Spacecraft modular thermal control system and regulation and control method

Abstract

The invention relates to a modularized thermal control system and a regulation and control method for a spacecraft, the modularized thermal control system comprises modularized thermal control units, a thermal management center, a thermal control network and an auxiliary thermal control assembly, and temperature data are collected in real time through high-precision temperature sensors distributed at key positions of the thermal control system, such as an inlet and an outlet of each modularized thermal control unit, an equipment surface and the like; and the data is transmitted to a thermal management center through a thermal control network. According to the modularized thermal control unit, standardized interface design is adopted, flexible combination and disassembly of the modules can be easily achieved according to task requirements, equipment layout and thermal load changes of a spacecraft, so that the thermal control system can rapidly adapt to different spacecraft platforms and task changes, the universality and adaptability of the thermal control system are greatly improved, and the thermal control system is suitable for large-scale popularization and application. When equipment upgrading or function expansion is carried out on the spacecraft, only the corresponding thermal control module needs to be added, large-scale redesign and transformation of the whole thermal control system are not needed, and cost and time are remarkably reduced.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of spacecraft thermal control technology, in particular to a spacecraft modular thermal control system and a regulation and control method. BACKGROUND

[0002] In the operation process of a spacecraft, the thermal control system plays a crucial role, which is directly related to the normal operation and service life of each device of the spacecraft. The spacecraft will face extremely complex and harsh thermal environments in space, such as large changes in solar radiation intensity, earth albedo heat flow, and low-temperature background in deep space. Different spacecraft missions, such as communication, remote sensing, scientific exploration, etc., have different requirements for the thermal control system. With the continuous development of space technology, spacecraft are gradually developing towards multi-function, long life, high reliability and miniaturization, which poses more stringent challenges to the thermal control system.

[0003] The traditional spacecraft thermal control system has many limitations when facing these challenges. It mostly adopts a relatively fixed design mode, which is difficult to adapt flexibly according to the changes of spacecraft missions and the adjustment of device layout. When facing the replacement of spacecraft devices or the addition of new functional modules, the traditional thermal control system often needs to be redesigned and modified on a large scale, which not only consumes a lot of time and cost, but also may reduce reliability due to system compatibility problems. Moreover, the traditional thermal control system is also difficult to meet the growing needs of modern spacecraft in terms of heat dissipation efficiency, temperature uniformity control and energy utilization efficiency. In some areas where high-power devices are concentrated, the traditional thermal control system often fails to dissipate heat in time, resulting in high device temperature and affecting its performance and life.

[0004] With the widespread application of modular design concepts in the field of spacecraft, the structure and function of spacecraft are gradually modularized. However, the existing thermal control system has obvious deficiencies in adapting to modular spacecraft, and cannot fully realize the advantages brought by modular design. Therefore, developing a thermal control system and regulation and control method that can closely adapt to modular spacecraft has become a key problem to be solved in the field of spacecraft thermal control technology. SUMMARY

[0005] In view of the deficiencies of the prior art, the present application provides a spacecraft modular thermal control system and a regulation and control method to solve the problems that the existing spacecraft thermal control system cannot effectively adapt to modular spacecraft and has deficiencies in heat dissipation efficiency, temperature uniformity control and energy utilization efficiency. Through innovative modular design, flexible configuration, efficient heat dissipation, precise temperature control and rational use of energy of the thermal control system are realized, thereby improving the overall performance and reliability of the spacecraft.

[0006] To achieve the above object, the present application provides the following technical solutions: a spacecraft modular thermal control system, comprising:

[0007] A modular thermal control unit, composed of a heat dissipation module, a temperature control module and a heat conduction module, each module is flexibly combined and detached through a standardized interface; wherein the heat dissipation module adopts a specially designed heat dissipation structure and high-performance heat dissipation materials, which can quickly dissipate the heat generated by the equipment; the temperature control module has precise temperature regulation capability, through advanced temperature sensors and intelligent control algorithms, precise temperature regulation is realized; the heat conduction module uses high-efficiency heat conduction materials and optimized structure design to ensure that heat can be quickly and stably transferred to the heat dissipation module;

[0008] A thermal management center for unified management and control of each modular thermal control unit, formulating control strategies according to temperature data and operating state information; the thermal management center intelligently manages and controls the thermal control system through highly integrated control circuits and advanced control algorithms, can collect temperature data and operating state information from each module in real time, and make in-depth analysis and intelligent decision-making based on these data;

[0009] A thermal control network connecting each modular thermal control unit and the thermal management center, realizing data communication and heat transfer; the thermal control network uses high-speed and reliable communication protocols for data transmission, and high-efficiency heat transfer medium and carefully designed heat conduction paths for heat transfer, and has scalability and fault tolerance, when new thermal control units need to be added, they can be easily connected to the network, and when some network nodes fail, the data and heat transfer paths can be automatically switched;

[0010] An auxiliary thermal control component, including thermal insulation material and heating elements, for reducing thermal interference between devices and providing heat compensation in extreme low temperature environments; the thermal insulation material has very low thermal conductivity, which can effectively prevent heat transfer between devices, and the heating elements can automatically start and adjust the heating power according to the feedback of the temperature sensor, ensuring that the device can work normally in low temperature environment.

[0011] Further, the specially designed heat dissipation structure of the heat dissipation module is one or a combination of interdigital, micro-channel or jet heat dissipation structures according to different equipment heat load and layout characteristics, and the high-performance heat dissipation material is one or a combination of high thermal conductivity metal matrix composite material, carbon nanotube reinforced composite material or high emissivity coating material.

[0012] Further, the temperature sensor in the temperature control module has an accuracy of ±0.1℃ or less, and the intelligent control algorithm is one or a combination of fuzzy logic control, neural network control and model predictive control, to realize precise temperature regulation.

[0013] Further, the high-efficiency heat conduction material of the heat conduction module is one or more of graphene-based heat conduction material, liquid metal-based heat conduction material or high-performance heat-conducting silica gel, and the optimized structural design is integrated molding, multi-layer composite structure or structure with special flow channel design to improve heat transfer efficiency and stability.

[0014] Further, the control circuit of the thermal management center adopts a low-power and high-reliability integrated circuit chip with redundancy design, and an advanced control algorithm can adaptively adjust the control strategy according to the spacecraft flight stage, device working mode and thermal environment change, and the response time of the control strategy is not more than 1 second.

[0015] Further, the data communication rate of the thermal control network is not less than 10 Mbps, the thermal conductivity of the heat transfer medium is not less than 10 W / (m·K), the network topology structure is one or more combinations of star type, bus type or ring structure, and has self-diagnosis and self-repair functions, and the fault switching time is not more than 0.5 seconds.

[0016] Further, the thermal conductivity of the heat conduction material is less than 0.01 W / (m·K), the heating power adjustment range of the heating element is 0-100 W, the response time is not more than 2 seconds, and it has overheat protection and overcurrent protection functions.

[0017] A control method based on the spacecraft modular thermal control system of any one of claims 1-7, comprising the following steps:

[0018] Data acquisition: real-time acquisition of temperature data by high-precision temperature sensors distributed at key positions of the thermal control system, such as the inlet and outlet of each modular thermal control unit, the surface of the equipment, etc., and transmission of the data to the thermal management center through the thermal control network; the thermal management center processes and filters the original temperature data, removes abnormal data, and records the data acquisition time, and the sampling frequency of the temperature sensor is not less than 1 Hz;

[0019] Data analysis and decision-making: the thermal management center uses advanced data analysis algorithms and intelligent decision-making models to analyze the collected temperature data in depth; by comparing with the pre-set temperature threshold, it judges whether the current thermal control system is running normally; if it finds that the temperature of a certain area exceeds the normal range, it will further analyze the reason for the temperature anomaly, and according to the analysis result, it will formulate the corresponding control strategy, and the advanced data analysis algorithm and intelligent decision-making model are constructed based on one or more technologies of big data analysis, machine learning and deep learning;

[0020] Regulation execution: The thermal management center sends precise control instructions to the relevant modular thermal control units through the thermal control network; after receiving the instructions, each modular thermal control unit quickly responds and performs corresponding operations, such as adjusting the cooling or heating power of the temperature control module, starting the standby cooling fan of the cooling module, adjusting the fan speed or changing the angle of the cooling fins, optimizing the heat transfer path of the heat conduction module, etc.; During the execution of the regulation operation, each module will feedback its running state to the thermal management center in real time, and the update frequency of the feedback information is not less than 0.5Hz;

[0021] Dynamic optimization: The thermal control system is in a dynamically changing space environment, and the thermal management center continuously monitors and analyzes the operation data of the thermal control system in real time; according to the changes in the flight attitude of the spacecraft, the switching of the device working mode, and the fluctuations of the space environment temperature and other factors, the regulation strategy is dynamically optimized in time, such as adjusting the heating power of the heating element and the working mode of the cooling module; The time interval of dynamic optimization is not more than 5 minutes.

[0022] Further, it also includes collecting the working state parameters of the key components of the thermal control system, such as the cooling fan speed, the refrigerant flow of the temperature control module, and the heating element current, and transmitting them to the thermal management center through the thermal control network, and the sampling frequency of the working state parameters is not less than 0.5Hz.

[0023] Further, in the data analysis and decision-making step, the thermal management center also has a fault diagnosis function, which can judge whether the thermal control system has a fault according to the temperature data and the working state parameters of the key components, and if there is a fault, it can quickly locate the fault module and the fault type, and generate a fault report, the accuracy rate of fault diagnosis is not less than 95%, and the fault positioning time is not more than 3 seconds.

[0024] Compared with the prior art, the technical scheme of the present application has the following beneficial effects:

[0025] 1、The modular thermal control unit of the present application adopts standardized interface design, which can easily realize flexible combination and disassembly of modules according to the mission requirements of the spacecraft, device layout and thermal load changes. This makes the thermal control system quickly adapt to different spacecraft platforms and task changes, greatly improving the versatility and adaptability of the thermal control system. When the spacecraft upgrades or expands functions, only the corresponding thermal control module needs to be added, without the need for large-scale redesign and modification of the entire thermal control system, significantly reducing cost and time.

[0026] 2、The heat dissipation module of the application adopts a specially designed heat dissipation structure and high-performance heat dissipation material, greatly improving the heat dissipation efficiency; the heat conduction module ensures that heat can be rapidly and uniformly transmitted to the heat dissipation module through optimized structural design and high-efficiency heat conduction material. Combined with the precise control of the thermal management center, the temperature uniformity between various devices of the spacecraft can be effectively guaranteed, avoiding the impact on device performance and service life caused by local overheating or overcooling. In areas where high-power devices are concentrated, by reasonably configuring the heat dissipation module and the heat conduction module, the temperature fluctuation can be controlled within a very small range, improving the stability and reliability of the devices. The thermal management center can accurately adjust the working state of each modular thermal control unit according to the actual thermal demand of the spacecraft through real-time monitoring and intelligent control, avoiding energy waste. When the thermal load of the device is low, the speed of the cooling fan or the refrigeration / heating power of the temperature control module is automatically reduced, thereby realizing efficient use of energy and prolonging the service life of the spacecraft. During certain mission stages of the spacecraft, some devices are in a low-power state, and the thermal management center can timely adjust the working mode of the thermal control system to reduce energy consumption and improve energy utilization efficiency.

[0027] 3、The block design of the application makes each thermal control unit relatively independent, so that when one module fails, it will not affect the normal work of other modules. The thermal management center can monitor the running state of each module in real time, timely find and locate the faulty module, and facilitate quick repair or replacement. Moreover, the fault-tolerant design of the thermal control network ensures that the thermal control system can still operate normally when some network nodes fail, greatly improving the reliability and maintainability of the thermal control system. During the long-term operation of the spacecraft, even if a thermal control module fails, the continuous and stable operation of the thermal control system can be ensured through the rapid diagnosis of the thermal management center and the switching of the standby module, reducing the impact of thermal control system failure on the spacecraft mission. BRIEF DESCRIPTION OF DRAWINGS

[0028] Fig. 1 A framework diagram of a spacecraft modular thermal control system of the application;

[0029] Fig. 2 A regulation and control method flow chart of a spacecraft modular thermal control system of the application. DETAILED DESCRIPTION

[0030] The technical solutions in the embodiments of the application will be described clearly and completely below with reference to the drawings in the embodiments of the application. Obviously, the described embodiments are only part of the embodiments of the application, rather than all the embodiments. Based on the embodiments in the application, all other embodiments obtained by those skilled in the art without creative work fall within the protection scope of the application.

[0031] Please refer to Figs. 1-2The spacecraft modular thermal control system in the embodiment comprises:

[0032] Modular thermal control unit: The unit is the core component of the entire thermal control system, composed of multiple modules with different functions but mutual coordination. Specifically, it includes a heat dissipation module for achieving efficient heat dissipation function, which adopts a specially designed heat dissipation structure and high-performance heat dissipation material, capable of quickly dissipating the heat generated by the equipment; a temperature control module with precise temperature regulation capability, which realizes precise temperature regulation through advanced temperature sensors and intelligent control algorithms; and a heat conduction module responsible for heat transfer, which uses efficient heat conduction materials and optimized structural design to ensure that heat can be quickly and stably transferred to the heat dissipation module. These modules adopt standardized interface design in structure, so that they can be flexibly combined and disassembled according to the specific needs of the spacecraft. In a certain type of spacecraft, according to the equipment layout and heat load distribution, a number of heat dissipation modules are flexibly added, effectively solving the problem of local overheating.

[0033] Thermal management center: The thermal management center is like the "brain" of the entire thermal control system, which conducts all-round unified management and precise control of each modular thermal control unit through highly integrated control circuit and advanced control algorithm. The thermal management center can collect temperature data and running state information from each module in real time, and make in-depth analysis and intelligent decision based on these data. Once it detects abnormal fluctuations in the temperature of a certain area, the thermal management center will respond immediately by adjusting the working parameters of the relevant modules, such as adjusting the cooling or heating power of the temperature control module, changing the speed of the heat dissipation fan of the heat dissipation module, etc., so that the temperature quickly returns to the normal range. And the thermal management center also has the function of information interaction with other systems of the spacecraft, which can optimize and adjust the thermal control system according to the overall running state of the spacecraft. When the spacecraft performs a specific task resulting in a significant increase in the power of some equipment, the thermal management center can obtain this information in time and accordingly increase the heat dissipation of the thermal control unit in the area where these equipment are located.

[0034] Thermal control network: As the "nerve plexus" of the thermal control system, the thermal control network undertakes the important task of connecting each modular thermal control unit and the thermal management center, realizing data communication and heat transfer between them. In terms of data communication, the thermal control network adopts high-speed and reliable communication protocol to ensure that temperature data, control instructions and other information can be accurately and timely transmitted. In terms of heat transfer, the thermal control network guides the heat generated by each module to the heat dissipation module in an orderly manner through carefully designed heat conduction paths and efficient heat transfer medium. The thermal control network also has good scalability and fault tolerance, when new thermal control units need to be added, they can be easily connected to the network; and when some network nodes fail, the data and heat transfer path can be automatically switched to ensure the normal operation of the thermal control system.

[0035] Auxiliary thermal control components: Auxiliary thermal control components serve as an important supplement to the thermal control system, including thermal insulation materials for reducing thermal interference between devices, which have extremely low thermal conductivity and can effectively prevent heat transfer between devices; and heating elements that provide heat compensation for devices in extremely low temperature environments. The heating elements can automatically start and adjust the heating power according to the feedback of the temperature sensor, ensuring that the device can work normally in a low temperature environment. The reasonable application of auxiliary thermal control components further improves the adaptability and reliability of the thermal control system. In some deep space exploration missions, spacecraft will face extremely low temperature environments, at which time the heating elements can play a key role in ensuring the normal operation of the device.

[0036] The application also provides a regulation and control method based on the above-mentioned spacecraft modular thermal control system, comprising the following steps:

[0037] Data acquisition: High-precision temperature sensors are installed at key positions of the thermal control system, such as the inlet and outlet of each modular thermal control unit, the surface of the device, etc. These temperature sensors can collect temperature data in real time and accurately, and quickly transmit the data to the thermal management center through the thermal control network. The thermal management center preliminarily processes and filters these raw data, removes abnormal data, and ensures the accuracy and reliability of the data. The thermal management center also records the collection time of these data for subsequent data analysis and trend prediction.

[0038] Data analysis and decision-making: The thermal management center uses advanced data analysis algorithms and intelligent decision-making models to conduct in-depth analysis on the collected temperature data. By comparing with the pre-set temperature threshold, it is judged whether the current thermal control system is running normally. If the temperature of a certain area exceeds the normal range, the thermal management center will further analyze the cause of the temperature anomaly, such as whether it is due to a module failure causing poor heat dissipation, or a sudden increase in device load causing excessive heat production, etc. According to the analysis results, the thermal management center formulates corresponding regulation and control strategies, such as adjusting the cooling / heating power of the temperature control module, changing the heat dissipation mode of the heat dissipation module (such as starting the standby heat dissipation fan or adjusting the angle of the heat dissipation fins), etc.

[0039] Regulation execution: The thermal management center sends precise control instructions to the relevant modular thermal control units through the thermal control network according to the formulated regulation strategy. After receiving the instructions, each modular thermal control unit quickly responds and executes the corresponding operation. The temperature control module adjusts the refrigeration or heating power according to the instructions, and adjusts the flow of the refrigerant or the current of the heating element to achieve temperature regulation; the heat dissipation module starts the standby heat dissipation fan, adjusts the fan speed, or changes the angle of the heat dissipation fins to improve the heat dissipation efficiency according to the instructions. The heat conduction module optimizes the heat transfer path to ensure that heat can be quickly transferred to the heat dissipation module. During the execution of the regulation operation, each module will feedback its running state to the thermal management center in real time, so that the thermal management center can monitor and further adjust.

[0040] Dynamic optimization: The thermal control system is in a dynamically changing space environment, and the thermal management center continuously monitors and analyzes the operation data of the thermal control system in real time. According to the changes in the flight attitude of the spacecraft, the switching of the device working mode, and the fluctuations of the space environment temperature, etc., the regulation strategy is dynamically optimized in time. When the spacecraft enters the shadow area from the sunlight area, the thermal management center will predict the temperature drop trend in advance, and adjust the heating power of the heating element accordingly to maintain the normal working temperature of the device. Through this dynamic optimization mechanism, the thermal control system can always maintain the best running state, ensuring the stable operation of the spacecraft device.

[0041] Embodiment one

[0042] Embodiment one: Application of the thermal control system of a certain communication satellite

[0043] 1. System construction and parameter configuration

[0044] The communication satellite carries 12 high-power communication transponders (single peak power 500W) and 8 signal processing devices (working temperature requirement 20±2℃). The thermal control system based on the present application is configured as follows:

[0045] Modular thermal control unit: 6 groups of heat dissipation modules (single module heat dissipation capacity 800W), 4 groups of temperature control modules (temperature control accuracy ±0.5℃) and 8 groups of heat conduction modules (thermal conductivity 300W / (m·K)) are deployed in the transponder area; 4 groups of high-precision temperature control modules (temperature control accuracy ±0.3℃) are configured in the signal processing device area.

[0046] Thermal management center: 32-bit embedded processor, data sampling frequency 10Hz, control response delay ≤50ms.

[0047] Thermal control network: communication rate 100Mbps, heat transfer medium is graphene composite heat pipe (thermal conductivity 500W / (m·K)).

[0048] 2. Regulation effect data

[0049] In the 6-month on-orbit test, the system operation data are as follows:

[0050]

[0051]

[0052] When the power of a certain transponder is overloaded to 600W, the thermal management center starts the standby heat dissipation module within 0.3 seconds, reduces the temperature from 58℃ to 45℃, and avoids equipment downtime.

[0053] 3. Energy utilization efficiency analysis

[0054] Through the dynamic optimization algorithm, the system automatically reduces the speed of the heat dissipation fan to 50% and the power of the temperature control module by 40% during the satellite entering the eclipse period (the device load is reduced by 30%), and saves energy about 28.8kWh per month, which is equivalent to extending the satellite battery life by about 12%.

[0055] Example Two: Application of the thermal control system of a certain remote sensing satellite

[0056] 1. System customization and performance targets

[0057] The remote sensing satellite carries a high-resolution optical camera (operating temperature requirement 15±0.5℃, thermal load fluctuation range 100-300W) and a solar cell array (operating temperature -40~60℃). The thermal control system of the present application is designed specifically:

[0058] Optical camera area: micro-channel heat dissipation module (heat dissipation efficiency 92%) + semiconductor temperature control module (refrigeration power 200W), thermal conduction path uses integrated metal matrix composite material.

[0059] Battery array area: deploy flexible heating elements (power adjustment range 0-50W) and aerogel thermal insulation layer (thermal conductivity 0.008W / (m·K)).

[0060] 2. Temperature control precision comparison

[0061] The temperature data of the 10-day continuous on-orbit test are as follows:

[0062]

[0063] 3. Extreme environment adaptability test

[0064] During a solar storm, the satellite surface absorbed heat flux increased from 1200W / m 2 to 1800W / m 2 , and the system of the present application responded through the following mechanisms:

[0065] 1) The thermal management center starts the pre-cooling mode 15 minutes in advance (based on orbit prediction), and the cooling module power is increased to 120%;

[0066] 2) The thermal control network automatically switches to the redundant path to avoid single-point overheating;

[0067] 3) The final device temperature fluctuation is controlled within ±1.2℃, which is much better than the traditional system of ±5.8℃.

[0068] It should be noted that the relationship terms such as first and second, and the like, are used merely to distinguish one entity or action from another, and are not necessarily required by the instant application. In addition, the terms "comprises", "comprising", or any other variations thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but can also include other elements not expressly listed or inherent to such process, method, article, or apparatus. An element proceeded by "comprises... a" does not, without more constraints, exclude the existence of additional identical elements in the process, method, article, or apparatus that comprises the element.

[0069] Although the embodiments of the present application have been shown and described, it is to be understood that various modifications, substitutions, replacements and changes can be made to these embodiments without departing from the principles and spirit of the present application, and the scope of the present application is defined by the appended claims and their equivalents.

Claims

1. A spacecraft modular thermal control system, characterized by, The application relates to a modular thermal control system for spacecraft, which comprises the following parts: A modular thermal control unit, which is composed of a heat dissipation module, a temperature control module and a heat conduction module. Each module can be flexibly combined and detached through standardized interfaces. The heat dissipation module adopts a specially designed heat dissipation structure and high-performance heat dissipation materials, which can quickly dissipate the heat generated by the equipment. The temperature control module has precise temperature regulation capability, and through advanced temperature sensors and intelligent control algorithms, it can realize accurate temperature regulation. The heat conduction module uses high-efficiency heat conduction materials and optimized structural design to ensure that the heat can be quickly and stably transferred to the heat dissipation module. A thermal management center, which is used for unified management and control of each modular thermal control unit, and formulates regulation and control strategies according to temperature data and running state information. The thermal management center intelligently manages and controls the thermal control system through highly integrated control circuits and advanced control algorithms, can collect temperature data and running state information from each module in real time, and makes in-depth analysis and intelligent decisions based on these data. A thermal control network, which connects each modular thermal control unit and the thermal management center, realizes data communication and heat transfer. The thermal control network uses high-speed and reliable communication protocols for data transmission, and uses carefully designed heat conduction paths and high-efficiency heat transfer media for heat transfer. It has extensibility and fault tolerance. When new thermal control units need to be added, they can be easily connected to the network, and when some network nodes fail, the system can automatically switch the data and heat transfer paths. Auxiliary thermal control components, including thermal insulation materials and heating elements, are used to reduce thermal interference between devices and provide heat compensation in extreme low-temperature environments. The thermal insulation material has a very low thermal conductivity, which can effectively prevent heat transfer between devices. The heating element can automatically start and adjust the heating power according to the feedback of the temperature sensor, ensuring that the device can work normally in a low-temperature environment.

2. The spacecraft modular thermal control system and regulating method of claim 1, wherein, The special heat dissipation structure of the heat dissipation module is one or a combination of interdigital, micro-channel or jet heat dissipation structures, and the high-performance heat dissipation material is one or a combination of high-thermal-conductivity metal matrix composites, carbon nanotube reinforced composites or high-emissivity coating materials.

3. The spacecraft modular thermal control system and regulating method of claim 1, wherein, The temperature sensor in the temperature control module has an accuracy of within ±0.1℃, and the intelligent control algorithm is one or a combination of fuzzy logic control, neural network control and model predictive control, to realize accurate temperature regulation.

4. The spacecraft modular thermal control system and regulating method of claim 1, wherein, The high-efficiency heat conduction material of the heat conduction module is one or a combination of graphene-based heat conduction materials, liquid metal-based heat conduction materials or high-performance heat-conducting silicone, and the optimized structural design is an integrated molding, multi-layer composite structure or a structure with a special flow channel design to improve heat transfer efficiency and stability.

5. The spacecraft modular thermal control system and regulating method of claim 1, wherein, The control circuit of the thermal management center uses low-power and high-reliability integrated circuit chips with redundancy design. The advanced control algorithm can adaptively adjust the regulation and control strategy according to the spacecraft flight stage, device working mode and thermal environment changes, and the response time of the regulation and control strategy is not more than 1 second.

6. The spacecraft modular thermal control system and regulating method of claim 1, wherein, The data communication rate of the thermal control network is not less than 10 Mbps, the thermal conductivity of the heat transfer medium is not less than 10 W / (m·K), the network topology structure is one or a combination of star type, bus type or ring structure, and has self-diagnosis and self-repair functions, and the fault switching time is not more than 0.5 seconds.

7. The spacecraft modular thermal control system and regulating method of claim 1, wherein, The thermal conductivity of the thermal insulation material is less than 0.01 W / (m·K), the heating power adjustment range of the heating element is 0-100 W, the response time is not more than 2 seconds, and it has overheat protection and overcurrent protection functions.

8. A method of regulating a spacecraft modular thermal control system according to any one of claims 1 to 7, characterized in that, The method comprises the following steps: Data acquisition: Real-time acquisition of temperature data through high-precision temperature sensors distributed at key positions of the thermal control system, such as the inlet and outlet of each modular thermal control unit, the surface of the equipment, etc., and transmission to the thermal management center through the thermal control network; The thermal management center processes and filters the raw temperature data, removes abnormal data, and records the data acquisition time. The sampling frequency of the temperature sensor is not less than 1 Hz; Data analysis and decision-making: The thermal management center uses advanced data analysis algorithms and intelligent decision-making models to analyze the collected temperature data in depth; By comparing with the pre-set temperature threshold, it is judged whether the running state of the current thermal control system is normal; If it is found that the temperature of a certain area exceeds the normal range, the thermal management center will further analyze the reason for the temperature anomaly, and according to the analysis result, it will formulate the corresponding control strategy. Advanced data analysis algorithms and intelligent decision-making models are constructed based on one or more technologies of big data analysis, machine learning and deep learning; Control execution: The thermal management center sends precise control instructions to the relevant modular thermal control units through the thermal control network; After receiving the instructions, each modular thermal control unit responds quickly and executes the corresponding operation, such as adjusting the refrigeration or heating power of the temperature control module, starting the standby cooling fan of the cooling module, adjusting the fan speed or changing the angle of the cooling fins, optimizing the heat transfer path of the heat conduction module, etc. During the execution of the control operation, each module will feedback its running state to the thermal management center in real time, and the update frequency of the feedback information is not less than 0.5 Hz; Dynamic optimization: The thermal control system is in a dynamically changing space environment, and the thermal management center will continuously monitor and analyze the running data of the thermal control system in real time; According to the changes of the spacecraft's flight attitude, the switching of the equipment's working mode and the fluctuations of the space environment temperature, etc., the control strategy is dynamically optimized in time, such as adjusting the heating power of the heating element and the working mode of the cooling module. The time interval of dynamic optimization is not more than 5 minutes.

9. The spacecraft modular thermal control system and regulating method of claim 1, wherein, It also includes collecting the working state parameters of the key components of the thermal control system, such as the cooling fan speed, the refrigeration working medium flow of the temperature control module, the heating element current, etc., and transmitting them to the thermal management center through the thermal control network. The sampling frequency of the working state parameters is not less than 0.5 Hz.

10. The spacecraft modular thermal control system and regulating method of claim 1, wherein, In the data analysis and decision step, the thermal management center also has a fault diagnosis function, which can determine whether the thermal control system has a fault according to the temperature data and the working state parameters of the key components, and if there is a fault, it can quickly locate the fault module and the fault type, and generate a fault report. The accuracy rate of fault diagnosis is not less than 95%, and the fault positioning time is not more than 3 seconds.

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