Thermal control device for satellite load vacuum thermal balance test

Abstract

The invention relates to the technical field of satellite load thermal balance tests, in particular to a thermal control device for a satellite load vacuum thermal balance test. The heat isolation cabin is mounted above the supporting assembly; the heat dissipation assembly comprises a heat dissipation plate arranged on one side plate of the heat isolation cabin, a first heat rapid transfer assembly connected with the heat dissipation plate and the heat isolation cabin, and a first heater arranged on the heat dissipation plate; the heat compensation assembly comprises a second heat rapid transfer assembly and a second heater arranged on the side plate, away from the heat dissipation plate, of the heat isolation cabin; and a program-controlled temperature acquisition system. The device provided by the invention can simulate all working conditions of a satellite load in an in-orbit space environment, can realize conversion of different working conditions without opening the tank, reduces air pumping and deflation of the vacuum tank, saves the satellite load heat balance test time, does not need frequent disassembly and assembly in the test process, and improves the test efficiency. And the risk caused by frequent disassembly and assembly to the satellite load is reduced.

Description

Technical Field

[0001] The invention relates to the technical field of satellite payload thermal balance test, and in particular to a satellite payload vacuum thermal balance test thermal control device. Background Art

[0002] During the satellite product development process, after the satellite payload is manufactured, a series of environmental tests will be conducted on the payload to verify whether the payload development meets the design requirements, reliability requirements and safety requirements. Among them, the vacuum thermal balance test is a test that simulates the thermal change environment of the satellite payload in the space environment to verify the thermal regulation performance and function of the satellite payload in various space thermal environments.

[0003] The satellite payload thermal control device is a device that simulates the satellite payload receiving various space heat flow conditions in the space environment, simulating the net dissipation and net input heat of the satellite payload in the space thermal environment according to the actual on-orbit operation state. Generally, the entire satellite payload, thermal control device and supporting components are placed in a vacuum tank to simulate the space vacuum environment. The vacuum tank is a vacuum environment, and a low-temperature heat sink is provided to simulate the space cold background. Then the thermal control device simulates different net dissipation and net input heat conditions.

[0004] The satellite payload thermal control device in the existing technology cannot cover all operating conditions of the satellite payload. It is necessary to frequently open and close the vacuum tank during the vacuum thermal balance test to adjust the heat simulation changes in the space environment. The working efficiency inside the tank is low, which consumes a lot of time and money, and also poses operational risks. Summary of the invention

[0005] The purpose of the present invention is to solve the shortcomings of the prior art and provide a satellite payload vacuum thermal balance test thermal control device, comprising: A support assembly, wherein the support assembly is integrally mounted and fixed in the vacuum tank; A thermal isolation cabin installed above the support assembly, the thermal isolation cabin comprising four side panels arranged in a matrix pattern; A heat dissipation component, comprising a heat dissipation plate disposed on one of the side panels of the heat isolation cabin, a first heat rapid transfer component connecting the heat dissipation plate and the heat isolation cabin, and a first heater disposed on the heat dissipation plate; The heat compensation component includes a second rapid heat transfer component and a second heater disposed on a side plate of the heat isolation chamber away from the heat sink; two ends of the second rapid heat transfer component are respectively connected to different side plates of the heat isolation chamber; A program-controlled temperature acquisition system is connected to the heat sink and the heat isolation cabin.

[0006] Further, the first heater is a polyimide film heater I; The heat sink is made of aluminum alloy plate, the front of the heat sink faces the cold air direction, and the front is sprayed with thermal control white paint to enhance the heat exchange capacity; the back of the heat sink is coated with several layers of thermal control to improve the temperature maintenance capacity of the heat sink; The polyimide film heater I is formed by a group of heaters evenly distributed on the front of the heat sink and connected in parallel; The heat dissipation component controls the net outflow of heat from the satellite payload, and the first rapid heat transfer component and the polyimide film heater I rapidly adjust the temperature of the heat sink, while simultaneously performing heat exchange between the heat sink and the thermal isolation cabin.

[0007] Furthermore, the second heater is a polyimide film heater II, and the polyimide film heater II is formed by a group of heaters evenly distributed on the heat isolation cabin and connected in parallel; The heat compensation component controls the net inflow of heat from the satellite payload, and the polyimide film heater II and the second rapid heat transfer component quickly adjust the temperature of the thermal isolation cabin, while performing heat exchange between the side panels of the thermal isolation cabin to improve the temperature uniformity of the thermal isolation cabin.

[0008] Furthermore, the first rapid heat transfer component and the second rapid heat transfer component both use gas-liquid two-phase flow micro-groove phase change heat pipes, which can quickly compensate and transfer heat in the heat isolation cabin.

[0009] Furthermore, the thermal isolation cabin is a hollow cover composed of four side panels, an opening is provided at the upper end of the thermal isolation cabin, a cavity for accommodating the satellite payload is formed in the middle of the thermal isolation cabin, and the satellite payload is thermally isolated from the surrounding environment by physical isolation; wherein, The thermal isolation cabin is composed of a number of carbon fiber panels and a thermal insulation structure. The inner sides of all side panels of the thermal isolation cabin are sprayed with thermal control black paint to improve the thermal radiation capacity of the thermal isolation cabin. The outer sides of all side panels of the thermal isolation cabin are covered with multi-layer thermal insulation components to improve the temperature maintenance capacity of the thermal isolation cabin. The thermal isolation cabin provides a structural installation interface and a thermal connection interface for the heat dissipation component and the heat compensation component.

[0010] Furthermore, the support assembly includes a support base, a transfer tool, a thermal insulation pad, and a load-bearing frame, which are used to provide an installation interface for the satellite payload, and to support the satellite payload as a whole and a thermal control device during hoisting, leveling, and transfer as well as testing; wherein, The transfer tool is installed and fixed on the support base, the load-bearing frame is installed and fixed on the transfer tool, and the thermal insulation pad is installed between the satellite payload and the load-bearing frame; The support assembly is coated with multiple layers of heat insulation components to reduce the heat exchange between the support assembly and the external environment. The heat insulation pad is made of 50mm thick fiberglass, which can increase the thermal resistance and block the heat outflow path of the satellite payload.

[0011] Furthermore, the program-controlled temperature acquisition system includes a program-controlled power supply, a temperature acquisition instrument, a thermistor I, and a thermistor II; wherein, The thermistor I is installed on the heat sink, the thermistor II is installed on the side panel of the heat isolation cabin, the programmable power supply and the temperature collector are placed outside the vacuum tank, and are connected to the thermistor I and the thermistor II through a wall socket and a cable; The program-controlled temperature acquisition system controls the switching of the polyimide film heater I and the polyimide film heater II according to the real-time temperature data of the thermistor I and the thermistor II collected by the temperature acquisition instrument, thereby adjusting the temperature of the thermal isolation cabin, thereby adjusting the heat input change of the satellite payload or maintaining a constant heat state.

[0012] Compared with the prior art, the present invention has the following beneficial effects: The invention discloses a thermal control device for a vacuum heat balance test of a satellite payload. The heat dissipation component can be used to quickly dissipate the heat of the satellite payload to simulate the net heat output environment of the satellite payload in the space environment; the heat compensation component can be used to quickly compensate the satellite payload to simulate the net heat input environment of the satellite payload in the space environment; the heat isolation cabin can be used to control the net outflow or net inflow of heat of the satellite payload in a variable or constant manner to simulate the external heat flow fluctuation of the satellite payload space environment and the actual heat flow state of the satellite payload in the space environment; the heat of the satellite payload is caused to fluctuate by rapid heat dissipation or compensation, so as to simulate the heat fluctuation caused by the change of heat flow outside the space environment. In summary, the thermal control device for a vacuum heat balance test of a satellite payload provided by the invention can simulate all the working conditions of the satellite payload in the orbital space environment, and can also realize the conversion of different working conditions without opening the tank, reduce the extraction and exhaust of the vacuum tank, save the thermal balance test time of the satellite payload, and at the same time, there is no need for frequent disassembly and assembly during the test, reducing the risk of frequent disassembly and assembly to the satellite payload. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] By reading the detailed description of the preferred embodiments below, various other advantages and benefits will become clear to those skilled in the art. The accompanying drawings are used to provide a further understanding of the present invention and constitute a part of the specification. Together with the embodiments of the present invention, they are used to explain the present invention and do not constitute a limitation of the present invention. In the accompanying drawings: Figure 1 A schematic diagram of a satellite payload vacuum thermal balance test thermal control device of the present invention Figure 1 .

[0014] Figure 2 A schematic diagram of a satellite payload vacuum thermal balance test thermal control device of the present invention Figure 2 .

[0015] Figure 3 A schematic diagram of a satellite payload vacuum thermal balance test thermal control device of the present invention Figure 3 .

[0016] Figure 4 The present invention is a schematic diagram of a support assembly of a thermal control device for a satellite payload vacuum thermal balance test.

[0017] Figure 5 The present invention is a schematic diagram of an embodiment of a thermal control device for a satellite payload vacuum thermal balance test.

[0018] Reference numerals 1. Heat dissipation components; 11. heat sink; 12. polyimide film heater I; 13. first rapid heat transfer component; 2. Heat compensation component; 21. Polyimide film heater II; 22. Second heat rapid transfer component; 3. Thermal isolation cabin; 4. Support components; 41. Support base; 42. Transfer tooling; 43. Thermal insulation pad; 44. Load-bearing frame; 5. Program-controlled temperature acquisition system; 51. Programmable power supply; 52. Temperature acquisition instrument; 53. Thermistor I; 54. Thermistor II; 6. Satellite payload. DETAILED DESCRIPTION

[0019] In order to make the purpose, technical solution and advantages of the present invention more clearly understood, the present invention is further described in detail below in conjunction with the accompanying drawings and specific implementation methods. It should be understood that the specific implementation methods described herein are only used to explain the present invention and are not used to limit the present invention.

[0020] In order to simplify the drawings, only the parts related to the present invention are schematically shown in each figure, and they do not represent the actual structure of the product. In addition, in order to simplify the drawings and facilitate understanding, in some figures, only one of the parts with the same structure or function is schematically drawn or marked. In this article, "one" not only means "only one", but also means "more than one".

[0021] First embodiment See also Figure 1-5 The technical solution of a satellite payload vacuum thermal balance test thermal control device provided in this embodiment includes the following: A satellite payload vacuum heat balance test thermal control device comprises a heat dissipation component 1, a heat sink 11, a polyimide film heater I to 12, a first heat rapid transfer component 13, a heat compensation component 2, a polyimide film heater II21, a second heat rapid transfer component 22, a heat isolation cabin 3, a support component 4, a support base 41, a transfer tooling 42, an insulation pad 43, a load-bearing frame 44, a programmable temperature acquisition system 5, a programmable power supply 51, a temperature acquisition instrument 52, a thermistor I to 53, a thermistor II to 54, and a satellite payload 6.

[0022] The heat dissipation component 1 includes a heat sink 11, a polyimide film heater 112, and a first rapid heat transfer component 13. The polyimide film heater 112 is pasted on the front of the heat sink 11, and the two ends of the first rapid heat transfer component 13 are respectively connected to the heat sink 11 and the heat isolation cabin 3.

[0023] The heat compensation component 2 includes a polyimide film heater II 21 and a second rapid heat transfer component 22. The polyimide film heater II 21 is attached to the side panel of the heat isolation chamber 3, and the two ends of the second rapid heat transfer component 22 are respectively connected to different side panels of the heat isolation chamber 3.

[0024] The thermal isolation cabin 3 is a hollow housing composed of four side panels, with an open upper end and a cavity in the middle for accommodating the satellite payload 6. The thermal isolation cabin 3 is integrally mounted on the support assembly 4. The thermal isolation cabin 3 provides a structural mounting interface and a thermal connection interface for the heat dissipation assembly 1 and the heat compensation assembly 2.

[0025] The support assembly 4 includes a support base 41, a transfer tooling 42, an insulation pad 43, and a load-bearing frame 44, which are used to provide an installation interface for the satellite payload 6, and to support the satellite payload 6 as a whole and a thermal control device during hoisting, leveling, and transfer, as well as testing.

[0026] The transfer tooling 42 is installed and fixed on the supporting base 41 , the load-bearing frame 44 is installed and fixed on the transfer tooling 42 , and the thermal insulation pad 43 is installed between the satellite payload 6 and the load-bearing frame 44 .

[0027] The program-controlled temperature acquisition system 5 includes a program-controlled power supply 51, a temperature acquisition instrument 52, a thermistor I 53, and a thermistor II 54. The thermistor I 53 is installed on the heat sink 11, and the thermistor II 54 is installed on the side panel of the heat isolation cabin 3. The program-controlled power supply 51 and the temperature acquisition instrument 52 are placed outside the vacuum tank and connected to the thermistor I 53 and the thermistor II 54 through a wall socket and a cable.

[0028] As an embodiment, the heat sink 11 is made of an aluminum alloy plate with a thickness of 10 mm, and the front side is sprayed with S781 thermal control white paint to enhance the heat exchange capacity. The back side of the heat sink 11 is coated with 25 layers of thermal control to improve the temperature maintenance capacity of the heat sink 11. The front side of the heat sink 11 is set to face the cold air, which is a cold and dark environment in space. During the vacuum thermal balance test, the cold air background is simulated by the heat sink in the vacuum tank, and the front side of the heat sink 11 faces the heat sink direction.

[0029] As an embodiment, the polyimide film heater I 12 is formed by a group of 16 heaters with a resistance of 23.7Ω~59.4Ω uniformly distributed on the heat sink 11 in parallel; the temperature of the heat sink 11 can be quickly adjusted.

[0030] As an embodiment, the first rapid heat transfer component 13 is composed of three gas-liquid two-phase flow micro-channel phase change heat pipes to achieve heat exchange between the heat sink 11 and the heat isolation cabin 3.

[0031] As an embodiment, the polyimide film heater II 21 is formed by a group of 36 heaters with a resistance of 73.5Ω~144Ω uniformly distributed on the thermal isolation chamber 3 in parallel; the temperature of the thermal isolation chamber 3 can be quickly adjusted.

[0032] As an embodiment, the second rapid heat transfer component 22 is composed of four gas-liquid two-phase flow micro-channel phase change heat pipes to achieve heat exchange between different side panels of the thermal isolation cabin 3.

[0033] As an embodiment, the thermal isolation cabin 3 is composed of four carbon fiber skin sandwiched with aluminum honeycomb core composite panels. The thermal isolation cabin 3 and the load-bearing frame 44 are installed with fiberglass insulation. The inner sides of all side panels of the thermal isolation cabin 3 are sprayed with E51-M thermal control black paint to improve the thermal radiation capacity of the inner cavity of the thermal isolation cabin 3. The outer surfaces of all side panels of the thermal isolation cabin 3 are covered with 25 layers of multi-layer insulation components to improve the temperature maintenance capacity of the thermal isolation cabin 3.

[0034] As an embodiment, the support assembly 4 is coated with 25 layers of multi-layer insulation components to reduce the heat exchange between the support assembly 44 and the external environment. The insulation pad 43 is made of 50 mm thick fiberglass, which can block the heat outflow path of the satellite payload 6.

[0035] As an embodiment, the heat dissipation component 1 can control the net outflow of heat from the satellite payload 6, and the heat compensation component 2 can control the net inflow of heat from the satellite payload 6. The program-controlled temperature acquisition system 5 controls the switching of the polyimide film heater I 12 and the polyimide film heater II 21 through the real-time temperature data of the thermistor I 53 and the thermistor II 54 acquired by the temperature acquisition instrument 52, so as to achieve the reversal or blocking control of the direction of heat transfer by the first heat rapid transfer component 13, and the temperature adjustment of the heat isolation cabin 3. When the temperature of the heat isolation cabin 3 acquired by the temperature acquisition instrument 52 is greater than the set value T, the voltage value of the program-controlled power supply 51 is reduced, and the heating amount of the polyimide film heater II 21 is reduced to reduce the net inflow of heat into the heat isolation cabin 3. At the same time, the heating amount of the polyimide film heater I 12 is reduced, and the first heat rapid transfer component 13 transfers the heat from the heat isolation cabin 3 to the heat sink 11 for heat dissipation. On the contrary, when the temperature of the thermal isolation cabin 3 collected by the temperature collector 52 is less than the set value T, the voltage value of the programmable power supply 51 is increased, and the heating amount of the polyimide film heater II 21 is increased to increase the net heat inflow of the thermal isolation cabin 3. At the same time, the heating amount of the polyimide film heater I 12 is increased, and the first heat rapid transfer component 13 transfers the heat from the heat sink 11 to the thermal isolation cabin 3, and simultaneously realizes the heat compensation of the thermal isolation cabin 3. In this way, the heat input change of the satellite payload 6 or the maintenance of a constant heat state is regulated.

[0036] As an embodiment, the steps of performing a vacuum thermal balance test using a satellite payload vacuum thermal balance test thermal control device of the present invention are as follows: 1) Satellite Payload Vacuum Thermal Balance Test After the integrated assembly and thermal control implementation of the thermal control device and the satellite payload 6 are completed, they are pushed into the vacuum tank, the cables inside and outside the tank are connected, and insulation and resistance inspections are carried out. After the rear cover tank is evacuated, when the vacuum degree in the tank is better than 1.33×10-3Pa, liquid nitrogen is introduced for cooling. When the heat sink temperature is lower than 100K, the test begins.

[0037] 2) At time t0, the satellite payload 6 enters the initial orbiting condition, and the satellite payload 6 is not turned on. The polyimide film heater II 21 on the heat compensation component 2 is turned on, and the initial power of the polyimide film heater II 21 is 60W. The program-controlled temperature acquisition system 5 performs closed-loop temperature control on the polyimide film heater II 21 and the thermistor II 54 through the real-time temperature data of the thermistor II 54 collected by the temperature acquisition instrument 52.

[0038] 3) At the moment t0+Δt1, the real-time temperature data of the thermistor II 54 changes by no more than 0.5°C, and it is determined that the initial operating condition of the orbit entry is stable.

[0039] 4) At the time t0+Δt1~t0+Δt2, a thermal balance test of the initial operating conditions of the satellite payload 6 entering orbit is carried out. During the thermal balance test, the upper temperature limit of the main components of the satellite payload 6 does not exceed 45°C, and the lower temperature limit is not lower than -15°C.

[0040] 5) At time t0+Δt2, the initial operating condition thermal balance test of the satellite payload 6 is completed, the test operating condition is switched to the low temperature operating condition, and the satellite payload 6 is turned on. The polyimide film heater I 12 on the heat dissipation component 1 is turned on, and the initial power of the polyimide film heater I 12 is 40W, and the polyimide film heater II 21 on the heat compensation component 2 is turned off. The program-controlled temperature acquisition system 5 performs closed-loop temperature control on the polyimide film heater I 12 and the thermistor I 53 through the real-time temperature data of the thermistor I 53 collected by the temperature acquisition instrument 52, and the satellite payload 6 enters the low temperature operating condition.

[0041] 6) At time t0+Δt3, the real-time temperature data of the thermistor I 53 does not change by more than 0.5°C, and it is determined that the low-temperature working condition is stable.

[0042] 7) At time t0+Δt3~t0+Δt4, a low temperature thermal balance test of the satellite payload 6 is performed, during which the upper temperature limit of each main component of the satellite payload 6 does not exceed 45°C, and the lower temperature limit is not lower than -15°C; 8) At time t0+Δt4, the low-temperature working condition of the satellite payload 6 ends, and the test working condition is switched to the high-temperature working condition. The polyimide film heater I 12 on the heat dissipation component 1 is turned on, and the polyimide film heater II 21 on the heat compensation component 2 is turned on. The initial start-up power of the polyimide film heater I 12 is 55W, and the initial start-up power of the polyimide film heater II 21 is 80W. The program-controlled temperature acquisition system 5 performs closed-loop temperature control on the polyimide film heater I 12, the polyimide film heater II 21, the thermistor I 53, and the thermistor II 54 through the real-time temperature data of the thermistor I 53 and the thermistor II 54 collected by the temperature acquisition instrument 52, and enters the high-temperature working condition of the satellite payload 6.

[0043] 9) At time t0+Δt5, the real-time temperature data of thermistor I 53 and thermistor II 54 do not change by more than 0.5° C., and it is determined that the high temperature working condition is stable.

[0044] 10) At time t0+Δt5~t0+Δt6, a high temperature thermal balance test of the satellite payload 6 is performed, during which the upper temperature limit of each main component of the satellite payload 6 does not exceed 45°C, and the lower temperature limit is not lower than -15°C; 11) At time t0+Δt6, the high temperature working condition of the satellite payload 6 ends.

[0045] 12) According to the above test method, the program-controlled temperature acquisition system 5 performs closed-loop control on the heater switch state, switch number and switch time of the heat dissipation component 1 and the heat compensation component 2, and repeats the test actions of step (2) to step (5) within the test cycle to switch between different test conditions of the satellite payload 6, and sequentially completes the thermal balance test of the satellite payload 6 under different conditions such as the safety mode condition, sensitivity condition, and attitude maneuvering condition.

[0046] A thermal balance test is carried out using a satellite payload vacuum thermal balance test thermal control device of the present invention. It can simulate the net heat output environment and net heat input environment of the satellite payload in the space environment, simulate all the working conditions of the satellite payload in the orbital space environment, and realize the transformation of different working conditions of the satellite payload vacuum thermal balance test without opening the tank, saving test time, improving test efficiency, and reducing the risks of frequent disassembly and assembly to the satellite payload.

[0047] Finally, it should be noted that the above are only preferred embodiments of the present invention and are not intended to limit the present invention. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art can still modify the technical solutions described in the aforementioned embodiments or replace some of the technical features therein by equivalents. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A satellite payload vacuum thermal balance test thermal control device, characterized in that: include: A support assembly, wherein the support assembly is integrally mounted and fixed in the vacuum tank; A thermal isolation cabin installed above the support assembly, the thermal isolation cabin comprising four side panels arranged in a matrix pattern; A heat dissipation component, comprising a heat dissipation plate disposed on one of the side panels of the heat isolation cabin, a first heat rapid transfer component connecting the heat dissipation plate and the heat isolation cabin, and a first heater disposed on the heat dissipation plate; The heat compensation component includes a second rapid heat transfer component and a second heater disposed on a side plate of the heat isolation chamber away from the heat sink; two ends of the second rapid heat transfer component are respectively connected to different side plates of the heat isolation chamber; A program-controlled temperature acquisition system is connected to the heat sink and the heat isolation cabin.

2. The satellite payload vacuum thermal balance test thermal control device according to claim 1, characterized in that: The first heater is a polyimide film heater I; The heat sink is made of aluminum alloy plate, the front of the heat sink faces the cold air direction, and the front is sprayed with thermal control white paint to enhance the heat exchange capacity; the back of the heat sink is coated with several layers of thermal control to improve the temperature maintenance capacity of the heat sink; The polyimide film heater I is formed by a group of heaters evenly distributed on the front of the heat sink and connected in parallel; The heat dissipation component controls the net outflow of heat from the satellite payload, and the first rapid heat transfer component and the polyimide film heater I rapidly adjust the temperature of the heat sink, while simultaneously performing heat exchange between the heat sink and the thermal isolation cabin.

3. The satellite payload vacuum thermal balance test thermal control device according to claim 2, characterized in that: The second heater is a polyimide film heater II, and the polyimide film heater II is formed by a group of heaters evenly distributed on the heat isolation cabin and connected in parallel; The heat compensation component controls the net inflow of heat from the satellite payload, and the polyimide film heater II and the second rapid heat transfer component quickly adjust the temperature of the thermal isolation cabin, while performing heat exchange between the side panels of the thermal isolation cabin to improve the temperature uniformity of the thermal isolation cabin.

4. The satellite payload vacuum thermal balance test thermal control device according to claim 1, characterized in that: The first rapid heat transfer component and the second rapid heat transfer component both use gas-liquid two-phase flow micro-groove phase change heat pipes, which can quickly compensate and transfer heat to the heat isolation cabin.

5. The satellite payload vacuum thermal balance test thermal control device according to claim 1, characterized in that: The thermal isolation cabin is a hollow cover composed of four side panels, an opening is provided at the upper end of the thermal isolation cabin, and a cavity for accommodating the satellite payload is formed in the middle of the thermal isolation cabin, so that the satellite payload is thermally isolated from the surrounding environment by means of physical isolation; wherein, The thermal isolation cabin is composed of a number of carbon fiber panels and a thermal insulation structure. The inner sides of all side panels of the thermal isolation cabin are sprayed with thermal control black paint to improve the heat radiation capacity inside the thermal isolation cabin. The outer sides of all side panels of the thermal isolation cabin are covered with multi-layer thermal insulation components to improve the temperature maintenance capacity of the thermal isolation cabin. The thermal isolation cabin provides a structural installation interface and a thermal connection interface for the heat dissipation component and the heat compensation component.

6. The satellite payload vacuum thermal balance test thermal control device according to claim 1, characterized in that: The support assembly includes a support base, a transfer tool, a thermal insulation pad, and a load-bearing frame, which are used to provide an installation interface for the satellite payload, and to support the satellite payload as a whole and a thermal control device during hoisting, leveling, and transfer, as well as testing; wherein, The transfer tool is installed and fixed on the support base, the load-bearing frame is installed and fixed on the transfer tool, and the thermal insulation pad is installed between the satellite payload and the load-bearing frame; The support component is coated with multiple layers of thermal insulation components to reduce the heat exchange between the support component and the external environment; the thermal insulation pad is made of 50mm thick fiberglass, which can increase the thermal resistance and block the heat outflow path of the satellite payload.

7. The satellite payload vacuum thermal balance test thermal control device according to claim 3, characterized in that: The program-controlled temperature acquisition system includes a program-controlled power supply, a temperature acquisition instrument, a thermistor I, and a thermistor II; wherein, The thermistor I is installed on the heat sink, the thermistor II is installed on the side panel of the heat isolation cabin, the programmable power supply and the temperature collector are placed outside the vacuum tank, and are connected to the thermistor I and the thermistor II through a wall socket and a cable; The program-controlled temperature acquisition system controls the switching of the polyimide film heater I and the polyimide film heater II according to the real-time temperature data of the thermistor I and the thermistor II collected by the temperature acquisition instrument, thereby adjusting the temperature of the thermal isolation cabin, thereby adjusting the heat input change of the satellite payload or maintaining a constant heat state.

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