Space environment simulation test system

Abstract

The invention discloses a space environment simulation test system, which comprises a space environment simulation platform, a satellite operation modeling platform, a data driver, a space environment simulation device and a test middle table, and is characterized in that the space environment simulation platform creates a space environment model according to vacuum, radiation and cold black space environment attributes; the satellite operation modeling platform establishes a satellite operation model in combination with satellite operation characteristics, the space environment simulation device simulates a space environment and satellite operation, and the data driver drives the space environment model and the satellite operation model to generate a prediction model. The data driver synchronously transmits the data to the analog quantity regulation and control platform to synchronously adjust the space environment simulation condition, and the test platform tests the satellite body to generate a test model. Compared with the prior art, the test platform realizes comparison and verification of the test process and the test result through visual comparison and analysis of the prediction model and the test model, so that reliable test data is obtained, and the accuracy of the simulation test is improved.

Description

Technical Field

[0001] The present invention belongs to the technical field of aerospace condition simulation, and specifically relates to a space environment simulation test system. Background Art

[0002] Space environment tests are important procedures in the satellite development process. The main function is to simulate orbital space environments such as vacuum, cold black, and solar radiation, and to expose problems of the satellite during launch and in-orbit operation in advance. Among them, conducting various thermal vacuum tests on the satellite and its components is an extremely important test content to detect the stability and durability of the whole satellite and its components in the extreme space temperature environment, as well as to test the electrical characteristics and reliability of the whole satellite and its components at different temperatures. At present, various space environment simulation test systems have been developed for thermal vacuum tests. For example, the patent with the application number CN201310255839.5 discloses a space environment simulation test system. This system realizes the cryogenic requirements below the liquid nitrogen temperature region through the large latent heat of vaporization of liquid nitrogen provided by the liquid nitrogen / gaseous nitrogen supply system, the sensible heat at large temperature differences, and the cold helium provided by the refrigerator system, and precisely controls according to the target temperature of the measurement and control system, and uses an electric heater for rewarming and high-temperature tests. Additionally, the patent with the application number CN202110744841.3 discloses a wide-temperature-region space environment simulation test system. This system combines a liquid nitrogen system and a GM refrigerator, sets an external heat sink and an internal heat sink, and effectively reduces the thermal radiation load of the external heat sink on the internal heat sink through polishing and nickel plating on the outer surface of the internal heat sink, thereby realizing the broadening of the temperature range.

[0003] However, although the above two space environment simulation test systems in the prior art have realized the simulation and control of the vacuum environment temperature, in the thermal vacuum test, since the space environment and the satellite operation state are not synchronously simulated and modeled, these two systems can only obtain the test data in the actual test operation, lacking the synchronous comparison with the data in the simulation and modeling environment, which is not conducive to the comparative analysis of the test process data and the test result data, and further affects the correction of the test operation process and the intuitive judgment of the test results, affecting the accuracy of the simulation test. Moreover, it may even lead to a large deviation in the test data due to the failure to timely discover the negligence in the test process. In addition, these two systems in the prior art do not synchronously consider parameters such as the satellite's own structure, the satellite's test flight orbit, and the flight attitude, further reducing the accuracy of the simulation test. Summary of the Invention

[0004] In order to overcome the above deficiencies in the prior art, the present invention provides a space environment simulation test system that is synchronously equipped with a space environment simulation platform and a satellite operation modeling platform, generates a predictive model and a test model that can be synchronously compared through the synchronous real-time operation of a data driver and a space environment simulation device, and is provided with a test middle platform.

[0005] In order to achieve the above object, the technical solution adopted by the present invention is as follows:

[0006] A space environment simulation test system comprises a space environment simulation platform, a satellite operation modeling platform connected to the space environment simulation platform, a data driver connected to both the satellite operation modeling platform and the space environment simulation platform, a space environment simulation device connected to the data driver, the satellite operation modeling platform and the space environment simulation platform, and a test platform connected to the space environment simulation device, the data driver, the satellite operation modeling platform and the space environment simulation platform, wherein:

[0007] The space environment simulation platform creates a space environment model according to the properties of vacuum, radiation, and cold black space environment; the satellite operation modeling platform establishes a satellite operation model according to the characteristics of the satellite body and the satellite operation characteristics; the space environment simulation device simulates the vacuum, radiation, cold black space environment, the satellite body, and the satellite operation, and has a simulation quantity control platform and a test platform built in; the data driver transmits the space environment data and the satellite operation data to the space environment model and the satellite operation model respectively to drive the generation of a prediction model that reveals the temperature distribution and changes inside and outside the satellite body. At the same time, the data driver synchronously transmits the space environment data and the satellite operation data to the simulation quantity control platform to synchronously adjust the space environment simulation conditions, and the test platform tests the satellite body to generate a test model that reveals the temperature distribution and changes inside and outside the satellite body; the test platform compares and analyzes the prediction model and the test model to verify the test process and test results.

[0008] Furthermore, the simulation process of the space environment simulation platform is as follows:

[0009] S101: Creating a space environment geometric model based on the characteristics of vacuum, radiation, and cold black space environments;

[0010] S102: Setting vacuum boundary conditions, radiation boundary conditions, and cold black space environment boundary conditions;

[0011] S103: Setting the data input interface of vacuum attribute, radiation attribute and cold black attribute;

[0012] S104: Divide the spatial environment geometric model with boundary conditions and data input interface into appropriate grids for discretization solution area;

[0013] S105: Select a solver and set solution parameters, start simulation calculation and create a space environment model.

[0014] Further, in step S102, when setting the vacuum boundary condition, the pressure in the geometric model region of the space environment is set to zero; when setting the radiation boundary condition, the solar radiation is regarded as parallel light, and the solar light flux and the solar light vector are set on the boundary of the model in combination with the solar constant; when setting the cold black space environment boundary condition, the temperature of the cold black space is set to 2.7K.

[0015] Further, the modeling steps of the satellite operation modeling platform are as follows:

[0016] S201: Collect parameter data of the satellite body, satellite operation orbit, and satellite operation attitude;

[0017] S202: Perform data cleaning and denoising preprocessing operations on the collected data, and determine the parameters required for modeling according to the preprocessed data and the actual situation of the satellite.

[0018] S203: Select SpaceSim as the modeling tool and generate a satellite operation model through modeling, and verify and debug the generated satellite operation model.

[0019] Further, the data driver includes a feature data extraction layer, a data induction layer, and a data synchronization and drive layer. Among them, the feature data extraction layer obtains the original space environment data and satellite operation data with the help of sensors and imaging devices. The data induction layer classifies, cleans, and arranges the obtained original space environment data and satellite operation data, and summarizes the data into a queue data set format; the data synchronization and drive layer synchronously transmits the summarized queue data set to the space environment model, the satellite operation model, and the analog quantity regulation platform for data drive.

[0020] Further, the feature data extraction layer is expressed by the following formula:

[0021] Feature=re.findall(f collect (p),S,I)

[0022] In the formula: Feature represents the original space environment feature data and the original satellite operation feature data, p represents the original string data corresponding to the space environment and satellite operation features, S represents that the data source is the sensor, I represents that the data source is the image, and f collect is a data acquisition function for collecting the original string data from the sensor and the image. re.findall represents the data extraction function, that is, extracting the feature data Feature from the f collect function.

[0023] Further, the data induction layer is expressed by the following formula:

[0024] Dintroduction = f mark (f Feature (d1, d2, d3, d4, d5, d6), S, I)

[0025] Where: D introduction represents the space environment data and satellite operation data after induction and collation, d1 represents vacuum attribute data, d2 represents radiation attribute data, d3 represents cold black environment attribute data, d4 represents satellite body characteristic data, d5 represents operation orbit data, d6 represents satellite operation attitude data, S represents the data source is a sensor, I represents the data source is an image, and f Feature represents a feature data extraction function, which is used to extract the data of d1, d2, d3, d4, d5, d6, and f mark is a data induction function, which is used to process and induct the extracted data into the format of a queue data set.

[0026] Furthermore, the data synchronization drive layer is expressed as the following formula:

[0027] D sync = f drive (f mark (d), S, I)

[0028] Where: D sync represents the drive data synchronously transmitted to the space environment model, satellite operation model, and analog quantity regulation platform. d represents the space environment data and satellite operation data after induction. S represents the data source is a sensor, I represents the data source is an image, and f mark is a data induction function, which is used to process and induct the extracted data into the format of a queue data set, and f drive represents a data synchronization drive function, which transmits the inducted queue data set to the space environment model, satellite operation model, and analog quantity regulation platform for data drive.

[0029] Furthermore, the test middle platform is provided with a monitoring and feedback unit. The monitoring and feedback unit monitors the test process data and test result data, analyzes the abnormal reasons for the monitored abnormal data, and forms adjustment suggestions to be fed back to the space environment simulation device, data driver, and satellite body for adjustment.

[0030] Furthermore, the space environment simulation device is internally provided with a vacuum chamber, a heat sink system, a radiation simulator, a test flight orbit, and a flight attitude controller to simulate the vacuum, radiation, cold black space environment, and satellite operation respectively. Among them, the analog quantity regulation platform regulates the vacuum chamber, heat sink system, radiation simulator, test flight orbit, and flight attitude controller according to the space environment data and satellite operation data in the data driver.

[0031] Compared with the prior art, the present invention has the following beneficial effects:

[0032] (1) The present invention creates a space environment model through a space environment simulation platform and establishes a satellite operation model through a satellite operation modeling platform. The space environment simulation device simulates the vacuum, radiation, cold black space environment, satellite body, and satellite operation, creating a test environment equivalent to the simulation environment for actual tests. The data driver transmits the space environment data and satellite operation data to the space environment model and satellite operation model respectively for data-driven generation of a prediction model revealing the temperature distribution and changes inside and outside the satellite body. The data driver synchronously transmits the space environment data and satellite operation data to the analog quantity regulation platform to synchronously adjust the space environment simulation status. The test platform tests the satellite body to generate a test model revealing the temperature distribution and changes inside and outside the satellite body. The test middle platform conducts an intuitive comparative analysis of the prediction model and the test model, realizing the comparative verification of the test process and test results, obtaining reliable test data, and improving the accuracy of the simulation test.

[0033] (2) The simulation process of the space environment simulation platform of the present invention creates a space environment geometric model, sets boundary conditions, sets data input interfaces, conducts grid division on the geometric model, and obtains simulation results through a solver, creating a space environment model with high simulation effects. Moreover, the entire simulation process is highly efficient. Additionally, through the specific setting of the boundary conditions of the vacuum, radiation, and cold black space environment, the simulation accuracy is further improved. The satellite operation modeling platform of the present invention provides high-quality parameter data support for modeling by collecting satellite body, satellite operation orbit, satellite operation attitude parameter data and corresponding data preprocessing. By selecting SpaceSim as the modeling tool and generating a satellite operation model, not only is the modeling efficiency high, but the establishment of the entire satellite operation model further improves the simulation accuracy.

[0034] (3) Through the setting of the feature data extraction layer, data induction layer, data synchronous drive layer, and corresponding function formulas, the data driver of the present invention realizes the extraction and induction of the space environment data and satellite operation data. Through data synchronous drive, not only are prediction models and test models convenient for comparison obtained, but also this real-time synchronous data drive method improves the implementation efficiency of the test.

[0035] (4) The monitoring and feedback unit of the test bench in the present invention monitors the test process data and test result data. Once abnormalities are detected, corrective adjustments can be made in a timely manner, preventing large deviations in test data caused by negligence during the test process. The space environment simulation device in the present invention is equipped with a vacuum chamber, a heat sink system, a radiation simulator, a test flight orbit, and a flight attitude controller, which not only realizes the simulation test function, but also further improves the accuracy of the simulation test by comprehensively considering parameters such as the space environment, the structure of the satellite itself, the test flight orbit of the satellite, and the flight attitude. BRIEF DESCRIPTION OF THE DRAWINGS

[0036] Figure 1 is a schematic diagram of the composition principle of the space environment simulation test system of the present invention;

[0037] Figure 2 is a schematic diagram of the composition principle of the space environment simulation device of the present invention;

[0038] Figure 3 is a schematic diagram of the simulation process of the space environment simulation platform of the present invention;

[0039] Figure 4 is a schematic diagram of the modeling steps of the satellite operation modeling platform of the present invention;

[0040] Figure 5 is a schematic diagram showing the comparison of the temperatures inside and outside the satellite body revealed by the prediction model and the test model of the present invention.

[0041] In the above-mentioned drawings, the component names corresponding to the reference numerals are as follows:

[0042] 1 - Space environment simulation platform, 2 - Satellite operation modeling platform, 3 - Data driver, 4 - Space environment simulation device, 401 - Analog quantity regulation platform, 402 - Test platform, 403 - Vacuum chamber, 404 - Heat sink system, 405 - Radiation simulator, 406 - Test flight orbit, 407 - Flight attitude controller, 5 - Test bench, 6 - Prediction model, 7 - Test model, 8 - Satellite body. SPECIFIC EMBODIMENTS

[0043] The present invention will be further described below with reference to the drawings and embodiments. The embodiments of the present invention include, but are not limited to, the following examples.

[0044] Embodiment

[0045] As Figures 1 - 5As shown in the figure, this embodiment provides a space environment simulation test system, including a space environment simulation platform 1, a satellite operation modeling platform 2, a data driver 3, a space environment simulation device 4, and a test middle platform 5. Among them, the space environment simulation platform 1 creates a space environment model according to the vacuum, radiation, and cold black space environment attributes. The satellite operation modeling platform 2 establishes a satellite operation model according to the satellite body characteristics and satellite operation characteristics. The space environment simulation device 4 simulates the vacuum, radiation, cold black space environment, satellite body 8, and satellite operation, and internally sets a simulation quantity control platform 401 and a test platform 402. The data driver 3 transmits space environment data and satellite operation data to the space environment model and the satellite operation model respectively for data-driven generation of a prediction model 6 that reveals the temperature distribution and changes inside and outside the satellite body. The data driver 3 synchronously transmits the space environment data and satellite operation data to the simulation quantity control platform 401 to synchronously adjust the space environment simulation status. The test platform 402 tests the satellite body 8 to generate a test model 7 that reveals the temperature distribution and changes inside and outside the satellite body. The test middle platform 5 conducts a comparative analysis of the prediction model 6 and the test model 7 to verify the test process and test results.

[0046] In this embodiment, the space environment simulation platform 1 and the satellite operation modeling platform 2 are bidirectionally docked, and the generated space environment model and satellite operation model are also correspondingly docked. The data driver 3 is an engine component that drives the model operation based on data. The prediction of the temperature distribution and changes inside and outside the satellite body by the prediction model 6 in this embodiment is as shown in (a) of Figure 5 The test model 7 obtains the temperature distribution and changes inside and outside the satellite body from actual tests, and the corresponding model is as shown in (b) of Figure 5 By visually comparing the prediction model 6 and the test model 7, analyzing the differences and deviation ranges between the two, the judgment and verification of the test process data and test result data are completed. The test data that passes the verification is the basis for satellite thermal design, including the design of the satellite outer surface coating and the temperature design for internal components, so as to keep the entire satellite within a certain temperature range and prevent the satellite from being damaged due to excessive or too low temperature.

[0047] In this embodiment, the space environment simulation platform 1 is a software platform for simulating and reproducing vacuum, radiation, and cold black space environment conditions, and its simulation process is as follows:

[0048] S101: Create a space environment geometric model according to the characteristics of the vacuum, radiation, and cold black space environment;

[0049] S102: Set the vacuum boundary conditions, radiation boundary conditions, and cold black space environment boundary conditions;

[0050] S103: Set the data input interfaces for the vacuum attribute, radiation attribute, and cold black attribute;

[0051] S104: Divide the spatial environment geometric model with boundary conditions and data input interfaces set into appropriate grids for discretizing the solution domain;

[0052] S105: Select a solver and set the solution parameters, start the simulation calculation, and create a spatial environment model.

[0053] In this embodiment, the vacuum boundary condition is used to simulate the vacuum environment in space, that is, the area where there are no gas molecules or other substances. During the simulation process, the pressure of the spatial environment geometric model area is set to zero; in the vacuum environment, thermal radiation is the most important way of energy transfer. The sun is the radiation source in the spatial environment. When setting the radiation boundary condition, the solar radiation is regarded as parallel light, and the solar irradiance and solar vector are set on the boundary of the model in combination with the solar constant; the cold black space environment boundary condition is used to simulate the low-temperature radiation environment in space. In this environment, objects exchange energy with the surrounding space through thermal radiation, and the temperature of the surrounding space is extremely low. In this embodiment, the temperature of the cold black space is set to 2.7K.

[0054] The satellite operation modeling platform 2 in this embodiment provides high-quality parameter data support for modeling by collecting parameter data related to satellite operation and corresponding data preprocessing, and creates a satellite operation model by selecting a modeling tool. The modeling steps of this platform are as follows:

[0055] S201: Collect parameter data of the satellite body 8, satellite operation orbit, and satellite operation attitude;

[0056] S202: Perform data cleaning and denoising preprocessing operations on the collected data, and determine the parameters required for modeling according to the preprocessed data and the actual situation of the satellite.

[0057] S203: Select SpaceSim as the modeling tool and model to generate a satellite operation model, and verify and debug the generated satellite operation model.

[0058] The satellite body parameters in the above steps include the physical structure, mass distribution, and centroid position of the satellite body. The satellite operation orbit parameters include the orbit altitude, orbit inclination, and eccentricity of the satellite operation. The satellite operation attitude parameters include the inertial characteristics, attitude control torque, satellite axis, and direction. The modeling tool SpaceSim selected in this embodiment is a modeling software for spacecraft. This modeling software is equipped with functional modules for calculating satellite operation orbits and satellite operation attitudes, which improves the efficiency and accuracy of modeling.

[0059] In this embodiment, the data driver 3 includes a feature data extraction layer, a data induction layer, and a data synchronization and driving layer. The feature data extraction layer obtains the original space environment data and satellite operation data with the aid of sensors and imaging devices, which is expressed by the following formula:

[0060] Feature=re.findall(f collect (p),S,I)

[0061] Where: Feature represents the original space environment feature data and original satellite operation feature data, p represents the original string data corresponding to the space environment and satellite operation features, S represents that the data source is a sensor, I represents that the data source is an image, and f collect is a data acquisition function for acquiring the original string data from sensors and images. re.findall represents a data extraction function, that is, extracting the feature data Feature from the f collect function.

[0062] The data induction layer classifies, cleans, and arranges the acquired original space environment data and satellite operation data, and inducts the data into the format of a queue data set, which is expressed by the following formula:

[0063] D introduction =f mark (f Feature (d1,d2,d3,d4,d5,d6),S,I)

[0064] Where: D introduction represents the space environment data and satellite operation data after induction and arrangement. d1 represents vacuum attribute data, d2 represents radiation attribute data, d3 represents cold black environment attribute data, d4 represents satellite body feature data, d5 represents operation orbit data, d6 represents satellite operation attitude data, S represents that the data source is a sensor, I represents that the data source is an image, and f Feature represents a feature data extraction function for extracting the data of d1, d2, d3, d4, d5, and d6. f mark is a data induction function for processing and inducting the extracted data into the format of a queue data set.

[0065] The data synchronization and driving layer synchronously transmits the inducted queue data set to the space environment model, the satellite operation model, and the analog quantity regulation platform 401 for data driving. The data synchronization and driving layer is expressed by the following formula:

[0066] D sync =f drive (f mark (d),S,I)

[0067] Where: D sync represents the drive data synchronously transmitted to the space environment model, satellite operation model, and analog regulation platform 401, d represents the summarized space environment data and satellite operation data, S represents that the data source is a sensor, I represents that the data source is an image, and f mark is a data summarization function for processing and summarizing the extracted data into a queue dataset format, and f drive represents the data synchronization drive function that transmits the summarized queue dataset to the space environment model, satellite operation model, and analog regulation platform 401 for data driving.

[0068] In this embodiment, the test platform 5 is provided with a monitoring and feedback unit for monitoring the test process data and test result data, analyzing the abnormal reasons for the monitored abnormal data, and forming adjustment suggestions to be fed back to the space environment simulation device 4, data driver 3, and satellite body 8 for adjustment. In addition, the test platform 5 is provided with a display unit and a data storage unit. Among them, the display unit is used to intuitively display the prediction model 6 and test model 7 and related test data, and the data storage unit is used to store each test data for easy query and use of the test data. The space environment simulation device 4 in this embodiment is internally provided with a vacuum chamber 403, a heat sink system 404, a radiation simulator 405, a test flight orbit 406, and a flight attitude controller 407. The analog regulation platform 401 regulates the vacuum chamber 403, heat sink system 404, radiation simulator 405, test flight orbit 406, and flight attitude controller 407 according to the space environment data and satellite operation data in the data driver 3, so as to realize the simulation of vacuum, radiation, cold black space environment, and satellite operation. The deployment and connection of the vacuum chamber 403, heat sink system 404, radiation simulator 405, test flight orbit 406, flight attitude controller 407, analog regulation platform 401, and test platform 402 in this embodiment can be realized through existing conventional software and hardware designs, and the specific software settings and circuit configurations are not elaborated in this embodiment. By comprehensively considering parameters such as the space environment, the structure of the satellite itself, the test flight orbit of the satellite, and the flight attitude, the accuracy of the simulation test is further improved in this embodiment.

[0069] When the present invention is used, first, the overall test system is built, including the construction of a space environment simulation platform 1, a satellite operation modeling platform 2, a data driver 3, a space environment simulation device 4, and a test middle platform 5. Among them, the space environment simulation device 4 includes the construction of a vacuum chamber 403, a heat sink system 404, a radiation simulator 405, a test flight orbit 406, a flight attitude controller 407, an analog quantity regulation platform 401, and a test platform 402. Before the test starts, the satellite body 8 to be tested is deployed into the space environment simulation device 4. During the test process, all parts of the overall test system work synchronously and collaboratively. The test middle platform 5 conducts a comparative analysis on the prediction model 6 and the test model 7 that reveal the temperature distribution and changes inside and outside the satellite body, and monitors the test process data and the test result data. Once an abnormality is found, corrective adjustments are made in a timely manner to prevent large deviations in the test data caused by negligence during the test process. The space environment simulation platform 1, the satellite operation modeling platform 2, and the data driver 3 in this embodiment can all be implemented by existing software technologies, and the specific simulation process, modeling steps, and software development process of the data driving process are not described in detail in this embodiment.

[0070] The above embodiments are only the preferred embodiments of the present invention, and do not limit the protection scope of the present invention. Any changes made by adopting the design principle of the present invention and non-creative labor on this basis shall fall within the protection scope of the present invention.

Claims

1. A space environment simulation test system, characterized in that: The invention comprises a space environment simulation platform (1), a satellite operation modeling platform (2) connected to the space environment simulation platform (1), a data driver (3) connected to both the satellite operation modeling platform (2) and the space environment simulation platform (1), a space environment simulation device (4) connected to the data driver (3), the satellite operation modeling platform (2) and the space environment simulation platform (1), and a test platform (5) connected to the space environment simulation device (4), the data driver (3), the satellite operation modeling platform (2) and the space environment simulation platform (1), wherein: The space environment simulation platform (1) creates a space environment model according to the properties of vacuum, radiation, and cold black space environment; the satellite operation modeling platform (2) establishes a satellite operation model according to the satellite body characteristics and satellite operation characteristics; the space environment simulation device (4) simulates the vacuum, radiation, cold black space environment, the satellite body (8), and satellite operation, and is internally provided with a simulation quantity control platform (401) and a test platform (402); the data driver (3) transmits the space environment data and the satellite operation data to the space environment model and the satellite operation model respectively to drive the generation of a prediction model (6) that reveals the internal and external temperature distribution and changes of the satellite body (8); at the same time, the data driver (3) synchronously transmits the space environment data and the satellite operation data to the simulation quantity control platform (401) to synchronously adjust the space environment simulation status; the test platform (402) tests the satellite body (8) to generate a test model (7) that reveals the internal and external temperature distribution and changes of the satellite body (8); the test platform (5) compares and analyzes the prediction model (6) and the test model (7) to verify the test process and test results.

2. A space environment simulation test system according to claim 1, characterized in that: The simulation process of the space environment simulation platform (1) is as follows: S101: Creating a space environment geometric model based on the characteristics of vacuum, radiation, and cold black space environments; S102: Setting vacuum boundary conditions, radiation boundary conditions, and cold black space environment boundary conditions; S103: Setting the data input interface of vacuum attribute, radiation attribute and cold black attribute; S104: Divide the spatial environment geometric model with boundary conditions and data input interface into appropriate grids for discretization solution area; S105: Select a solver and set solution parameters, start simulation calculation and create a space environment model.

3. A space environment simulation test system according to claim 2, characterized in that: In step S102, when setting the vacuum boundary condition, the pressure of the space environment geometric model area is set to zero; when setting the radiation boundary condition, the solar radiation is regarded as parallel light, and the solar flux and solar vector are set on the boundary of the model in combination with the solar constant; when setting the cold black space environment boundary condition, the temperature of the cold black space is set to 2.7K.

4. A space environment simulation test system according to claim 2, characterized in that: The modeling steps of the satellite operation modeling platform (2) are: S201: Collecting parameter data of the satellite body (8), satellite orbit, and satellite attitude; S202: Perform data cleaning and denoising preprocessing operations on the collected data, and determine the parameters required for modeling based on the preprocessed data and the actual situation of the satellite; S203: Select SpaceSim as a modeling tool to generate a satellite operation model, and verify and debug the generated satellite operation model.

5. A space environment simulation test system according to claim 1, characterized in that: The data driver (3) comprises a feature data extraction layer, a data summarization layer, and a data synchronization driver layer, wherein the feature data extraction layer obtains original space environment data and satellite operation data with the help of sensors and imaging devices, and the data summarization layer classifies, cleans, and arranges the obtained original space environment data and satellite operation data, and summarizes the data into a queue data set format; the data synchronization driver layer synchronously transmits the summarized queue data set to the space environment model, the satellite operation model, and the analog quantity control platform (401) for data driving.

6. A space environment simulation test system according to claim 5, characterized in that: The feature data extraction layer is expressed as the following formula: Feature=re.findall(f collect (p),S,I) Where: Feature represents the original space environment feature data and the original satellite operation feature data, p represents the original string data corresponding to the space environment and satellite operation features, S represents the data source is the sensor, I represents the data source is the image, and f collect is a data collection function used to collect raw string data from sensors and images. re.findall represents the data extraction function, that is, from f collect Extract feature data Feature in the function.

7. A space environment simulation test system according to claim 6, characterized in that: The data summarization layer is expressed as the following formula: D introduction =f mark (f Feature (d1,d2,d3,d4,d5,d6),S,I) Where: D introduction represents the summarized and sorted space environment data and satellite operation data, d1 represents vacuum attribute data, d2 represents radiation attribute data, d3 represents cold black environment attribute data, d4 represents satellite body feature data, d5 represents operation orbit data, d6 represents satellite operation attitude data, S represents data source is sensor, I represents data source is image, f Feature Represents the feature data extraction function, which is used to extract the data of d1, d2, d3, d4, d5, and d6. mark It is a data summarization function, which is used to process the extracted data and summarize it into a queue data set format.

8. A space environment simulation test system according to claim 7, characterized in that: The data synchronization driver layer is expressed as the following formula: D sync =f drive (f mark (d),S,I) Where: D sync represents the driving data synchronously transmitted to the space environment model, the satellite operation model, and the analog quantity control platform (401), d represents the summarized space environment data and satellite operation data, S represents the data source is a sensor, I represents the data source is an image, and f mark It is a data summarization function, which is used to process the extracted data and summarize it into a queue data set format. drive It represents a data synchronization driving function, which transmits the summarized queue data set to the space environment model, the satellite operation model, and the simulation quantity control platform (401) for data driving.

9. A space environment simulation test system according to claim 1, characterized in that: The test platform (5) is provided with a monitoring feedback unit, which monitors the test process data and the test result data, analyzes the abnormal causes of the monitored abnormal data, and forms adjustment suggestions to be fed back to the space environment simulation device (4), the data driver (3), and the satellite body (8) for adjustment.

10. A space environment simulation test system according to any one of claims 1 to 9, characterized in that: The space environment simulation device (4) is provided with a vacuum chamber (403), a heat sink system (404), a radiation simulator (405), a test flight track (406), and a flight attitude controller (407) for simulating vacuum, radiation, a cold black space environment, and satellite operation, respectively. The simulation quantity control platform (401) controls the vacuum chamber (403), the heat sink system (404), the radiation simulator (405), the test flight track (406), and the flight attitude controller (407) according to the space environment data and the satellite operation data in the data driver (3).

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