Temperature control device and temperature control method for space optical load reflector

Abstract

The present invention relates to the field of space optics technology, and provides a temperature control device for a space optical payload reflector and a temperature control method thereof. The temperature control device includes a payload body, a solar panel, a reflector, and a temperature control assembly. The solar panel is disposed on the outer surface of the payload body. The reflector is mounted within a housing cavity of the payload body. When affected by an external heat flux, the temperature fluctuation trend of the reflector within the payload body is correlated with the fluctuation trend of the solar radiation external heat flux of the solar panel. The temperature control assembly is connected to the reflector and includes a thermoelectric cooling plate, a thin film heater, and a temperature measuring element. The thermoelectric cooling plate is electrically connected to the solar panel, and the thin film heater and the temperature measuring element are controlled by a payload temperature control circuit board. The present application utilizes the external heat flux that causes the temperature fluctuation of the mirror body to generate electricity through the solar panel and drive the thermoelectric cooling plate to provide cooling to the reflector, thereby controlling the temperature fluctuation of the reflector.

Description

Technical Field

[0001] The present invention relates to the field of space optics technology, and in particular to a temperature control device and a temperature control method for a space optical load reflector. Background Art

[0002] In space optical systems, mirrors are key optical components, and their performance directly impacts the imaging quality and stability of the entire system. During on-orbit operation, the mirrors of space optical payloads are subject to periodic temperature fluctuations due to external thermal factors such as solar radiation, Earthshine, and deep-space background radiation. This external heat flux not only creates an asymmetric temperature distribution within the mirror, but also causes surface deformation, which in turn affects the imaging accuracy and stability of the optical system. Summary of the Invention

[0003] This application aims to address at least one of the technical problems existing in the related art. To address the issue of on-orbit temperature fluctuations of reflectors due to light exposure, this application proposes a temperature control device for a reflector on a space optical payload. This device utilizes external heat flux that causes temperature fluctuations in the mirror body, generates electricity through solar panels, and drives thermoelectric cooling elements to provide cooling to the reflector, thereby controlling the temperature fluctuations.

[0004] The present application also proposes a temperature control method for a space optical load reflector.

[0005] A temperature control device for a space optical load mirror according to an embodiment of the first aspect of the present application includes:

[0006] A load body, wherein the load body is provided with a load light incident surface, the load light incident surface is provided with a load light incident port, and the load light incident port is connected to the accommodating cavity inside the load body;

[0007] a solar panel, disposed on the outer surface of the load body;

[0008] A reflector is installed in the accommodating cavity and is provided at the light entrance of the load. When affected by external heat flow, the temperature fluctuation trend of the reflector in the load body is correlated with the fluctuation trend of the solar radiation external heat flow of the solar panel;

[0009] A temperature control component is connected to the reflector, and the temperature control component includes a thermoelectric cooling plate, a thin film heating plate and a temperature measuring element. The thermoelectric cooling plate is electrically connected to the solar panel, and the thin film heating plate and the temperature measuring element are controlled by a load temperature control circuit board, wherein the temperature measuring element is used to measure the temperature of the reflector, and the thermoelectric cooling plate and the thin film heating plate are used to adjust the temperature of the reflector.

[0010] According to the temperature control device of the space optical payload reflector in the embodiment of the present application, the temperature fluctuation on the reflector has a certain time consistency with the heat flow fluctuation law outside the solar panel, ensuring that the solar panel has a certain amount of sunlight capture when the temperature of the reflector rises. The solar panel can generate electricity to drive the thermoelectric cooling plate, provide input to generate open-loop cooling output, thereby suppressing the temperature increase of the reflector.

[0011] According to one embodiment of the present application, a heat insulation component is included, and the heat insulation component is provided between the solar panel and the outer surface of the load body.

[0012] According to one embodiment of the present application, the solar panel is electrically connected to the thermoelectric cooling sheet, the solar panel converts solar radiation into electrical energy, and the thermoelectric cooling sheet converts electrical energy into cooling capacity.

[0013] According to one embodiment of the present application, the thermal insulation assembly includes a thermal insulation gasket and several thermal insulation parts, the thermal insulation gasket is installed on the outer surface of the load body, the solar panel is installed on the thermal insulation gasket, and several thermal insulation parts are arranged between the outer surface of the load body and the solar panel.

[0014] According to one embodiment of the present application, the thermoelectric cooling plate, the thin film heating plate and the temperature measuring element are all arranged on the back side of the reflector.

[0015] According to one embodiment of the present application, the temperature control assembly includes a heat conductor, which is installed on the back of the reflector, and the thermoelectric cooling plate, the thin film heating plate and the temperature measuring element are installed on the heat conductor.

[0016] According to one embodiment of the present application, the temperature control component includes a crankshaft and a heat sink, the crankshaft is arranged on the back of the reflector, and an insulating space is provided between the crankshaft and the back of the reflector; the heat sink connects the crankshaft and the hot end of the thermoelectric cooling plate to form a heat path, wherein the crankshaft is a heat sink for the hot end of the thermoelectric cooling plate.

[0017] According to one embodiment of the present application, there are two thermoelectric cooling plates, which are arranged on the upper and lower sides of the back of the reflector; and / or there are two thin film heating plates, which are arranged on the upper and lower sides of the back of the reflector.

[0018] According to one embodiment of the present application, the temperature control component includes a controller, which is electrically connected to the temperature measuring element and the thin film heater, and is used to control the working state of the thin film heater according to the temperature data measured by the temperature measuring element.

[0019] According to a second aspect of the present application, a temperature control method for a space optical load reflector is provided in an embodiment, which is applied to the temperature control device for the space optical load reflector. The temperature control method for the space optical load reflector includes:

[0020] obtaining the temperature of the reflector;

[0021] Send the acquired temperature data to the controller;

[0022] The controller controls the working state of the thin film heater according to the comparison result of the temperature data and the preset temperature range; when the temperature of the reflector is lower than the lower limit of the preset temperature range, the thin film heater is started to heat the reflector; when the temperature of the reflector is higher than the upper limit of the preset temperature range, the thin film heater is turned off, and the thermoelectric cooling plate receives the electrical energy of the solar panel and converts it into cold energy to cool the reflector.

[0023] Additional aspects and advantages of the present application will be given in part in the description below, and in part will become obvious from the description below, or will be learned through practice of the present application. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] In order to more clearly illustrate the technical solutions in the present invention or the prior art, a brief introduction is given below to the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0025] Figure 1 This is one of the structural schematic diagrams of the temperature control device of the space optical load mirror provided in the embodiment of the present application.

[0026] Figure 2 This is the second structural schematic diagram of the temperature control device of the space optical load mirror provided in the embodiment of the present application.

[0027] Figure 3 It is a structural schematic diagram of the reflector and temperature control assembly provided in an embodiment of the present application.

[0028] Figure 4 This is a graph showing the external heat flux curve experienced by a solar panel and the reflector temperature curve during one orbital cycle of an embodiment of the present application.

[0029] Figure 5 This is a comparison chart of simulation analysis results of the temperatures of the front and rear mirrors of the temperature control device for the space optical load mirror of the present application.

[0030] Figure 6This is a schematic diagram of the steps of the temperature control method of the space optical load mirror provided in an embodiment of the present application.

[0031] Reference numerals:

[0032] 1. Solar panel; 2. Thermal insulation gasket; 3. Thermal insulation component; 4. Load heat dissipation surface; 5. Load light inlet; 6. Reflector; 7. Crankshaft; 8. Thin-film heater; 9. Temperature measuring element; 10. Thermoelectric cooling element; 11. Thermal conductor; 12. Heat dissipation component; 13. Load body; 14. Load light inlet; 15. Accommodation cavity; 16. Temperature control component; 17. Thermal insulation component. DETAILED DESCRIPTION

[0033] The following embodiments of the present invention are described in further detail with reference to the accompanying drawings and examples. The following examples are used to illustrate the present invention, but are not intended to limit the scope of the present invention.

[0034] In the description of the embodiments of the present application, it should be noted that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating the orientation or positional relationship, are based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing the embodiments of the present application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operate in a specific orientation, and therefore cannot be understood as limiting the embodiments of the present application. In addition, the terms "first", "second", and "third" are used for descriptive purposes only and cannot be understood as indicating or implying relative importance.

[0035] In the description of the embodiments of this application, it should be noted that, unless otherwise expressly specified or limited, the terms "connected" and "connection" should be understood in a broad sense. For example, they can refer to fixed or detachable connections, where fixed connections can include integral connections; they can refer to mechanical or electrical connections; and they can refer to direct connections or indirect connections through an intermediary. Those skilled in the art will understand the specific meanings of the above terms in the embodiments of this application based on the specific circumstances.

[0036] In the embodiments of the present application, unless otherwise expressly specified or limited, a first feature being "above" or "below" a second feature may mean that the first and second features are in direct contact, or that the first and second features are in indirect contact through an intermediate medium. Furthermore, a first feature being "above," "above," and "above" a second feature may mean that the first feature is directly above or obliquely above the second feature, or simply means that the first feature is higher in level than the second feature. A first feature being "below," "below," and "below" a second feature may mean that the first feature is directly below or obliquely below the second feature, or simply means that the first feature is lower in level than the second feature.

[0037] In the description of this specification, the description with reference to the terms "one embodiment", "some embodiments", "example", "specific example", or "some examples" means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the embodiments of the present application. In this specification, the schematic representations 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 any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art can combine and combine different embodiments or examples described in this specification and the features of different embodiments or examples, unless they are contradictory.

[0038] In space optical systems, the performance of the reflector 6, a key optical component, directly impacts the imaging quality and stability of the entire system. However, during on-orbit operation, the reflector 6 of existing space optical payloads experiences significant surface and internal temperature fluctuations due to the influence of external thermal environments such as solar radiation, Earthshine, and deep-space background radiation. These temperature fluctuations not only cause thermal expansion or contraction of the reflector 6 material but can also cause deformation of the optical surface, thereby affecting the imaging accuracy and stability of the optical system.

[0039] In order to solve the problem of temperature fluctuation of the reflector 6 in orbit due to the influence of light, the present application proposes a temperature control device for the reflector of a space optical payload. The device utilizes the external heat flow that causes the temperature fluctuation of the mirror body to generate electricity through the solar panel 1 and drive the thermoelectric cooling plate 10 to provide cooling to the reflector 6, thereby controlling the temperature fluctuation of the reflector 6.

[0040] The following combination Figures 1-6 The present invention describes a temperature control device and a temperature control method for a space optical load reflecting mirror.

[0041] According to the embodiment of the present application, a temperature control device for a space optical load reflector (hereinafter referred to as a temperature control device) is proposed. Figures 1 to 3The temperature control device includes a load body 13, a solar panel 1, a reflector 6 and a temperature control component 16, wherein the load body 13 is provided with a load light entrance surface 14, and the load light entrance surface 14 is provided with a load light entrance port 5, and the load light entrance port 5 is connected to the accommodating cavity 15 inside the load body 13; the solar panel 1 is arranged on the outer surface of the load body 13; the reflector 6 is installed in the accommodating cavity 15, and the reflector 6 is arranged at the load light entrance port 5. When affected by external heat flow, the temperature fluctuation trend of the reflector 6 in the load body 13 is associated with the fluctuation trend of the solar radiation external heat flow 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 cooling plate 10, a thin film heating plate 8 and a temperature measuring element 9, wherein the temperature measuring element 9 is used to measure temperature, the thermoelectric cooling plate 10 is electrically connected to the solar panel 1, the thin film heating plate 8 and the temperature measuring element 9 are controlled by the load temperature control circuit board, and the thermoelectric cooling plate 10 and the thin film heating plate 8 are used to adjust the temperature of the reflector 6.

[0042] According to the temperature control device of the space optical load reflector in the embodiment of the present application, the temperature fluctuation on the reflector 6 has a certain time consistency with the heat flow fluctuation law outside the solar panel 1, ensuring that the solar panel 1 has a certain amount of sunlight capture when the temperature of the reflector 6 rises. The solar panel 1 can generate electricity to drive the thermoelectric cooling plate 10, providing input to generate open-loop cooling output, thereby suppressing the temperature increase of the reflector 6.

[0043] It can be understood that the load body 13 is the main structure of the temperature control device, which is used to carry and fix other components. The load body 13 is provided with a load heat dissipation surface 4 and a load light incident surface 14. The solar panel 1 is arranged on the outer surface of the load body 13, and is used to capture solar radiation and convert it into electrical energy. The solar panel 1 provides cooling power for the thermoelectric cooling plate 10 in the temperature control component 16. The reflector 6 is installed in the accommodating cavity 15 inside the load body 13, located at the load light entrance 5, and is used to reflect light. The thermoelectric cooling plate 10 converts electrical energy into cold energy, which is used to reduce the temperature of the reflector 6. The thin film heating plate 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, and provide data support for the temperature control of the thin film heating plate.

[0044] The temperature fluctuation trend of the reflector 6 within the payload body 13 is associated with the fluctuation trend of the solar radiation external heat flow of the solar panel 1. The temperature fluctuation of the reflector 6 and the fluctuation pattern of the external heat flow of the solar panel 1 (such as solar radiation) need to have a certain time consistency. This means that when the temperature of the reflector 6 rises, the solar panel 1 can capture enough sunlight and generate electricity, thereby driving the thermoelectric cooling plate 10 to provide cooling and suppressing the further increase of the temperature of the reflector 6. By directly driving the thermoelectric cooling plate 10 through the solar panel 1, a rapid output of cooling can be achieved without a complex feedback control system, simplifying the device structure and improving reliability. Combined with the thermoelectric cooling plate 10 and the thin film heating plate 8, the device can flexibly adjust the temperature of the reflector 6 according to the feedback of the temperature measuring element 9 to ensure that it fluctuates within the ideal range. The temperature control device of the present application uses the solar panel 1 to generate electricity. The device does not need to rely on an external power supply circuit and is suitable for space optical systems that operate in orbit for a long time.

[0045] It should be noted that the thin film heater 8 and the temperature measuring element 9 are closed-loop controlled, and the solar panel 1 directly supplies power to the thermoelectric cooling element 10, which is open-loop controlled. The present application monitors and adjusts the temperature of the reflector 6 in real time by combining closed-loop control with open-loop control, thereby avoiding the influence of temperature fluctuations on the performance of the optical system. The thin film heater 8 and the temperature measuring element 9 perform heating compensation and temperature control through the load temperature control circuit board. When the external heat flow is large, the temperature of the reflector is too high, and the heating compensation cannot achieve a cooling effect. At this time, the heat of the solar panel 1 increases, driving the thermoelectric cooling element 10 to output more coldness to cool the reflector 6.

[0046] According to one embodiment of the present application, a heat insulation component 17 is included, and the heat insulation component 17 is provided between the solar panel 1 and the load body 13 .

[0047] Thermal insulation assembly 17 is located between solar panel 1 and payload body 13, forming a thermal isolation layer to block heat conduction between the two. This layout ensures that solar panel 1 efficiently captures solar energy without transferring excessive heat to payload body 13, thereby preventing adverse effects on the temperature control of payload body 13 internal components and reflector 6.

[0048] The thermal insulation assembly 17 can be made of low thermal conductivity materials, such as ceramic fiber, aerogel, or multi-layer insulation (MLI). These materials have excellent thermal insulation properties and can effectively reduce heat transfer.

[0049] The structure of the heat insulation assembly 17 can be designed as a multi-layer composite form to further enhance its heat insulation effect. For example, a vacuum insulation layer or a reflective film structure is used to minimize heat radiation and heat convection.

[0050] According to one embodiment of the present application, the thermal insulation assembly 17 includes a thermal insulation gasket 2 and several thermal insulation parts 3, the thermal insulation gasket 2 is installed on the load body 13, the solar panel 1 is installed on the thermal insulation gasket 2, and several thermal insulation parts are arranged between the thermal insulation gasket 2 and the solar panel 1.

[0051] The thermal insulation spacer 2 connects the solar panel 1 and the load body 13. Its primary function is to reduce heat conduction between the solar panel 1 and the load body 13. The thermal insulation spacer 2 can be made of a low-thermal-conductivity material, such as polyimide or epoxy fiberglass, to reduce conductive heat transfer. The thermal insulation components 3 can be made of multi-layer insulation components, aerogel, vacuum insulation panels, etc., to reduce radiative heat transfer.

[0052] According to an embodiment of the present application, the thermoelectric cooling plate 10 , the thin film heating plate 8 and the temperature measuring element 9 are all arranged on the back side of the reflector 6 .

[0053] Thermoelectric cooling element 10 is directly mounted on the back of reflector 6, converting electrical energy into cooling, thereby rapidly reducing the temperature of reflector 6. Because thermoelectric cooling element 10 is in close contact with the back of reflector 6, its cooling energy can directly act on reflector 6, reducing the heat transfer path and time, and improving the response speed of temperature control.

[0054] Thin-film heaters 8 are also mounted on the back of the reflector 6 to heat the reflector 6 when needed to balance temperature fluctuations. Thin-film heaters 8 are thin, flexible, and evenly distributed across the back of the reflector 6, ensuring consistent heating.

[0055] The temperature measuring element 9 is provided on the back of the reflector 6 for real-time monitoring of the temperature change of the reflector 6. The temperature measuring element 9 can be a thermocouple, thermistor or other high-precision temperature sensor, which can provide accurate temperature data for the temperature control component 16, thereby achieving closed-loop control.

[0056] According to one embodiment of the present application, the temperature control assembly 16 includes a heat conductor 11 , which is mounted on the back of the reflector 6 , and the thermoelectric cooling plate 10 , the thin film heating plate 8 and the temperature measuring element 9 are mounted on the heat conductor 11 .

[0057] The primary function of the thermal conductor 11 is to evenly distribute the cooling or heating generated by the thermoelectric cooling sheet 10 and the thin-film heater 8, preventing localized overheating or overheating. Thermal conductor 11 can be made of aluminum-based graphite sheets, which offer high thermal conductivity and are lightweight, enabling rapid heat transfer and uniform temperature maintenance. Alternatively, other high-thermal-conductivity metals (such as copper and aluminum) or non-metallic materials (such as ceramic composites) can be used as alternatives to thermal conductor 11. The specific choice depends on actual needs.

[0058] The heat conductor 11 is mounted directly on the back of the reflector 6, covering a portion of the reflector 6 to ensure that heat or cold is evenly transferred to all parts of the reflector 6. The thermoelectric cooling plate 10, thin film heater 8, and temperature measuring element 9 are mounted on the heat conductor 11, achieving close contact with the back of the reflector 6 through the heat conductor 11, thereby improving heat transfer efficiency.

[0059] According to one embodiment of the present application, the temperature control component 16 includes a crankshaft 7 and a heat sink 12, wherein the crankshaft 7 is arranged on the back of the reflector 6, the crankshaft 7 provides a structural mounting surface for the reflector 7, and an insulating 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 plate 10 to form a thermal path, wherein the crankshaft 7 is a heat sink for the hot end of the thermoelectric cooling plate 10.

[0060] Crankshaft 7 is mounted on the back of reflector 6, but an insulating space is provided between the crankshaft and the back of reflector 6, effectively blocking heat transfer to reflector 6 and preventing direct heat transfer to reflector 6. Crankshaft 7 acts as a heat sink for the hot end of thermoelectric cooler 10, absorbing and dissipating heat generated during operation. The design of crankshaft 7 not only serves as a mounting interface for reflector 6 but also provides a heat dissipation channel for the hot end of thermoelectric cooler 10, ensuring the proper operation of reflector 6.

[0061] Heat sink 12 connects crankshaft 7 and the hot end of thermoelectric cooler 10, forming an efficient heat conduction path. Heat sink 12 can be made of flexible graphite sheets, which offer high thermal conductivity and excellent flexibility, adapting to complex installation environments. Alternatively, heat sink 12 can utilize a fin structure to increase heat dissipation efficiency by increasing surface area. Other materials with high thermal conductivity (such as copper and aluminum) or structures (such as heat pipes) are also possible alternatives to heat sink 12.

[0062] According to one embodiment of the present application, there are two thermoelectric cooling sheets 10, which are disposed on the upper and lower sides of the back surface of the reflector 6; and / or there are two thin-film heating sheets 8, which are disposed on the upper and lower sides of the back surface of the reflector 6. With the thermoelectric cooling sheets 10 and thin-film heating sheets 8 symmetrically distributed on the upper and lower sides, cooling or heating can be evenly transferred to all parts of the reflector 6, significantly improving the temperature uniformity of the reflector 6.

[0063] According to one embodiment of the present application, the temperature control component 16 includes a controller, which is electrically connected to the temperature measuring element 9, the thermoelectric cooling plate 10 and the thin film heating plate 8. The controller is used to control the working state of the thin film heating plate 8 according to the temperature data measured by the temperature measuring element 9.

[0064] The controller's built-in control logic and algorithms accurately determine whether to activate thin-film heater 8 based on temperature data changes. For example, if temperature sensor 9 detects that the temperature of reflector 6 is below a preset threshold, the controller activates thin-film heater 8 to provide heat. If the temperature falls below the preset threshold, solar panel 1, influenced by external heat flow, autonomously activates thermoelectric cooler 10 to provide cooling.

[0065] In one embodiment, the controller can also adjust the working intensity of the thin film heating plate 8 in advance according to the rate and trend of temperature change to achieve more accurate temperature control.

[0066] 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 reflector 6, the temperature control method of this application can achieve high-precision temperature control and ensure communication quality.

[0067] The temperature control device of a space optical load reflector of the present invention is composed of a load reflector 6, a solar panel 1, a thin film heating plate 8, a temperature measuring element 9, a thermoelectric cooling plate 10 and a graphite sheet heat conducting component. The solar panel 1 is installed in a heat-insulated manner from the load body 13, and a multi-layer heat insulation component 173 is designed between the load body 13 and the solar panel 1 to enhance the heat insulation effect. The installation position of the solar panel 1 is selected based on the temperature fluctuation of the reflector 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 reflector 6 as much as possible, so as to ensure that the solar panel 1 has a certain amount of sunlight capture when the temperature of the reflector 6 rises, and generates electricity to drive the thermoelectric cooling plate 10 for cooling. When selecting the solar panel 1, it is necessary to ensure that its output power can meet the needs of the thermoelectric cooling plate 10. It is necessary to select a solar panel 1 whose maximum output voltage matches the operating voltage range of the cooling plate.

[0068] The reflector 6 is thermally insulated from the crankshaft 7, reducing thermal coupling between the mirror and surrounding components. A thin-film heater 8, temperature sensor 9, and thermoelectric cooler 10 are all mounted on the back of the reflector 6, ensuring temperature control through heating and cooling. To improve temperature uniformity across the reflector 6, an aluminum-based graphite sheet is applied to the back of the mirror. To address heat dissipation issues at the hot end of the thermoelectric cooler 10, a flexible graphite sheet is applied to the hot end of the thermoelectric cooler 10, establishing a thermal path between the cooler and the crankshaft 7.

[0069] The temperature control device for the space optical load reflector of the present application is described below with reference to a specific embodiment:

[0070] A temperature control device for a space optical payload reflector comprises a solar panel 1, a thermal insulation gasket 2, a multi-layer thermal insulation assembly 173, a payload heat dissipation surface 4, a payload light inlet 5, a reflector 6, a crankshaft 7, a thin-film heater 8, a temperature measuring element 9, a thermoelectric cooler 10, an aluminum-based graphite sheet, and a flexible graphite sheet. The solar panel 1 is thermally insulated and mounted externally to the payload body 13. Thermal coupling between the solar panel 1 and the payload is reduced through the thermal insulation gasket 2 and the multi-layer thermal insulation assembly 173. The load heat dissipation surface 4 provides a relatively cool background for the internal reflector 6, cooling the reflector 6 on-orbit to maintain a temperature below the required operating level during periods of no sunlight. A closed-loop temperature control system, formed by the thin-film heater 8 and the temperature measuring element 9, controls the reflector 6 to a target temperature. To save energy, precise temperature control of the reflector 6 requires reducing thermal coupling between the reflector 6 and the crankshaft 7, ensuring that both are thermally insulated. The crankshaft 7 is constructed of a material with a low thermal expansion coefficient, providing a mounting interface for the reflector 6 and also serving as a heat sink for the hot end of the thermoelectric cooler 10. A thermoelectric cooler 10 is mounted on the back of the reflector 6. When sunlight on track causes the reflector 6 to heat up, it provides a certain amount of cooling to the reflector 6, suppressing temperature fluctuations and achieving target temperature control. The back of the mirror is first coated with an aluminum-based graphite sheet, followed by a thin-film heater 8, a temperature measuring element 9, and the thermoelectric cooler 10, achieving a uniform mirror surface temperature. A flexible graphite sheet is attached between the hot end of the thermoelectric cooler 10 and the crankshaft 7, utilizing the heat capacity of the crankshaft 7 to dissipate heat from the hot end of the thermoelectric cooler 10.

[0071] The advantages of the present invention are its light weight, simple system configuration, no impact on the pointing rotating parts, and suitability for on-orbit temperature control of smaller components. This method can control the growth of the outer envelope size outside the payload. No additional consumption of the payload's own power consumption resources is required. By utilizing the reason for the increase in the temperature of the reflector 6 (increased external heat flow), cooling is generated, effectively suppressing its temperature increase. When the temperature of the reflector 6 is highest, it is also when the power generation power of the solar panel 1 is the highest, that is, when the cooling capacity of the thermoelectric cooling plate 10 is the largest. The design of the solar panel 1 and the thermoelectric cooling plate 10 completes the real-time supply of the cooling capacity of the pointing mirror. This solves the problem of zero-energy cooling strategy for smaller payloads on the satellite and improves the adaptability of the payload's on-orbit temperature.

[0072] The curve of the heat flux outside the solar panel and the temperature of the reflector 6 (without the thermoelectric cooling sheet 10) during one orbital cycle of an embodiment is as follows: Figure 4 shown.

[0073] According to the external heat flow analysis, the maximum external heat flow per unit area is 1400W / m 2 , based on a conservative estimate of 20% power generation efficiency, 0.01m 2Solar panel 1 can generate up to 2.8W of electricity. A conservative calculation of a 10COP for the thermoelectric cooler (TCE) of 0.4 yields a maximum cooling capacity of 1.12W. In this example, the combined heat flux and ambient radiation from reflector 6 on-orbit is less than 1W. Theoretical analysis demonstrates that the output power of the small-area solar panel 1 can meet the cooling requirements of reflector 6 during on-orbit temperature fluctuations.

[0074] The simulation analysis results of the temperature of the front and rear mirrors using the temperature control device of this application are compared as follows Figure 5 shown.

[0075] The simulation results show that before using the temperature control device of this example, the temperature of the solar radiation reflector 6 fluctuates up to 24.5°C. After using this example, the thermoelectric cooling plate 10 can effectively reduce the on-orbit temperature of the reflector 6 without consuming additional energy resources of the load itself, and the maximum temperature is only 21.5°C, so that the on-orbit temperature of the reflector 6 meets the on-orbit working requirements (20°C±3°C).

[0076] It is foreseeable that if the size of the solar panel 1 is increased or the installation position of the solar panel 1 is optimized, the temperature fluctuation of the reflector 6 on track can be completely avoided. This method is suitable for application scenarios with higher temperature requirements.

[0077] According to the second aspect of the present application, a temperature control method for a space optical load reflector (hereinafter referred to as a temperature control method) is provided as an embodiment, which is applied to the temperature control device of the space optical load reflector. The temperature control method for the space optical load reflector includes steps 100, 200 and 300. Please refer to Figure 6 .

[0078] Step 100: Obtain the temperature of the reflector 6.

[0079] Step 200: Send the acquired temperature data to the controller.

[0080] Step 300: The controller controls the operating state of the thin-film heater 8 based on the comparison result of the temperature data with 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 heater 8 is activated 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 heater 8 is turned off. The thermoelectric cooling plate 10 receives the electrical energy from the solar panel 1 and converts it into cold energy to cool the reflector 6.

[0081] In step 100, the temperature control device can measure the temperature of the reflector 6 in real time through a temperature measuring element 9 installed on the back of the reflector 6. The temperature measuring element 9 can be a thermocouple, thermistor or other high-precision temperature sensor to ensure the accuracy and real-time performance of the temperature data.

[0082] In step 200, the temperature measuring element 9 can transmit the measured temperature data to the controller. The controller, as the core of the heating function of the temperature control assembly 16, is responsible for processing and analyzing the temperature data and making decisions based on pre-set control logic. The operating state of the thermoelectric cooler 10 depends on the lighting conditions of the solar panel 1. When the temperature of the reflector 6 gradually rises, the lighting area of ​​the surface solar panel 1 becomes poor, and the power generation increases, resulting in an increase in the cooling capacity of the thermoelectric cooler 10, thereby cooling the reflector 6.

[0083] In step 300 , the controller has a preset temperature range (eg, a lower limit of Tmin and an upper limit of Tmax) built in to determine whether the temperature of the reflector 6 is in an ideal state.

[0084] If the real-time temperature data is lower than Tmin, the controller activates the thin film heater 8, which converts electrical energy into heat to quickly increase the temperature of the reflector 6. The working intensity of the thin film heater 8 can also be dynamically adjusted according to the size of the temperature deviation to ensure the accuracy and uniformity of the heating process.

[0085] It can be understood that by acquiring temperature data in real time and combining it with the controller's intelligent judgment, this method can ensure that the temperature of the reflector 6 is always maintained within a preset range, preventing temperature fluctuations from affecting the performance of the optical system. By combining closed-loop and open-loop control, the device can monitor and adjust the temperature of the reflector 6 in real time, preventing the impact of temperature fluctuations on the performance of the optical system.

[0086] 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 it. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent replacements for some of the technical features therein. However, these modifications or replacements do not deviate the essence of the corresponding technical solutions 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 entrance surface (14), the load light entrance surface (14) is provided with a load light entrance port (5), and the load light entrance port (5) is connected to the accommodating cavity (15) inside the load body (13); A solar panel (1) is provided on the outer surface of the load body (13); A reflector (6) is installed in the accommodating cavity (15) and is provided at the load light inlet (5). When affected by an external heat flow, the temperature fluctuation trend of the reflector (6) in the load body (13) is correlated with the 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), and the temperature control component (16) includes a thermoelectric cooling plate (10), a thin film heating plate (8) and a temperature measuring element (9). The thermoelectric cooling plate (10) is electrically connected to the solar panel (1), and the thin film heating plate (8) and the temperature measuring element (9) are 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 plate (10) and the thin film heating plate (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 assembly (17) comprises a thermal insulation gasket (2) and a plurality of thermal insulation members (3), wherein 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 members (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 mirror (6) according to claim 1, characterized in that: The thermoelectric cooling plate (10), the thin film heating plate (8) and the temperature measuring element (9) are all arranged on the back side of the reflector (6).

5. The temperature control device of the space optical load mirror (6) according to claim 4, characterized in that: The temperature control assembly (16) includes a heat conducting member (11), the heat conducting member (11) is mounted on the back of the reflector (6), and the thermoelectric cooling plate (10), the thin film heating plate (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 mirror (6) according to claim 4, characterized in that: The temperature control assembly (16) includes a crankshaft (7) and a heat sink (12), wherein 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 plate (10) to form a heat path, wherein the crankshaft (7) is a heat sink for the hot end of the thermoelectric cooling plate (10).

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

8. The temperature control device of the space optical load mirror (6) according to any one of claims 1 to 7, characterized in that: The temperature control component (16) includes 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) based on the 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) according to 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 electrical energy of the solar panel (1) and converts it into cold energy to cool the reflector (6).

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