the four-way valve 281; the three branches of the outlet main pipe 292 are respectively connected to the regulating valve 24 through pipelines, and the main path is connected to the medium outlet metal hose 42; the pressure compensator bracket 221 is fixed to the tooling base plate 21 by means of bolt connection, and the pressure compensator 22 is fixed to the pressure compensator bracket 221 by a clamp and is connected to one port of the four-way valve 281 through a pipeline; the addition and discharge service valve 282 is connected to one port of the four-way valve 281 through a pipeline; the medium inlet pipe 41 is connected to one end of the four-way valve 281.

[0034] As Figure 3 It is a schematic structural diagram of a temperature control assembly. The heat exchange plate 31 is connected to the medium inlet pipe 41 and the medium outlet pipe 42, forms a medium loop with the temperature-controlled pump assembly 2, and is placed flat on the first insulating heat-conducting pad 32; below the first insulating heat-conducting pad 32 is the heat-conducting plate 33, and the heat-conducting plate 33 is placed flat on the second insulating heat-conducting pad 34; below the second insulating heat-conducting pad 34 is the liquid nitrogen cold plate 35, and the liquid nitrogen cold plate 35 is connected to the liquid nitrogen metal hose 36, and external liquid nitrogen can enter the liquid nitrogen cold plate 35 through the liquid nitrogen metal hose 36.

[0035] As Figure 4 It is a schematic structural diagram of the heat-conducting plate 33. On the side of the heat-conducting plate 33 in contact with the second insulating heat-conducting pad 34, several grooves 331 and wire grooves 332 are opened. Several heating sheets 333 are pasted in the grooves 331. The heating sheet wires 334 connect the heating sheets 333. The heating sheet wires 334 pass through the wire grooves 332 and are connected to the heating sheet power supply device 7 outside the thermal vacuum chamber 1.

[0036] Working principle:

[0037] The temperature control pump assembly 2 and the heat exchange plate 31 form a closed loop through the medium inlet pipe 41 and the medium outlet pipe 42. Before the test, at room temperature, the inlet main pipe pressure sensor 251, the pump outlet pressure sensor 252, and the outlet main pipe pressure sensor 253 are powered by the control box 5 and the computer 6 outside the thermal vacuum chamber 1 to display the pressure values in the loop. Then, the entire closed loop is evacuated through the addition and evacuation service valve 282, and the closed loop is filled with the medium through the addition and evacuation service valve 282 until the internal pressure of the loop rises to about 0.15 MPa and the filling stops.

[0038] The pump controller 26 and the temperature control pump 27 in the temperature control pump assembly 2 are powered by the control box 5 and the computer 6 outside the thermal vacuum chamber 1 to drive them to work, and the medium in the closed loop circulates. The medium passes through the inlet main pipe 291, and the inlet main pipe pressure sensor 251 can monitor the pressure therein. Then, the medium passes through the three branches of the inlet main pipe 251, and the medium is filtered by the three filters 23 respectively, and then enters the three temperature control pumps 27 respectively. The pump outlet pressure sensor 252 can monitor the outlet pressure of each of the 3 temperature control pumps 27. The medium passes through the regulating valve 24, and the opening degree of the regulating valve 24 can change the medium flow rate of each branch. Then, the medium converges to the main path through the three branches of the outlet main pipe 292. The pressure sensor 251 is used to monitor the pressure in the inlet main pipe 291, and the outlet main pipe pressure sensor 253 is used to monitor its pressure. The medium flows to the heat exchange plate 31 through the medium outlet pipe 42, and heat exchange occurs in the heat exchange plate 31, and then flows into the four-way valve 281 in the temperature control pump assembly 2 through the medium inlet metal hose 41 to form a cycle.

[0039] The temperature inside the thermal vacuum chamber 1 is controlled so that the internal temperature cycles between -25°C and 65°C. When the temperature decreases, the medium in the closed loop will contract due to cooling, resulting in a pressure drop. At this time, the medium in the pressure compensator 22 compensates the pressure of the closed loop through the four-way valve 281 to keep the internal pressure of the system relatively balanced; conversely, when the temperature increases, the medium in the closed loop will expand due to heating, resulting in a pressure increase. At this time, the medium in the closed loop will flow to the pressure compensator 22 through the four-way valve 281 to keep the internal pressure of the system relatively balanced.

[0040] The temperature control component 3 can also control the temperature of the medium. When it is necessary to increase the temperature of the medium, the heating sheet power supply device 7 is energized, and the heating sheet 333 attached to the heat conduction plate 33 starts to work. The temperature of the heat conduction plate 33 rises, and the heat is transferred to the heat exchange plate 31 through the first insulating heat conduction pad 32. The medium in the heat exchange plate 31 realizes heat exchange through heat conduction; when it is necessary to decrease the temperature of the medium, the heating sheet power supply device 7 is de-energized, and external liquid nitrogen is introduced into the liquid nitrogen cold plate 35 through the liquid nitrogen metal hose 36. The temperature of the liquid nitrogen cold plate 35 drops rapidly, and the low temperature is transferred to the heat conduction plate 33 through the second insulating heat conduction pad 34, and then transferred to the heat exchange plate 31 through the first insulating heat conduction pad 32. The medium in the heat exchange plate 31 realizes heat exchange through heat conduction.

[0041] Among them, a plurality of grooves 331 are formed in the heat conduction plate 33. On the one hand, it is for arranging the heating sheet 333, and on the other hand, it is to prevent the contact area between the heat conduction plate 33 and the second insulating heat conduction pad 34 from being too large, so that the temperature drops too fast when liquid nitrogen is passed.

[0042] The content not described in detail in the specification of the present invention belongs to the well-known technology of those skilled in the art.

Claims

1. A thermal vacuum test system for a spacecraft temperature control pump, characterized in that, It includes a thermal vacuum chamber (1), a temperature control component (3), a control box (5), a computer (6), and a heating sheet power supply device (7); inside the thermal vacuum chamber (1), a first heating cage (8) and a second heating cage (9) are placed. The temperature control pump component (2) is placed in the first heating cage (8), and the temperature control component (3) is placed in the second heating cage (9). The temperature control pump component (2) and the temperature control component (3) are connected into a loop through a medium inlet pipe (41) and a medium outlet pipe (42); the control box (5), the computer (6), and the heating sheet power supply device (7) are placed outside the thermal vacuum chamber (1) and are connected to the temperature control pump component (2) and the temperature control component (3) inside the thermal vacuum chamber (1) through several cables. The temperature control pump component (2) includes: a pump controller (26), a temperature control pump (27), a filter (23), a filter bracket (231), a regulating valve (24), a pressure sensor (252) at the pump outlet, a pump inlet pipe (271), and a pump outlet pipe (272), all of which are in parallel in three units and serve as backups for each other; the pump controller (26) and the temperature control pump (27) are of an integrated structure, and the pump controller (26) is fixed on a tooling bottom plate (21); the filter bracket (231) is fixed to the tooling bottom plate; the filter (23) is fixed to the filter bracket (231) by a clamp, with one end connected to one end of the pump inlet pipe (271) and the other end connected to one branch of the inlet main pipe (291) through a pipeline; one end of the pump inlet pipe (271) is connected to the inlet of the temperature control pump (27) and the other end is connected to the outlet of the filter (23); one end of the regulating valve (24) is connected to the pump outlet pipe (272) and the other end is connected to one branch of the outlet main pipe (292); one end of the pump outlet pipe (272) is connected to the outlet of the temperature control pump (27) and the other end is connected to the regulating valve (24); the pressure sensor (252) at the pump outlet is installed on the pump outlet pipe (272) for monitoring the pressure at the pump outlet; the three branches of the inlet main pipe (291) are respectively connected to the inlet ends of the filters (23), and the main path is connected to one port of a four-way valve (281); the three branches of the outlet main pipe (292) are respectively connected to the regulating valves (24), and the main path is connected to the medium outlet pipe (42); a pressure compensator bracket (221) is fixed to the tooling bottom plate (21); a pressure compensator (22) is fixed to the pressure compensator bracket (221) by a clamp and is connected to one port of the four-way valve (281) through a pipeline; a charging and discharging service valve (282) is connected to one port of the four-way valve (281) through a pipeline; the medium inlet pipe (41) is connected to one end of the four-way valve (281).

2. The thermal vacuum test system for a spacecraft temperature control pump according to claim 1, characterized in that The temperature control component (3) includes: a heat exchange plate (31), a first insulating heat-conducting pad (32), a heat-conducting plate (33), a second insulating heat-conducting pad (34), a liquid nitrogen cold plate (35), and a liquid nitrogen metal hose (36); the heat exchange plate (31) is respectively connected to the medium inlet pipe (41) and the medium outlet pipe (42), forms a medium loop with the temperature control pump component (2), and is installed on the first insulating heat-conducting pad (32); the first insulating heat-conducting pad (32) is installed on the heat-conducting plate (33), and the heat-conducting plate (33) is installed on the second insulating heat-conducting pad (34); the second insulating heat-conducting pad (34) is installed on the liquid nitrogen cold plate (35), and the liquid nitrogen cold plate (35) is respectively connected to the liquid nitrogen metal hose (36), and external liquid nitrogen enters the liquid nitrogen cold plate (35) through the liquid nitrogen metal hose (36).

3. The thermal vacuum test system for a spacecraft temperature control pump according to claim 2, characterized in that, On one side of the heat-conducting plate (33) in contact with the second insulating heat-conducting pad (34), a plurality of grooves (331) and wire grooves (332) are provided. A plurality of heating sheets (333) are pasted in the grooves (331). Heating sheet wires (334) connect the heating sheets (333). The heating sheet wires (334) pass through the wire grooves (332) and are connected to the heating sheet power supply device (7) outside the thermal vacuum chamber (1).

4. The test method of a thermal vacuum test system for a spacecraft temperature control pump according to claim 3, characterized in that, including: The temperature control pump component (2) and the heat exchange plate (31) form a closed loop through the medium inlet pipe (41) and the medium outlet pipe (42); Before the test, at room temperature, the inlet main pipe pressure sensor (251), the pump outlet pressure sensor (252), and the outlet main pipe pressure sensor (253) are powered by the control box (5) and the computer (6) to display the pressure values in the loop; the entire closed loop is evacuated through the addition and evacuation service valve (282), and the closed loop is filled with the medium through the addition and evacuation service valve (282) until the pressure in the loop cavity rises to the set value and then the filling stops; The pump controller (26) and the temperature control pump (27) in the temperature control pump component (2) are powered by the control box (5) and the computer (6) to drive the pump controller (26) and the temperature control pump (27) to work, so that the medium in the closed loop circulates; the medium passes through the inlet main pipe (291), and the inlet main pipe pressure sensor (251) monitors the pressure in the inlet main pipe (291). The medium passes through three branches of the inlet main pipe (291), and the medium is filtered by three filters (23) respectively and then enters three temperature control pumps (27) respectively. The pump outlet pressure sensor (252) monitors the outlet pressure of each of the three temperature control pumps (27). The medium passes through the regulating valve (24), and the opening degree of the regulating valve (24) changes the medium flow rate of each branch. The medium passes through three branches of the outlet main pipe (292) and converges to the main path. The outlet main pipe pressure sensor (253) is used to monitor the pressure of the outlet main pipe (292); The medium flows into the heat exchange plate (31) through the medium outlet pipe (42), heat exchange occurs in the heat exchange plate (31), and then flows into the four-way valve (281) in the temperature control pump component (2) through the medium inlet pipe (41) to form a cycle.

5. The test method according to claim 4, wherein It also includes: Control the temperature inside the thermal vacuum chamber (1) so that the internal temperature cycles between -25°C and 65°C; When the temperature decreases, the medium in the closed loop contracts due to cold, resulting in a pressure drop. At this time, the medium in the pressure compensator (22) passes through the four-way valve (281) to compensate the pressure of the closed loop, so that the internal pressure of the system remains relatively balanced. Conversely, when the temperature increases, the medium in the closed loop expands due to heat, resulting in a pressure increase. At this time, the medium in the closed loop flows through the four-way valve (281) into the pressure compensator (22), so that the internal pressure of the system remains relatively balanced.

6. The test method according to claim 5, characterized in that It also includes: Use a temperature control component (3) to control the temperature of the medium. When it is necessary to increase the temperature of the medium, the heating sheet power supply device (7) is energized, and the heating sheet (333) attached to the heat conduction plate (33) starts to work. The temperature of the heat conduction plate (33) increases, and the heat is transferred to the heat exchange plate (31) through the first insulating heat conduction pad (32). The medium in the heat exchange plate (31) realizes heat exchange through heat conduction; When it is necessary to decrease the temperature of the medium, the heating sheet power supply device (7) is de-energized, and external liquid nitrogen is introduced into the liquid nitrogen cold plate (35) through the liquid nitrogen metal hose (36). The temperature of the liquid nitrogen cold plate (35) decreases rapidly, and the low temperature is transferred to the heat conduction plate (33) through the second insulating heat conduction pad (34), and then transferred to the heat exchange plate (31) through the first insulating heat conduction pad (32). The medium in the heat exchange plate (31) realizes heat exchange through heat conduction.

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