Temperature control device of space optical load reflector and temperature control method thereof

Abstract

The invention relates to the technical field of space optics, and provides a temperature control device and method for a space optical load reflector, and the device comprises a load body, a solar panel, a reflector, and a temperature control assembly. The solar panel is arranged on the outer surface of the load body; the reflecting mirror is installed in the containing cavity of the load body, and under the condition that the reflecting mirror is affected by external heat flow, the temperature fluctuation trend of the reflecting mirror in the load body is associated with the solar irradiation external heat flow fluctuation trend of the solar panel; the temperature control assembly is connected to the reflecting mirror and comprises a thermoelectric refrigeration sheet, a thin film heating sheet and a temperature measuring element, the thermoelectric refrigeration sheet is electrically connected to the solar panel, and the thin film heating sheet and the temperature measuring element are controlled by the load temperature control circuit board. The external heat flow causing temperature fluctuation of the mirror body is utilized, power is generated through the solar panel, the thermoelectric refrigeration sheet is driven to provide cooling capacity for the reflecting mirror, and temperature fluctuation of the reflecting mirror is controlled.

Description

Technical Field

[0001] The present invention relates to the field of space optical technologies, and particularly to a temperature control device and a temperature control method for a reflector of a space optical payload. Background Art

[0002] In a space optical system, as a key optical component, the performance of a reflector directly affects the imaging quality and stability of the entire system. During the on-orbit operation of a space optical payload reflector, due to the influence of external thermal environments such as solar radiation, earth albedo, and deep space background radiation, the temperature of the reflector will fluctuate periodically. The influence of this external heat flux will not only cause an asymmetric temperature distribution of the mirror body, but also lead to surface deformation, thereby affecting the imaging accuracy and stability of the optical system. Summary of the Invention

[0003] This application aims to solve at least one of the technical problems existing in the related art. Aiming at the problem of the on-orbit temperature fluctuation of the reflector affected by light, for this purpose, this application proposes a temperature control device for a space optical payload reflector, which utilizes the external heat flux that causes the temperature fluctuation of the mirror body, generates electricity through a solar panel and drives a thermoelectric cooler to provide cooling capacity for the reflector to control the temperature fluctuation of the reflector.

[0004] This application also proposes a temperature control method for a space optical payload reflector.

[0005] A temperature control device for a space optical payload reflector according to an embodiment of the first aspect of this application includes: A payload body, on which a payload light incident surface is provided, a payload light incident port is provided on the payload light incident surface, and the payload light incident port communicates with an accommodation cavity inside the payload body; A solar panel, provided on the outer surface of the payload body; A reflector, installed in the accommodation cavity, provided at the payload light incident port. In the case of being affected by an external heat flux, the temperature fluctuation trend of the reflector in the payload body is associated with the solar radiation external heat flux fluctuation trend of the solar panel; A temperature control component, connected to the reflector. The temperature control component includes a thermoelectric cooler, a thin film heating sheet, and a temperature measuring element. The thermoelectric cooler is electrically connected to the solar panel, and the thin film heating sheet and the temperature measuring element are controlled by a payload temperature control circuit board. Among them, the temperature measuring element is used to measure the temperature of the reflector, and the thermoelectric cooler and the thin film heating sheet are used to adjust the temperature of the reflector.

[0006] The temperature control device of the space optical payload mirror according to the embodiment of the present application ensures that the solar panel has a certain amount of sunlight capture at the moment when the temperature of the mirror rises by virtue of the time consistency between the temperature fluctuation on the mirror and the law of the external heat flux fluctuation of the solar panel. The solar panel can generate electricity to drive the thermoelectric cooler, providing input to generate an open-loop cooling output, thereby suppressing the temperature rise of the mirror.

[0007] According to an embodiment of the present application, it includes a heat insulation component, and the heat insulation component is arranged between the outer surfaces of the solar panel and the payload body.

[0008] According to an embodiment of the present application, the solar panel is electrically connected to the thermoelectric cooler. The solar panel converts solar radiation into electrical energy, and the thermoelectric cooler converts electrical energy into cooling capacity.

[0009] According to an embodiment of the present application, the heat insulation component includes a heat insulation gasket and a plurality of heat insulation members. The heat insulation gasket is installed on the outer surface of the payload body, the solar panel is installed on the heat insulation gasket, and a plurality of the heat insulation members are arranged between the outer surface of the payload body and the solar panel.

[0010] According to an embodiment of the present application, the thermoelectric cooler, the thin film heating sheet, and the temperature measuring element are all arranged on the back surface of the mirror.

[0011] According to an embodiment of the present application, the temperature control component includes a heat conducting member. The heat conducting member is installed on the back surface of the mirror, and the thermoelectric cooler, the thin film heating sheet, and the temperature measuring element are installed on the heat conducting member.

[0012] According to an embodiment of the present application, the temperature control component includes a crankshaft and a heat dissipation member. The crankshaft is arranged on the back surface of the mirror, and there is an insulating space between the crankshaft and the back surface of the mirror; the heat dissipation member is connected to the hot end of the crankshaft and the thermoelectric cooler to form a heat path. Among them, the crankshaft is the heat sink of the hot end of the thermoelectric cooler.

[0013] According to an embodiment of the present application, the number of the thermoelectric coolers is two, which are arranged on the upper and lower sides of the back surface of the mirror; and / or, the number of the thin film heating sheets is two, which are arranged on the upper and lower sides of the back surface of the mirror.

[0014] According to an embodiment of the present application, the temperature control component includes a controller. The controller is electrically connected to the temperature measuring element and the thin film heating sheet, and is used to control the working state of the thin film heating sheet according to the temperature data measured by the temperature measuring element.

[0015] According to a temperature control method for a space optical payload mirror provided by the second aspect of the present application, which is applied to the temperature control device of the above-mentioned space optical payload mirror, the temperature control method for the space optical payload mirror includes: Obtain the temperature of the mirror; Send the obtained temperature data to the controller; The controller controls the working state of the thin film heating sheet according to the comparison result between the temperature data and the preset temperature range; when the temperature of the mirror is lower than the lower limit of the preset temperature range, start the thin film heating sheet to heat the mirror; when the temperature of the mirror is higher than the upper limit of the preset temperature range, turn off the thin film heating sheet, and the thermoelectric cooler receives the electric energy of the solar panel and converts it into cold energy to cool the mirror.

[0016] Additional aspects and advantages of the present application will be given in part in the following description, become apparent in part from the following description, or be learned through the practice of the present application. Description of the Drawings

[0017] In order to more clearly illustrate the technical solutions in the present invention or the prior art, the following will briefly introduce the drawings required for use in the description of the embodiments or the prior art. Obviously, the drawings in the following description are some embodiments of the present invention. For those of ordinary skill in the art, without creative efforts, other drawings can also be obtained based on these drawings.

[0018] Figure 1 It is one of the schematic structural diagrams of the temperature control device for the space optical payload mirror provided by the embodiment of the present application.

[0019] Figure 2 It is the second schematic structural diagram of the temperature control device for the space optical payload mirror provided by the embodiment of the present application.

[0020] Figure 3 It is the schematic structural diagram of the mirror and the temperature control component provided by the embodiment of the present application.

[0021] Figure 4 It is the curve of the external heat flux received by the solar panel and the temperature curve of the mirror within one orbital period of an embodiment of the present application.

[0022] Figure 5 It is the comparison diagram of the simulation analysis results of the mirror temperature before and after using the temperature control device for the space optical payload mirror of the present application.

[0023] Figure 6 It is the schematic diagram of the steps of the temperature control method for the space optical payload mirror provided by the embodiment of the present application.

[0024] Reference Signs: 1. Solar panel; 2. Heat insulation gasket; 3. Heat insulation member; 4. Load heat dissipation surface; 5. Load light inlet; 6. Reflector; 7. Crankshaft; 8. Film heating sheet; 9. Temperature measuring element; 10. Thermoelectric cooling sheet; 11. Heat conducting member; 12. Heat dissipation member; 13. Load body; 14. Load light incident surface; 15. Accommodation cavity; 16. Temperature control assembly; 17. Heat insulation assembly; Detailed Embodiments

[0025] The following further describes in detail the embodiments of the present application in conjunction with the accompanying drawings and examples. The following examples are used to illustrate the present application, but cannot be used to limit the scope of the present application.

[0026] In the description of the embodiments of the present application, it should be noted that the orientation or positional relationship indicated by the terms "center", "longitudinal", "transverse", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. is based on the orientation or positional relationship shown in the accompanying drawings, and is only for the convenience of describing the embodiments of the present application and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation to the embodiments of the present application. In addition, the terms "first", "second", and "third" are only used for descriptive purposes and cannot be understood as indicating or implying relative importance.

[0027] In the description of the embodiments of the present application, it should be noted that unless otherwise clearly specified and limited, the terms "connected" and "connected" should be understood in a broad sense. For example, it may be a fixed connection, which may include an integral connection; it may be a mechanical connection or an electrical connection; it may be directly connected or indirectly connected through an intermediate medium. For those of ordinary skill in the art, the specific meanings of the above terms in the embodiments of the present application can be understood according to specific situations.

[0028] In the embodiments of the present application, unless otherwise clearly specified and limited, the first feature being "on" or "under" the second feature may be that the first and second features are in direct contact, or the first and second features are indirectly in contact through an intermediate medium. Moreover, the first feature being "above", "over" and "on" the second feature may be that the first feature is directly above or obliquely above the second feature, or simply means that the first feature is at a higher horizontal height than the second feature. The first feature being "under", "below" and "beneath" the second feature may be that the first feature is directly below or obliquely below the second feature, or simply means that the first feature is at a lower horizontal height than the second feature.

[0029] In the description of this specification, the descriptions referring to terms such as "one embodiment", "some embodiments", "examples", "specific examples", or "some examples", etc., mean that the specific features, structures, materials, or characteristics described in connection with the embodiment or example are included in at least one embodiment or example of the embodiments of this application. In this specification, the schematic expressions of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials, or characteristics described can be combined in a suitable manner in any one or more embodiments or examples. In addition, without contradiction, those skilled in the art can combine and combine the different embodiments or examples described in this specification and the features of different embodiments or examples.

[0030] In a space optical system, the mirror 6 is a key optical element, and its performance directly affects the imaging quality and stability of the entire system. However, during the in-orbit operation of the existing space optical payload mirror 6, due to the influence of external thermal environments such as solar radiation, earth albedo, and deep space background radiation, the temperature on the surface and inside of the mirror 6 will show significant fluctuations. Such temperature fluctuations will not only cause thermal expansion or contraction of the mirror 6 material, but may also cause deformation of the optical surface, thereby affecting the imaging accuracy and stability of the optical system.

[0031] To address the problem of the temperature fluctuation of the mirror 6 affected by light during in-orbit operation, for this purpose, this application proposes a temperature control device for a space optical payload mirror, which utilizes the external heat flux that causes the temperature fluctuation of the mirror body, generates electricity through the solar panel 1 and drives the thermoelectric cooler 10 to provide cooling capacity to the mirror 6, and controls the temperature fluctuation of the mirror 6.

[0032] The following will be combined with Figures 1 - 6 Describe the temperature control device and its temperature control method for the space optical payload mirror of the present invention.

[0033] According to an embodiment of this application, a temperature control device for a space optical payload mirror (hereinafter simply referred to as the temperature control device) is proposed. Please refer to Figures 1 to 3, the temperature control device includes a load body 13, a solar panel 1, a reflector 6, and a temperature control component 16. A load light-incident surface 14 is provided on the load body 13. A load light-incident port 5 is provided on the load light-incident surface 14, and the load light-incident port 5 communicates with an accommodation cavity 15 inside the load body 13; the solar panel 1 is provided on the outer surface of the load body 13; the reflector 6 is installed in the accommodation cavity 15, and the reflector 6 is provided at the load light-incident port 5. In the case of being affected by external heat flux, the temperature fluctuation trend of the reflector 6 inside the load body 13 is correlated with the solar irradiance external heat flux fluctuation trend of the solar panel 1; the temperature control component 16 is connected to the reflector 6, and the temperature control component 16 includes a thermoelectric cooler 10, a thin-film heating sheet 8, and a temperature measuring element 9. Among them, the temperature measuring element 9 is used to measure temperature. The thermoelectric cooler 10 is electrically connected to the solar panel 1, and the thin-film heating sheet 8 and the temperature measuring element 9 are controlled by a load temperature control circuit board. The thermoelectric cooler 10 and the thin-film heating sheet 8 are used to adjust the temperature of the reflector 6.

[0034] For the temperature control device of the space optical load reflector according to the embodiment of the present application, the temperature fluctuation on the reflector 6 has a certain time consistency with the external heat flux fluctuation law of the solar panel 1, ensuring that the solar panel 1 has a certain amount of sunlight capture at the moment when the temperature of the reflector 6 rises. The solar panel 1 can generate electricity to drive the thermoelectric cooler 10, providing input to generate an open-loop cooling output, thereby suppressing the temperature rise of the reflector 6.

[0035] It can be understood that the load body 13 is the main structure of the temperature control device, used to carry and fix other components. A load heat dissipation surface 4 and a load light-incident surface 14 are provided on the load body 13. The solar panel 1 is provided on the outer surface of the load body 13, used to capture solar radiation and convert it into electrical energy. The solar panel 1 provides refrigeration power for the thermoelectric cooler 10 in the temperature control component 16. The reflector 6 is installed in the accommodation cavity 15 inside the load body 13, located at the load light-incident port 5, and is used to reflect light. The thermoelectric cooler 10 converts electrical energy into cold energy to reduce the temperature of the reflector 6. The thin-film heating sheet 8 is used to heat the reflector 6 when needed to ensure the lower limit of the working temperature. The temperature measuring element 9 is used to measure the temperature of the reflector 6 in real time, providing data support for the temperature control of the thin-film heating sheet.

[0036] The temperature fluctuation trend of the mirror 6 inside the payload body 13 is correlated with the solar irradiance external heat flux fluctuation trend of the solar panel 1. The temperature fluctuation of the mirror 6 and the fluctuation law of the external heat flux (such as solar radiation) of the solar panel 1 need to have a certain time consistency. This means that at the moment when the temperature of the mirror 6 rises, the solar panel 1 can capture sufficient sunlight and generate electric energy, thereby driving the thermoelectric cooler 10 to provide cooling capacity to inhibit the further increase in the temperature of the mirror 6. By directly driving the thermoelectric cooler 10 with the solar panel 1, rapid output of cooling capacity can be achieved without a complex feedback control system, simplifying the device structure and improving reliability. Combining the thermoelectric cooler 10 and the thin film heating element 8, the device can flexibly adjust the temperature of the mirror 6 according to the feedback of the temperature measuring element 9 to ensure that it fluctuates within an ideal range. The temperature control device of the present application uses the solar panel 1 to generate electricity, and the device does not need to rely on an external power supply circuit, and is applicable to a space optical system operating in orbit for a long time.

[0037] It should be noted that the thin film heating element 8 and the temperature measuring element 9 belong to closed-loop control, and the solar panel 1 directly supplies power to the thermoelectric cooler 10, which belongs to open-loop control. The present application combines closed-loop control and open-loop control to monitor and adjust the temperature of the mirror 6 in real time, avoiding the influence of temperature fluctuations on the performance of the optical system. The thin film heating element 8 and the temperature measuring element 9 perform heating compensation temperature control through the payload temperature control circuit board. When the external heat flux is large, the mirror temperature is on the high side, and heating compensation cannot achieve a cooling effect. At this time, the heat of the solar panel 1 increases, driving the thermoelectric cooler 10 to output more cooling capacity to cool the mirror 6.

[0038] According to an embodiment of the present application, it includes a heat insulation component 17, and the heat insulation component 17 is arranged between the solar panel 1 and the payload body 13.

[0039] The heat insulation component 17 is located between the solar panel 1 and the payload body 13, forming a heat isolation layer for blocking heat conduction between the two. This layout ensures that while the solar panel 1 efficiently captures solar energy, it will not transfer too much heat to the payload body 13, thereby avoiding adverse effects on the internal components of the payload body 13 and the temperature control of the mirror 6.

[0040] The heat insulation component 17 can be made of materials with low thermal conductivity, such as ceramic fiber, aerogel or multi-layer insulation material (MLI). These materials have excellent heat isolation performance and can effectively reduce heat transfer.

[0041] The structure of the heat insulation component 17 can be designed in a multi-layer composite form to further enhance its heat insulation effect. For example, a vacuum insulation layer or a reflective film structure is adopted to minimize heat radiation and heat convection.

[0042] According to an embodiment of the present application, the heat insulation assembly 17 includes a heat insulation gasket 2 and a plurality of heat insulation members 3. The heat insulation gasket 2 is installed on the load body 13, the solar panel 1 is installed on the heat insulation gasket 2, and a plurality of the heat insulation members are provided between the heat insulation gasket 2 and the solar panel 1.

[0043] The heat insulation gasket 2 connects the solar panel 1 and the load body 13, and its main function is to reduce the heat conduction between the solar panel 1 and the load body 13. The heat insulation gasket 2 can be made of a material with low thermal conductivity, such as polyimide or epoxy fiberglass, to achieve the purpose of reducing heat conduction and heat transfer. A plurality of heat insulation members 3 can be made of multi-layer heat insulation assemblies, aerogels, vacuum insulation panels, etc., to achieve the purpose of reducing radiative heat transfer.

[0044] According to an embodiment of the present application, the thermoelectric cooling chip 10, the thin film heating chip 8, and the temperature measuring element 9 are all provided on the back of the mirror 6.

[0045] The thermoelectric cooling chip 10 is directly installed on the back of the mirror 6, converting electrical energy into cold energy to quickly reduce the temperature of the mirror 6. Since the thermoelectric cooling chip 10 is closely attached to the back of the mirror 6, its cold energy can directly act on the mirror 6, reducing the heat transfer path and time, and improving the response speed of temperature control.

[0046] The thin film heating chip 8 is also installed on the back of the mirror 6 and is used to heat the mirror 6 when needed to balance temperature fluctuations. The thin film heating chip 8 has the characteristics of being thin, light, and flexible, and can be evenly distributed on the back of the mirror 6 to ensure the consistency of the heating effect.

[0047] The temperature measuring element 9 is provided on the back of the mirror 6 and is used to monitor the temperature change of the mirror 6 in real time. The temperature measuring element 9 can be a thermocouple, a thermistor, or other high-precision temperature sensors, which can provide accurate temperature data for the temperature control assembly 16 to achieve closed-loop control.

[0048] According to an embodiment of the present application, the temperature control assembly 16 includes a heat conducting member 11. The heat conducting member 11 is installed on the back of the mirror 6, and the thermoelectric cooling chip 10, the thin film heating chip 8, and the temperature measuring element 9 are installed on the heat conducting member 11.

[0049] The main function of the heat conducting member 11 is to evenly distribute the cold energy or heat generated by the thermoelectric cooling chip 10 and the thin film heating chip 8, avoiding local overheating or overcooling. The heat conducting member 11 can be an aluminum-based graphite sheet, which has the characteristics of high thermal conductivity and light weight, and can quickly transfer heat and maintain uniform temperature. In addition, other metals with high thermal conductivity (such as copper and aluminum) or non-metallic materials (such as ceramic composites) can also be used as alternative materials for the heat conducting member 11, and the specific selection is determined according to actual needs.

[0050] The heat-conducting member 11 is directly mounted on the back surface of the mirror 6, covering a part of the mirror 6 area, ensuring that the cold or heat can be evenly transferred to all parts of the mirror 6. The thermoelectric cooler 10, the thin-film heating sheet 8 and the temperature measuring element 9 are mounted on the heat-conducting member 11, and are in close contact with the back surface of the mirror 6 through the heat-conducting member 11, improving the heat transfer efficiency.

[0051] According to an embodiment of the present application, the temperature control assembly 16 includes a crankshaft 7 and a heat dissipation member 12. The crankshaft 7 is disposed on the back surface of the mirror 6. The crankshaft 7 provides a structural mounting surface for the mirror 7, and an insulating space is provided at intervals between the crankshaft 7 and the back surface of the mirror 6. The heat dissipation member 12 is connected to the hot end of the crankshaft 7 and the thermoelectric cooler 10 to form a heat conduction path. Among them, the crankshaft 7 is a heat sink for the hot end of the thermoelectric cooler 10.

[0052] The crankshaft 7 is disposed on the back surface of the mirror 6, but there is an insulating space between the crankshaft 7 and the back surface of the mirror 6, effectively blocking the transfer of heat to the mirror 6 and ensuring that the heat will not be directly transferred to the mirror 6. The crankshaft 7 serves as a heat sink for the hot end of the thermoelectric cooler 10, and is used to absorb and dissipate the heat generated when the thermoelectric cooler 10 works. The design of the crankshaft 7 not only has the function of the mounting interface of the mirror 6, but also provides a heat dissipation channel for the hot end of the thermoelectric cooler 10, ensuring the normal operation of the mirror 6.

[0053] The heat dissipation member 12 is connected to the crankshaft 7 and the hot end of the thermoelectric cooler 10 to form an efficient heat conduction path. The heat dissipation member 12 can adopt a flexible graphite sheet. This material has a high thermal conductivity coefficient and good flexibility, and can adapt to complex installation environments. In addition, the heat dissipation member 12 can also adopt a heat dissipation fin structure to improve the heat dissipation efficiency by increasing the surface area. Other materials with high thermal conductivity (such as copper, aluminum) or structures (such as heat pipes) can also be used as alternative solutions for the heat dissipation member 12.

[0054] According to an embodiment of the present application, the number of the thermoelectric coolers 10 is two, which are disposed on the upper and lower sides of the back surface of the mirror 6; and / or, the number of the thin-film heating sheets 8 is two, which are disposed on the upper and lower sides of the back surface of the mirror 6. Through the symmetric distribution of the thermoelectric coolers 10 and the thin-film heating sheets 8 on the upper and lower sides, the cold or heat can be evenly transferred to all parts of the mirror 6, significantly improving the temperature uniformity of the mirror 6.

[0055] According to an embodiment of the present application, the temperature control assembly 16 includes a controller. The controller is electrically connected to the temperature measuring element 9, the thermoelectric cooler 10 and the thin-film heating sheet 8. The controller is used to control the working state of the thin-film heating sheet 8 according to the temperature data measured by the temperature measuring element 9.

[0056] The control logic and algorithms built into the controller can accurately determine whether to activate the thin-film heating sheet 8 based on changes in temperature data. For example, when the temperature measuring element 9 detects that the temperature of the mirror 6 is lower than the preset threshold, the controller will activate the thin-film heating sheet 8 to provide heat; when the temperature is lower than the preset threshold, the solar panel 1 is autonomously driven by the external heat flow to provide cooling through the thermoelectric cooler 10.

[0057] In one embodiment, the controller can also adjust the working intensity of the thin-film heating sheet 8 in advance according to the rate and trend of temperature changes to achieve more precise temperature control.

[0058] This application is particularly suitable for high-precision space optical system scenarios. In laser communication tasks that require strict control of the temperature of the mirror 6, the temperature control method of this application can achieve high-precision temperature control and ensure communication quality.

[0059] A temperature control device for a space optical payload mirror of the present invention is composed of a payload mirror 6, a solar panel 1, a thin-film heating sheet 8, a temperature measuring element 9, a thermoelectric cooler 10, a graphite sheet heat conduction component, etc. The solar panel 1 is installed in heat insulation with the payload body 13, and a multi-layer heat insulation component 173 is designed between the payload body 13 and the solar panel 1 to enhance the heat insulation effect. The installation position of the solar panel 1 is selected according to the temperature fluctuation of the mirror 6 and the actual external heat flow of the installation surface. The external heat flow fluctuation of the selected installation surface position needs to have a certain time consistency with the temperature fluctuation of the mirror 6 as much as possible, so as to ensure that the solar panel 1 has a certain amount of sunlight capture at the moment when the temperature of the mirror 6 rises, generating electricity to drive the thermoelectric cooler 10 to refrigerate. When selecting the solar panel 1, it is necessary to ensure that its output power can meet the requirements of the thermoelectric cooler 10. A solar panel 1 with a maximum output voltage matching the working voltage range of the cooler needs to be selected.

[0060] The mirror 6 is installed in heat insulation with the crankshaft 7 to reduce the thermal coupling between the mirror body and the surrounding components. The thin-film heating sheet 8, the temperature measuring element 9, and the thermoelectric cooler 10 are all installed on the back of the mirror 6 to ensure the temperature control ability of the mirror 6 through heating and refrigeration methods. In order to improve the temperature uniformity of the mirror 6 body, an aluminum-based graphite sheet is implemented on the back of the mirror body. To solve the heat dissipation problem at the hot end of the thermoelectric cooler 10, a flexible graphite sheet is implemented at the hot end of the thermoelectric cooler 10 to establish a heat path with the crankshaft 7.

[0061] The following describes the temperature control device for the space optical payload mirror of this application in combination with a specific embodiment: A temperature control device for a reflector of a space optical payload, which is composed of a solar panel 1, a heat insulation gasket 2, a multi-layer heat insulation component 173, a payload heat dissipation surface 4, a payload light inlet 5, a reflector 6, a crankshaft 7, a thin film heating sheet 8, a temperature measuring element 9, a thermoelectric refrigeration sheet 10, an aluminum-based graphite sheet and a flexible graphite sheet. The solar panel 1 is installed outside the payload body 13 in a heat-insulated manner, and the heat coupling with the payload is reduced through the heat insulation gasket 2 and the multi-layer heat insulation component 173. The payload heat dissipation surface 4 provides a relatively cold background for the internal reflector 6, cools the reflector 6 in orbit, and enables its temperature not to exceed the working requirement temperature level during the period without illumination. The temperature control of the target temperature of the reflector 6 is carried out through a temperature control closed-loop circuit composed of the thin film heating sheet 8 and the temperature measuring element 9. In order to save energy consumption, when precise temperature control of the reflector 6 is achieved, it is necessary to reduce the heat coupling between the reflector 6 and the crankshaft 7 and install them in a heat-insulated manner. The crankshaft 7 is made of a material with a low coefficient of thermal expansion, provides the installation interface of the reflector 6, and at the same time serves as the heat sink of the hot end of the thermoelectric refrigeration sheet 10. The thermoelectric refrigeration sheet 10 is installed on the back of the reflector 6. When the temperature of the reflector 6 rises due to sunlight irradiation in orbit, a certain amount of refrigeration capacity is provided for the reflector 6 to suppress its temperature fluctuation and achieve the control of the target temperature. First, an aluminum-based graphite sheet is implemented on the back of the pointing mirror, and then the thin film heating sheet 8, the temperature measuring element 9, and the thermoelectric refrigeration sheet 10 are implemented to achieve the effect of uniform temperature on the mirror surface. A flexible graphite sheet is pasted between the hot end of the thermoelectric refrigeration sheet 10 and the crankshaft 7, and the heat capacity of the crankshaft 7 is used to dissipate the heat of the hot end of the thermoelectric refrigeration sheet 10.

[0062] The advantages of the present invention are that it is light in weight, the system configuration is simple, it does not affect the pointing and rotating components, and it is suitable for the on-orbit temperature control of smaller components. The growth of the outer envelope size outside the payload by this method is controllable. There is no need to consume additional power resources of the payload itself. By using the reason for the increase in the temperature of the reflector 6 (the increase in external heat flux), cold is generated to effectively suppress the increase in its temperature. When the temperature of the reflector 6 is the highest, it is also the moment when the power generation power of the solar panel 1 is the highest, that is, the moment when the refrigeration capacity of the thermoelectric refrigeration sheet 10 is the largest. The real-time supply of the cold quantity required by the pointing mirror is completed through the design of the solar panel 1 and the thermoelectric refrigeration sheet 10. It solves the zero-energy refrigeration strategy for smaller payloads on the satellite and improves the self-adaptability of the payload on-orbit temperature.

[0063] During one orbital period of an embodiment, the curves of the external heat flux of the solar panel and the temperature of the reflector 6 (without the thermoelectric refrigeration sheet 10) are as Figure 4 shown.

[0064] According to the analysis of the external heat flux, the maximum external heat flux per unit area reaches 1400 W / m 2 , and conservatively estimated according to the power generation efficiency of 20%, 0.01 m 2The power generation of the solar panel 1 can reach 2.8W. Calculated conservatively according to a COP of 0.4 for the thermoelectric cooler 10, the maximum cooling capacity can be 1.12W. In this example, the sum of the external heat flux outside the orbit and the surrounding radiation of the mirror 6 is less than 1W. Theoretical analysis proves that the output power of the small-area solar panel 1 can meet the cooling capacity compensation requirements during the on-orbit temperature fluctuation stage of the mirror 6.

[0065] The simulation analysis results of the mirror temperature before and after using the temperature control device of this application are compared as follows Figure 5 as shown.

[0066] It can be seen from the simulation results that before using the temperature control device of this example, due to solar radiation, the temperature of the mirror 6 fluctuates up to 24.5°C at most. After using this example, without consuming additional energy resources of the payload itself, the thermoelectric cooler 10 can effectively reduce the on-orbit temperature of the mirror 6, and the maximum temperature is only 21.5°C, making the on-orbit temperature of the mirror 6 meet the on-orbit working requirements (20°C ± 3°C).

[0067] It can be foreseen that if the size of the solar panel 1 is increased or the installation position of the solar panel 1 is optimized, the on-orbit temperature fluctuation of the mirror 6 can be completely avoided, and this method is suitable for application scenarios with higher temperature requirements.

[0068] According to a temperature control method for a space optical payload mirror provided in the second aspect of this application (hereinafter simply referred to as the temperature control method), which is applied to the temperature control device of the above-mentioned space optical payload mirror, the temperature control method for the space optical payload mirror includes step 100, step 200 and step 300. Please refer to Figure 6 。

[0069] Step 100: Obtain the temperature of the mirror 6.

[0070] Step 200: Send the obtained temperature data to the controller.

[0071] Step 300: The controller controls the working state of the thin film heating sheet 8 according to the comparison result between the temperature data and the preset temperature range; when the temperature of the mirror 6 is lower than the lower limit of the preset temperature range, start the thin film heating sheet 8 to heat the mirror 6. When the temperature of the mirror 6 is higher than the upper limit of the preset temperature range, turn off the thin film heating sheet 8, and the thermoelectric cooler 10 receives the electric energy of the solar panel 1 and converts it into cold energy to cool the mirror 6; In step 100, the temperature control device can measure the temperature of the mirror 6 in real time through the temperature measuring element 9 installed on the back of the mirror 6. The temperature measuring element 9 can be a thermocouple, a thermistor or other high-precision temperature sensors to ensure the accuracy and real-time nature of the temperature data.

[0072] In step 200, the temperature measuring element 9 can transmit the measured temperature data to the controller. As the core of the heating function of the temperature control component 16, the controller is responsible for processing and analyzing the temperature data and making decisions according to the preset control logic. The working state of the thermoelectric cooler 10 depends on the illumination condition of the solar panel 1. When the temperature of the mirror 6 gradually increases, the illumination area of the surface solar panel 1 is poor, the power generation increases, resulting in an increase in the cooling capacity of the thermoelectric cooler 10, and the temperature of the mirror 6 is reduced.

[0073] In step 300, the controller is built-in with a preset temperature range (for example, the lower limit is Tmin and the upper limit is Tmax) to determine whether the temperature of the mirror 6 is in an ideal state.

[0074] If the real-time temperature data is lower than Tmin, the controller activates the thin film heating sheet 8, and converts electrical energy into heat to quickly increase the temperature of the mirror 6. The working intensity of the thin film heating sheet 8 can also be dynamically adjusted according to the magnitude of the temperature deviation to ensure the accuracy and uniformity of the heating process.

[0075] It can be understood that by obtaining the temperature data in real time and combining with the intelligent judgment of the controller, this method can ensure that the temperature of the mirror 6 always remains within the preset range, avoiding the influence of temperature fluctuations on the performance of the optical system. By combining closed-loop control and open-loop control, the device can monitor and adjust the temperature of the mirror 6 in real time, avoiding the influence of temperature fluctuations on the performance of the optical system.

[0076] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit them; although the present invention has been described in detail with reference to the foregoing embodiments, those of ordinary skill in the art should understand that: they can still modify the technical solutions recorded in the foregoing embodiments, or perform equivalent replacements for some of the technical features; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the various embodiments of the present invention.

Claims

1. A temperature control device for a space optical load reflector, characterized in that: include: A load body (13), wherein the load body (13) is provided with a load light incident surface (14), the load light incident surface (14) is provided with a load light incident port (5), and the load light incident port (5) is connected to a containing cavity (15) inside the load body (13); A solar panel (1) is arranged on the outer surface of the load body (13); A reflector (6) is installed in the accommodating cavity (15) and is disposed at the load light entrance (5); when affected by an external heat flow, a temperature fluctuation trend of the reflector (6) in the load body (13) is associated with a fluctuation trend of the solar radiation external heat flow of the solar panel (1); A temperature control component (16) is connected to the reflector (6), the temperature control component (16) comprising a thermoelectric cooling sheet (10), a thin film heating sheet (8) and a temperature measuring element (9), the thermoelectric cooling sheet (10) being electrically connected to the solar panel (1), the thin film heating sheet (8) and the temperature measuring element (9) being controlled by a load temperature control circuit board, wherein the temperature measuring element (9) is used to measure the temperature of the reflector (6), and the thermoelectric cooling sheet (10) and the thin film heating sheet (8) are used to adjust the temperature of the reflector (6).

2. The temperature control device of the space optical load reflector (6) according to claim 1, characterized in that: It comprises a heat insulation component (17), wherein the heat insulation component (17) is arranged between the solar panel (1) and the outer surface of the load body (13).

3. The temperature control device of the space optical load reflector (6) according to claim 2, characterized in that: The thermal insulation component (17) comprises a thermal insulation gasket (2) and a plurality of thermal insulation components (3); the thermal insulation gasket (2) is mounted on the outer surface of the load body (13); the solar panel (1) is mounted on the thermal insulation gasket (2); and the plurality of thermal insulation components (3) are arranged between the outer surface of the load body (13) and the solar panel (1).

4. The temperature control device of the space optical load reflector (6) according to claim 1, characterized in that: The thermoelectric cooling sheet (10), the thin-film heating sheet (8) and the temperature measuring element (9) are all arranged on the back side of the reflecting mirror (6).

5. The temperature control device of the space optical load reflector (6) according to claim 4, characterized in that: The temperature control component (16) comprises a heat conducting member (11), wherein the heat conducting member (11) is mounted on the back of the reflector (6), and the thermoelectric cooling sheet (10), the thin film heating sheet (8) and the temperature measuring element (9) are mounted on the heat conducting member (11).

6. The temperature control device of the space optical load reflector (6) according to claim 4, characterized in that: The temperature control component (16) comprises a crankshaft (7) and a heat sink (12); the crankshaft (7) is arranged on the back of the reflector (6), and a heat insulation space is provided between the crankshaft (7) and the back of the reflector (6); the heat sink (12) connects the crankshaft (7) and the hot end of the thermoelectric cooling sheet (10) to form a heat path, wherein the crankshaft (7) is a heat sink at the hot end of the thermoelectric cooling sheet (10).

7. The temperature control device of the space optical load reflector (6) according to claim 4, characterized in that: The number of the thermoelectric cooling sheets (10) is two, which are arranged on the upper and lower sides of the back side of the reflector (6); and / or the number of the thin film heating sheets (8) is two, which are arranged on the upper and lower sides of the back side of the reflector (6).

8. The temperature control device of the space optical load reflector (6) according to any one of claims 1 to 7, characterized in that: The temperature control component (16) comprises a controller, which is electrically connected to the temperature measuring element (9) and the thin film heating plate (8) and is used to control the working state of the thin film heating plate (8) according to temperature data measured by the temperature measuring element (9).

9. A temperature control method for a space optical load reflector (6), characterized in that: A temperature control device for a space optical load reflector (6) as claimed in claim 1, wherein the temperature control method for the space optical load reflector (6) comprises: Obtaining the temperature of the reflector (6); Send the acquired temperature data to the controller; The controller controls the working state of the thin film heating plate (8) according to the comparison result between the temperature data and the preset temperature range; when the temperature of the reflector (6) is lower than the lower limit of the preset temperature range, the thin film heating plate (8) is started to heat the reflector (6); when the temperature of the reflector (6) is higher than the upper limit of the preset temperature range, the thin film heating plate (8) is turned off, and the thermoelectric cooling plate (10) receives the electric energy of the solar panel (1) and converts it into cold energy to cool the reflector (6).

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