Modularized satellite inter-module temperature equalizing system and thermal control system

Abstract

The invention relates to the technical field of aerospace thermal control, in particular to a modular satellite inter-module temperature equalizing system and a thermal control system. The temperature equalizing system comprises a driving section, a driven section and a plurality of hoses, the driving section and the driven section are communicated through a hose to form a circulating pipeline; the driving section comprises a first pipeline, a pump and a second pipeline which are sequentially connected, and the driven section comprises a third pipeline; two ends of the hose are respectively connected with the driving section and the driven section; the circulation pipeline is filled with a thermal control working medium, and the pump provides driving force for flowing of the thermal control working medium in the circulation pipeline. The thermal control system comprises a plurality of temperature equalizing systems among the modularized satellite modules and further comprises a plurality of modularized satellite modules, and each driving section and each driven section are installed on the edges of every two adjacent modularized satellite modules respectively. The temperature equalizing system and the thermal control system are easy to fold and unfold, the temperature equalizing effect is not affected by folding and unfolding, the requirement for the folding and unfolding functions of a modular satellite folded and unfolded for multiple times can be met, and the temperature equalizing system and the thermal control system are easy to integrate with standardized modules of the modular satellite.

Description

Technical Field

[0001] This application relates to the field of aerospace thermal control technology, and in particular to a modular satellite module temperature equalization system and thermal control system. Background Technology

[0002] To avoid excessive temperature differences between similar components, which could lead to phase discrepancies, the thermal control system of a communication satellite must ensure temperature uniformity among them. For modular communication satellites with multiple folding and unfolding configurations, the thermal control system must guarantee temperature uniformity among similar components within each module of the entire array. Therefore, it is necessary to enhance heat transfer between modules and reduce temperature differences between them. Simultaneously, the thermal control system design must also adapt to the requirements of modularity, mass production, easy expansion, and deployability.

[0003] Traditional thermal control systems typically use heat pipes, VC vapor chambers, and fluid loops to enhance heat transfer and reduce temperature differences in order to ensure temperature uniformity. However, if heat pipes and VC vapor chambers are fixedly installed on multiple modules, it will affect the unfolding process. If they are fixedly installed on only one side of the module, it will be impossible to guarantee heat conduction between them and adjacent modules after unfolding.

[0004] Existing fluid loop system designs are not yet adapted to the requirements of modularity, mass production, and easy expansion. Summary of the Invention

[0005] The purpose of this application is to provide a modular satellite module temperature equalization system and thermal control system to address at least one of the technical problems involved in the background art.

[0006] Firstly, this application provides a modular satellite module temperature equalization system, including an active section, a driven section, and several flexible hoses; The active section and the driven section are respectively used to install on two adjacent modular satellite modules, and the active section and the driven section are connected by the hose to form a circulation pipeline; The active section includes a first pipeline, a pump, and a second pipeline connected in sequence, with self-sealing disconnectors connected to the ends of the first pipeline and the second pipeline away from the pump, respectively. The driven section includes a third pipeline, and self-sealing disconnectors are connected to both ends of the third pipeline; The two ends of the hose are respectively connected to the self-sealing disconnector of the active section and the self-sealing disconnector of the driven section. The circulation pipeline is filled with a thermal control working fluid, and the pump provides driving force for the flow of the thermal control working fluid in the circulation pipeline.

[0007] In a preferred embodiment, the driven section further includes a flow sensor and a fourth pipeline, wherein the third pipeline, the flow sensor and the fourth pipeline are connected in sequence, and a self-sealing disconnector is connected to the end of the third pipeline and the fourth pipeline away from the flow sensor, respectively. The flow sensor is used to detect the flow rate of the thermal control fluid in the circulation pipeline per unit time.

[0008] In a preferred embodiment, in the deployed state of the temperature equalization system between modular satellite modules, the central axes of the active segment and the driven segment are coplanar.

[0009] In a preferred embodiment, when the temperature equalization system between modular satellite modules is deployed, the flexible tube is in a bent shape to allow for folding allowance.

[0010] In a preferred embodiment, the thermal control fluid is at least one of ammonia, aqueous ethylene glycol solution, perfluorotriethylamine, hydrofluoroether, and perfluoropolyether.

[0011] In a preferred embodiment, at least one of the first pipeline, the second pipeline, the third pipeline, and the fourth pipeline includes a pipe body and fins; The fins are planar, with one side fitting against the tube body and the other side used for contacting the surface of the modular satellite module.

[0012] In a preferred embodiment, the inner diameter of the tube is 2mm to 6mm and the wall thickness is 0.5mm to 1.5mm; the width of the fins is 6mm to 12mm.

[0013] Secondly, this application provides a thermal control system, including a temperature equalization system between multiple modular satellite modules, and also including multiple modular satellite modules and a controller; The modular satellite module includes a mounting plate, and a plurality of mounting positions for mounting controlled heat sources are provided on the surface of the mounting plate, and temperature sensors are respectively provided in each edge region of the mounting plate; Multiple modular satellite modules are assembled into a whole by splicing the sides of each mounting plate. The temperature equalization system between each modular satellite module is installed at the edge of two adjacent mounting plates; The pump, the flow sensor, and the temperature sensor are each electrically connected to the controller.

[0014] In a preferred embodiment, two adjacent mounting plates have a common splicing edge; in the temperature equalization system between each modular satellite module, the active segment is arranged along the splicing edge of one mounting plate, and the driven segment is arranged along the splicing edge of the other adjacent mounting plate.

[0015] In a preferred embodiment, the side surface of the mounting plate with the mounting position is a positive even-numbered polygon with a side count of 4 or more.

[0016] In a preferred embodiment, the number of active segments and passive segments are the same on a single mounting plate; The active segment and the driven segment are installed alternately or sequentially on each side of the mounting plate.

[0017] The beneficial effects of this application are: Compared to heat pipes and VC vapor chambers, the modular satellite module heat exchange system provided in this application is easy to unfold and unfold without affecting the heat exchange effect, and can meet the unfolding function requirements of modular satellites that need to be unfolded multiple times.

[0018] In addition, the temperature equalization system and thermal control system between the modular satellite modules are easy to integrate with the standardized modules of the modular satellite, and can be adjusted and expanded arbitrarily according to the number of modular satellite modules required, making it easy to mass-produce. Attached Figure Description

[0019] To more clearly illustrate the technical solutions of the specific embodiments of this application, the accompanying drawings used in the description of the specific embodiments will be briefly introduced below. Obviously, the accompanying drawings described below are some embodiments of this application. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0020] Figure 1 A first-view schematic diagram of a modular satellite module temperature equalization system provided in an embodiment of this application; Figure 2 A second-view schematic diagram of a modular satellite module temperature equalization system provided in an embodiment of this application; Figure 3 This is a cross-sectional view of the first pipeline; Figure 4 A schematic planar structure diagram of a first embodiment of a single module of the thermal control system provided in this application; Figure 5 A schematic planar structure diagram of a second embodiment of a single module of the thermal control system provided in this application; Figure 6 for Figure 5 A schematic diagram of the three-dimensional structure; Figure 7 for Figure 5 A schematic diagram of the exploded structure; Figure 8 For multiple Figure 5 The diagram shows a three-dimensional structure where individual modules are interconnected. Figure 9For 4×4 Figure 5 The diagram shows the structure of a modular satellite composed of single modules. Figure 10 A temperature simulation diagram of components for a 4×4 modular satellite that does not use the inter-module temperature equalization system provided in the embodiments of this application; Figure 11 A schematic diagram of component temperature simulation for the inter-module temperature equalization system provided in this application embodiment for a 4×4 modular satellite; Figure 12 A schematic planar structure diagram of a third embodiment of a single module of the thermal control system provided in this application; Figure 13 For 7 Figure 12 The diagram shows a modular satellite three-dimensional structure composed of single modules. Figure label: 1-First conduit; 101-Pipe body; 102-Fin; 2-Second pipeline; 3-Third pipeline; 4-Fourth pipeline; 5-Pump; 6-Flow sensor; 7-Self-sealing disconnector; 8-Temperature sensor; 9-Mounting plate; 10-Mounting position; 11-Hose. Detailed Implementation

[0021] The technical solutions of this application will now be clearly and completely described with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of this application. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0022] In the description of this application, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0023] In the description of this application, it should be noted that, unless otherwise expressly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection between two components. Those skilled in the art can understand the specific meaning of the above terms in this application based on the specific circumstances.

[0024] like Figure 1 and Figure 2 As shown, the modular satellite module temperature equalization system provided in this embodiment includes an active section, a driven section, and several flexible hoses 11; The active section and the driven section are respectively installed on two adjacent modular satellite modules, and the active section and the driven section are connected by hose 11 to form a circulation pipeline; The active section includes a first pipeline 1, a pump 5, and a second pipeline 2 connected in sequence, with self-sealing disconnectors 7 connected to the ends of the first pipeline 1 and the second pipeline 2 away from the pump 5, respectively. The driven section includes a third pipe 3, a flow sensor 6 and a fourth pipe 4 connected in sequence, and a self-sealing disconnector 7 is connected to the end of the third pipe 3 and the fourth pipe 4 away from the flow sensor 6 respectively; The two ends of the hose 11 are connected to the self-sealing disconnector 7 of the active section and the self-sealing disconnector 7 of the driven section, respectively. The hose 11 can deform without being damaged during the unfolding process.

[0025] The self-sealing disconnector 7 is used to fill the active section, driven section, and hose 11 with a heat-controlled working fluid, and to connect the active section, driven section, and hose 11 to form a circulation pipeline, and to self-seal before connection.

[0026] The circulating pipeline is filled with a thermal control working fluid. Pump 5 provides driving force for the flow of the thermal control working fluid in the circulating pipeline. Flow sensor 6 is used to detect the flow rate of the thermal control working fluid in the circulating pipeline per unit time.

[0027] In the deployed state of the temperature equalization system between modular satellite modules, the central axes of the active and driven sections are coplanar, and the hose 11 is in a bent state to allow for folding allowance.

[0028] like Figure 3 As shown, the first pipeline 1 includes a pipe body 101 and fins 102; the fins 102 are planar, with one side attached to the pipe body 101 and the other side used to attach and contact the surface of the modular satellite module, so that the cross-section of the first pipeline 1 is “Ω” shaped.

[0029] In this embodiment, the inner diameter of the tube body 101 is 2mm~6mm, preferably 4mm, and the wall thickness is 0.5mm~1.5mm, preferably 1mm; the width of the fin 102 is 6mm~12mm, preferably 8mm.

[0030] Similarly, the second pipe 2, the third pipe 3, and the fourth pipe 4 can all adopt the same structure as the first pipe 1, which will not be elaborated here.

[0031] The heat control fluid in the circulation pipeline is at least one of ammonia, ethylene glycol aqueous solution, perfluorotriethylamine, hydrofluoroether, and perfluoropolyether.

[0032] In another implementation, the driven section may not be equipped with a flow sensor 6, but can be connected to the self-sealing disconnectors 7 at both ends by a third pipe 3.

[0033] In a preferred embodiment, pump 5 is flat and preferably a piezoelectric ceramic pump, which is installed on the circulation pipeline to provide driving force for the flow of the thermostatic working fluid.

[0034] Compared to heat pipes and VC vapor chambers, the vapor chamber system provided in this embodiment is easy to fold and unfold, and folding and unfolding does not affect the vapor chamber effect, which can meet the requirements of modular satellites that need to be folded and unfolded multiple times.

[0035] In a preferred embodiment, the main structures of both the active and driven segments are made of high thermal conductivity metal materials compatible with the thermal control fluid. The metal materials can withstand the space environment in which the satellite is located without any change in material properties, and can also withstand the pressure difference between the thermal control fluid and the external space vacuum environment. Using high thermal conductivity metal materials can reduce the temperature difference between the thermal control fluid and the controlled heat source, ensuring the temperature control requirements of the controlled heat source.

[0036] In a preferred embodiment, the main structure of the active and driven sections uses a high thermal conductivity metal material compatible with the thermal control working fluid, which is at least one of aluminum alloy, magnesium alloy, magnesium-lithium alloy, and aluminum-lithium alloy.

[0037] Optionally, the components of the active section and the components of the driven section are connected by welding. Compared with the non-metallic sealing rings used in threaded connections, which increase leakage and cause compatibility issues with the thermostat, the welding method does not use non-metallic sealing rings, thereby reducing leakage and avoiding thermostat compatibility problems.

[0038] In this embodiment, the welding method is vacuum brazing, flame brazing, or argon arc welding.

[0039] This embodiment also provides a thermal control system, including a temperature equalization system between multiple modular satellite modules, and also includes multiple modular satellite modules; The modular satellite module includes a mounting plate, and several mounting positions for mounting controlled heat sources are set on the surface of the mounting plate. Temperature sensors are set in each edge area of ​​the mounting plate. Multiple modular satellite modules are assembled into a whole by splicing the sides of each mounting plate. The temperature equalization system between each modular satellite module is installed at the edge of two adjacent mounting plates.

[0040] like Figure 4 As shown, a single module of the aforementioned thermal control system is provided. The mounting plate 9 has a square structure with several mounting positions 10 arranged in an array on it. The active section of the temperature equalization system between the two modular satellite modules is provided along two edges of the mounting plate 9, including a first pipe 1, a pump 5, a second pipe 2, and self-sealing disconnectors 7 at both ends; the driven section of the temperature equalization system between the two modular satellite modules is provided along the other two edges, including a third pipe 3 and self-sealing disconnectors 7 at both ends.

[0041] The active section and the driven section are connected to the mounting plate 9 by heat transfer, such as by clamp connection and filling the gap with heat-conducting filler; or the active section and the mounting plate 9, as well as the driven section and the mounting plate 9, are directly integrated into one structure; or the active section and the mounting plate 9, as well as the driven section and the mounting plate 9, are welded together.

[0042] In use, multiple single-module mounting plates 9 are spliced ​​side by side, with the side with the active section facing the side with the driven section, and then adjacent active and driven sections are connected by hoses 11.

[0043] like Figures 5-7 As shown, this embodiment also provides a single module of a better thermal control system.

[0044] The mounting plate 9 is a square structure with several mounting positions 10 arranged in an array on it. Two active sections of the modular satellite module temperature equalization system are located along two edges of the mounting plate 9, including a first pipe 1, a pump 5, a second pipe 2, and self-sealing disconnectors 7 at both ends. Two driven sections of the same system are located along the other two edges, including a third pipe 3, a flow sensor 6, a fourth pipe 4, and self-sealing disconnectors 7 at both ends. Temperature sensors 8 are located at each corner of the mounting plate 9.

[0045] The active section and the driven section are connected to the mounting plate 9 by heat transfer, such as by clamp connection and filling the gap with heat-conducting filler; or the active section and the mounting plate 9, as well as the driven section and the mounting plate 9, are directly integrated into one structure; or the active section and the mounting plate 9, as well as the driven section and the mounting plate 9, are welded together.

[0046] In use, multiple single-module mounting plates 9 are spliced ​​side-by-side, with the side containing the active section aligned with the side containing the driven section. Adjacent active and driven sections are then connected via hoses 11. Pump 5, flow sensor 6, and temperature sensor 8 are electrically connected to the controller.

[0047] When the thermal control system is running, the controller determines whether to increase / decrease the power of the pump 5 based on the temperature uniformity collected by the temperature sensor 8 on the edge area of ​​the adjacent mounting plate 9, thereby adjusting the flow rate of the thermal control working fluid.

[0048] Depend on Figures 5-7 The modular satellite three-dimensional structure formed by connecting the individual modules shown is as follows: Figure 8 As shown, the connection relationship between each module and the arrangement of the temperature equalization system between modular satellite modules on each module can be clearly seen.

[0049] The following is a comparative example illustrating the temperature control effect of this application.

[0050] like Figure 9 As shown, the modular communication satellite consists of 4×4 standardized single modules. Each module's TR (Transient Temperature Regulator) component mounting plate has an area of ​​640mm×640mm, with 64 mounting positions per plate. One TR component is installed in each position, evenly distributed. Each TR component has a maximum heat output of 1.75W, and the temperature difference between all TR components in the entire satellite must not exceed 0.5℃. The temperature equalization system between modular satellite modules has an inner diameter of 4mm and a wall thickness of 1mm for each tube. It uses piezoelectric pumps and is equipped with flow sensors. Clearance holes are made inside the mounting plate according to the pump and sensor positions. The fins are screwed onto the mounting plate after being coated with thermal grease.

[0051] When the satellite orbits at an altitude of 535 km and the angle between the sunlight and the orbital plane is 0°, if the temperature equalization system of this embodiment is not used, such as Figure 10 As shown, according to simulation analysis, the highest temperature of the TR component is 70.96℃, the lowest temperature is 70.15℃, and the temperature difference is 0.81℃, which is greater than the design threshold and does not meet the requirements.

[0052] Under the same conditions, using the temperature equalization system provided in this embodiment, when the flow rate of each system is 420 ml / min, such as Figure 11 As shown, according to simulation analysis, the highest temperature of the TR component is 69.97℃ and the lowest temperature is 69.65℃, with a temperature difference of 0.32℃, which meets the design requirements.

[0053] In other embodiments, the mounting plate is not limited to a square, and the side surface with the mounting position can be a positive even-numbered polygon with 6 or more sides.

[0054] On one of the mounting plates, the number of active segments and driven segments are the same; each active segment and each driven segment is installed alternately or continuously on each side of the mounting plate.

[0055] like Figure 12 As shown, the mounting plate 10 of the single module is in the shape of a regular hexagon, and several mounting positions 10 are arranged in a hexagonal array on it. Active and passive sections are staggered on the six sides of the mounting plate 9, and temperature sensors 8 are respectively installed at each corner of the mounting plate 9.

[0056] When using, such as Figure 13 As shown, 7 can be Figure 12 The mounting plates of the single module shown are spliced ​​side by side to form a thermal control system.

[0057] The modular satellite module temperature equalization system and thermal control system of this application are easy to integrate with the standardized modules of modular satellites, can be arbitrarily adjusted and expanded according to the quantity requirements of modular satellite modules, and are easy to mass-produce.

[0058] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of this application, and are not intended to limit them. Although this application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features therein. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of this application.

Claims

1. A modular satellite module inter-module temperature equalization system, characterized in that, It includes a driving section, a driven section, and several hoses; The active section and the driven section are respectively used to install on two adjacent modular satellite modules, and the active section and the driven section are connected by the hose to form a circulation pipeline; The active section includes a first pipeline, a pump, and a second pipeline connected in sequence, with self-sealing disconnectors connected to the ends of the first pipeline and the second pipeline away from the pump, respectively. The driven section includes a third pipeline, and self-sealing disconnectors are connected to both ends of the third pipeline; The two ends of the hose are respectively connected to the self-sealing disconnector of the active section and the self-sealing disconnector of the driven section. The circulation pipeline is filled with a thermal control working fluid, and the pump provides driving force for the flow of the thermal control working fluid in the circulation pipeline.

2. The modular satellite module temperature equalization system according to claim 1, characterized in that, The driven section also includes a flow sensor and a fourth pipeline. The third pipeline, the flow sensor, and the fourth pipeline are connected in sequence, and self-sealing disconnectors are respectively connected to the ends of the third pipeline and the fourth pipeline away from the flow sensor. The flow sensor is used to detect the flow rate of the thermal control fluid in the circulation pipeline per unit time.

3. The modular satellite module temperature equalization system according to claim 2, characterized in that, In the deployed state of the temperature equalization system between modular satellite modules, the central axes of the active segment and the driven segment are coplanar.

4. The modular satellite module temperature equalization system according to claim 2, characterized in that, The thermal control fluid is at least one of ammonia, ethylene glycol aqueous solution, perfluorotriethylamine, hydrofluoroether, and perfluoropolyether.

5. The modular satellite module temperature equalization system according to claim 2, characterized in that, At least one of the first pipeline, the second pipeline, the third pipeline, and the fourth pipeline includes a tube body and fins; The fins are planar, with one side fitting against the tube body and the other side used for contacting the surface of the modular satellite module.

6. The modular satellite module temperature equalization system according to claim 5, characterized in that, The inner diameter of the tube is 2mm~6mm, and the wall thickness is 0.5mm~1.5mm; the width of the fins is 6mm~12mm.

7. A thermal control system, characterized in that, The system includes a modular satellite module temperature equalization system as described in any one of claims 2 to 6, and further includes multiple modular satellite modules and a controller; The modular satellite module includes a mounting plate, and a plurality of mounting positions for mounting controlled heat sources are provided on the surface of the mounting plate, and temperature sensors are respectively provided in each edge region of the mounting plate; Multiple modular satellite modules are assembled into a whole by splicing the sides of each mounting plate. The temperature equalization system between each modular satellite module is installed at the edge of two adjacent mounting plates; The pump, the flow sensor, and the temperature sensor are each electrically connected to the controller.

8. The thermal control system according to claim 7, characterized in that, Two adjacent mounting plates have a common splicing edge; in the temperature equalization system between each modular satellite module, the active segment is arranged along the splicing edge of one mounting plate, and the driven segment is arranged along the splicing edge of the other adjacent mounting plate.

9. The thermal control system according to claim 7, characterized in that, The mounting plate has a mounting position on one side surface that is a positive even-numbered polygon with 4 or more sides.

10. The thermal control system according to claim 9, characterized in that, On one of the mounting plates, the number of the active segment and the number of the driven segment are the same; The active segment and the driven segment are installed alternately or sequentially on each side of the mounting plate.

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