Thermal control method of integrated spacecraft screen display system

Abstract

The invention discloses a thermal control method of an integrated spacecraft screen display system. The thermal control method comprises a heat insulation method, a heat conduction method and a heating method. The heat insulation method comprises the steps that the star screen displayer is installed on an installation platform in a heat insulation mode, a heat insulation assembly is installed on the side wall of the star screen displayer, and the heat insulation assembly is used for reducing heat leakage of the star screen displayer to the space environment; the heat conduction method comprises the following steps: arranging a heat transfer assembly in the star screen display, wherein the heat transfer assembly is used for guiding heat generated in the star screen display to the surface of a structural shell of the star screen display; the heating method comprises the steps that the detection temperature of the star screen displayer is obtained, if the detection temperature is lower than a preset temperature threshold value, the star screen displayer is heated, otherwise, the star screen displayer is not heated, and the method has the advantages that heat can be actively controlled, the temperature of the star screen displayer can be stabilized within a certain range, and the service life of a star screen system is prolonged.

Description

Technical Field

[0001] The present application relates to the technical field of satellite screen display systems, and in particular to a thermal control method for an integrated spacecraft screen display system. Background Art

[0002] At present, the screen display system of satellites and other spacecraft (hereinafter referred to as the star screen system) is mainly composed of a single star screen machine (i.e., star screen display), a star screen camera, connecting cables, etc. The entire satellite screen display system can be assembled based on the internal platform of the satellite or rocket.

[0003] In the prior art, the star screen system generally does not have an active thermal control function, and therefore cannot maintain the internal temperature of the star screen display in the star screen system within a certain range. It is difficult to adapt to the complex space environment, and the star screen display has a low service life, which affects the operating efficiency and performance of the star screen system. Summary of the invention

[0004] The main purpose of this application is to provide a thermal control method for an integrated spacecraft screen display system, aiming to solve the technical problem that the existing star screen display cannot actively control heat, affecting the operating efficiency and performance of the star screen system.

[0005] To achieve the above-mentioned purpose, the present application provides a thermal control method for an integrated spacecraft screen display system, including a heat insulation method, a heat conduction method and a heating method; wherein:

[0006] The heat insulation method includes: heat-insulatingly mounting the star screen display on a mounting platform, and installing a heat insulation component on a side wall of the star screen display, wherein the heat insulation component is used to reduce heat leakage from the star screen display to the space environment;

[0007] The heat conduction method comprises: arranging a heat transfer component in the star screen display, the heat transfer component is used to conduct the heat generated inside the star screen display to the surface of the structural shell of the star screen display;

[0008] The heating method includes: obtaining the detected temperature of the star screen display, and if the detected temperature is lower than a preset temperature threshold, heating the star screen display, otherwise, not heating it.

[0009] Optionally, the thermal insulation component includes multiple reflective screens and multiple spacer layers, the multiple reflective screens and multiple spacer layers are staggered and overlapped with each other, the outermost layer of the thermal insulation component is the reflective screen, the reflective screen is used to reflect external heat radiation, and the spacer layer is used to isolate adjacent reflective screens.

[0010] Optionally, the reflective screen comprises a plastic film, and both sides of the plastic film are plated with gold material or aluminum material with a preset thickness.

[0011] Optionally, the spacer layer is made of a material with low thermal conductivity.

[0012] Optionally, the heat transfer component includes a thermally conductive boss, one side of the thermally conductive boss is in contact with the structural shell, the other side of the thermally conductive boss is provided with a thermally conductive filler, and the thermally conductive boss is in contact with the target component through the thermally conductive filler; wherein the target component is a heat-generating component on a control panel in a star screen display.

[0013] Optionally, obtaining the detected temperature of the star screen display includes:

[0014] The detection temperature of the star screen display is obtained through the temperature measuring component.

[0015] Optionally, heating the star screen display comprises:

[0016] The display screen in the star screen display is heated by a heating component; wherein the heating component is arranged on the back of the display screen.

[0017] Optionally, the temperature control method further includes:

[0018] The outer surface of the structural shell is subjected to black anodizing treatment to form a black anodized layer.

[0019] Optionally, the outer surface of the structural shell is subjected to black anodizing treatment to form a black anodized layer, comprising:

[0020] Surface treatment of the structural shell;

[0021] The surface treated structural shell is pickled using an acid solution to dissolve the oxide film on the surface of the structural shell;

[0022] The acid-washed structural shell is neutralized with an alkaline solution to adjust the pH value of the surface of the structural shell;

[0023] The neutralized structural shell is placed in an electrolytic cell containing an electrolyte and powered to perform an anodic oxidation reaction;

[0024] Using a dye to dye the surface of the structural shell after the anodizing reaction so that the surface of the structural shell appears black;

[0025] The black anodized layer is prepared by filling the tiny pores in the structural shell through a sealing process.

[0026] Optionally, the structural shell is subjected to surface treatment, including:

[0027] Cleaning the surface of the structural shell;

[0028] Use a degreasing agent to remove oil and wax from the surface of the cleaned structural shell.

[0029] The beneficial effects that this application can achieve are as follows:

[0030] The temperature control measures for the star screen display in the present application are taken from three aspects at the same time. First, the star screen display is heat-insulated and installed on the installation platform. At the same time, a heat insulation component is installed on the side wall of the star screen display. The heat insulation component can isolate the external heat flow from the star screen display, thereby reducing the heat leakage of the star screen display to the space environment and playing a role of heat insulation; at the same time, the heat transfer component added to the star screen display can be used to guide the heat generated inside the star screen display to the surface of its structural shell, thereby radiating the waste heat to the space heat sink; and temperature control measures are also combined to monitor the detection temperature of the star screen display in real time. If the detection temperature is lower than the preset temperature threshold, the star screen display is heated, otherwise, no heating is required; therefore, through the above The three measures of heat insulation, heat conduction and heating are coordinated and coordinated, and reasonable thermal control measures are adopted to organize the heat exchange between the star screen display and the space environment, and between the internal devices of the star screen display to control the temperature level and temperature distribution in the star screen display, so that the star screen display has controllable and adjustable heat exchange characteristics, so that the temperature of the star screen display is always stable within a certain range, and its thermal properties can be automatically adjusted according to the actual thermal state of the star screen display during operation, so as to achieve precise control of the thermal state of the star screen display. This active thermal control method can adapt to the complex space environment and ensure the long-term and stable operation of the star screen display in orbit, thereby extending the service life of the star screen system and improving the operating efficiency and performance of the star screen system. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] In order to more clearly illustrate the specific embodiments of the present application or the technical solutions in the prior art, the following is a brief introduction to the drawings required for the specific embodiments or the prior art description. In all drawings, similar elements or parts are generally identified by similar reference numerals. In the drawings, the elements or parts are not necessarily drawn according to the actual scale.

[0032] Figure 1 This is a schematic diagram of the principle of a thermal control method for an integrated spacecraft screen display system in an embodiment of the present application;

[0033] Figure 2 It is a structural schematic diagram of the star screen system in the embodiment of the present application;

[0034] Figure 3 This is a schematic diagram of the exploded structure of the star screen display in the embodiment of the present application;

[0035] Figure 4 This is a schematic diagram of the installation structure of the star screen display in the embodiment of the present application;

[0036] Figure 5 A schematic diagram of heat exchange between a star screen display and a space environment in an embodiment of the present application;

[0037] Figure 6 It is a schematic diagram of the structure of the heat insulation assembly in the embodiment of the present application;

[0038] Figure 7 This is a schematic diagram of the installation structure of the heat transfer component in the embodiment of the present application;

[0039] Figure 8 It is a schematic diagram of the internal heat transfer path of the star screen display in the embodiment of the present application.

[0040] Reference numerals:

[0041] 100-star screen display, 110-structural shell, 120-display screen, 130-control board, 131-target components, 140-heating assembly, 200-camera, 300-cable, 400-connector, 500-bracket, 600-installation platform, 700-thermal insulation assembly, 710-reflective screen, 720-spacer layer, 800-heat transfer assembly, 810-thermal conductive boss, 820-thermal conductive filler.

[0042] The realization of the purpose, functional features and advantages of this application will be further explained in conjunction with embodiments and with reference to the accompanying drawings. DETAILED DESCRIPTION

[0043] The following will be combined with the drawings in the embodiments of the present application to clearly and completely describe the technical solutions in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of this application.

[0044] It should be noted that all directional indications in the embodiments of the present application (such as up, down, left, right, front, back, etc.) are only used to explain the relative position relationship, movement status, etc. between the components in a certain specific posture. If the specific posture changes, the directional indication will also change accordingly.

[0045] In this application, unless otherwise clearly specified and limited, the terms "connection", "fixation", etc. should be understood in a broad sense. For example, "connection" can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements, unless otherwise clearly defined. For ordinary technicians in this field, the specific meanings of the above terms in this application can be understood according to specific circumstances.

[0046] In addition, if there are descriptions involving "first", "second", etc. in the embodiments of the present application, the descriptions of "first", "second", etc. are only used for descriptive purposes and cannot be understood as indicating or implying their relative importance or implicitly indicating the number of technical features indicated. Therefore, the features defined as "first" and "second" may explicitly or implicitly include at least one of the features. In addition, the meaning of "and / or" appearing in the full text includes three parallel schemes. Taking "A and / or B" as an example, it includes scheme A, or scheme B, or a scheme that satisfies both A and B. In addition, the technical solutions between the various embodiments can be combined with each other, but it must be based on the ability of ordinary technicians in the field to implement. When the combination of technical solutions is contradictory or cannot be implemented, it should be considered that such a combination of technical solutions does not exist and is not within the scope of protection required by this application.

[0047] Example

[0048] Reference Figure 1-Figure 8 This embodiment provides a thermal control method for an integrated spacecraft screen display system, including a heat insulation method, a heat conduction method and a heating method; wherein,

[0049] The heat insulation method includes: heat-insulating and installing the star screen display 100 on the installation platform 600, installing a heat insulation component 700 on the side wall of the star screen display 100, and the heat insulation component 700 is used to reduce the heat leakage of the star screen display 100 to the space environment;

[0050] The heat conduction method includes: arranging a heat transfer component 800 in the star screen display 100, the heat transfer component 800 is used to conduct the heat generated inside the star screen display 100 to the surface of the structural shell 110 of the star screen display 100;

[0051] The heating method includes: obtaining the detected temperature of the star screen display 100, and if the detected temperature is lower than a preset temperature threshold, heating the star screen display 100, otherwise, not heating.

[0052] like Figure 2As shown, the integrated spacecraft screen display system (i.e., the star screen system) includes a star screen display 100, the star screen display 100 is connected to a cable 300 through a connector 400, the cable 300 is connected to a camera 200, and the camera 200 is arranged on a bracket 500, wherein the star screen display 100 includes a structural shell 110, a display screen 120 and a control panel 130 are arranged in the structural shell 110, and the structural shell 110 is generally composed of a panel frame and a back plate, the panel frame is sleeved on the outside of the display screen 120, and the control panel 130 is arranged on the inside of the back plate. The camera 200 and the star screen display 100 are installed on two mutually perpendicular surfaces of a satellite or a rocket platform, and are connected by a cable 300. The angle of the camera 200 can be flexibly adjusted according to the replacement of the bracket 500 to ensure the imaging quality. The main task of the camera 200 is to shoot the star screen display content and the earth background, etc. The power supply of the star screen system is provided by a satellite platform or other platforms, but the traditional satellite screen display system is not installed with a star screen system with a thermal control system, so it cannot well maintain the internal temperature within a certain range.

[0053] In this embodiment, the temperature control measures for the star screen display 100 are taken from three aspects at the same time. First, the star screen display 100 is installed on the installation platform 600 in a heat-insulating manner, and a heat insulation component 700 is installed on the side wall of the star screen display 100. The heat insulation component 700 can isolate the external heat flow from the star screen display 100, thereby reducing the heat leakage of the star screen display 100 to the space environment and playing a role in heat insulation; at the same time, the heat transfer component 800 added to the star screen display 100 can be used to guide the heat generated inside the star screen display 100 (up to about 20W) to the surface of its structural shell 110, thereby radiating the waste heat to the space heat sink; in addition, the temperature control measures are combined to monitor the detection temperature of the star screen display 100 in real time. If the detection temperature is lower than the preset temperature threshold, the star screen display 100 is heated. , otherwise, no heating is required; therefore, through the coordinated cooperation of the above three measures of heat insulation, heat conduction and heating, reasonable thermal control measures are adopted to organize the heat exchange between the star screen display 100 and the space environment and between the internal devices of the star screen display 100 to control the temperature level and temperature distribution inside the star screen display 100, so that the star screen display 100 has controllable and adjustable heat exchange characteristics, so that the temperature of the star screen display 100 is always stable within a certain range, that is, according to the actual thermal state of the star screen display 100 during operation, its thermal properties can be automatically adjusted, so as to achieve precise control of the thermal state of the star screen display 100. This active thermal control method can adapt to the complex space environment and ensure the long-term and stable operation of the star screen display 100 in orbit, thereby extending the service life of the star screen system and improving the operating efficiency and performance of the star screen system. Therefore, the star screen system equipped with the above temperature control measures is suitable for installation on a variety of space platforms, such as satellites, rockets and other platforms.

[0054] It should be noted that the above-mentioned external heat flow, namely the external heat flow in space, refers to various space radiation heat sources reaching the outer surface of the spacecraft when it is in orbit. The main sources of external heat flow include solar radiation and sunlight reflected by the earth (called albedo), as well as the earth's own thermal radiation. Heat sink is a special term in thermodynamics, referring to an object or system with stable temperature. The above-mentioned space heat sink is the stable background temperature of the space environment. Since the screen storage temperature of the star screen display 100 is -30℃-80℃ and the operating temperature is -20℃-70℃, the setting of the above-mentioned temperature threshold range depends on the specific application scenario and requirements. In actual applications, it is necessary to select and adjust according to the actual situation. For example, the temperature threshold of this embodiment can be set to 10℃-15℃, that is, heating is performed when the detection temperature is lower than 10℃, and heating is stopped when it is heated to higher than 15℃.

[0055] In addition, the functions of the control panel 130 can be flexibly customized according to needs, and generally have the following basic functions:

[0056] (1) It has the function of playing and displaying stored files;

[0057] (2) having a function of recording the display screen 120;

[0058] (3) receiving video files from the platform and storing the received video files;

[0059] (4) Receive instructions from the satellite platform to play and display stored video files;

[0060] (5) receiving instructions from the satellite platform, recording the playback content, and storing the recorded files;

[0061] (6) receiving instructions from the satellite platform and sending the stored recorded files to the satellite platform;

[0062] (7) Receive instructions from the satellite platform and delete stored video files and recorded files;

[0063] (8) The ability to receive satellite platform commands and send telemetry of the operating status to the satellite platform during power-on operation.

[0064] As an optional embodiment, the thermal insulation component 700 includes multiple reflective screens 710 and multiple spacer layers 720, and the multiple reflective screens 710 and the multiple spacer layers 720 are staggered and overlapped with each other. The outermost layer of the thermal insulation component 700 is the reflective screen 710, and the reflective screen 710 is used to reflect external heat radiation, and the spacer layer 720 is used to isolate adjacent reflective screens 710.

[0065] In this embodiment, the heat insulation component 700 is a multi-layer structure, wherein the reflective screen 710 is the core part of the heat insulation component 700 of the multi-layer structure, and forms a high thermal resistance to the radiant heat flow through layer-by-layer reflection, thereby achieving a good heat insulation effect. According to the design requirements, the number and stacking method of the reflective screen 710 may be different, mainly used to prevent the heat radiation from the hot wall and reduce the radiation heat exchange. In the multi-layer heat insulation component 700, the reflective screen 710 plays a vital role, which can effectively isolate the external heat and protect the internal equipment from the high temperature environment. The spacer layer 720 is located between the reflective screens 710, and plays the role of isolation and support. Through the staggered stacking method, the spacer layer 720 and the reflective screen 710 together constitute the basic structure of the multi-layer heat insulation component 700. The main function of the spacer layer 720 is to reduce the contact heat conduction between the reflective screens 710 and improve the heat insulation performance of the multi-layer heat insulation component 700. At the same time, it can also increase the strength and stability of the component, so that it can maintain a good heat insulation effect in various environments.

[0066] It should be noted that the star screen display 100 is covered with a multi-layer heat insulation component 700 except for the front and mounting surfaces of the screen to reduce heat leakage to the space environment. The covering area is about 0.069m2, reducing heat leakage by about 7W. The multi-layer heat insulation component 700 is usually composed of multiple units, each unit includes a reflective screen 710 and a spacer layer 720, and 5 units, 10 units, 15 units, 20 units, etc. are commonly used.

[0067] As an optional embodiment, the reflective screen 710 includes a plastic film, and the double sides of the plastic film are plated with a preset thickness of gold material or aluminum material. Here, the reflective screen 710 is usually made of a low-emissivity double-sided aluminum-plated film, and sometimes a material with a certain thickness of gold or aluminum evaporated on the plastic film is also used. The double-sided aluminum-plated film has a high reflectivity and a low emissivity, and can effectively reflect the heat flux incident thereon.

[0068] As an optional embodiment, the material of the spacer layer 720 is a low thermal conductivity material. Here, the spacer layer 720 is usually made of a low thermal conductivity material, such as a polyester mesh, etc. These materials have the characteristics of a small contact area, low thermal conductivity, low particle contamination and adaptability to the temperature experienced during flight.

[0069] As an optional embodiment, the heat transfer component 800 includes a thermally conductive boss 810, one side of the thermally conductive boss 810 is in contact with the structural shell 110, and the other side of the thermally conductive boss 810 is provided with a thermally conductive filler 820, and the thermally conductive boss 810 is in contact with the target component 131 through the thermally conductive filler 820; wherein the target component 131 is a heat-generating component on the control board 130 in the star screen display 100, and the heat-generating component mainly refers to a component with high power consumption and easy to generate heat.

[0070] In this embodiment, a part of the heat generated by the target component 131 will be directly radiated to the structural shell 110, and at the same time, a part of the heat generated by the target component 131 will be transferred to the control board 130, and the control board 130 will transfer the heat to the back plate of the structural shell 110. Combined with the design of the thermal conductive boss 810, the remaining heat generated by the target component 131 can be transferred to the panel frame part of the structural shell 110 through the thermal conductive filler 820 and the thermal conductive boss 810, thereby forming multiple heat transfer paths, playing a better heat conduction role, and effectively radiating the waste heat to the spatial heat sink.

[0071] It should be noted that the heat-conducting boss 810 and the target component 131 can be pressed together by screws to reduce the conduction thermal resistance. When the gap between the target component 131 and the structural shell 110 is small, the heat-conducting filler 820 can be applied to improve the heat-conducting effect; the heat-conducting filler 820 can be made of thermal grease, which has a good heat-conducting effect.

[0072] As an optional implementation manner, obtaining the detected temperature of the star screen display 100 includes:

[0073] The detection temperature of the star screen display 100 is obtained through the temperature measuring component.

[0074] Heating the star screen display 100 includes:

[0075] The display screen 120 in the star screen display 100 is heated by the heating component 140 ; ​​wherein the heating component 140 is arranged on the back side of the display screen 120 .

[0076] In this embodiment, by setting a temperature measuring component and cooperating with the setting of the heating circuit, the temperature threshold of the temperature measuring component can be set through the satellite service software. When the temperature is lower than the threshold, the heating component 140 is turned on, and when the temperature is higher than the threshold, the heating component 140 is turned off. Here, the temperature measuring component can use a thermistor, and its model can be MF501, which is an oxide material and is made under specific temperature and atmosphere conditions. It has the advantages of fast response speed, accurate linearity, strong stability, and relatively low price. It is widely used in temperature measurement and electrical control and other fields, and its temperature measurement range is -40 to +70. The heating component 140 can use a heater such as a heating plate to evenly heat the display screen 120.

[0077] As an optional implementation, the temperature control method further includes:

[0078] The outer surface of the structural shell 110 is subjected to black anodizing treatment to form a black anodized layer.

[0079] In this embodiment, the surface emissivity of the structural shell 110 after black anodizing is usually high, which helps to more effectively dissipate heat in the form of radiation. High emissivity means that heat can be transferred to the surrounding environment more quickly, thereby improving heat dissipation efficiency. The black anodized layer has a strong absorption capacity for visible light and infrared radiation. Since black itself is a color with low reflectivity, it can absorb most of the incident light, thereby reducing the intensity of the reflected light. In addition, the oxide layer formed during the anodizing process usually has a certain degree of roughness. This rough surface structure can further reduce the reflection of light because the light will scatter on the rough surface instead of forming a clear reflection like on a smooth surface. The surface after black anodizing usually presents a matte effect, that is, the reflected light is more dispersed and has a lower intensity. This matte effect helps to reduce the reflection problem, especially in the camera 200 shooting scene where light interference needs to be reduced; when the sun is directly shining on the star screen display 100, it can effectively reduce the reflection of the display screen 120. The impact of the camera 200, the surface emissivity ≥ 0.85, is conducive to heat dissipation when it is not directly shining.

[0080] As an optional embodiment, the outer surface of the structural shell 110 is subjected to black anodizing treatment to form a black anodized layer, including:

[0081] Performing surface treatment on the structural shell 110;

[0082] The surface-treated structural shell 110 is pickled with an acid solution to dissolve the oxide film on the surface of the structural shell 110;

[0083] Using an alkaline solution to neutralize the acid-washed structural shell 110 to adjust the pH value of the surface of the structural shell 110;

[0084] The neutralized structural shell 110 is placed in an electrolytic cell containing an electrolyte and powered to perform an anodic oxidation reaction;

[0085] Using a dye to dye the surface of the structural shell 110 after the anodizing reaction, so that the surface of the structural shell 110 appears black;

[0086] The tiny pores in the structural shell 110 are filled by the sealing process to complete the preparation of the black anodized layer.

[0087] In this embodiment, the structural shell 110 is first surface treated to ensure that its surface is clean; then pickling is performed to dissolve the oxide film on the surface to expose a pure aluminum surface, which is conducive to the anodizing reaction; then neutralization treatment is performed to adjust the pH value of the surface to create a suitable environment for anodizing; then anodizing reaction is performed, and during the electrolysis process, a dense aluminum oxide film will be formed on the surface of the aluminum part of the structural shell 110, and this film has excellent corrosion resistance and wear resistance; then dyeing is performed, and the choice of dye should be determined according to specific needs and process conditions, and metal salts, inorganic dyes or organic dyes can be used for dyeing; finally, pore sealing treatment is performed to fill the tiny pores generated during the anodizing process to improve the density and corrosion resistance of the anodized film. The sealing treatment usually occurs in nickel acetate or an acid bath, which helps to harden the coating and prevent color bleeding and fading, and finally a high-quality black anodized layer can be prepared.

[0088] As an optional implementation, surface treatment is performed on the structural shell 110, including:

[0089] Cleaning the surface of the structural shell 110;

[0090] The oil and wax on the surface of the cleaned structural shell 110 are removed using a degreasing agent.

[0091] In this embodiment, during the surface treatment, cleaning is first performed to clean the oil, dust and impurities on the surface of the aluminum part of the structural shell 110 to ensure the purity of the surface and prepare for the subsequent anodizing treatment, and then degreasing is performed to ensure the uniformity and quality of the anodized film.

[0092] The above are only preferred embodiments of the present application, and are not intended to limit the patent scope of the present application. Any equivalent structure or equivalent process transformation made using the contents of the present application specification and drawings, or directly or indirectly applied in other related technical fields, are also included in the patent protection scope of the present application.

Claims

1. A thermal control method for an integrated spacecraft screen display system, characterized in that: It includes a heat insulation method, a heat conduction method and a heating method; wherein, The heat insulation method comprises: heat-insulatingly mounting the star screen display on a mounting platform, and installing a heat insulation component on a side wall of the star screen display, wherein the heat insulation component is used to reduce heat leakage from the star screen display to the space environment; The heat conduction method comprises: arranging a heat transfer component in the star screen display, wherein the heat transfer component is used to conduct the heat generated inside the star screen display to the surface of the structural shell of the star screen display; The heating method includes: obtaining the detected temperature of the star screen display, and if the detected temperature is lower than a preset temperature threshold, heating the star screen display, otherwise, not heating it.

2. The thermal control method of the integrated spacecraft screen display system according to claim 1, characterized in that: The thermal insulation component includes multiple reflective screens and multiple spacer layers, which are staggered and overlapped with each other. The outermost layer of the thermal insulation component is the reflective screen, which is used to reflect external heat radiation, and the spacer layer is used to isolate adjacent reflective screens.

3. The thermal control method of the integrated spacecraft screen display system according to claim 2, characterized in that: The reflection screen comprises a plastic film, and both sides of the plastic film are plated with gold material or aluminum material with a preset thickness.

4. The thermal control method of the integrated spacecraft screen display system according to claim 3, characterized in that: The material of the spacing layer is a material with low thermal conductivity.

5. The thermal control method of the integrated spacecraft screen display system according to claim 1, characterized in that: The heat transfer component includes a heat-conducting boss, one side of which is in contact with the structural shell, and the other side of which is provided with a heat-conducting filler, and the heat-conducting boss is in contact with a target component through the heat-conducting filler; wherein the target component is a heat-generating component on a control panel in the star screen display.

6. The thermal control method of the integrated spacecraft screen display system according to claim 1, characterized in that: The obtaining the detected temperature of the star screen display comprises: The detection temperature of the star screen display is obtained through a temperature measuring component.

7. The thermal control method of the integrated spacecraft screen display system according to claim 1 or 6, characterized in that: The step of heating the star screen display comprises: The display screen in the star screen display is heated by a heating component; wherein the heating component is arranged on the back of the display screen.

8. The thermal control method of the integrated spacecraft screen display system according to claim 1, characterized in that: The temperature control method further comprises: The outer surface of the structural shell is subjected to black anodizing treatment to form a black anodized layer.

9. The thermal control method of the integrated spacecraft screen display system according to claim 8, characterized in that: The step of performing black anodizing on the outer surface of the structural shell to form a black anodized layer comprises: performing surface treatment on the structural shell; Using an acid solution to pickle the surface-treated structural shell to dissolve the oxide film on the surface of the structural shell; Using an alkaline solution to neutralize the acid-washed structural shell to adjust the pH value of the surface of the structural shell; placing the neutralized structural shell into an electrolytic cell containing an electrolyte and applying electricity to perform an anodic oxidation reaction; Using a dye to dye the surface of the structural shell after the anodizing reaction so that the surface of the structural shell appears black; The tiny pores in the structural shell are filled by a sealing process to complete the preparation of the black anodized layer.

10. The thermal control method of the integrated spacecraft screen display system according to claim 9, characterized in that: The surface treatment of the structural shell comprises: Cleaning the surface of the structural shell; The oil and wax on the surface of the cleaned structural shell are removed using a degreasing agent.

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