Thermal control device for satellite payload vacuum thermal balance test

Abstract

The present application relates to satellite load thermal balance test technical field, especially to a kind of satellite load vacuum thermal balance test heat control device, comprising: support assembly;Thermal insulation cabin is installed above the support assembly;Heat dissipation component, including the heat sink of being arranged on one side panel of the thermal insulation cabin, first heat rapid transfer component connected heat sink and the thermal insulation cabin and first heater arranged on the heat sink;Heat compensation component, including second heat rapid transfer component, second heater arranged on the side panel of thermal insulation cabin far from heat sink;Program-controlled temperature acquisition system.The device provided by the present application can simulate all working conditions of satellite load in-orbit space environment, while different working conditions can be changed without opening the tank, reducing the vacuum tank pumping, saving satellite load thermal balance test time, at the same time, without frequent disassembly during test, reduce the risk brought by the satellite load of frequent disassembly.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of satellite load thermal balance test, and particularly relates to a satellite load vacuum thermal balance test thermal control device. BACKGROUND

[0002] In the process of satellite product development, after the satellite load is manufactured, a series of environmental tests are performed on the load to verify whether the load development meets the design requirements, reliability requirements and safety requirements. Among them, the vacuum thermal balance test is a test for simulating the heat change environment of the satellite load in the space environment to verify the heat regulation performance and function of the satellite load in various space thermal environments.

[0003] The satellite load thermal control device is a device for simulating the reception of various space heat flows by the satellite load in the space environment, simulating the net dissipation and net input heat of the satellite load under the actual operating state in the space. Generally, the entire satellite load, the thermal control device and the support assembly are arranged in a vacuum tank to simulate the space vacuum environment. The vacuum tank is in a vacuum environment and is provided with a low-temperature heat sink to simulate the space cold background. Then, the thermal control device simulates different net dissipation and net input heat conditions.

[0004] The satellite load thermal control device in the prior art cannot cover all working conditions of the satellite load. It is necessary to frequently open and close the vacuum tank in the vacuum thermal balance test to adjust the heat simulation change under the space environment. The work efficiency in the tank is low, a large amount of time and funds are consumed, and there is an operation risk. SUMMARY

[0005] The purpose of the present application is to solve the problems in the prior art and provide a satellite load vacuum thermal balance test thermal control device, which comprises:

[0006] A support assembly is integrally installed and fixed in the vacuum tank.

[0007] A heat insulation cabin is installed above the support assembly, and the heat insulation cabin comprises four side plates arranged in a matrix pattern.

[0008] A heat dissipation assembly comprises a heat dissipation plate arranged on one side plate of the heat insulation cabin, a first heat rapid transfer assembly connected between the heat dissipation plate and the heat insulation cabin, and a first heater arranged on the heat dissipation plate.

[0009] A heat compensation assembly comprises a second heat rapid transfer assembly and a second heater arranged on a side plate of the heat insulation cabin away from the heat dissipation plate. The two ends of the second heat rapid transfer assembly are respectively connected to different side plates of the heat insulation cabin.

[0010] A temperature acquisition system is connected with the heat dissipation plate and the heat isolation cabin.

[0011] Further, the first heater is a polyimide film heater I.

[0012] The heat dissipation plate is made of an aluminum alloy plate, the front surface of the heat dissipation plate faces the cold air direction, and the front surface is sprayed with heat control white paint to enhance the heat exchange capacity; the back surface of the heat dissipation plate is coated with several layers of heat control to improve the temperature maintenance capacity of the heat dissipation plate.

[0013] The polyimide film heater I is composed of a group of heaters uniformly distributed on the front surface of the heat dissipation plate and connected in parallel.

[0014] The heat dissipation assembly controls the net outflow heat of the satellite load, and the first heat rapid transfer assembly and the polyimide film heater I rapidly regulate the temperature of the heat dissipation plate and exchange heat between the heat dissipation plate and the heat isolation cabin.

[0015] Further, the second heater is a polyimide film heater II, and the polyimide film heater II is composed of a group of heaters uniformly distributed on the heat isolation cabin and connected in parallel.

[0016] The heat compensation assembly controls the net inflow heat of the satellite load, and the polyimide film heater II and the second heat rapid transfer assembly rapidly regulate the temperature of the heat isolation cabin and exchange heat between the side plates of the heat isolation cabin, thereby improving the temperature uniformity of the heat isolation cabin.

[0017] Further, the first heat rapid transfer assembly and the second heat rapid transfer assembly both adopt gas-liquid two-phase flow micro-channel phase change heat pipes, which can rapidly compensate and transfer heat of the heat isolation cabin.

[0018] Further, the heat isolation cabin is a hollow cover composed of four side plates, the upper end of the heat isolation cabin is provided with an opening, the middle of the heat isolation cabin forms a cavity for accommodating the satellite load, and the satellite load is thermally isolated from the surrounding environment by physical isolation; wherein,

[0019] The heat isolation cabin is composed of several carbon fiber plates and heat insulation structures, the inner sides of all side plates of the heat isolation cabin are sprayed with heat control black paint to improve the heat radiation capacity of the heat isolation cabin, and the outer surfaces of all side plates of the heat isolation cabin are coated with multiple heat insulation assemblies to improve the temperature maintenance capacity of the heat isolation cabin. The heat isolation cabin provides structural mounting interfaces and thermal connection interfaces for the heat dissipation assembly and the heat compensation assembly.

[0020] Further, the support assembly comprises a support base, a transfer tool, a heat insulation pad and a force bearing frame, which are used to provide the mounting interface, hoisting, leveling, transfer and support of the satellite load and the thermal control device during the test of the satellite load as a whole.

[0021] The transfer tool is fixed on the support base, and the force bearing frame is fixed on the transfer tool, and the heat insulation pad is installed between the satellite load and the force bearing frame.

[0022] The support assembly is surrounded by a multi-layer heat insulation assembly to reduce the heat exchange between the support assembly and the external environment. The heat insulation pad is made of 50mm thick glass steel, which can increase the thermal resistance and block the heat outflow path of the satellite load.

[0023] Further, the program-controlled temperature acquisition system comprises a program-controlled power supply, a temperature acquisition instrument, a thermistor I and a thermistor II.

[0024] The thermistor I is installed on the heat dissipation plate, the thermistor II is installed on the side plate of the heat isolation cabin, and the program-controlled power supply and the temperature acquisition instrument are placed outside the vacuum tank and connected with the thermistor I and the thermistor II through a wall socket and a cable.

[0025] The program-controlled temperature acquisition system controls the on-off 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, so as to adjust the temperature of the heat isolation cabin and change the heat input or maintain the constant heat state of the satellite load.

[0026] Compared with the prior art, the beneficial effects of the present application are:

[0027] The satellite load vacuum heat balance test thermal control device provided by the application can simulate all working conditions of the satellite load in the on-orbit space environment, meanwhile, the change of different working conditions can be realized in the state of not opening the tank, the evacuation of the vacuum tank is reduced, the satellite load heat balance test time is saved, meanwhile, the satellite load is not required to be frequently disassembled and assembled in the test process, the risk of the satellite load caused by frequent disassembly and assembly is reduced. BRIEF DESCRIPTION OF DRAWINGS

[0028] Various other advantages and benefits will become apparent to those of ordinary skill in the art upon reading the following detailed description of the preferred embodiments. The accompanying drawings provide a further understanding of the present application and constitute a part of this specification that illustrates specific embodiments of the present application and which, together with the description, serve to explain the present application. In the drawings:

[0029] Figure 1 A satellite load vacuum heat balance test thermal control device provided by the application Figure 1 .

[0030] Figure 2 A satellite load vacuum heat balance test thermal control device provided by the application Figure 2 .

[0031] Figure 3 A satellite load vacuum heat balance test thermal control device provided by the application Figure 3 .

[0032] Figure 4 A satellite load vacuum heat balance test thermal control device provided by the application

[0033] Figure 5 A satellite load vacuum heat balance test thermal control device provided by the application

[0034] REFERENCE NUMERALS

[0035] 1. heat dissipation assembly

[0036] 11. Radiating plate; 12. Polyimide film heater I; 13. First heat fast transfer assembly;

[0037] 2. Heat compensation assembly; 21. Polyimide film heater II; 22. Second heat fast transfer assembly;

[0038] 3. Heat isolation cabin;

[0039] 4. Support assembly;

[0040] 41. Support base; 42. Transfer tooling; 43. Heat insulation pad; 44. Force bearing frame;

[0041] 5. Programmable temperature acquisition system;

[0042] 51. Programmable power supply; 52. Temperature acquisition instrument; 53. Thermistor I; 54. Thermistor II;

[0043] 6. Satellite payload. DETAILED DESCRIPTION

[0044] In order to make the objects, technical solutions and advantages of the present application clearer, the present application will be further described in detail below in conjunction with the drawings and specific embodiments. It should be understood that the specific embodiments described herein are only used to explain the present application and should not be used to limit the present application.

[0045] In order to make the drawings simple, only the parts related to the present application are shown in the drawings, which do not represent the actual structure of the product. In addition, in order to make the drawings simple and easy to understand, in some drawings, only one of the parts with the same structure or function is shown, or only one of them is marked. In this paper, "one" not only means "only one", but also means "more than one".

[0046] First embodiment

[0047] Please refer to Figures 1-5 The technical scheme of the satellite payload vacuum heat balance test thermal control device provided by the embodiment is as follows:

[0048] A satellite payload vacuum heat balance test thermal control device, comprising a heat dissipation assembly 1, a radiating plate 11, a polyimide film heater I 12, a first heat fast transfer assembly 13, a heat compensation assembly 2, a polyimide film heater II 21, a second heat fast transfer assembly 22, a heat isolation cabin 3, a support assembly 4, a support base 41, a transfer tooling 42, a heat insulation pad 43, a force bearing frame 44, a programmable temperature acquisition system 5, a programmable power supply 51, a temperature acquisition instrument 52, a thermistor I 53, a thermistor II 54, and a satellite payload 6.

[0049] The heat dissipation assembly 1 comprises a heat sink 11, a polyimide film heater I 12, and a first heat rapid transfer assembly 13. The polyimide film heater I 12 is pasted on the front surface of the heat sink 11, and the two ends of the first heat rapid transfer assembly 13 are respectively connected to the heat sink 11 and the heat isolation cabin 3.

[0050] The heat compensation assembly 2 comprises a polyimide film heater II 21 and a second heat rapid transfer assembly 22. The polyimide film heater II 21 is pasted on the side plate of the heat isolation cabin 3, and the two ends of the second heat rapid transfer assembly 22 are respectively connected to different side plates of the heat isolation cabin 3.

[0051] The heat isolation cabin 3 is a hollow cover body composed of four side plates, with an open upper end and a cavity for accommodating the satellite load 6 formed in the middle. The heat isolation cabin 3 is integrally installed on the support assembly 4. The heat 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.

[0052] The support assembly 4 comprises a support base 41, a transfer tool 42, a heat insulation pad 43, and a force bearing frame 44, which are used to provide an installation interface, lifting, leveling, transfer, and support for the satellite load 6 and the thermal control device during testing.

[0053] The transfer tool 42 is fixedly installed on the support base 41, the force bearing frame 44 is fixedly installed on the transfer tool 42, and the heat insulation pad 43 is installed between the satellite load 6 and the force bearing frame 44.

[0054] The program-controlled temperature acquisition system 5 comprises 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, the thermistor II 54 is installed on the side plate of the heat isolation cabin 3, and 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.

[0055] As an embodiment, the heat sink 11 is made of an aluminum alloy plate with a thickness of 10 mm, and the front surface is sprayed with S781 thermal control white paint to enhance the heat exchange capacity. The back surface 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 surface of the heat sink 11 faces the cold space, which is a spatial cold black environment. During the vacuum thermal equilibrium test, the cold space background is simulated by a heat sink in the vacuum tank, and the front surface of the heat sink 11 faces the direction of the heat sink.

[0056] 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.

[0057] 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.

[0058] As an embodiment, the polyimide film heater II 21 is formed by a group of 36 heaters with a resistance of 73.5Ω to 144Ω uniformly distributed on the thermal isolation chamber 3 in parallel; the temperature of the thermal isolation chamber 3 can be quickly adjusted.

[0059] As an embodiment, the second rapid heat transfer component 22 is composed of four gas-liquid two-phase flow micro-groove phase change heat pipes to achieve heat exchange between different side panels of the thermal isolation cabin 3.

[0060] 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.

[0061] As an example, the support assembly 4 is coated with 25 layers of multi-layer insulation to reduce heat exchange between the support assembly 44 and the external environment. The insulation pad 43 is made of 50 mm thick fiberglass to block the heat outflow path of the satellite payload 6.

[0062] As an embodiment, the heat dissipation assembly 1 can control the net outflow of heat of the satellite load 6, and the heat compensation assembly 2 can control the net inflow of heat of the satellite load 6. The programmable temperature acquisition system 5 controls the on-off of the polyimide film heater I 12 and the polyimide film heater II 21 by the real-time temperature data of the thermistor I 53 and the thermistor II 54 collected by the temperature acquisition instrument 52, realizes the direction reversal or blockage control of the heat transferred by the first heat rapid transfer assembly 13, and adjusts the temperature of the heat isolation cabin 3. When the temperature of the heat isolation cabin 3 collected by the temperature acquisition instrument 52 is greater than the set value T, the voltage value of the programmable power supply 51 is reduced, the heating amount of the polyimide film heater II 21 is reduced, and the net inflow of heat of the heat isolation cabin 3 is reduced. At the same time, the heating amount of the polyimide film heater I 12 is reduced, and the first heat rapid transfer assembly 13 transfers the heat from the heat isolation cabin 3 to the heat sink 11 for heat dissipation. Conversely, when the temperature of the heat isolation cabin 3 collected by the temperature acquisition instrument 52 is less than the set value T, the voltage value of the programmable power supply 51 is increased, the heating amount of the polyimide film heater II 21 is increased, and the net inflow of heat of the heat isolation cabin 3 is increased. At the same time, the heating amount of the polyimide film heater I 12 is increased, and the first heat rapid transfer assembly 13 transfers the heat from the heat sink 11 to the heat isolation cabin 3, thereby realizing the heat compensation of the heat isolation cabin 3. In this way, the adjustment of the heat input change or the constant heat state maintenance of the satellite load 6 is realized.

[0063] As an embodiment, the steps of the satellite load vacuum heat balance test heat control device of the application for vacuum heat balance test are as follows:

[0064] 1) After the satellite load vacuum heat balance test heat control device and the satellite load 6 complete the integrated assembly and heat control implementation, they are pushed into the vacuum tank, the cable connection inside and outside the tank is completed, the insulation and resistance value are checked, the tank is vacuumized, the vacuum degree in the tank is better than 1.33*10-3Pa, liquid nitrogen is introduced for cooling, and when the heat sink temperature is lower than 100K, the test is started.

[0065] 2) At t0, the initial in-orbit working condition of the satellite load 6 is entered, and the satellite load 6 is not started. The polyimide film heater II 21 of the heat compensation assembly 2 is turned on, and the initial opening power of the polyimide film heater II 21 is 60W. The programmable temperature acquisition system 5 controls the polyimide film heater II 21 and the thermistor II 54 by the real-time temperature data of the thermistor II 54 collected by the temperature acquisition instrument 52.

[0066] 3) At t0+Δt1, the real-time temperature data of the thermistor II 54 changes by no more than 0.5℃, and it is determined that the initial orbiting working condition is stable.

[0067] 4) At t0+Δt1~t0+Δt2, the thermal balance test of the satellite payload 6 in the initial orbiting working condition is carried out, and the upper limit of the temperature of each main component of the satellite payload 6 is no more than 45℃, and the lower limit of the temperature is no less than -15℃.

[0068] 5) At t0+Δt2, the thermal balance test of the satellite payload 6 in the initial orbiting working condition is completed, the test working condition is switched to the low-temperature working condition, and the satellite payload 6 is started. The polyimide film heater I 12 on the heat dissipation assembly 1 is turned on, the initial opening power of the polyimide film heater I 12 is 40W, and the polyimide film heater II 21 on the heat compensation assembly 2 is turned off. The real-time temperature data of the thermistor I 53 collected by the temperature acquisition instrument 52 of the programmable temperature acquisition system 5 is used for closed-loop temperature control of the polyimide film heater I 12 and the thermistor I 53, and the satellite payload 6 enters the low-temperature working condition.

[0069] 6) At t0+Δt3, the real-time temperature data of the thermistor I 53 changes by no more than 0.5℃, and it is determined that the low-temperature working condition is stable.

[0070] 7) At t0+Δt3~t0+Δt4, the thermal balance test of the satellite payload 6 in the low-temperature working condition is carried out, and the upper limit of the temperature of each main component of the satellite payload 6 is no more than 45℃, and the lower limit of the temperature is no less than -15℃.

[0071] 8) At t0+Δt4, the low-temperature working condition of the satellite payload 6 is completed, the test working condition is switched to the high-temperature working condition, the polyimide film heater I 12 on the heat dissipation assembly 1 is turned on, the polyimide film heater II 21 on the heat compensation assembly 2 is turned on, the initial opening power of the polyimide film heater I 12 is 55W, the initial opening power of the polyimide film heater II 21 is 80W, and the real-time temperature data of the thermistor I 53 and the thermistor II 54 collected by the temperature acquisition instrument 52 of the programmable temperature acquisition system 5 is used for closed-loop temperature control of the polyimide film heater I 12, the polyimide film heater II 21, the thermistor I 53 and the thermistor II 54, and the satellite payload 6 enters the high-temperature working condition.

[0072] 9) At t0+Δt5, the real-time temperature data of the thermistor I 53 and the thermistor II 54 changes by no more than 0.5℃, and it is determined that the high-temperature working condition is stable.

[0073] 10) At time t0+Δt5 to t0+Δt6, a high-temperature operating condition thermal balance test is performed on the satellite payload 6. During the thermal balance test, the upper temperature limit of each major component of the satellite payload 6 does not exceed 45° C., and the lower temperature limit is not lower than -15° C.;

[0074] 11) At time t0+Δt6, the high-temperature working condition of the satellite payload 6 ends.

[0075] 12) According to the above test method, the program-controlled temperature acquisition system 5 controls the heater switch state, switch number and switch time of the heat dissipation component 1 and the heat compensation component 2 in a closed loop, and repeats the test actions of steps (2) to (5) within the test cycle to switch between different test conditions of the satellite payload 6, and completes the thermal balance test of the satellite payload 6 under different working conditions such as the safety mode working condition, sensitivity working condition, and attitude maneuvering working condition in sequence.

[0076] A thermal balance test is conducted using a satellite payload vacuum thermal balance test thermal control device according to the present invention.

[0077] It can simulate the net heat output environment and net heat input environment of the satellite payload in the space environment, and can simulate all the working conditions of the satellite payload in the orbital space environment, so as to 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 brought to the satellite payload by frequent disassembly and assembly.

[0078] Finally, it should be noted that the above are merely 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 will be able to modify the technical solutions described in the aforementioned embodiments or substitute equivalents for some of the technical features. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention shall be included within the scope of protection of the present invention.

Claims

1. A thermal control device for a vacuum thermal balance test of a satellite payload, characterized in that, The application relates to a satellite load vacuum heat balance test thermal control device. The support assembly is integrally fixed in a vacuum tank; The support assembly comprises a support base, a transfer tool, a heat insulation pad and a force bearing frame, is used for providing an installation interface, hoisting, leveling, transfer and test support of the satellite load and a thermal control device, wherein the transfer tool is fixed on the support base, the force bearing frame is fixed on the transfer tool, and the heat insulation pad is arranged between the satellite load and the force bearing frame; the support assembly is wrapped with a plurality of heat insulation assemblies to reduce heat exchange between the support assembly and the external environment; the heat insulation pad is made of 50mm thick glass steel, can increase thermal resistance and block a heat outflow path of the satellite load; A heat isolation cabin is arranged above the support assembly, and the heat isolation cabin comprises four side plates arranged in a matrix form; 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 between 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 a side plate of the heat isolation cabin away from the heat dissipation plate; two ends of the second heat rapid transfer assembly are connected to different side plates of the heat isolation cabin respectively; A program-controlled temperature acquisition system is connected with the heat dissipation plate and the heat isolation cabin.

2. The thermal control device for a vacuum thermal balance test of a satellite payload according to claim 1, characterized in that: The first heater is a polyimide film heater I; The heat dissipation plate is made of an aluminum alloy plate, the front surface of the heat dissipation plate faces a cold air direction, the front surface is sprayed with thermal control white paint to enhance heat exchange capacity, and the back surface of the heat dissipation plate is wrapped with a plurality of thermal control layers to improve temperature maintenance capacity of the heat dissipation plate; The polyimide film heater I is composed of a group of heaters uniformly distributed on the front surface of the heat dissipation plate and connected in parallel; The heat dissipation assembly controls net outflow heat of the satellite load, the first heat rapid transfer assembly and the polyimide film heater I rapidly regulate the temperature of the heat dissipation plate and simultaneously exchange heat between the heat dissipation plate and the heat isolation cabin.

3. The satellite load vacuum heat balance test thermal control device according to claim 2, wherein: The second heater is a polyimide film heater II, and the polyimide film heater II is composed of a group of heaters uniformly distributed on the heat isolation cabin and connected in parallel; The heat compensation assembly controls net inflow heat of the satellite load, the polyimide film heater II and the second heat rapid transfer assembly rapidly regulate the temperature of the heat isolation cabin and simultaneously exchange heat between the side plates of the heat isolation cabin to improve temperature uniformity of the heat isolation cabin.

4. The thermal control device for a vacuum thermal balance test of a satellite payload according to claim 1, characterized in that: The first heat rapid transfer assembly and the second heat rapid transfer assembly are both gas-liquid two-phase flow micro-channel phase change heat pipes, which can rapidly compensate and transfer heat of the heat isolation cabin.

5. The thermal control device for a vacuum thermal balance test of a satellite payload according to claim 1, characterized in that: The heat isolation cabin is a hollow cover composed of four side plates, and an opening is arranged at the upper end of the heat isolation cabin, and a cavity for accommodating the satellite load is formed in the middle of the heat isolation cabin, so as to thermally isolate the satellite load from the surrounding environment by physical isolation. The heat isolation cabin is composed of a plurality of carbon fiber plates and heat insulation structures, the inner sides of all the side plates of the heat isolation cabin are sprayed with heat control black paint to improve the heat radiation capacity in the heat isolation cabin, and the outer surfaces of all the side plates of the heat isolation cabin are covered with a plurality of heat insulation components to improve the temperature maintenance capacity of the heat isolation cabin; the heat isolation cabin provides structural mounting interfaces and thermal connection interfaces for the heat dissipation component and the heat compensation component.

6. The thermal control device for a vacuum thermal balance test of a satellite payload according to claim 3, characterized in that: The program-controlled temperature acquisition system comprises a program-controlled power supply, a temperature acquisition instrument, a thermistor I and a thermistor II. The thermistor I is installed on the heat dissipation plate, the thermistor II is installed on the side plate of the heat isolation cabin, and the program-controlled power supply and the temperature acquisition instrument are placed outside the vacuum tank and connected with the thermistor I and the thermistor II through a wall socket and a cable. The program-controlled temperature acquisition system controls the on-off 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, so as to adjust the temperature of the heat isolation cabin and adjust the heat input change or constant heat state maintenance of the satellite load.

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