A space environment simulation test system

Abstract

The present invention discloses a space environment simulation test system, including a space environment simulation platform, a satellite operation modeling platform, a data driver, a space environment simulation device, and a test platform. The space environment simulation platform creates a space environment model based on the vacuum, radiation, and cold black space environment properties. The satellite operation modeling platform establishes a satellite operation model based on the satellite operation characteristics. The space environment simulation device simulates the space environment and satellite operation. The data driver drives the space environment model and the satellite operation model to generate a prediction model. The data driver synchronously transmits data to the simulation quantity control platform to synchronously adjust the space environment simulation status. The test platform tests the satellite body to generate a test model. The test platform of the present invention realizes comparative verification of the test process and test results through intuitive comparative analysis of the prediction model and the test model, thereby obtaining reliable test data and improving the accuracy of the simulation test.

Description

Technical Field

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

[0002] Space environment testing is a crucial procedure in the satellite development process. Its primary function is to simulate orbital space environments, such as vacuum, cold darkness, and solar radiation, to expose problems encountered during satellite launch and on-orbit operation in advance. Conducting various thermal vacuum tests on satellites and their components is an extremely important part of the test, used to detect the stability and durability of satellite systems and components in extreme space temperature environments, as well as to test the electrical characteristics and reliability of satellite systems and components at different temperatures. Currently, various space environment simulation test systems have been developed for thermal vacuum testing. For example, patent application number CN201310255839.5 discloses a space environment simulation test system. This system utilizes the large latent heat of vaporization and sensible heat under large temperature differences provided by a liquid nitrogen / gas nitrogen supply system, as well as cold helium provided by a refrigerator system, to achieve deep cooling requirements below the liquid nitrogen temperature range. The system also precisely controls the target temperature according to the measurement and control system, and utilizes electric heaters for rewarming and high-temperature testing. In addition, the patent with application number CN202110744841.3 discloses a wide-temperature space environment simulation test system. The system combines a liquid nitrogen system and a GM refrigerator to set up an external heat sink and an internal heat sink, and polishes the outer surface of the internal heat sink with bright nickel plating, thereby effectively reducing the thermal radiation load of the external heat sink on the internal heat sink and achieving a widening of the temperature range.

[0003] However, although the two space environment simulation test systems in the above-mentioned prior art have realized the simulation and control of the vacuum environment temperature, in the thermal vacuum test, due to the lack of synchronous simulation modeling of the space environment and the satellite operation status, the two systems can only obtain the test data in the actual operation of the test, and lack synchronous comparison with the data in the simulation modeling environment, which is not conducive to the comparative analysis of the test process data and the test result data, thereby affecting the correction of the test operation process and the intuitive judgment of the test results, affecting the accuracy of the simulation test, and may even cause significant deviations in the test data due to the failure to timely discover negligence in the test process. Moreover, the two systems in the prior art do not synchronously consider parameters such as the satellite's own structure, satellite test flight orbit and flight attitude, further reducing the accuracy of the simulation test. Summary of the Invention

[0004] In order to overcome the above-mentioned deficiencies in the prior art, the present invention provides a space environment simulation test system that is equipped with a space environment simulation platform and a satellite operation modeling platform, which generates a prediction 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 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 includes 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 based on the properties of vacuum, radiation, and cold black space environment; the satellite operation modeling platform establishes a satellite operation model based on the characteristics of the satellite body and satellite operation characteristics; the space environment simulation device simulates vacuum, radiation, cold black space environment, satellite body, and satellite operation, and has a built-in simulation quantity control platform and test platform; the data driver transmits the 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 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 satellite operation data to the simulation quantity control platform to synchronously adjust the space environment simulation conditions. 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 for vacuum properties, radiation properties, and cold black properties;

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

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

[0014] Furthermore, 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.

[0015] Furthermore, the modeling steps of the satellite operation modeling platform are:

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

[0017] S202: performing data cleaning and denoising preprocessing operations on the collected data, and determining the parameters required for modeling based on the preprocessed data and the actual conditions of the satellite;

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

[0019] Furthermore, the data driver includes 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 equipment, 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, satellite operation model, and analog quantity control platform for data driving.

[0020] Furthermore, the feature data extraction layer is expressed as the following formula:

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

[0022] 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 It 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.

[0023] Furthermore, the data summarization layer is expressed as the following formula:

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

[0025] 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 data of d1, d2, d3, d4, d5, and d6. mark It is a data summarization function used to process the extracted data and summarize it into a queue data set format.

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

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

[0028] Where: D sync represents the driving data synchronously transmitted to the space environment model, satellite operation model, and analog control platform, d represents the summarized space environment data and satellite operation data, S represents the data source is the sensor, I represents the data source is the image, and f mark It is a data summarization function used to process the extracted data and summarize it into a queue data set format. drive It represents the data synchronization driving function, which transmits the summarized queue data set to the space environment model, satellite operation model, and simulation control platform for data driving.

[0029] Furthermore, the test platform is provided with a monitoring and feedback unit, which monitors the test process data and 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, data driver, and satellite body for adjustment.

[0030] Furthermore, the space environment simulation device is equipped with a vacuum chamber, a heat sink system, a radiation simulator, a test flight track, and a flight attitude controller to simulate vacuum, radiation, cold black space environment, and satellite operation respectively, wherein the simulation quantity control platform controls the vacuum chamber, heat sink system, radiation simulator, test flight track, 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 vacuum, radiation, cold black space environment, satellite body, and satellite operation, creating a test environment equivalent to the simulation environment for actual experiments. The data driver transmits the space environment data and satellite operation data to the space environment model and the satellite operation model respectively to generate a prediction model that reveals the temperature distribution and changes inside and outside the satellite body. The data driver simultaneously transmits the space environment data and satellite operation data to the simulation quantity control platform to synchronously adjust the space environment simulation conditions. 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 performs intuitive comparative analysis on the prediction model and the test model, realizes comparative verification of the test process and test results, obtains reliable test data, and improves 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 model with high simulation effect by sequentially creating a space environment geometric model, setting boundary conditions, setting a data input interface, gridding the geometric model, and obtaining simulation results through solver calculation. The entire simulation process is highly efficient. In addition, the simulation accuracy is further improved by specifically setting the boundary conditions of the vacuum, radiation, and cold black space environments. The satellite operation modeling platform of the present invention provides high-quality parameter data support for modeling by collecting satellite bodies, satellite operation orbits, satellite operation attitude parameter data and corresponding data preprocessing. By selecting SpaceSim as a 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 accuracy of the simulation.

[0034] (3) The data driver of the present invention realizes the extraction and summarization of space environment data and satellite operation data through the setting of feature data extraction layer, data summarization layer, data synchronization drive layer and corresponding function formulas. Through data synchronization drive, not only the prediction model and test model that are easy to compare are obtained, but also this real-time synchronous data drive method improves the implementation efficiency of the experiment.

[0035] (4) The monitoring and feedback unit of the test platform of the present invention monitors the test process data and test result data. Once an abnormality is found, it can make timely corrections and adjustments, thus preventing large deviations in the test data caused by negligence during the test process. The space environment simulation device of the present invention is equipped with a vacuum chamber, a heat sink system, a radiation simulator, a test flight track, and a flight attitude controller. It not only realizes the simulation test function, but also further improves the accuracy of the simulation test by comprehensively considering the space environment and the satellite's own structure, the satellite test flight track and the flight attitude and other parameters. BRIEF DESCRIPTION OF THE DRAWINGS

[0036] Figure 1 Schematic diagram of the structure principle of the space environment simulation test system of the present invention;

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

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

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

[0040] Figure 5 The present invention discloses a schematic diagram of the temperature comparison between the inside and outside of the satellite body according to the prediction model and the test model.

[0041] In the above 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- Simulation quantity control platform, 402- Test platform, 403- Vacuum chamber, 404- Heat sink system, 405- Radiation simulator, 406- Test flight track, 407- Flight attitude controller, 5- Test platform, 6- Prediction model, 7- Test model, 8- Satellite body. DETAILED DESCRIPTION

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

[0044] Example

[0045] like Figure 1-Figure 5As shown, 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 platform 5. Among them, the space environment simulation platform 1 creates a space environment model based on the vacuum, radiation, and cold black space environment properties. The satellite operation modeling platform 2 establishes a satellite operation model based on 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 has a built-in 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 simultaneously transmits the space environment data and satellite operation data to the simulation quantity control platform 401 to synchronously adjust the space environment simulation conditions. 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 platform 5 compares and analyzes 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 is bidirectionally connected to the satellite operation modeling platform 2, and the space environment model and satellite operation model generated by them are also connected accordingly. The data driver 3 is an engine component that drives the model operation based on data. The prediction model 6 in this embodiment predicts the temperature distribution and changes inside and outside the satellite body. The corresponding model is as follows Figure 5 As shown in (a) in the figure, the test model 7 is to obtain the temperature distribution and changes inside and outside the satellite body from the actual test. The corresponding model is as follows Figure 5 As shown in (b), the prediction model 6 and the test model 7 are visually compared, and the differences and deviations between the two are analyzed, so as to complete the judgment and verification of the test process data and the test result data. The verified test data is the basis for the satellite thermal design, including the design of the satellite's outer surface coating and the temperature design for internal components, so that the entire satellite is kept within a certain temperature range to prevent damage to the satellite due to excessively high or low temperatures.

[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. The simulation process is as follows:

[0048] S101: Creating a space environment geometric model based on the characteristics of vacuum, radiation, and cold black space environments;

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

[0050] S103: Setting the data input interface for vacuum properties, radiation properties, and cold black properties;

[0051] S104: Divide the spatial environment geometric model with the boundary conditions and data input interface into appropriate grids for discretization solution area;

[0052] S105: Select the solver and set the solution parameters, start the simulation calculation and create the 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 geometric model area of ​​the space environment is set to zero; in a vacuum environment, thermal radiation is the main way of energy transfer. The sun is the radiation source in the space environment. 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; 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 completes the creation of the satellite operation model by selecting modeling tools. The modeling steps of this platform are as follows:

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

[0056] S202: performing data cleaning and denoising preprocessing operations on the collected data, and determining the parameters required for modeling based on the preprocessed data and the actual conditions of the satellite;

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

[0058] The satellite parameters in the above steps include the physical structure, mass distribution, and center of mass of the satellite. The satellite orbit parameters include the satellite's orbital altitude, orbital inclination, and eccentricity. The satellite attitude parameters include the satellite's inertial characteristics, attitude control torque, and satellite axis and orientation. The modeling tool SpaceSim used in this embodiment is a spacecraft-oriented modeling software. This modeling software includes functional modules for calculating satellite orbits and satellite 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 summarization layer, and a data synchronization driver layer. The feature data extraction layer uses sensors and imaging devices to obtain raw space environment data and satellite operation data, which can be expressed as follows:

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

[0061] 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 It 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.

[0062] The data summarization layer classifies, cleans, and arranges the acquired raw space environment data and satellite operation data, and summarizes the data into a queue data set format, which is expressed as the following formula:

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

[0064] 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 data of d1, d2, d3, d4, d5, and d6. mark It is a data summarization function used to process the extracted data and summarize it into a queue data set format.

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

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

[0067] Where: D sync represents the driving data synchronously transmitted to the space environment model, satellite operation model, and analog 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 used to process the extracted data and summarize it into a queue data set format. drive It represents the data synchronization driving function, which transmits the summarized queue data set to the space environment model, satellite operation model, and simulation control platform 401 for data driving.

[0068] The test platform 5 in this embodiment is equipped with a monitoring and feedback unit for monitoring test process data and test result data, analyzing the causes of abnormal data detected, and generating adjustment suggestions for feedback to the space environment simulation device 4, data driver 3, and satellite body 8 for adjustment. In addition, the test platform 5 is equipped with a display unit and a data storage unit. The display unit is used to intuitively display the prediction model 6 and test model 7 as well as related test data, and the data storage unit is used to store various test data for easy query and use. The space environment simulation device 4 in this embodiment is equipped 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. The simulation 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 based on the space environment data and satellite operation data in the data driver 3, thereby achieving 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 track 406, flight attitude controller 407, analog quantity control platform 401, and test platform 402 in this embodiment can be implemented using conventional existing software and hardware designs. The specific software configuration and circuit structure are not detailed in this embodiment. This embodiment further enhances the accuracy of the simulation test by comprehensively considering parameters such as the space environment, the satellite's inherent structure, the satellite's test flight track, and its flight attitude.

[0069] When the present invention is used, the overall test system is first constructed, 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 platform 5. The space environment simulation device 4 includes a vacuum chamber 403, a heat sink system 404, a radiation simulator 405, a test flight track 406, a flight attitude controller 407, a simulation quantity control platform 401, and a test platform 402. Before the test begins, the satellite body 8 to be tested is deployed in the space environment simulation device 4. During the test, the various parts of the overall test system work synchronously and collaboratively. The test platform 5 compares and analyzes the generated 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 test result data. Once an abnormality is found, it is corrected and adjusted in time to prevent significant deviations in the test data due to negligence during the test. The space environment simulation platform 1, satellite operation modeling platform 2, and data driver 3 of this embodiment can all be implemented with existing software technology. The specific simulation process, modeling steps, and software development process of the data-driven process are not repeated in this embodiment.

[0070] The above embodiments are only preferred embodiments of the present invention and are not intended to limit the scope of protection of the present invention. Any changes that adopt the design principles of the present invention and any changes made through non-creative work on this basis should fall within the scope of protection 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 for vacuum properties, radiation properties, and cold black properties; S104: Divide the spatial environment geometric model with the boundary conditions and data input interface into appropriate grids for discretization solution area; S105: Select the solver and set the solution parameters, start the simulation calculation and create the spatial 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: performing data cleaning and denoising preprocessing operations on the collected data, and determining the parameters required for modeling based on the preprocessed data and the actual conditions 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) includes 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 equipment, 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 It 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 data of d1, d2, d3, d4, d5, and d6. mark It is a data summarization function 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 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, satellite operation model, and 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 equipped 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 respectively simulating vacuum, radiation, a cold black space environment, and satellite operation, wherein 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 satellite operation data in the data driver (3).

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