Spacecraft space environment safety guarantee system and method based on three-step calculation

Abstract

The invention discloses a spacecraft space environment safety guarantee system and method based on three-step calculation, and the system comprises two subsystems: a space environment data service subsystem and a three-step calculation and analysis subsystem, and the three-step calculation and analysis subsystem calls data and an algorithm model from the space environment data service subsystem. The space environment safety guarantee analysis based on the three-step calculation is executed; the space environment data service subsystem comprises a metadatabase and a comprehensive database; the metadatabase comprises space environment space-based monitoring data, space environment foundation monitoring data and data from a specified space environment mechanism; the comprehensive database comprises a space environment numerical calculation model library and a spacecraft business application rule algorithm model library; the three-step calculation and analysis subsystem comprises a sun-earth space environment analysis and calculation module, a spacecraft orbit ring layer environment analysis and calculation module and a spacecraft task influence risk assessment and calculation module, and three-step calculation is executed through the three modules.

Description

Technical Field

[0001] This application relates to the field of aerospace technology, and in particular, to a spacecraft space environment safety assurance system and method based on three-step calculation. Background Art

[0002] With the rise and development of space technology, the number of various spacecraft in orbit continues to grow. As high-value, high-tech, and high-precision products, in actual engineering applications, whether it is the design, development, and deployment of spacecraft, or the operation control management and business applications of spacecraft systems, it is necessary to fully consider the impact of space environment factors on their safety assurance.

[0003] The space environment where a spacecraft flies can be called the fourth environment except for land, sea, and atmosphere. In the vast space from the sun to the earth, it is filled with substances such as magnetic fields, plasmas, and particle radiation. Solar activities will cause changes in the distribution and physical state of various species in the space environment. For example, the substances erupted by the sun can propagate along interplanetary space to the earth. During the propagation process, the environment in the sun-earth space is disturbed, which directly or indirectly affects the attitude control, communication navigation, orbital stability, payload operation status, etc. of the spacecraft. In severe cases, it can cause abnormal functions of some components of the spacecraft, which will not only lead to mission interruption but also affect the reliability of the spacecraft to perform space missions.

[0004] The existing risk assessment of spacecraft flight activities is usually based on the observation data of ground monitoring stations or a certain space probe, and then combined with a single model for local risk judgment or specific factors for risk judgment. This risk assessment method lacks a full-process risk analysis from the source of solar activities to the spacecraft operation environment, and does not fully consider the impact of various environmental factors in the entire sun-earth space on flight activities. It is difficult to meet the analysis requirements of safety assurance for different orbits, different spacecraft, and different missions. Therefore, the current risk assessment method has great limitations in the assessment of the spacecraft flight environment.

[0005] To further improve the environmental safety assurance of spacecraft to perform space missions, this solution is proposed. Summary of the Invention

[0006] In view of this, the embodiments of this application provide a spacecraft space environment safety assurance system and method based on three-step calculation.

[0007] The embodiment of the present application provides a spacecraft space environment safety guarantee system based on three-step calculation, including two subsystems: a space environment data service subsystem and a three-step calculation and analysis subsystem. The three-step calculation and analysis subsystem retrieves data and algorithm models from the space environment data service subsystem to perform space environment safety guarantee analysis based on three-step calculation. Among them, the space environment data service subsystem includes: a metadata database and a comprehensive database. Among them, the metadata database includes: space environment space-based monitoring data, space environment ground-based monitoring data, and data from designated space environment agencies. The comprehensive database includes: a space environment numerical calculation model library and a spacecraft service application rule algorithm model library. The three-step calculation and analysis subsystem includes: a solar-terrestrial space environment analysis and calculation module, a spacecraft orbit layer environment analysis and calculation module, and a spacecraft mission impact risk assessment calculation module, which perform three-step calculation through three modules. Among them, the solar-terrestrial space environment analysis and calculation module calls the data and models in the space environment data service subsystem, extracts the solar-terrestrial space environment situation data calculation model from them, inputs the data in the metadata database into the model for multi-source data fusion processing calculation, and outputs space environment data and space environment situation. The spacecraft orbit layer environment analysis and calculation module calls the data and models in the space environment data service subsystem, extracts the spacecraft orbit parameters, mission algorithm rules, and spacecraft flight orbit risk warning calculation model from them, inputs the spacecraft orbit parameters and mission algorithm rules and the output data of the solar-terrestrial space environment analysis and calculation module into the model for flight orbit layer risk calculation, and outputs orbit layer environment impact data and flight risk situation of each layer. The spacecraft mission impact risk assessment calculation module calls the data and models in the space environment data service subsystem, extracts the protection level of spacecraft service devices and spacecraft mission constraint rules from them, and extracts the required spacecraft service devices and mission risk calculation model according to the current mission requirements, inputs the protection level of spacecraft service devices and spacecraft mission constraint rules and the orbit layer environment impact data into the model for matching calculation, and outputs device risk data of spacecraft service devices, mission risk data of the spacecraft, and mission risk situation.

[0008] Optionally, according to the embodiment of the present application, the solar-terrestrial space environment analysis and calculation module performs multi-source data fusion processing calculation, including: matching the required metadata for the solar-terrestrial space environment situation data calculation model in the metadata database, and performing classification identification, filtering and de-duplication, and / or interpolation and filling for the metadata; constructing a solar-terrestrial space grid, where the observation point grid has corresponding metadata and the non-observation point grid has no corresponding metadata; for the observation point grid, using the solar-terrestrial space environment situation data calculation model to perform neural network calculation on the space observation data, and for the non-observation point grid, using the fitting interpolation algorithm to calculate the space environment data parameter values of the non-observation point to obtain the space environment data of the solar-terrestrial space grid.

[0009] Optionally, according to the embodiments of the present application, the solar-terrestrial space environment analysis and calculation module performs multi-source data fusion processing and calculation, further including: using a data visualization algorithm model to perform visualization calculation and scene rendering on the space environment data to generate a space environment situation.

[0010] Optionally, according to the embodiments of the present application, the spacecraft orbital layer environment analysis and calculation module performs flight orbit layer risk calculation, including: importing the output data of the solar-terrestrial space environment analysis and calculation module, multi-source space environment data extracted from the meta-database, and spacecraft orbital parameters extracted from the comprehensive database into the space radiation model, geomagnetic field model, ionosphere model, space atmosphere model, and space debris model, and obtaining the basic data of the space environment impacts corresponding to various space environment impact factors through model operations; matching the orbital parameters of low Earth orbit (LEO), medium Earth orbit (MEO), geostationary orbit (GEO), inclined geosynchronous orbit (IGSO), and interplanetary flight orbit with the basic data to screen out the space environment impact factors and corresponding space environment impact data related to each orbital layer from the basic data; extracting the risk thresholds of spacecraft mission requirements from the mission algorithm rules and performing cross-filtering processing with the space environment impact data of different orbital layers, and outputting the orbital environment data in which each environmental impact factor poses a safety hazard to various spacecraft in each orbital layer.

[0011] Optionally, according to the embodiments of the present application, the spacecraft orbital layer environment analysis and calculation module generates a flight risk situation, specifically including: based on the orbital environment data in which various spacecraft in each orbital layer pose a safety hazard and each spacecraft orbital parameter, performing situation visualization calculation and scene rendering on the impact risks of environmental impact factors on various spacecraft in each layer to generate the flight risk situation of various spacecraft in the orbital layer.

[0012] Optionally, according to an embodiment of the present application, the spacecraft mission impact risk assessment calculation module generates device risk data of spacecraft service devices and mission risk data of the spacecraft, including: using the orbital environment data of the spacecraft in the orbital layer generated by the spacecraft orbital layer environment analysis calculation module, multi-source space environment data extracted from the meta-database, and information of the spacecraft service devices, and respectively invoking the space radiation risk model, geomagnetic field risk model, ionospheric risk model, space atmosphere risk model, and space debris risk model in the comprehensive database to perform spacecraft environmental impact risk model operations to respectively generate service application environment data of the spacecraft in each orbital layer; matching the category of the spacecraft with the environmental risk factors in each orbital layer to extract the environmental risk factors and service application environment data of the spacecraft respectively related to each type of spacecraft from the service application environment data of the spacecraft in each orbital layer; extracting the risk thresholds of each spacecraft service device from the protection levels of the spacecraft service devices provided in the comprehensive database, and performing cross-filtering processing on the risk thresholds of each spacecraft service device and the service application environment data of the corresponding spacecraft to output the device risk data of each spacecraft service device affected by the environmental risk factors, where the device risk data of each spacecraft service device includes device risk level assessment result data; and extracting the risk thresholds of various spacecraft mission requirements from the mission constraint rules provided in the comprehensive database, and performing cross-filtering processing on the risk thresholds of various spacecraft mission requirements and the service application environment data of the corresponding spacecraft to output the mission risk data of various spacecraft affected by the environmental risk factors, where the mission risk data of various spacecraft includes mission risk level assessment result data.

[0013] Optionally, according to an embodiment of the present application, the spacecraft mission impact risk assessment calculation module generates the mission risk situation of each spacecraft service device, including: performing situation visualization calculation and scene rendering based on the impact of the device risk data of each spacecraft service device by the environmental impact factors and the impact of the mission risk data of the spacecraft on various spacecraft mission requirements to generate the mission risk situation of each spacecraft service.

[0014] An embodiment of the present application provides a method for risk assessment of spacecraft flight activities, including: generating a risk assessment result of spacecraft flight activities based on the above spacecraft space environment security guarantee system based on three-step calculation.

[0015] An embodiment of the present application provides an electronic device, which includes a processor and a memory storing computer program instructions; when the processor executes the computer program instructions, the steps of the above method are implemented.

[0016] An embodiment of the present application provides a computer-readable storage medium, on which computer program instructions are stored. When the computer program instructions are executed by a processor, the steps of the method described above are implemented.

[0017] An embodiment of the present application provides a computer program product, which includes computer program instructions. When the computer program instructions are executed by a processor, the steps of the method described above are implemented.

[0018] By adopting the three-step calculation-based spacecraft space environment safety guarantee system provided by the embodiment of the present application, in the three-step calculation-based spacecraft space environment safety guarantee system, through the meta-database in the space environment data service subsystem, the unified access of space-based, ground-based monitoring data and data of designated space environment institutions is realized. Based on the space environment numerical calculation model library and spacecraft service application rule algorithm model library included in the comprehensive database resources, data preparation is made for accurately calculating the safety hazards suffered by the spacecraft subsequently, thereby improving the reliability of the analysis results of spacecraft space environment safety guarantee.

[0019] In the three-step calculation analysis subsystem, first, data fusion and quality optimization processing are performed on multi-source data through the solar-terrestrial space environment analysis calculation module, so as to accurately construct the situation of the current solar-terrestrial space environment; furthermore, based on the spacecraft orbit layer environment analysis calculation module, the flight orbit parameters are combined with the task algorithm rules to dynamically identify the environmental impact risk data and risk thresholds of different orbit layers, and then determine the environmental impact factor risk data corresponding to different types of spacecraft; finally, through the spacecraft mission impact risk assessment calculation module, based on the protection capabilities and mission constraint requirements of spacecraft service devices, the device risk data of spacecraft service devices, the mission risk data of the spacecraft and the mission risk situation are output.

[0020] An embodiment of the present application provides a three-step calculation-based spacecraft space environment safety guarantee system, which constructs a complete data analysis and processing process from solar-terrestrial deep space environment analysis calculation, spacecraft orbit layer environment analysis calculation, and spacecraft mission risk assessment calculation, and can meet the analysis needs of safety guarantee for different orbits, different spacecrafts, and different missions. It provides reliable support for the spacecraft to carry out high-precision mission planning, risk avoidance and resource scheduling in a complex and changeable space environment, and thus helps to improve the safety and controllability of the spacecraft mission during operation. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the following briefly introduces the drawings in the embodiments of the present application.

[0022] Figure 1It is a principle flowchart of a spacecraft space environment safety assurance system based on three-step calculation provided by an embodiment of the present application.

[0023] Figure 2 It is a flowchart of solar-terrestrial space environment analysis and calculation provided by an embodiment of the present application.

[0024] Figure 3 It is a flowchart of spacecraft orbital layer environment analysis and calculation provided by an embodiment of the present application.

[0025] Figure 4 It is a flowchart of spacecraft mission impact risk assessment calculation provided by an embodiment of the present application.

[0026] Figure 5 It is a schematic diagram of a hardware support electronic device for implementing the spacecraft space environment safety assurance analysis method of an embodiment of the present application. Specific embodiments

[0027] The principles and spirits of the present application will be described below with reference to several exemplary embodiments. It should be understood that the purpose of providing these embodiments is to make the principles and spirits of the present application clearer and more thorough, so that those skilled in the art can better understand and then implement the principles and spirits of the present application. The exemplary embodiments provided herein are only a part of the embodiments of the present application, rather than all of the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments herein without creative efforts fall within the scope of protection of the present application.

[0028] It should be noted that the acquisition, storage, use, processing, etc. of data in the embodiments of the present application all comply with the relevant regulations of national laws and regulations.

[0029] In this article, terms such as first, second, and third are only used to distinguish one entity (or operation) from another entity (or operation), and do not require or imply any order or association between these entities (or operations).

[0030] The embodiments of the present application relate to terminal devices and / or servers. Those skilled in the art know that the embodiments of the present application can be implemented as a system, device, equipment, method, computer-readable storage medium, or computer program product. Therefore, the present disclosure can be specifically implemented in at least one of the following forms: complete hardware, complete software, or a combination of hardware and software.

[0031] With the rise and development of space technology, the number of various spacecraft in orbit continues to grow. As high-value, high-tech, and high-precision products, in actual engineering applications, whether it is spacecraft design, development, deployment, or spacecraft system operation control management and business applications, it is necessary to fully consider the impact of space environmental factors on their safety guarantee.

[0032] The spacecraft space environment safety guarantee system based on three-step calculation provided by the embodiments of the present application can accurately analyze various influencing factors faced by the spacecraft and its payloads and the degree of influence suffered, realize a more comprehensive and refined assessment of the influence suffered by the spacecraft and its payloads during the flight process, and provide a more reliable decision-making basis for flight mission adjustment, orbit scheduling, and payload protection. It is mainly completed in steps through the method of "basic data + model matching": (1) Analyze and calculate the 5-layer environment of the solar-terrestrial space environment based on multi-source data of the space environment. For example, the 5 layers of the solar-terrestrial space environment are the solar / planetary interplanetary region, the solar wind / magnetosphere coupling region, the inner magnetosphere region, the ionosphere region, and the middle and upper atmosphere region; (2) Analyze and calculate the environment based on the orbit layer of the spacecraft operation; (3) Analyze, predict, warn, and assess risks of the environmental situation based on the spacecraft business, and realize a more refined quantitative assessment of the degree of influence on the spacecraft at different times and different spatial positions, which can significantly improve the effectiveness of the spacecraft space environment safety guarantee task.

[0033] Specifically, the present application provides a spacecraft space environment safety guarantee system and method based on three-step calculation. Attached Figure 1 is a schematic diagram of the architecture of the spacecraft space environment safety guarantee system based on three-step calculation according to the embodiments of the present application.

[0034] See Figure 1 , the spacecraft space environment safety guarantee system based on three-step calculation includes two subsystems: the space environment data service subsystem and the three-step calculation analysis subsystem. Among them, the three-step calculation analysis subsystem retrieves data and algorithm models from the space environment data service subsystem to perform the space environment safety guarantee analysis based on three-step calculation.

[0035] The space environment data service subsystem includes: a metadata database and a comprehensive database.

[0036] The metadata database includes: space environment space-based monitoring data, space environment ground-based monitoring data, and data from designated space environment agencies.

[0037] The comprehensive database includes: a space environment numerical calculation model library and a spacecraft business application rule algorithm model library.

[0038] The three-step calculation and analysis subsystem includes: a solar-terrestrial space environment analysis and calculation module, a spacecraft orbit layer environment analysis and calculation module, and a spacecraft mission impact risk assessment calculation module. Three-step calculation is performed through these three modules.

[0039] Specifically, the solar-terrestrial space environment analysis and calculation module calls the data and models in the space environment data service subsystem, extracts the solar-terrestrial space environment situation data calculation model from them, inputs the data in the metadata database into the model for multi-source data fusion processing calculation, and outputs the space environment data and the space environment situation.

[0040] The spacecraft orbit layer environment analysis and calculation module calls the data and models in the space environment data service subsystem, extracts the spacecraft orbit parameters, mission algorithm rules, and spacecraft flight orbit risk warning calculation model from them, inputs the spacecraft orbit parameters, mission algorithm rules, and the output data of the solar-terrestrial space environment analysis and calculation module into the model for flight orbit layer risk calculation, and outputs the orbit layer environment impact data and the flight risk situation of each layer.

[0041] The spacecraft mission impact risk assessment calculation module calls the data and models in the space environment data service subsystem, extracts the protection level of spacecraft service devices and spacecraft mission constraint rules from them, and extracts the required spacecraft service devices and mission risk calculation model according to the current mission requirements. Input the protection level of spacecraft service devices, spacecraft mission constraint rules, and orbit layer environment impact data into the model for matching calculation, and output the device risk data of spacecraft service devices, the mission risk data of the spacecraft, and the mission risk situation.

[0042] The following combines specific embodiments to elaborate in detail on the composition, functions, and operation methods of each module in the above system.

[0043] Communication can be carried out between the space environment data service subsystem and the three-step calculation and analysis subsystem. A user service dedicated information network can be pre-constructed between the space environment data service subsystem and the three-step calculation and analysis subsystem for the spacecraft space environment security guarantee system based on three-step calculation to obtain the required data. The space environment data service subsystem library can store the metadata provided by space-based monitoring devices, ground-based monitoring devices, and space environment agencies. The space environment data service subsystem also includes a comprehensive database, which can be at least divided into a space environment numerical calculation model library and a spacecraft service application rule algorithm model library.

[0044] The Space Environment Data Service Subsystem can communicate with at least any one of space-based monitoring devices, ground-based monitoring devices, and space environment agencies. As the data sources, the space-based monitoring devices, ground-based monitoring devices, and space environment agencies can import the data they generate into the Space Environment Data Service Subsystem. The Space Environment Data Service Subsystem stores the metadata provided by the space-based monitoring devices, ground-based monitoring devices, and space environment agencies.

[0045] In some embodiments, the space-based monitoring devices include space environment observation satellites with different orbital altitudes. For example, satellites such as ACE satellite, GOES satellite, POES satellite, etc., which are used to collect space environment observation data.

[0046] The ground-based monitoring devices include space environment observation devices located on the ground. For example, devices such as GNSS receiving station arrays, geomagnetic stations, coronagraphs, ionospheric radars, etc.

[0047] The space environment agency can include professional agencies engaged in space weather monitoring, space environment modeling, early warning release, and technology research. The space environment agency can provide the observation data processed professionally to the Space Environment Data Service Subsystem, and can also provide verified and accurate product data, such as F10.7 index, KP index, etc.

[0048] The metadata of the space-based monitoring devices, ground-based monitoring devices, and space environment agencies can be used as metadata. To improve the data quality of the metadata, the metadata from multiple sources can be fused and processed. Specifically, the Sun-Earth Space Environment Analysis and Calculation Module performs multi-source data fusion and processing calculations, including: matching the required metadata for the Sun-Earth space environment situation data calculation model in the metadata database, and performing classification identification, filtering and deduplication, and / or interpolation and filling for the metadata; constructing a Sun-Earth space grid, where the observation point grid has corresponding metadata, and the non-observation point grid has no corresponding metadata; for the observation point grid, using the Sun-Earth space environment situation data calculation model to perform neural network calculations on the space observation data, and for the non-observation point grid, using the fitting interpolation algorithm to calculate the space environment data parameter values of the non-observation point, so as to obtain the space environment data of the Sun-Earth space grid.

[0049] Figure 2 is a flowchart of the Sun-Earth space environment analysis and calculation provided by the embodiments of the present application. Combined with Figure 2 shown, the fusion processing can at least include at least any one or more of the following processing steps: access and aggregation, classification identification, filtering and deduplication, interpolation and filling, quality optimization, storage into the database, etc., which are processing processes to improve data quality. After the multi-source data is fused and processed, it can be used to generate space environment data and space environment situation.

[0050] Optionally, during the fusion process, the observed data can be processed for unified time alignment, format conversion, and duplicate value removal, so as to solve the problems of inconsistent data accuracy and coverage of different observation devices, and facilitate improving the data quality. Classify and label these metadata sources, physical types, timestamps, spatial positions, etc., to form structured metadata with data labels. From these labeled metadata, extract the metadata obtained within the target time period and having geographical spatial coordinates or orbital position identifiers, and determine the position nodes corresponding to the metadata according to the geographical spatial coordinates or orbital position identifiers, so as to obtain the spatial environment data corresponding to multiple observation points within the target time period.

[0051] In some embodiments of the present application, the solar-terrestrial space environment analysis and calculation module can pre-construct a solar-terrestrial space grid, and obtain more comprehensive space environment data by determining the spatial environment data corresponding to each grid. In the embodiments of the present application, by complementing the spatial environment data of non-observation point grids, higher-precision and continuous space environment data is obtained as the basis for safety guarantee analysis, which helps to improve the reliability of the safety guarantee analysis results.

[0052] In some embodiments, space weather events may pose safety hazards to spacecraft and payloads, etc. Different types of space weather events may result in different safety hazards. Based on this, in the metadata provided by the space environment data service subsystem, extract the data required for judging and predicting space weather events. For example, convert the physical quantity names, unit formats, and time granularities of the metadata into a preset data format to improve the accuracy of judging whether a space weather event occurs.

[0053] Specifically, in the metadata, extract the parameter values of the event parameters corresponding to the weather event, determine the temporal variation characteristics and position variation characteristics of the parameter values of the event parameters, and then, based on the pre-constructed space weather event judgment rules, determine whether a space weather event occurs, and when a space weather event occurs, information such as the start time, peak value, end time, and involved spatial positions corresponding to the space weather event. Exemplarily, the space weather data can at least include the following information: the parameter values of the event parameters corresponding to the weather event, the temporal variation characteristics and position variation characteristics of the parameter values of the event parameters, and when a space weather event occurs, information such as the start time, peak value, end time, and involved spatial positions corresponding to the space weather event.

[0054] In some embodiments, a specific space weather sample database is established for space weather events, and space weather data is stored through the space weather sample database. Optionally, the space weather data can be divided and stored according to the source of the event. For example, the corresponding sources of the space weather data include solar activities, geomagnetic activities, and cosmic high-energy particle activities. The solar activity information includes: solar flares, coronal mass ejections, solar winds, and solar proton events; the geomagnetic activity information includes: geomagnetic activities and magnetospheric disturbances; the cosmic high-energy particle activity information includes: cosmic rays and high-energy particle bursts.

[0055] In the embodiments of the present application, when security analysis is required, it is not necessary to recalculate in real time and in full volume. The required data can be directly extracted, thereby improving the calculation efficiency. In addition, the more space weather data stored in the space weather sample database, the more accurate the judgment of weather events can be, which in turn helps to improve the reliability of security analysis.

[0056] Based on the embodiments of the present application, in the spacecraft space environment security system based on three-step calculation, through the meta-database in the space environment data service subsystem, the unified access of space-based and ground-based monitoring data and the data of designated space environment agencies is realized. Based on the space environment numerical calculation model library and the spacecraft business application rule algorithm model library included in the comprehensive database resources, data preparation is done for accurately calculating the security hazards suffered by the spacecraft later. For accurately calculating the influence degrees of the spacecraft suffered from environmental factors such as high-energy particle radiation, middle and upper atmospheric drag, ionospheric disturbance, and space debris collision, the reliability of the analysis results of the spacecraft space environment security can be improved.

[0057] In some embodiments of the present application, the multi-source data fusion processing calculation performed by the solar-terrestrial space environment analysis and calculation module further includes: using the data visualization algorithm model to perform visualization calculation and scene rendering on the space environment data to generate the space environment situation.

[0058] In some embodiments of the present application, after the processing of space environment data is completed, next, risk data processing can be performed. Specifically, the spacecraft orbit layer environment analysis and calculation module performs flight orbit layer risk calculation, including: importing the output data of the solar-terrestrial space environment analysis and calculation module, multi-source space environment data extracted from the meta-database, and spacecraft orbit parameters extracted from the comprehensive database into the space radiation model, geomagnetic field model, ionosphere model, space atmosphere model, and space debris model, and obtaining the basic data of the space environment impact corresponding to various space environment impact factors through model operations; matching the orbit parameters of low Earth orbit (LEO), medium Earth orbit (MEO), geostationary orbit (GEO), inclined geosynchronous orbit (IGSO), and interplanetary flight orbit with the basic data to screen out the space environment impact factors and corresponding space environment impact data related to each orbit layer from the basic data; extracting the risk thresholds of spacecraft mission requirements from the mission algorithm rules, and performing cross-filtering processing with the space environment impact data of different orbit layers to output the orbit environment data in which each environmental impact factor poses a safety hazard to various spacecraft in each orbit layer.

[0059] Figure 3 is a flowchart of spacecraft orbit layer environment analysis and calculation provided by an embodiment of the present application. As shown in combination with Figure 3 shown, the space environment models provided by the spacecraft space environment safety guarantee system based on three-step calculation can at least include multiple model categories such as space radiation model, geomagnetic field model, ionosphere model, space atmosphere model, and space debris model, and obtain the basic data of the space environment impact corresponding to various space environment impact factors through model operations.

[0060] Regarding the models that can be adopted, there are already rich space environment algorithm models in the art. For example, for the atmosphere, middle and upper atmosphere, ionosphere, magnetic field, radiation belt, space debris, etc., there are known algorithm models that can be used. The main environmental impact factors / parameters involved in the relevant models are, for example: atmospheric density, temperature, pressure, upper atmospheric density, thermospheric atmospheric density, horizontal wind, electron density, temperature, composition, ions (O*, H+, He+, NO+, O2+), Earth's magnetic field strength and vector, Earth's magnetic field trapped protons and electrons, space debris density and velocity, and so on.

[0061] Different orbit altitudes correspond to their respective space environment impact factors. For example, the LEO orbit is mainly affected by ionospheric disturbances and space debris, the MEO orbit is mainly affected by the change in radiation belt intensity, the GEO orbit is mainly affected by solar wind changes and magnetic storm interference, and the interplanetary flight orbit will be mainly affected by more complex solar particle events and cosmic rays. Details are not listed here one by one.

[0062] After determining the basic data of the space environment impact corresponding to the space environment impact factors, the orbital parameters of the low Earth orbit (LEO), medium Earth orbit (MEO), geostationary orbit (GEO), inclined geosynchronous orbit (IGSO), and interplanetary flight orbit are matched with the basic data to screen out the space environment impact factors and the corresponding space environment impact data related to each orbital layer from the basic data.

[0063] Each orbital layer corresponds to at least one space environment impact factor. By extracting the risk threshold of the spacecraft mission requirements in the task algorithm rules and performing cross-filtering processing with the space environment impact data of different orbital layers, the orbital environment data indicating that various environmental impact factors pose safety hazards to various spacecraft in each orbital layer is output.

[0064] Exemplarily, Table 1 shows some environmental impact factors and the impacts generated by the environmental impact factors corresponding to each orbital layer.

[0065] Table 1 Space Environment Factors and Their Impacts on Each Orbital Layer

[0066] According to the embodiments of the present application, by calling the spacecraft orbital parameters extracted from the comprehensive database and various spacecraft flight orbit risk warning calculation models, the basic data corresponding to different spatial positions of various space environment impact factors within different altitude ranges is accurately generated. Furthermore, in combination with the orbital parameters of each flight orbit, the orbital environment data indicating that various environmental impact factors pose safety hazards to various spacecraft in each orbital layer is found.

[0067] In some embodiments, the spacecraft orbital layer environment analysis and calculation module generates a flight risk situation, which specifically includes: based on the orbital environment data indicating that various environmental impact factors pose safety hazards to various spacecraft in each orbital layer and the orbital parameters of each spacecraft, performing situation visualization calculation and scenario rendering on the impact risks of the environmental impact factors on various spacecraft in each layer to generate the flight risk situation of various spacecraft in the orbital layer.

[0068] Based on the flight risk situation, the change process of the risk over time can be intuitively reflected, enabling relevant staff to conveniently understand the high-risk areas and the risk evolution path, which helps to improve the safety of spacecraft in the complex space environment.

[0069] In some embodiments, the spacecraft mission impact risk assessment calculation module generates device risk data for spacecraft service devices and mission risk data for the spacecraft, including: the orbital environment data of the spacecraft in the orbital layers generated by the spacecraft orbital layer environment analysis calculation module, multi-source space environment data extracted from the meta-database, and information on spacecraft service devices, and respectively invoking the space radiation risk model, geomagnetic field risk model, ionosphere risk model, space atmosphere risk model, and space debris risk model in the comprehensive database to perform spacecraft environment impact risk model operations, and respectively generating the service application environment data of the spacecraft in each orbital layer. Matching the category of the spacecraft with the environmental risk factors in each orbital layer to extract the environmental risk factors and the service application environment data of the spacecraft respectively related to each type of spacecraft from the service application environment data of the spacecraft in each orbital layer.

[0070] In the protection levels of spacecraft service devices provided by the comprehensive database, extract the risk thresholds of each spacecraft service device, and perform cross-filtering processing on the risk thresholds of each spacecraft service device and the service application environment data of the corresponding spacecraft to output the device risk data of each spacecraft service device affected by environmental risk factors. The device risk data of each spacecraft service device includes device risk level assessment result data; and, in the mission constraint rules provided by the comprehensive database, extract the risk thresholds of various spacecraft mission requirements, and perform cross-filtering processing on the risk thresholds of various spacecraft mission requirements and the service application environment data of the corresponding spacecraft to output the mission risk data of various spacecraft affected by environmental risk factors. Among them, the mission risk data of various spacecraft includes mission risk level assessment result data.

[0071] Exemplarily, spacecraft include, for example, communication satellites, remote sensing satellites, navigation satellites, space stations, near-space vehicles, etc., and environmental risk factors include, for example, radiation, geomagnetism, ionosphere, atmosphere, debris, etc.

[0072] Figure 4 is a flowchart of a spacecraft mission impact risk assessment calculation provided by an embodiment of the present application. As shown in combination with Figure 4 screen out the environmental risk factors corresponding to each type of spacecraft, match the category of the spacecraft with the environmental risk factors in each orbital layer, and then determine the environmental risk factors and the service application environment data of the spacecraft respectively related to each type of spacecraft.

[0073] Different spacecraft and different missions have different capabilities to withstand the environment. Based on this, the spacecraft orbital layer environment analysis and calculation module is configured to generate device risk data for spacecraft service devices and mission risk data for spacecraft according to the actual usage and flight missions of the spacecraft. Specifically, the risk thresholds of each spacecraft service device are cross-filtered with the service application environment data of the corresponding spacecraft to output the device risk data of each spacecraft service device due to environmental risk factors, and the risk thresholds of various spacecraft mission requirements are cross-filtered with the service application environment data of the corresponding spacecraft to output the mission risk data of various spacecraft due to environmental risk factors. Through cross-filtering analysis, it is determined one by one which environmental risk factors in the orbital layer will pose a safety hazard to spacecraft service devices or flight missions, so as to comprehensively find out the environmental impact factors with safety risks, and then the parameter values corresponding to these environmental impact factors can be output.

[0074] Spacecraft service devices include devices related to the operation of the spacecraft platform itself and payloads. Among them, after being affected by safety risks, the payload may have the following abnormal operating conditions: computer software errors, communication and measurement and control interruptions, charging / discharging, chemical damage, radiation damage, mechanical damage, attitude anomalies, and orbit perturbations, etc., which are not listed one by one here.

[0075] The environmental impact factors faced by spacecraft at different flight altitudes are not exactly the same, and the tolerance capabilities of spacecraft and their payloads may also be different. For example, the environmental impact factors faced by spacecraft such as solar electromagnetic radiation, ionosphere, Earth radiation belts, and upper atmosphere. Among them, solar electromagnetic radiation will have an obvious impact on the temperature of the spacecraft, and the upper atmosphere will have a general impact on the temperature of the spacecraft; the ionosphere will affect the communication and measurement and control capabilities of the payload; while the Earth radiation belts will not have an obvious impact on the temperature of the spacecraft and the communication and measurement and control of the payload, but the Earth radiation belts may cause computer software errors in the payload.

[0076] The tolerance levels of different payloads to safety hazards, and even for the same type of payload, due to different usage situations, there will also be differences in their tolerance levels. Therefore, in the embodiments of the present application, for each payload, the matching risk threshold is called to achieve more refined safety guarantee analysis.

[0077] For example, in the face of the same environment of high-energy electron flux, for an imaging payload with a high radiation protection level, its tolerance ability is relatively strong, and the impact level in the evaluation result may be "slight impact"; while for the same type of payload that has been in operation for many years and has aging problems, the impact level in the evaluation result may be "moderate impact" or even "severe impact". As a specific example, the risk of single-event upset can be divided into 5 impact levels. As shown in Table 2, different impact levels correspond to different degrees of being affected.

[0078] Table 2 Single-particle Risk Level Classification

[0079] Since there are also differences in the precision requirements for the reliability of device operation due to different mission requirements, therefore, based on this, the spacecraft mission impact risk assessment calculation module is configured to extract the risk thresholds of various spacecraft mission requirements from the mission constraint rules provided by the comprehensive database, and perform cross-filtering processing on the risk thresholds of various spacecraft mission requirements and the service application environment data of the corresponding spacecraft, and output the mission risk data of various spacecraft affected by environmental risk factors, where the mission risk data of various spacecraft includes the evaluation result data of the mission risk level.

[0080] In an example, when the environmental impact factor includes the influence factor of magnetospheric plasma, it may cause the risk of deep charging of the spacecraft. In the environment of magnetospheric plasma, the influence level information of the deep charging of the spacecraft can be divided into 5 influence levels. As shown in Table 3, different influence levels correspond to different degrees of influence.

[0081] Table 3 Deep Charging Influence Level Classification

[0082] It can be understood that the specific values provided in the embodiments of the present application are for the convenience of understanding the specific solutions of the present application, rather than specific limitations on the technical solutions of the present application. The basis for the classification of specific numerical risk levels can be adjusted according to actual application requirements.

[0083] Based on the device risk data provided by the space environment security guarantee and the generated mission risk data of the spacecraft, for any spacecraft, the device risk data of the spacecraft service devices and the mission risk data of the spacecraft existing at that location can be found in combination with the space positions passed by the spacecraft during its flight period, so that a security guarantee analysis result can be provided for each spacecraft.

[0084] In some alternative embodiments, the spacecraft mission impact risk assessment calculation module generates the mission risk situation of each spacecraft service device, including: performing situation visualization calculation and scene rendering based on the influence of the environmental impact factor on the device risk data of each spacecraft service device and the influence of the mission risk data of the spacecraft on various spacecraft mission requirements, and generating the mission risk situation of each spacecraft service.

[0085] Based on the dynamic effect diagram, the time-varying process of the risk situation can be intuitively reflected, enabling relevant staff to conveniently understand high-risk areas and the risk evolution path, which helps improve the safety of spacecraft in complex space environments.

[0086] To more clearly introduce the spacecraft space environment safety assurance system based on three-step calculation of this application, the following is another embodiment of this application.

[0087] In the first step, during the processing of space data, metadata can be called in the space environment data service subsystem to calculate and generate solar-terrestrial space environment background data and space weather data. Among them, the processing of metadata includes, but is not limited to, processes for improving data quality such as access and aggregation, classification and identification, filtering and deduplication, interpolation and filling, quality optimization, and storage in the database.

[0088] Optionally, after generating the fused metadata, situation data of the space environment can also be generated based on the fused metadata. The data situation generation process includes, but is not limited to, processes such as data reading, customized requirement verification, model matching, visualization calculation, data verification, scene rendering, and situation data presentation, and finally outputs space environment data and space environment situation.

[0089] In the second step, when analyzing and calculating the orbital layers, the corresponding space environment models of each orbital layer can be called respectively. For example, space radiation models, geomagnetic field models, ionosphere models, space atmosphere models, and space debris models, etc., are not listed one by one here. Input the spacecraft orbital parameters, task algorithm rules, and the output data of the solar-terrestrial space environment analysis and calculation module into the model to obtain the basic data of the space environment impacts corresponding to various space environment impact factors. Match different orbital parameters with the basic data to screen out the space environment impact factors and corresponding space environment impact data related to each orbital layer from the basic data. Extract the risk thresholds required for the spacecraft tasks from the task algorithm rules, and conduct cross-filtering analysis of the spacecraft task requirement risk thresholds and environmental impact factors, and output the risk data of the space environment factors on the spacecraft in each layer; Optionally, based on the orbital environment data that poses safety hazards to various spacecraft in each orbital layer and the orbital parameters of each spacecraft, conduct situation visualization calculation and scene rendering on the impact risks of environmental impact factors on various spacecraft in each layer to generate the flight risk situation of various spacecraft in the orbital layer.

[0090] Finally, during the risk assessment process, the data and models in the space environment data service subsystem are called to extract the protection levels of spacecraft service devices and the spacecraft mission constraint rules, and the required spacecraft service devices and mission risk calculation models are extracted according to the current mission requirements. The protection levels of spacecraft service devices, the spacecraft mission constraint rules, and the orbital layer environment impact data are input into the models to generate the service application environment data of spacecraft in each orbital layer respectively.

[0091] Match various spacecraft with the service application environment data of the spacecraft, and cross-filter and analyze the respective environmental risk factors of various spacecraft and the service application environment data of the spacecraft. Output the device risk data of each spacecraft service device due to environmental risk factors, and the device risk data includes the device risk level assessment result data.

[0092] Optionally, based on the impact of environmental impact factors on the device risk data of each spacecraft service device, and based on the impact of the mission risk data of the spacecraft on the mission requirements of various spacecraft, perform situation visualization calculation and scene rendering to generate the mission risk situation of each spacecraft service, so as to facilitate relevant staff to understand the environmental conditions of the sun-earth space.

[0093] Corresponding to the spacecraft space environment safety guarantee system based on three-step calculation of the present application, an embodiment of the present application further provides a spacecraft space environment safety guarantee analysis method based on three-step calculation, which is used to generate the risk assessment result of spacecraft flight activities.

[0094] The process of the spacecraft space environment safety guarantee analysis method based on three-step calculation is as shown in the appendix Figure 1 As shown, the safety guarantee result is generated through three-step calculation. For specific details, reference can be made to the corresponding part of the spacecraft space environment safety guarantee system based on three-step calculation provided in the above embodiment of the present application. For the sake of brevity, it will not be elaborated here.

[0095] The electronic device in the embodiment of the present application can be a user terminal device, a server, or other computing devices, or a cloud server. Figure 5 The schematic diagram of the hardware structure of the electronic device showing the embodiment of the present application is shown. The electronic device may include a processor 501 and a memory 502 storing computer program instructions. When the processor 501 executes the computer program instructions, it realizes the process or function of the method in any of the above embodiments.

[0096] Specifically, the processor 501 may include a central processing unit (CPU), or an application specific integrated circuit (ASIC), or may be one or more integrated circuits configured to implement the embodiments of the present application. The memory 502 may include a mass memory for data or instructions. For example, the memory 502 may be at least one of the following: a hard disk drive (HDD), a read-only memory (ROM), a random access memory (RAM), a floppy disk drive, a flash memory, an optical disc, a magneto-optical disc, a magnetic tape, a universal serial bus (USB) drive, or other physical / tangible memory storage devices. Additionally, the memory 502 may include removable or non-removable (or fixed) media. Further, the memory 502 may be internal or external to the integrated gateway disaster recovery device. The memory 502 may be a non-volatile solid-state memory. In other words, generally, the memory 502 includes a tangible (non-transitory) computer-readable storage medium (such as a memory device) encoded with computer-executable instructions, and when the software is executed (such as by one or more processors), it can perform the operations described in the methods of the embodiments of the present application. The processor 501 realizes the processes or functions of any one of the methods in the above embodiments by reading and executing the computer program instructions stored in the memory 502.

[0097] In one example, Figure 5 The illustrated electronic device may further include a communication interface 503 and a bus 510. Among them, the processor 501, the memory 502, and the communication interface 503 are connected through the bus 510 to complete communication with each other. The communication interface 503 is mainly used to implement communication between the modules, devices, units, and / or devices in the embodiments of the present application. The bus 510 includes hardware, software, or both, and can couple the components of the online data flow charging device to each other. For example, the bus may include at least one of the following: an accelerated graphics port (AGP) or other graphics bus, an enhanced industry standard architecture (EISA) bus, a front-side bus (FSB), a hypertransport (HT) interconnect, an industry standard architecture (ISA) bus, an infinite bandwidth interconnect, a low pin count (LPC) bus, a memory bus, a microchannel architecture (MCA) bus, a peripheral component interconnect (PCI) bus, a PCI-Express (PCI-X) bus, a serial advanced technology attachment (SATA) bus, a video electronics standards association local (VLB) bus, or other suitable buses. The bus 510 may include one or more buses. Although the embodiments of the present application describe or illustrate specific buses, the embodiments of the present application may consider any suitable bus or interconnect method.

[0098] Combined with the methods in the above embodiments, an embodiment of the present application further provides a computer-readable storage medium, on which computer program instructions are stored, and when the computer program instructions are executed by a processor, the processes or functions of any one of the methods in the above embodiments are implemented.

[0099] In addition, an embodiment of the present application further provides a computer program product, on which computer program instructions are stored, and when the computer program instructions are executed by a processor, the processes or functions of any one of the methods in the above embodiments are implemented.

[0100] The flowcharts and / or block diagrams of the methods, devices, systems and computer program products of the embodiments of the present application have been described above by way of example, and the relevant aspects have been described. It should be understood that each block in the flowchart and / or block diagram, or a combination thereof, can be implemented by computer program instructions, or by dedicated hardware that performs the specified function or action, or by a combination of dedicated hardware and computer instructions. For example, these computer program instructions can be provided to the processor of a general-purpose computer, a special-purpose computer or other programmable data processing device to form a machine, so that these instructions executed by the processor enable the implementation of the specified function / action in each block or a combination thereof in the flowchart and / or block diagram. Such a processor can be a general-purpose processor, a special-purpose processor, a special application processor or a field programmable logic circuit.

[0101] The functional blocks shown in the block diagrams of the embodiments of the present application can be implemented as hardware, software, firmware or a combination thereof. When implemented in hardware, it can be, for example, an electronic circuit, an application specific integrated circuit (ASIC), appropriate firmware, a plug-in, a functional card, etc.; when implemented in software, it is a program or code segment used to perform the required tasks. The program or code segment can be stored in a memory, or transmitted via a data signal carried in a carrier wave on a transmission medium or a communication link. The code segment can be downloaded via a computer network such as the Internet, an intranet, etc.

[0102] It should be noted that the present application is not limited to the specific configurations and processes described above or shown in the figures. The above are only specific embodiments of the present application. Those skilled in the art can clearly understand that for the convenience and brevity of description, the specific working processes of the described system, device, module or unit can refer to the corresponding processes in the method embodiments and will not be described in detail again. It should be understood that the protection scope of the present application is not limited thereto. Any person skilled in the art can think of various equivalent modifications or substitutions within the technical scope disclosed by the present application, and these modifications or substitutions should be covered within the protection scope of the present application.

Claims

1. A spacecraft space environment safety guarantee system based on three-step calculation, characterized in that, It includes two subsystems: the space environment data service subsystem and the three-step calculation and analysis subsystem. The three-step calculation and analysis subsystem retrieves data and algorithm models from the space environment data service subsystem to perform the analysis of space environment security assurance based on three-step calculation. Among them, the space environment data service subsystem includes: a metadata database and a comprehensive database. Among them, the metadata database includes: space environment space-based monitoring data, space environment ground-based monitoring data, and data from designated space environment agencies; the comprehensive database includes: a space environment numerical calculation model library and a spacecraft service application rule algorithm model library; the three-step calculation and analysis subsystem includes: a solar-terrestrial space environment analysis and calculation module, a spacecraft orbit layer environment analysis and calculation module, and a spacecraft mission impact risk assessment calculation module, which perform the three-step calculation through the three modules. Among them, the solar-terrestrial space environment analysis and calculation module calls the data and models in the space environment data service subsystem, extracts the solar-terrestrial space environment situation data calculation model from them, inputs the data in the metadata database into the model for multi-source data fusion processing calculation, and outputs space environment data and space environment situation; the spacecraft orbit layer environment analysis and calculation module calls the data and models in the space environment data service subsystem, extracts spacecraft orbit parameters, mission algorithm rules, and a spacecraft flight orbit risk warning calculation model from them, inputs the spacecraft orbit parameters and mission algorithm rules and the output data of the solar-terrestrial space environment analysis and calculation module into the model for flight orbit layer risk calculation, and outputs orbit layer environment impact data and the flight risk situation of each layer; the spacecraft mission impact risk assessment calculation module calls the data and models in the space environment data service subsystem, extracts the protection level of spacecraft service devices and spacecraft mission constraint rules from them, and extracts the required spacecraft service devices and mission risk calculation model according to the current mission requirements, inputs the protection level of spacecraft service devices and spacecraft mission constraint rules and the orbit layer environment impact data into the model for matching calculation, and outputs the device risk data of spacecraft service devices, the mission risk data of the spacecraft, and the mission risk situation.

2. The system according to claim 1, wherein The multi-source data fusion processing calculation performed by the solar-terrestrial space environment analysis and calculation module includes: matching the required metadata for the solar-terrestrial space environment situation data calculation model in the metadata database, and performing classification identification, filtering and de-duplication, and / or interpolation and filling for the metadata; constructing a solar-terrestrial space grid, where the observation point grid has corresponding metadata and the non-observation point grid has no corresponding metadata; for the observation point grid, using the solar-terrestrial space environment situation data calculation model to perform neural network calculation on space observation data, and for the non-observation point grid, using the fitting interpolation algorithm to calculate the space environment data parameter values of the non-observation point to obtain the space environment data of the solar-terrestrial space grid.

3. The system according to claim 2, characterized in that, The multi-source data fusion processing calculation performed by the solar-terrestrial space environment analysis and calculation module also includes: Use a data visualization algorithm model to perform visualization calculations and scene rendering on the space environment data to generate a space environment situation.

4. The system according to claim 1, characterized in that, The spacecraft orbital layer environment analysis and calculation module performs flight orbit layer risk calculations, including: Import the output data of the solar-terrestrial space environment analysis and calculation module, multi-source space environment data extracted from the meta-database, and spacecraft orbit parameters extracted from the comprehensive database into the space radiation model, geomagnetic field model, ionosphere model, space atmosphere model, and space debris model. Through model operations, obtain the basic data of the space environment impacts corresponding to various space environment impact factors; Match the orbit parameters of low Earth orbit (LEO), medium Earth orbit (MEO), geostationary orbit (GEO), inclined geosynchronous orbit (IGSO), and interplanetary flight orbit with the basic data to screen out the space environment impact factors and corresponding space environment impact data related to each orbit layer from the basic data; Extract the spacecraft mission requirement risk thresholds from the mission algorithm rules, and perform cross-filtering processing with the space environment impact data of different orbit layers to output the orbit environment data of the safety hazards of various environmental impact factors to various spacecraft in each orbit layer.

5. The system according to claim 4, wherein The spacecraft orbital layer environment analysis and calculation module generates a flight risk situation, specifically including: Based on the orbit environment data of the safety hazards of various spacecraft in each orbit layer and the orbit parameters of each spacecraft, perform situation visualization calculations and scene rendering on the impact risks of environmental impact factors on various spacecraft in each layer to generate the flight risk situation of various spacecraft in the orbit layer.

6. The system according to claim 1, wherein The spacecraft mission impact risk assessment and calculation module generates device risk data for spacecraft service devices and mission risk data for spacecraft, including: Import the orbit environment data of the spacecraft in the orbit layer generated by the spacecraft orbital layer environment analysis and calculation module, multi-source space environment data extracted from the meta-database, and information on spacecraft service devices, and separately call the space radiation risk model, geomagnetic field risk model, ionosphere risk model, space atmosphere risk model, and space debris risk model in the comprehensive database to perform spacecraft environmental impact risk model operations to respectively generate the service application environment data of spacecraft in each orbit layer; Match the categories of spacecraft with the environmental risk factors of each orbit layer to extract the environmental risk factors and the service application environment data of spacecraft related to various spacecraft respectively from the service application environment data of spacecraft in each orbit layer; Extract the risk thresholds of each spacecraft service device from the protection levels of spacecraft service devices provided in the comprehensive database, and perform cross-filtering processing on the risk thresholds of each spacecraft service device and the service application environment data of the corresponding spacecraft to output the device risk data of environmental risk factors for each spacecraft service device. The device risk data of each spacecraft service device includes the evaluation result data of the device risk level; and, In the task constraint rules provided by the comprehensive database, extract the risk thresholds for various spacecraft mission requirements, and perform cross-filtering processing on the risk thresholds of various spacecraft mission requirements and the business application environment data of the corresponding spacecraft to output the task risk data of various spacecraft due to environmental risk factors. Among them, the task risk data of various spacecraft includes the evaluation result data of the task risk level.

7. The system according to claim 6, characterized in that, The spacecraft mission impact risk assessment calculation module generates the task risk situation of each spacecraft business device, including: Based on the impact of environmental impact factors on the device risk data of each spacecraft business device, and based on the impact of the task risk data of the spacecraft on various spacecraft mission requirements, perform situation visualization calculation and scene rendering to generate the task risk situation of each spacecraft business.

8. A method for ensuring the safety of the spacecraft space environment based on three-step calculation, characterized in that, including Based on the spacecraft space environment safety guarantee system based on the three-step calculation described in any one of claims 1 to 7, generate the device risk data and task risk situation of each target device in the spacecraft business.

9. A computer-readable storage medium, characterized in that, The computer-readable storage medium stores computer program instructions, and when the computer program instructions are executed by a processor, the method described in claim 8 is implemented.

10. A computer program product, characterized in that It includes computer program instructions, and when the computer program instructions are executed by a processor, the method described in claim 8 is implemented.

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