Space environment risk auxiliary decision support system

Abstract

The invention discloses a space environment risk aided decision support system. The system comprises a data acquisition module; the environmental parameter calculation module is used for calculating equipment or task related environmental parameters according to the collected monitoring data; the risk assessment module is used for determining a risk index of the environment influencing the equipment body or the task thereof based on the equipment position parameter, the equipment performance parameter and the environment parameter; the decision support module is used for querying historical cases from the case database for any effect risk; calculating the similarity between the target sub-environment parameters of the current task and the historical case; and if the target historical case meeting the similarity requirement exists, generating a decision suggestion by referring to the treatment measures of the target historical case. The method can improve the ability of space environment safeguards to cope with space environment risks.

Description

Technical Field

[0001] This application relates to the technical field of spacecraft operation monitoring, and particularly to a space environment risk auxiliary decision support system, method, electronic device, computer-readable storage medium, and computer program product. Background Art

[0002] With the rapid development of space technology, the number of spacecraft entering space has increased sharply, making people increasingly concerned about the impact of the space environment on spacecraft and related missions and equipment. In the space environment, spacecraft face various potential risks. For example, events such as coronal mass ejections, solar flares, solar proton events, magnetic storms, high-energy electron bursts, ionospheric storms, and ionospheric scintillations caused by solar activities may cause spacecraft failures, communication interruptions, navigation malfunctions, and the collapse of power station transmission networks, resulting in social and economic losses in multiple aspects.

[0003] Especially in recent years, solar activities have been frequent, leading to an increase in the uncertainty of the space environment. For example, in May 2024, the largest geomagnetic storm in nearly 20 years and the largest solar flare event in nearly 10 years broke out. These extreme space weather phenomena have had a significant impact on the normal operation of related high-tech equipment.

[0004] In this context, people's awareness of the risks of related equipment or missions affected by the space environment has been continuously improved. Real-time monitoring of space environment changes and assessment of their potential impact on related equipment or missions have become key links to ensure the safety of spacecraft and related missions. Therefore, it is particularly important to be able to conduct risk disposal in a timely manner. This not only helps to improve the survival ability of spacecraft but also increases the success rate of missions. Summary of the Invention

[0005] In view of this, the embodiments of this application provide a space environment risk auxiliary decision support system, method, electronic device, computer-readable storage medium, and computer program product for providing auxiliary decision support for the risks of the impact of the space environment on equipment or missions, and improving the survival ability of spacecraft and the success rate of missions.

[0006] In a first aspect, the embodiments of this application provide a space environment risk auxiliary decision support system, including:

[0007] A data acquisition module, configured to acquire monitoring data of equipment and the space environment at a target moment, where the monitoring data includes equipment position parameters, equipment performance parameters, solar activity data, atmospheric data, ionospheric data, and geomagnetic activity data;

[0008] An environmental parameter calculation module, configured to input the target time, equipment position parameters, solar activity data, atmospheric data, and geomagnetic activity data into corresponding space environment models according to the input data requirements of various space environment models, and calculate equipment- or mission-related environmental parameters by combining monitoring data and model output data;

[0009] A risk assessment module, configured to evaluate the effect risk index of mission risks affected by the space environment. The mission risks include spacecraft body risks and related equipment mission risks; the spacecraft body risks are based on equipment position parameters, equipment performance parameters, and environmental parameters to determine multiple effect risk indices under the influence of various environmental effects; the related equipment mission risks are based on equipment position parameters, signal frequencies, and ionospheric parameters of the signal transmission path to determine the effect risk index under the influence of related mission environmental effects;

[0010] A decision support module, configured to give suggestions on countermeasures for mission risks; for any one of the effect risk indices in the mission risks that is greater than or equal to the preset risk threshold, query historical cases in the case database that are the same as the equipment, the same as the mission type, and the same as the effect risk type; and calculate the similarity between the current mission and the historical cases according to the effect risk index and its corresponding target sub-environmental parameters; if there is a target historical case with a similarity greater than or equal to the similarity threshold, generate an effect risk decision suggestion by referring to the disposal measures of the target historical case.

[0011] According to some embodiments of the present application, optionally, the effect risk index of the target historical case is greater than or equal to the effect risk index of the current mission; the decision support module is further configured to, if there is no target historical case, query the target risk disposal measure suggestion corresponding to the effect risk index from the pre-established decision suggestion expert database as the effect risk decision suggestion.

[0012] According to some embodiments of the present application, optionally, the multiple environmental effects include single event upset effect, deep dielectric charging effect, surface charging effect, displacement damage effect, ionization damage effect, orbit decay effect, and debris collision effect. Correspondingly, the multiple effect risk indices include single event risk index E1, deep dielectric charging risk index E2, surface charging risk index E3, displacement damage risk index E4, ionization damage risk index E5, orbit decay risk index E6, and debris collision risk index E7.

[0013] According to some embodiments of the present application, optionally, the target sub-environmental parameters corresponding to the single event risk index E1 at least include the proton flux of the orbit where the spacecraft is located;

[0014] When the single event risk index E1 is equal to x1, the effect risk decision suggestion is to pay attention to changes in the space environment;

[0015] When the single - particle risk index E1 is equal to x2, the effect risk decision recommendation is to strengthen monitoring and increase the monitoring arc segments;

[0016] When the single - particle risk index E1 is equal to x3, the effect risk decision recommendation is to collect telemetry data in real - time, monitor the functional changes of the corresponding vulnerable devices, and when necessary, the single machine containing sensitive devices enters the safe state;

[0017] When the single - particle risk index E1 is equal to x4, the effect risk decision recommendation is that some single machines containing sensitive devices enter the safe state, where x4 > x3 > x2 > x1 and all are positive numbers.

[0018] According to some embodiments of the present application, optionally, the target sub - environment parameters corresponding to the deep charge - discharge risk index E2 at least include the electron flux of the orbit where the spacecraft is located; the target sub - environment parameters corresponding to the surface charge - discharge risk index E3 at least include the geomagnetic index; the target sub - environment parameters corresponding to the displacement damage risk index E4 at least include the proton flux of the orbit where the spacecraft is located; the target sub - environment parameters corresponding to the ionization damage risk index E5 at least include the proton flux and electron flux of the orbit where the spacecraft is located; the target sub - environment parameters corresponding to the orbit decay risk index E6 at least include the atmospheric density; the target sub - environment parameters corresponding to the debris collision risk index E7 at least include the orbital elements of the space debris and the orbital elements of the spacecraft.

[0019] According to some embodiments of the present application, optionally, the related mission environment effects include the Faraday rotation effect, the ionospheric dispersion effect, the ionospheric time - delay effect, the ionospheric scintillation effect, and the ionospheric absorption effect. The effect risk indices affected by the related mission environment effects include the ionosphere - affecting satellite communication risk index R1, the ionosphere - affecting satellite navigation risk index R2, the ionosphere - affecting SAR imaging risk index R3, the ionosphere - affecting short - wave communication risk index R4, and the ionosphere - affecting ground - based radar risk index R5; the target sub - environment parameters corresponding to the ionosphere - affecting satellite communication risk index R1, the ionosphere - affecting satellite navigation risk index R2, the ionosphere - affecting SAR imaging risk index R3, the ionosphere - affecting short - wave communication risk index R4, and the ionosphere - affecting ground - based radar risk index R5 at least include the ionospheric electron density.

[0020] According to some embodiments of the present application, optionally, the risk assessment module is further configured to calculate the comprehensive risk index Er, and use the maximum risk index among the comprehensive risk index Er, the surface charge - discharge risk index E3, the orbit decay risk index E6, and the debris collision risk index E7 as the overall risk index of the spacecraft:

[0021] Among them, Er represents the comprehensive risk index caused by four environmental effects of different devices of the spacecraft, and the four environmental effects include: single - event upset effect, deep charge - discharge effect, displacement damage effect, and ionization damage effect;

[0022] The decision support module is further configured to, when the overall spacecraft risk index is one of the effect risk indexes of the surface charging and discharging risk index E3, the orbit decay risk index E6, or the debris collision risk index E7, use the effect risk decision recommendation corresponding to the effect risk index as the overall spacecraft decision recommendation; when the overall spacecraft risk index is the comprehensive risk index Er, use the effect risk decision recommendations corresponding to the single event upset risk index E1, the deep charging and discharging risk index E2, the displacement damage risk index E4, and the ionization damage risk index E5 as the overall spacecraft decision recommendation.

[0023] According to some embodiments of the present application, optionally, the decision support module is further configured to, when the overall spacecraft risk index is the comprehensive risk index Er, use the effect risk decision recommendations corresponding to the single event upset risk index E1, the deep charging and discharging risk index E2, the displacement damage risk index E4, and the ionization damage risk index E5 as the overall spacecraft decision recommendation.

[0024] According to some embodiments of the present application, optionally, the single event upset risk index, the deep charging and discharging risk index, the surface charging and discharging risk index, the displacement damage risk index, the ionization damage risk index, the orbit decay risk index, and the debris collision risk index of the spacecraft body are determined by calculating the number of single event upsets of multiple sensitive devices in the spacecraft, the charging electric field at multiple sensitive devices, the surface charging potential of the spacecraft, the displacement damage dose of multiple sensitive devices, the ionization damage dose of multiple sensitive devices, the orbit decay amount, and the probability of the spacecraft colliding with space debris, respectively;

[0025] The ionosphere influence satellite communication risk index, the ionosphere influence satellite navigation risk index, the ionosphere influence SAR imaging risk index, the ionosphere influence shortwave communication risk index, and the ionosphere influence ground-based radar risk index of the related equipment mission are determined by calculating the signal-to-noise ratio / bit error rate, the navigation positioning error, the imaging resolution, the shortwave communication reliability / compatibility, and the range error / angle error, respectively.

[0026] According to some embodiments of the present application, optionally, the multiple space environment models include the International Geomagnetic Reference Field model, the Earth radiation belt model, the atmosphere model, and the ionosphere model; the environmental parameter calculation module includes:

[0027] The geomagnetic parameter calculation unit is configured to input the target time, the longitude of the spacecraft, the latitude of the spacecraft, and the altitude of the spacecraft into the International Geomagnetic Reference Field model to obtain the target geomagnetic parameters at the location of the spacecraft, and the target geomagnetic parameters include at least the magnetic shell parameters and the magnetic field strength at the location of the spacecraft in the Earth's magnetic field;

[0028] A proton flux calculation unit, which, for a low-orbit satellite at medium and low latitudes, inputs target geomagnetic parameters into an Earth radiation belt model to obtain the proton flux of the orbit where the spacecraft is located; for the high-latitude region of a low-orbit satellite and a medium- or high-orbit satellite during a solar proton event, the flux refers to the high-energy proton detection results of a geosynchronous orbit operational satellite.

[0029] An electron flux calculation unit, which, for a low-orbit satellite, inputs target geomagnetic parameters into an Earth radiation belt model to obtain the electron flux of the orbit where the spacecraft is located; for a medium- or high-orbit satellite, it is necessary to refer to the high-energy electron detection data of a geosynchronous orbit.

[0030] An atmospheric parameter calculation unit, which inputs the target time, the longitude of the spacecraft, the latitude of the spacecraft, the altitude of the spacecraft, the solar radiation intensity, and the geomagnetic activity index into an atmospheric model to obtain atmospheric parameters, where the atmospheric parameters include atmospheric temperature, atmospheric density, and the content of each element in the atmosphere.

[0031] An ionospheric parameter calculation unit, which inputs the longitude of the spacecraft, the latitude of the spacecraft, the altitude of the spacecraft, solar activity data, and the geomagnetic activity index into an ionospheric model to obtain ionospheric parameters of the signal transmission path, where the ionospheric parameters of the signal transmission path include the critical frequency of each layer, the electron density of each layer, the peak height of each layer, and TEC.

[0032] In a second aspect, an embodiment of the present application provides a method for assisting in space environment risk decision-making support, including:

[0033] Collect monitoring data of equipment and the space environment at the target time, where the monitoring data includes equipment position parameters, equipment performance parameters, solar activity data, atmospheric data, ionospheric data, and geomagnetic activity data.

[0034] According to the input data requirements of various space environment models, input the target time, equipment position parameters, solar activity data, atmospheric data, and geomagnetic activity data into the corresponding space environment models, and combine the monitoring data and the model output data to calculate equipment- or mission-related environment parameters.

[0035] Evaluate the effect risk index of the mission risk of the space environment impact, where the mission risk includes the risk of the spacecraft body and the mission risk of related equipment; the risk of the spacecraft body is based on the equipment position parameters, equipment performance parameters, and environment parameters to determine multiple effect risk indexes under the influence of various environmental effects; the mission risk of related equipment is based on the equipment position parameters, signal frequency, and ionospheric parameters of the signal transmission path to determine the effect risk index under the influence of the related mission environmental effects.

[0036] Give suggestions on countermeasures for task risks; for any one of the effect risk indices in the task risks that is greater than or equal to the preset risk threshold, query historical cases from the case database that are the same as the equipment, the same as the task type, and the same as the effect risk type; and calculate the similarity between the current task and the historical cases according to the effect risk index and its corresponding target sub-environment parameters; if there are target historical cases with a similarity greater than or equal to the similarity threshold, generate effect risk decision suggestions by referring to the disposal measures of the target historical cases.

[0037] In a third aspect, 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 space environment risk auxiliary decision support method as described above are implemented.

[0038] In a fourth aspect, an embodiment of the present application 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 steps of the space environment risk auxiliary decision support method as described above are implemented.

[0039] In a fifth aspect, an embodiment of the present application provides a computer program product, which includes computer program instructions, and when the computer program instructions are executed by a processor, the steps of the space environment risk auxiliary decision support method as described above are implemented.

[0040] By using the space environment risk auxiliary decision support system, method, electronic device, computer-readable storage medium and computer program product provided by the embodiments of the present application, it is possible to analyze the impacts of various environmental effects and related task environmental effects on the spacecraft body and its tasks based on the monitoring data of multiple data sources collected, determine multiple effect risk indices of the spacecraft body under various environmental effects, determine multiple effect risk indices of the spacecraft-related tasks under various related task environmental effects, and realize a relatively comprehensive space environment risk assessment. In addition, for various effect risks in the risks of the spacecraft body and related equipment tasks, according to the effect risk indices of various effect risks, effect risk decision suggestions are automatically generated, which can provide corresponding countermeasures for the spacecraft to reduce the impact of the space environment, improve the ability of the spacecraft and its environmental support personnel to cope with space environment risks, and help improve the survival ability and mission success rate of the spacecraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0041] 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.

[0042] Figure 1 It is a structural block diagram of a space environment risk auxiliary decision support system according to an embodiment of the present application.

[0043] Figure 2 It is a structural block diagram of an environmental parameter calculation module in the space environment risk auxiliary decision support system according to an embodiment of the present application.

[0044] Figure 3 It is a structural block diagram of a risk assessment module in the space environment risk auxiliary decision support system according to an embodiment of the present application.

[0045] Figure 4 It is a schematic flowchart of a space environment risk auxiliary decision support method according to an embodiment of the present application.

[0046] Figure 5 It is a schematic hardware structure diagram of an electronic device according to an embodiment of the present application. Specific embodiments

[0047] The principles and spirit 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 spirit of the present application clearer and more thorough, so that those skilled in the art can better understand and then implement the principles and spirit of the present application. The exemplary embodiments provided herein are only a part of the embodiments of the present application, rather than all 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.

[0048] Real-time monitoring of space environment changes and assessment of their potential impacts on spacecraft and their missions have become a key link in ensuring the safe operation of spacecraft and protecting critical missions. In order to enable spacecraft to respond quickly and effectively during solar storms, the present application provides a space environment risk auxiliary decision support system, method, electronic device, computer-readable storage medium and computer program product, aiming to provide corresponding auxiliary decision support for spacecraft against space environment risks and improve the survival ability and mission success rate of spacecraft.

[0049] First, the space environment risk auxiliary decision support system provided by the implementation of the present application will be introduced below.

[0050] Figure 1 It is a structural block diagram of a space environment risk auxiliary decision support system according to an embodiment of the present application. As Figure 1 shown, the space environment risk auxiliary decision support system 20 according to an embodiment of the present application may include a data acquisition module 201, an environmental parameter calculation module 202, a risk assessment module 203, and a decision support module 204.

[0051] The data acquisition module 201 can be used to acquire the monitoring data of the equipment and the space environment at the target time. Among them, the target time can be any time, and this application does not make any restrictions on this. The monitoring data can include equipment position parameters, solar activity data, atmospheric data, ionospheric data, and geomagnetic activity data. In some other examples, in order to improve the comprehensiveness and accuracy of risk assessment, the monitoring data can also include interplanetary environment data, particle data, etc., and this application does not make any restrictions on this. Exemplarily, the equipment can include spacecraft and ground monitoring equipment (such as radars, etc.). The spacecraft can be a satellite, such as a communication satellite, a meteorological satellite, or a navigation satellite, or it can also be other spacecraft, such as a rocket, a spaceship, or a space station, etc. The equipment position parameters can include the position data of the spacecraft and the ground monitoring equipment, such as the longitude of the spacecraft, the latitude of the spacecraft, the altitude of the spacecraft, and the orbital elements of the spacecraft, etc.

[0052] The environmental parameter calculation module 202 can be used to calculate the environmental parameters related to the equipment or the mission. Specifically, according to the input data requirements of various space environment models respectively, the target time, the equipment position parameters, the solar activity data, the atmospheric data, and the geomagnetic activity data can be input into the corresponding space environment models, and combined with the monitoring data and the model output data, the environmental parameters related to the equipment or the mission can be calculated.

[0053] In some embodiments, the various space environment models include the International Geomagnetic Reference Field (IGRF) model, the Earth radiation belt model, the atmospheric model, and the International Reference Ionosphere (IRI) model. The environmental parameter calculation module 202 can specifically be used to input the target time and the equipment position parameters into the International Geomagnetic Reference Field model to obtain the target geomagnetic parameters at the position of the spacecraft; input the target geomagnetic parameters into the Earth radiation belt model (such as the electron model AE-8 / AE-9 and the proton model AP-8 / AP-9) to obtain the electron flux in the orbit of the spacecraft and the proton flux in the orbit of the spacecraft; input the target time, the equipment position parameters, the atmospheric data, the solar activity data, and the geomagnetic activity data into the atmospheric model (such as the MSISE-00 atmospheric model) to obtain the atmospheric parameters; input the equipment position parameters, the solar activity data, and the geomagnetic activity data into the ionosphere model to obtain the ionospheric parameters of the signal transmission path.

[0054] Among them, the environmental parameters include but are not limited to the electron flux in the orbit of the spacecraft, the proton flux in the orbit of the spacecraft, the atmospheric parameters, and the ionospheric parameters of the signal transmission path.

[0055] The risk assessment module 203 can be used to evaluate the effect risk index of the mission risk affected by the space environment. The mission risk can include the spacecraft body risk and the mission risk of related equipment. The spacecraft body risk can be based on the equipment position parameters, equipment performance parameters, and environmental parameters to determine multiple effect risk indexes of the spacecraft under the influence of various environmental effects.

[0056] For example, in some specific examples, the various environmental effects can include seven environmental effects such as single event upset effect, deep dielectric charging effect, surface charging effect, displacement damage effect, ionization damage effect, orbital decay effect, and debris collision effect. Correspondingly, the multiple effect risk indexes can include single event risk index E1, deep dielectric charging risk index E2, surface charging risk index E3, displacement damage risk index E4, ionization damage risk index E5, orbital decay risk index E6, and debris collision risk index E7.

[0057] The mission risk of related equipment can be based on the ionospheric data including equipment position parameters, signal frequency, and signal transmission path to determine the effect risk index under the influence of related mission environmental effects. Among them, the related mission environmental effects can include Faraday rotation effect, ionospheric dispersion effect, ionospheric time delay effect, ionospheric scintillation effect, and ionospheric absorption effect. The effect risk index under the influence of related mission environmental effects can include the ionosphere affecting satellite communication risk index R1, the ionosphere affecting satellite navigation risk index R2, the ionosphere affecting SAR imaging risk index R3, the ionosphere affecting shortwave communication risk index R4, and the ionosphere affecting ground-based radar risk index R5.

[0058] In some embodiments, the risk assessment module 203 can specifically be used to calculate the effect values of various environments affecting the equipment or mission based on the equipment position parameters, equipment performance parameters, and environmental parameters; and determine the risk indexes of various environments affecting the equipment or mission according to the effect values of various environments affecting the equipment or mission and their respective risk thresholds.

[0059] According to the processing method of the embodiments of the present application, first, it is necessary to calculate the effect values of various environments affecting the equipment or mission, and then determine each effect risk index according to the effect values of various environments affecting the equipment or mission and their respective risk thresholds. The effect values of various environments affecting the equipment or mission can be calculated based on the equipment position parameters, equipment performance parameters, and environmental parameters. In some embodiments, for example, the various environmental effects can include single event upset effect, deep dielectric charging effect, surface charging effect, displacement damage effect, ionization damage effect, orbital decay effect, and debris collision effect. The related mission environmental effects can include Faraday rotation effect, ionospheric dispersion effect, ionospheric time delay effect, ionospheric scintillation effect, and ionospheric absorption effect.

[0060] According to the magnitude of the effect values of equipment or tasks affected by multiple environments, multiple effect risk indices E can be determined. For example, for any environmental effect or related mission environmental effect, the effect risk index corresponding to the effect value [0.01, 0.1) of this environmental effect or related mission environmental effect can be set to 1, indicating low risk; the effect risk index corresponding to the effect value [0.1, 1) of this environmental effect or related mission environmental effect can be set to 2, indicating medium risk, and so on. The larger the effect risk index, the higher the risk level. The classification standard can be flexibly adjusted according to the actual situation, and this application does not make any restrictions on it.

[0061] The effect risk index can reflect to a certain extent the robustness of spacecraft design and the severity of the space environment risks currently faced by the spacecraft. Corresponding to multiple environmental effects, multiple effect risk indices can include single-event upset risk index E1, deep dielectric charging risk index E2, surface charging risk index E3, displacement damage risk index E4, ionization damage risk index E5, orbit decay risk index E6, and debris collision risk index E7. Among them, the larger the effect risk index of a certain environmental effect (such as any one of E1 - E7), the higher the effect risk of this type caused by the space environment to the spacecraft. Corresponding to multiple related mission environmental effects, the effect mission risk indices under the influence of related mission environmental effects can include ionospheric influence on satellite communication risk index R1, ionospheric influence on satellite navigation risk index R2, ionospheric influence on SAR imaging risk index R3, ionospheric influence on shortwave communication risk index R4, and ionospheric influence on ground-based radar risk index R5.

[0062] The effect values corresponding to different environmental effects or related mission environmental effects can be different. For example, the effect value corresponding to the single-event upset effect can be the number of single-event upsets per unit, the effect value corresponding to the deep dielectric charging effect can be the deep dielectric charging electric field, such as the charging electric fields at multiple sensitive devices of the spacecraft, the effect value corresponding to the surface charging effect can be the surface charging potential of the spacecraft, the effect value corresponding to the displacement damage effect can be the displacement damage dose, such as the displacement damage doses of multiple sensitive devices of the spacecraft, and so on.

[0063] For example, in some embodiments, for the single-event upset effect, the corresponding single-event risk index E1 can be determined according to the calculated value of the single-event upset times. For example, when the single-event upset times are in the range of [0.01, 0.1), the corresponding single-event risk index E1 is 1, indicating a low risk. Here, [0.01, 0.1) means that this interval starts from 0.01 but does not include 0.1. When the single-event upset times are in the range of [0.1, 1), the corresponding single-event risk index E1 is 2, indicating a medium risk. When the single-event upset times are in the range of [1, 10), the corresponding single-event risk index E1 is 3, indicating a high risk. When the single-event upset times are greater than or equal to 10, the corresponding single-event risk index E1 is 4, indicating an extremely high risk.

[0064] Similarly, the corresponding deep charge-discharge risk index E2 can be determined according to the deep charge-discharge electric field. The corresponding surface charge-discharge risk index E3 can be determined according to the surface charge-discharge potential. The corresponding displacement damage risk index E4 can be determined according to the displacement damage dose. The corresponding ionization damage risk index E5 can be determined according to the ionization damage dose. The corresponding orbit decay risk index E6 can be determined according to the orbit decay amount. The corresponding debris collision risk index E7 can be determined according to the debris collision probability. The ionosphere impact satellite communication risk index R1 can be determined according to the signal-to-noise ratio / bit error rate value. The ionosphere impact satellite navigation risk index R2 can be determined according to the navigation positioning error. The ionosphere impact SAR imaging risk index R3 can be determined according to the imaging resolution. The ionosphere impact short-wave communication risk index R4 can be determined according to the short-wave communication reliability / compatibility. The ionosphere impact ground-based radar risk index R5 can be determined according to the range error / angle error.

[0065] The decision support module 204 can be used to give suggestions on countermeasures for mission risks. Query historical cases similar to the effect risk from the case database based on the equipment name, mission type, effect risk type, effect risk index, and relevant environmental parameters; combine the countermeasures of the similar historical cases and the corresponding risk countermeasure suggestions in the pre-established decision suggestion database to give decision support suggestions.

[0066] For example, for any one of the effect risks in the spacecraft body risk and the relevant equipment mission risks, when the effect risk index of the effect risk is greater than or equal to the preset risk threshold, the decision support module 204 can automatically generate the effect risk decision suggestion corresponding to the effect risk index of the effect risk. The size of the preset risk threshold can be flexibly adjusted according to the actual situation, and the present application does not limit this.

[0067] Effect risk decision-making suggestions may include pre-plan suggestions and suggestions taken from similar historical cases. A decision-making suggestion expert database can be established in advance. For various types of effect risks, the decision-making suggestion expert database can store risk disposal measure suggestions corresponding to different magnitudes of effect risk indices. The pre-plan suggestions can be the risk disposal measure suggestions stored in the decision-making suggestion expert database, which can be generated based on expert experience and support subsequent editing and modification by users according to their experience. The suggestions taken from similar historical cases are the disposal measures taken in historical cases similar to the current task (or the current space environment risk).

[0068] Specifically, for any effect risk with an effect risk index greater than or equal to the preset risk threshold among the risks of the spacecraft body and related equipment tasks, the decision support module 204 can query historical cases similar to the current task's effect risk from the case database according to the equipment name, task type, and effect risk type, that is, similar historical cases, for analysis and reference. The same equipment means the same as the spacecraft or radar to be analyzed. The same task type means the same as the type of the task currently executed by the spacecraft, such as both being communication tasks, navigation tasks, or short-wave communication tasks, etc. The same effect risk type means the same as the effect risk to be queried, such as single-event upset effect, deep charging and discharging effect, surface charging and discharging effect, displacement damage effect, ionization damage effect, orbit decay effect, debris collision effect, Faraday rotation effect, ionospheric dispersion effect, ionospheric time delay effect, ionospheric scintillation effect, or ionospheric absorption effect. The risk indices are similar, such as both being 3 or differing by only 1.

[0069] After querying the similar historical cases of the effect risk, the decision support module 204 can calculate the similarity between the target sub-environment parameters of the current task and those of the historical cases according to the effect risk index of the effect risk and the corresponding target sub-environment parameters. For different types of effect risks, the corresponding target sub-environment parameters for different types of effect risks can be different. For example, for the single-event upset effect, the target sub-environment parameter corresponding to the single-particle risk index E1 can be the proton flux of the orbit where the spacecraft is located. For the deep charging and discharging effect, the target sub-environment parameter corresponding to the deep charging and discharging risk index E2 can be the electron flux of the orbit where the spacecraft is located, and so on.

[0070] If there are target historical cases with a similarity greater than or equal to the similarity threshold, then generate effect risk decision-making suggestions by referring to the disposal measures of the target historical cases. For example, the disposal measures of the target historical cases can be extracted as the effect risk decision-making suggestions. The magnitude of the similarity threshold can be flexibly adjusted according to the actual situation, and this application does not limit it.

[0071] In some embodiments, when there are multiple target historical cases with a similarity greater than or equal to the similarity threshold, the multiple target historical cases that reach the similarity threshold can be sorted in descending order of similarity, and the disposal measures of the top N target historical cases can be extracted as a reference for the effect risk decision-making recommendation, where N is a positive integer. Exemplarily, N can be equal to 1, 2, or 3, etc.

[0072] In some embodiments, if there are no target historical cases, the decision support module 204 can query the target risk disposal measure recommendation corresponding to the effect risk index from the pre-established decision recommendation expert database as the effect risk decision-making recommendation.

[0073] For ease of understanding, the processing process of the decision support module 204 will be described below by taking the single-event upset effect as an example.

[0074] Assume that the effect risk index of the single-event upset effect is greater than or equal to the preset risk threshold. Then, for the single-event upset effect, the decision support module 204 can query from the case database historical single-event upset effect cases that have the same spacecraft equipment, the same mission type, are the same single-event upset effect, and have a risk index greater than or equal to the effect risk index of the single-event upset effect, that is, similar historical single-event upset effect cases.

[0075] After querying the similar historical single-event upset effect cases of the single-event upset effect, the decision support module 204 can read the proton flux of the orbit where the spacecraft is located during the occurrence period of the similar historical single-event upset effect cases, and calculate the similarity between the proton flux of the orbit where the spacecraft of the current mission is located and the proton flux of the orbit where the spacecraft is located during the occurrence period of the similar historical single-event upset effect cases. If there are target historical single-event upset effect cases with a similarity greater than or equal to the similarity threshold, generate an effect risk decision-making recommendation by referring to the disposal measures of the target historical single-event upset effect cases. If there are no target historical single-event upset effect cases, the decision support module 204 can query the target risk disposal measure recommendation corresponding to the effect risk index of the single-event upset effect from the pre-established decision recommendation expert database as the effect risk decision-making recommendation.

[0076] The space environment risk auxiliary decision support system provided by the embodiments of the present application can analyze the impacts of various environmental effects and related mission environmental effects on the spacecraft body and its missions based on the monitoring data of multiple data sources collected, determine multiple effect risk indices of the spacecraft body under various environmental effects, and determine multiple effect risk indices of the spacecraft-related missions under various related mission environmental effects, realizing a relatively comprehensive space environment risk assessment. In addition, for various effect risks in the risks of the spacecraft body and related equipment missions, effect risk decision-making suggestions are automatically generated according to the effect risk indices of various effect risks, which can provide corresponding countermeasures for the spacecraft to reduce the impact of the space environment, improve the ability of the spacecraft and its environmental support personnel to cope with space environment risks, and help improve the survival ability and mission success rate of the spacecraft.

[0077] According to some embodiments of the present application, in addition to outputting effect risk decision-making suggestions, the decision support module 204 can also output prompt information describing the current space environment, effect risk types, and effect risk indices, so as to provide reference for technicians.

[0078] For the convenience of understanding, the environmental parameter calculation module 202 and the risk assessment module 203 will be illustrated by examples below.

[0079] Figure 2 It is a structural block diagram of the environmental parameter calculation module in the space environment risk auxiliary decision support system of the embodiments of the present application. As Figure 2 shown, according to some embodiments of the present application, optionally, the environmental parameter calculation module 202 may include a geomagnetic parameter calculation unit 301, a proton flux calculation unit 302, an electron flux calculation unit 303, an atmospheric parameter calculation unit 304, and an ionospheric parameter calculation unit 305.

[0080] The geomagnetic parameter calculation unit 301 can be used to input the target time, the longitude of the spacecraft, the latitude of the spacecraft, and the altitude of the spacecraft into the International Geomagnetic Reference Field Model (IGRF model) to obtain the target geomagnetic parameters at the location of the spacecraft.

[0081] Among them, the target geomagnetic parameters at least include the magnetic shell parameter L and the magnetic field intensity B at the location of the spacecraft. Of course, the target geomagnetic parameters may also include other geomagnetic parameters, which are not limited in the present application.

[0082] The proton flux calculation unit 302 can be used to input the target geomagnetic parameters into the Earth radiation belt model (such as the proton models AP-8 / AP-9) for low-orbit satellites at medium and low latitudes to obtain the calculation results of the proton flux model for the orbit where the spacecraft is located. Then, combined with the measured data, the model calculation is corrected to calculate the proton flux for the orbit where the spacecraft is located. For the high-latitude region of low-orbit satellites and medium- and high-orbit satellites during solar proton events, the proton flux can refer to the high-energy proton detection results of geostationary operational satellites.

[0083] The electron flux calculation unit 303 can be used to input the target geomagnetic parameters into the Earth radiation belt model (such as the electron models AE-8 / AE-9) for low-orbit satellites to obtain the calculation results of the electron flux model for the orbit where the spacecraft is located. Then, combined with the measured data, the model calculation is corrected to calculate the electron flux for the orbit where the spacecraft is located. For medium- and high-orbit satellites, the electron flux can refer to the high-energy electron detection data of geostationary orbits.

[0084] The atmospheric parameter calculation unit 304 can be used to input the target time, the longitude of the spacecraft, the latitude of the spacecraft, the altitude of the spacecraft, the solar radiation intensity (F10.7), and the geomagnetic activity index (Ap) into the atmospheric model (such as the MSISE-00 atmospheric model) to obtain atmospheric parameters. Among them, the atmospheric parameters can include atmospheric temperature, atmospheric density, and the content of each element in the atmosphere.

[0085] The ionospheric parameter calculation unit 305 can be used to input the longitude of the spacecraft, the latitude of the spacecraft, the altitude of the spacecraft, the solar activity data, and the geomagnetic activity index (Ap) into the ionospheric model (IRI model) to obtain the ionospheric parameters of the signal transmission path.

[0086] Among them, the ionospheric parameters of the signal transmission path can at least include the critical frequencies of each layer of plasma in the ionosphere, the electron density of each layer, the peak height of each layer, and TEC.

[0087] By calculating the monitoring data of multiple data sources collected by the environmental parameter calculation module 202, the environmental parameters can be obtained. The environmental parameters can include the electron flux, proton flux, atmospheric parameters, and ionospheric parameters of the signal transmission path for the orbit where the spacecraft is located, etc.

[0088] According to some embodiments of the present application, optionally, the single event upset risk index, deep dielectric charging risk index, surface charging risk index, displacement damage risk index, ionization damage risk index, orbit decay risk index, and debris collision risk index of the spacecraft body can be determined by calculating the number of single event upsets of multiple sensitive devices in the spacecraft, the charging electric field at multiple sensitive devices, the surface charging potential of the spacecraft, the displacement damage dose of multiple sensitive devices, the ionization damage dose of multiple sensitive devices, the orbit decay amount, and the probability of the spacecraft colliding with space debris, respectively.

[0089] The ionosphere influence satellite communication risk index, ionosphere influence satellite navigation risk index, ionosphere influence SAR imaging risk index, ionosphere influence shortwave communication risk index, and ionosphere influence ground-based radar risk index of the related equipment mission can be determined by calculating the signal-to-noise ratio / bit error rate, navigation positioning error, imaging resolution, shortwave communication reliability / compatibility, range error / angle error, respectively.

[0090] Figure 3 This is a structural block diagram of the risk assessment module in the space environment risk assisted decision support system according to the embodiments of the present application. As Figure 3 shown, according to some embodiments of the present application, optionally, the risk assessment module 203 includes a single event upset risk index calculation unit 401, a deep dielectric charging risk index calculation unit 402, a surface charging risk index calculation unit 403, a displacement damage risk index calculation unit 404, an ionization damage risk index calculation unit 405, an orbit decay risk index calculation unit 406, a debris collision risk index calculation unit 407, an ionosphere influence satellite communication risk index calculation unit 408, an ionosphere influence satellite navigation risk index calculation unit 409, an ionosphere influence SAR imaging risk index calculation unit 410, an ionosphere influence shortwave communication risk index calculation unit 411, and an ionosphere influence ground-based radar target detection risk index calculation unit 412.

[0091] The single event upset risk index calculation unit 401 can be used to calculate the number of single event upsets of multiple sensitive devices in the spacecraft according to the proton flux of the orbit where the spacecraft is located, the three-dimensional shielding data of the spacecraft, and the single event upset sensitive device parameters; obtain the single event upset risk indices of multiple sensitive devices according to the number of single event upsets of multiple sensitive devices in the spacecraft and the risk threshold; calculate the final single event upset risk index according to the single event upset risk indices of multiple sensitive devices and the preset weight parameters of multiple sensitive devices. The three-dimensional shielding data of the spacecraft may include the thicknesses in various directions at one or more positions of the spacecraft. Among them, the higher the number of single event upsets of multiple sensitive devices in the spacecraft, the greater the risk of single event upset effect, and correspondingly, the greater the single event upset risk index. The magnitudes of the weight parameters of multiple sensitive devices can be flexibly adjusted according to actual situations, and the present application does not limit this.

[0092] The deep charging and discharging risk index calculation unit 402 can be used to calculate the charging electric field at multiple sensitive devices in the spacecraft according to the electron flux of the orbit where the spacecraft is located, the ionospheric parameters of the signal transmission path, the three-dimensional shielding data of the spacecraft, and the deep charging and discharging sensitive device parameters; obtain the deep charging risk indices of multiple sensitive devices according to the deep charging electric fields of multiple sensitive devices in the spacecraft and the risk threshold; calculate the deep charging and discharging risk index according to the charging electric fields at multiple sensitive devices in the spacecraft and the preset weight parameters of multiple sensitive devices. Among them, the higher the charging potential at multiple sensitive devices in the spacecraft, the greater the risk of deep charging and discharging effect, and correspondingly, the greater the deep charging and discharging risk index. The magnitudes of the weight parameters of multiple sensitive devices can be flexibly adjusted according to actual situations, and the present application does not limit this.

[0093] The surface charging and discharging risk index calculation unit 403 can be used to calculate the surface charging potential of the spacecraft according to the geomagnetic activity index and local time or plasma parameters; obtain the surface charging and discharging risk index according to the surface charging potential of the spacecraft and the surface charging and discharging risk threshold. Among them, the surface charging potential is positively correlated with the surface charging and discharging risk index. That is, the higher the surface charging potential of the spacecraft, the greater the surface charging and discharging risk. The conversion relationship between the surface charging potential and the surface charging and discharging risk index can be preset, such as setting the conversion coefficient between the two, and then based on this conversion relationship or conversion coefficient, converting the surface charging potential of the spacecraft into the surface charging and discharging risk index. The conversion relationship or conversion coefficient can be flexibly adjusted according to actual situations, and the present application does not limit this.

[0094] The displacement damage risk index calculation unit 404 can be used to calculate the displacement damage doses of multiple sensitive devices in the spacecraft according to the proton flux of the orbit where the spacecraft is located and the three-dimensional shielding data of the spacecraft; calculate the displacement damage effect risk index according to the displacement damage doses of the multiple sensitive devices and the displacement damage risk threshold; calculate the displacement damage risk index according to the displacement damage doses of the multiple sensitive devices in the spacecraft and the preset weight parameters of the multiple sensitive devices. Among them, the higher the displacement damage doses of the multiple sensitive devices in the spacecraft, the greater the displacement damage effect risk, and correspondingly, the greater the displacement damage effect risk index. The magnitudes of the weight parameters of the multiple sensitive devices can be flexibly adjusted according to the actual situation, and the present application does not limit this.

[0095] The ionization damage risk index calculation unit 405 can be used to calculate the ionization damage doses of multiple sensitive devices in the spacecraft according to the electron flux of the orbit where the spacecraft is located, the ionization layer parameters of the signal transmission path, the proton flux of the orbit where the spacecraft is located, and the three-dimensional shielding data of the spacecraft; calculate the ionization damage effect risk index according to the ionization damage doses of the multiple sensitive devices and the ionization damage risk threshold; calculate the ionization damage risk index according to the ionization damage doses of the multiple sensitive devices in the spacecraft and the preset weight parameters of the multiple sensitive devices. The ionization damage effect is similar to the displacement damage effect and will not be elaborated here.

[0096] The orbit decay risk index calculation unit 406 can be used to calculate the orbit decay amount according to the orbit atmospheric parameters of the spacecraft and the surface-to-mass ratio of the spacecraft; obtain the orbit decay risk index according to the orbit decay amount and the orbit decay risk threshold. Among them, the orbit decay amount is positively correlated with the orbit decay risk index. That is, the greater the orbit decay amount, the greater the orbit decay risk index. The conversion relationship between the orbit decay amount and the orbit decay risk index can be preset, such as setting the conversion coefficient between the two, and then based on this conversion relationship or conversion coefficient, convert the orbit decay amount into the orbit decay risk index. The conversion relationship or conversion coefficient can be flexibly adjusted according to the actual situation, and the present application does not limit this.

[0097] The debris collision risk index calculation unit 407 can be used to calculate the probability of the spacecraft colliding with space debris according to the orbital elements of the space debris and the orbital elements of the spacecraft; obtain the debris collision risk index according to the probability of the spacecraft colliding with space debris and the collision risk threshold. Among them, the probability of the spacecraft colliding with space debris is positively correlated with the debris collision risk index. That is, the higher the probability of the spacecraft colliding with space debris, the greater the debris collision risk index. It is also possible to convert the probability of the spacecraft colliding with space debris into the debris collision risk index by setting the conversion relationship or conversion coefficient between the two.

[0098] The ionospheric impact on satellite communication risk index calculation unit 408 can be used to calculate the signal-to-noise ratio (SNR) and bit error rate (BER) of satellite-ground communication based on the communication frequency and ionospheric parameters of the signal transmission path; and obtain the ionospheric impact on satellite communication risk index based on the SNR / BER of satellite-ground communication and the satellite-ground communication risk threshold. Among them, the SNR is positively correlated with the ionospheric impact on satellite communication risk index, and the BER is inversely correlated with the ionospheric impact on satellite communication risk index. That is, the greater the SNR, the smaller the ionospheric impact on satellite communication risk; the greater the BER, the greater the ionospheric impact on satellite communication risk. It is also possible to convert the SNR / BER of satellite-ground communication into the ionospheric impact on satellite communication risk index by setting the conversion relationship or conversion coefficient between the two.

[0099] The ionospheric impact on satellite navigation risk index calculation unit 409 can be used to calculate the navigation positioning error based on the signal frequency and ionospheric parameters of the signal transmission path; and obtain the ionospheric impact on satellite navigation risk index based on the navigation positioning error and the navigation positioning error risk threshold. Among them, the navigation positioning error is positively correlated with the ionospheric impact on satellite navigation risk index. That is, the greater the navigation positioning error, the greater the ionospheric impact on satellite navigation risk. It is also possible to convert the navigation positioning error into the ionospheric impact on satellite navigation risk index by setting the conversion relationship or conversion coefficient between the two.

[0100] The ionospheric impact on SAR imaging risk index calculation unit 410 can be used to calculate the decrease in imaging resolution based on the signal frequency and ionospheric parameters of the signal transmission path; and obtain the ionospheric impact on SAR imaging risk index based on the decrease in imaging resolution and the imaging resolution risk threshold. Among them, the decrease in imaging resolution is positively correlated with the ionospheric impact on SAR imaging risk index. That is, the greater the decrease in imaging resolution, the greater the ionospheric impact on SAR imaging risk. It is also possible to convert the decrease in ionospheric impact on SAR imaging resolution into the ionospheric impact on SAR imaging risk index by setting the conversion relationship or conversion coefficient between the two.

[0101] The ionospheric impact on shortwave communication risk index calculation unit 411 can be used to calculate the reliability / compatibility of shortwave communication based on the communication frequency and ionospheric parameters of the signal transmission path; and obtain the ionospheric impact on shortwave communication risk index based on the reliability / compatibility of shortwave communication and the shortwave communication risk threshold. Among them, the reliability / compatibility is inversely correlated with the ionospheric impact on shortwave communication risk index. That is, the smaller the reliability / compatibility, the greater the ionospheric impact on shortwave communication risk. It is also possible to convert the reliability / compatibility into the ionospheric impact on shortwave communication risk index by setting the conversion relationship or conversion coefficient between the two.

[0102] The ionosphere influence ground-based radar target detection risk index calculation unit 412 can be used to calculate the ionosphere influence ground-based radar target detection range error / angle error according to the communication frequency, target position, and ionosphere parameters of the signal transmission path; and obtain the ionosphere influence ground-based radar target detection risk index according to the ionosphere influence ground-based radar target detection range error / angle error and the ionosphere influence ground-based radar range error / angle error risk threshold. Among them, the range error / angle error is positively correlated with the ionosphere influence ground-based radar target detection risk index. That is, the larger the range error / angle error, the greater the ionosphere influence ground-based radar target detection risk. It is also possible to convert the range error / angle error into the ionosphere influence ground-based radar target detection risk index by setting the conversion relationship or conversion coefficient between the two.

[0103] As described above, for different types of effect risks, the target sub-environment parameters corresponding to different types of effect risks can be different. The decision support module 204 can be used to calculate the similarity between the target sub-environment parameters of the current task and the target sub-environment parameters of the historical case; and then judge whether to generate an effect risk decision suggestion by referring to the handling measures of the target historical case according to the similarity.

[0104] In some specific embodiments, optionally, the target sub-environment parameters corresponding to the single-particle risk index E1 can at least include the proton flux of the orbit where the spacecraft is located. That is, for the single-event upset effect, the decision support module 204 can be used to read the proton flux of the orbit where the spacecraft is located during the occurrence period of the similar historical single-event upset effect case, and calculate the similarity between the proton flux of the orbit where the spacecraft is located in the current task and the proton flux of the orbit where the spacecraft is located during the occurrence period of the similar historical single-event upset effect case, and then judge whether to generate an effect risk decision suggestion by referring to the handling measures of the similar historical single-event upset effect case according to the similarity.

[0105] Correspondingly, for various environmental effects, the effect risk decision-making suggestions corresponding to different effect risk indices can be different. For example, taking the single-event upset effect as an example, when the single-event risk index E1 is equal to x1, the effect risk decision-making suggestion is to pay attention to the changes in the space environment; when the single-event risk index E1 is equal to x2, the effect risk decision-making suggestion is to strengthen monitoring and increase the monitoring arc segment; when the single-event risk index E1 is equal to x3, the effect risk decision-making suggestion is to collect telemetry data in real time, monitor the functional changes of the vulnerable devices, and when necessary, the single unit containing the sensitive devices enters the safe state; when the single-event risk index E1 is equal to x4, the effect risk decision-making suggestion is that some single units containing sensitive devices enter the safe state, where x4 > x3 > x2 > x1 and all are positive numbers. The magnitudes of x1, x2, x3, and x4 can be flexibly adjusted according to the actual situation, and the present application does not limit this. For example, in some examples, x1 = 1, x2 = 2, x3 = 3, and x4 = 4.

[0106] In some specific embodiments, optionally, the target sub-environment parameters corresponding to the deep charging and discharging risk index E2 can at least include the electron flux of the orbit where the spacecraft is located. That is, for the deep charging and discharging effect, the decision support module 204 can be used to read the electron flux of the orbit where the spacecraft is located during the occurrence period of similar historical deep charging and discharging effect cases, calculate the similarity between the electron flux of the orbit where the current mission spacecraft is located and the electron flux of the orbit where the spacecraft was located during the occurrence period of similar historical deep charging and discharging effect cases, and then determine whether to generate an effect risk decision-making suggestion by referring to the disposal measures of similar historical deep charging and discharging effect cases based on the similarity.

[0107] The target sub-environment parameters corresponding to the surface charging and discharging risk index E3 can at least include the geomagnetic index. The target sub-environment parameters corresponding to the displacement damage risk index E4 can at least include the proton flux of the orbit where the spacecraft is located. The target sub-environment parameters corresponding to the ionization damage risk index E5 can at least include the proton flux and electron flux of the orbit where the spacecraft is located. The target sub-environment parameters corresponding to the orbit decay risk index E6 can at least include the atmospheric density. The target sub-environment parameters corresponding to the debris collision risk index E7 can at least include the orbital elements of the space debris and the orbital elements of the spacecraft. The calculation process of the similarity of R1 - R5, E3 to E7 is similar to the calculation process of the similarity of the single-event risk index E1 and the deep charging and discharging risk index E2, and will not be elaborated here.

[0108] According to some embodiments of the present application, optionally, the risk assessment module 203 may also be used to calculate a comprehensive risk index Er, and use the maximum risk index among the comprehensive risk index Er, the surface charging and discharging risk index E3, the orbit decay risk index E6, and the debris collision risk index E7 as the overall spacecraft risk index. Among them, the comprehensive risk index Er represents the comprehensive risk index caused by four environmental effects of different devices of the spacecraft. The four environmental effects include: single event upset effect, deep charging and discharging effect, displacement damage effect, and ionization damage effect.

[0109] For example, in some specific examples, the risk assessment module 203 may be used to determine the overall spacecraft risk index based on the following expression, based on multiple effect risk indices of the spacecraft:

[0110] RS = max(Er, E3, E6, E7) (1)

[0111] Wherein, RS is the overall spacecraft risk index; max(.) is the operation of taking the maximum value; Er represents the comprehensive risk index caused by four environmental effects of different devices of the spacecraft. The four environmental effects include: single event upset effect, deep charging and discharging effect, displacement damage effect, and ionization damage effect. That is, the one with the greatest impact on the spacecraft risk among Er, E3, E6, and E7 is selected as the overall spacecraft risk index.

[0112] Correspondingly, the decision support module 204 may also be used to, when the overall spacecraft risk index is one of the effect risk indices of the surface charging and discharging risk index E3, the orbit decay risk index E6, or the debris collision risk index E7, use the effect risk decision recommendation corresponding to the effect risk index as the overall spacecraft decision recommendation; when the overall spacecraft risk index is the comprehensive risk index Er, use the effect risk decision recommendations corresponding to the single particle risk index E1, the deep charging and discharging risk index E2, the displacement damage risk index E4, and the ionization damage risk index E5 as the overall spacecraft decision recommendation.

[0113] In this way, the space environment risk auxiliary decision support system can not only output decision recommendations corresponding to various effect risk levels for various effect risks, but also output decision recommendations corresponding to the overall spacecraft risk level for the overall spacecraft risk, and preferably provide corresponding countermeasures for the spacecraft to reduce the impact of the space environment, and improve the ability of the spacecraft to cope with space environment risks.

[0114] According to some embodiments of the present application, optionally, the risk assessment module 203 may also be used to calculate the comprehensive risk index Er according to the following expression:

[0115] Er = w1*D1 + w2*D2 + …… + wm*Dm (2)

[0116] Dm = max(E1, E2, E4, E5) (3)

[0117] Wherein, the subscript m is the number of different sensitive devices in the spacecraft; w is the weight of the influence of different sensitive devices on the spacecraft. Er represents the comprehensive risk index caused by four environmental effects of different sensitive devices of the spacecraft on the spacecraft. The risk of each sensitive device is the maximum value among E1, E2, E4, and E5. Different sensitive devices have different influences on the spacecraft. According to factors such as the magnitude of the influence of the sensitive device on the spacecraft, its weight is determined, and the weighted sum is used to obtain the comprehensive risk of at least Er. The sensitive devices in the spacecraft may include devices and sensors for detecting, measuring, and collecting various data.

[0118] When the overall risk index of the spacecraft is the comprehensive risk index Er, the four effect risk decision-making suggestions corresponding to the single-particle risk index E1, the deep charging and discharging risk index E2, the displacement damage risk index E4, and the ionization damage risk index E5 can be used as the overall decision-making suggestions for the spacecraft.

[0119] Correspondingly, the relevant mission risk decision-making suggestions can be determined according to the corresponding mission, and this application does not limit this.

[0120] Based on the same technical concept as the space environment risk auxiliary decision-making support system provided in the above product embodiment, this application also provides a space environment risk auxiliary decision-making support method.

[0121] Figure 4 It is a schematic flowchart of a space environment risk auxiliary decision-making support method according to an embodiment of this application. As Figure 4 shown, the space environment risk auxiliary decision-making support method provided by the embodiment of this application may include the following steps:

[0122] S501: Collect the monitoring data of the equipment and the space environment at the target moment. The monitoring data includes equipment position parameters, equipment performance parameters, solar activity data, atmospheric data, ionospheric data, and geomagnetic activity data;

[0123] S502: According to the input data requirements of various space environment models, input the target moment, equipment position parameters, solar activity data, atmospheric data, and geomagnetic activity data into the corresponding space environment models, and combine the monitoring data and the model output data to calculate the equipment or mission-related environmental parameters;

[0124] S503: Evaluate the effect risk index of the mission risk affected by the space environment;

[0125] Among them, the mission risks include the risks of the spacecraft body and the mission risks of related equipment; the risks of the spacecraft body are based on the equipment position parameters, equipment performance parameters, and environmental parameters to determine multiple effect risk indices of the spacecraft under the influence of various environmental effects; the mission risks of related equipment are based on the ionospheric data including equipment position parameters, signal frequencies, and signal transmission paths to determine the effect risk indices under the influence of related mission environmental effects;

[0126] S504: Give suggestions on countermeasures for mission risks; among them, for any effect risk with an effect risk index greater than or equal to the preset risk threshold in the mission risks, query historical cases in the case database that are the same as the equipment, have the same mission type, and the same effect risk type; and calculate the similarity between the current mission and the historical case according to the effect risk index and its corresponding target sub-environment parameters; if there is a target historical case with a similarity greater than or equal to the similarity threshold, generate an effect risk decision suggestion by referring to the disposal measures of the target historical case.

[0127] The specific processes of S501 to S504 have been described in detail above when introducing the space environment risk auxiliary decision support system, and will not be elaborated here.

[0128] The space environment risk auxiliary decision support method provided by the embodiments of the present application can analyze the impacts of various environmental effects and related mission environmental effects on the spacecraft body and its missions based on the monitoring data of multiple data sources collected, determine multiple effect risk indices of the spacecraft body under various environmental effects, determine multiple effect risk indices of the related missions of the spacecraft under various related mission environmental effects, and achieve a relatively comprehensive space environment risk assessment. In addition, for various effect risks in the risks of the spacecraft body and related equipment missions, according to the effect risk indices of various effect risks, effect risk decision suggestions are automatically generated, which can provide corresponding countermeasures for the spacecraft to reduce the impact of the space environment, improve the ability of the spacecraft and its environmental support personnel to cope with space environment risks, and help improve the survival ability and mission success rate of the spacecraft.

[0129] It should be noted that Figure 4 The space environment risk auxiliary decision support method shown has the same or corresponding technical features as the space environment risk auxiliary decision support system provided by the above product embodiments, and can achieve the same or corresponding technical effects. For the sake of brief description, it will not be elaborated here.

[0130] The electronic device in the embodiments of the present application can be a user terminal device, can be a server, can also be other computing devices, or can be a cloud server. Figure 5A schematic diagram of a hardware structure of an electronic device according to an embodiment of the present application. The electronic device may include a processor 601 and a memory 602 storing computer program instructions. When the processor 601 executes the computer program instructions, the processes or functions of the methods according to any of the above embodiments are implemented.

[0131] Specifically, the processor 601 may include a central processing unit (CPU), or an application specific integrated circuit (ASIC), or one or more integrated circuits configured to implement the embodiments of the present application. The memory 602 may include a mass storage for data or instructions. For example, the memory 602 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 disk, a magneto-optical disk, a magnetic tape, a universal serial bus (USB) drive, or other physical / tangible memory storage devices. Also, the memory 602 may include removable or non-removable (or fixed) media. Further, the memory 602 may be inside or outside the integrated gateway disaster recovery device. The memory 602 may be a non-volatile solid state memory. In other words, generally, the memory 602 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), the operations described in the methods of the embodiments of the present application can be performed. The processor 601 implements the processes or functions of any of the methods in the above embodiments by reading and executing the computer program instructions stored in the memory 602.

[0132] In one example, Figure 5The electronic device shown may further include a communication interface 603 and a bus 610. Among them, the processor 601, the memory 602, and the communication interface 603 are connected through the bus 610 to complete communication with each other. The communication interface 603 is mainly used to implement communication between various modules, devices, units, and / or devices in the embodiments of the present application. The bus 610 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: Accelerated Graphics Port (AGP) or other graphics buses, Extended Industry Standard Architecture (EISA) bus, Front Side Bus (FSB), HyperTransport (HT) interconnect, Industry Standard Architecture (ISA) bus, InfiniBand interconnect, Low Pin Count (LPC) bus, Memory bus, MicroChannel Architecture (MCA) bus, Peripheral Component Interconnect (PCI) bus, PCI-Express (PCI-X) bus, Serial Advanced Technology Attachment (SATA) bus, Video Electronics Standards Association Local (VLB) bus, or other suitable buses. The bus 610 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.

[0133] Combined with the method in the above embodiments, the embodiments of the present application further provide a computer-readable storage medium, on which computer program instructions are stored. 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.

[0134] In addition, the embodiments of the present application further provide a computer program product, on which computer program instructions are stored. 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.

[0135] The flowcharts and / or block diagrams of the methods, devices, systems, and computer program products in 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 or combination of blocks in the flowchart and / or block diagram can be implemented by computer program instructions, can be implemented by dedicated hardware that performs a specified function or action, or can be implemented 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 dedicated computer, or other programmable data processing devices to form a machine, so that these instructions executed by such a processor enable the implementation of the specified functions / actions in each block or combination of blocks in the flowchart and / or block diagram. Such a processor can be a general-purpose processor, a dedicated processor, a special application processor, or a field programmable logic circuit.

[0136] The functional blocks shown in the structural 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 for performing 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.

[0137] 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 simplicity 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 elaborated here. It should be understood that the protection scope of the present application is not limited thereto. Any person skilled in the art within the technical scope disclosed in the present application can think of various equivalent modifications or substitutions, and these modifications or substitutions should be covered within the protection scope of the present application.

Claims

1. A space environment risk assisted decision-making support system, characterized in that, Including: A data acquisition module, which is used to acquire the monitoring data of the equipment and the space environment at the target moment. The monitoring data includes equipment position parameters, equipment performance parameters, solar activity data, atmospheric data, ionospheric data, and geomagnetic activity data; An environmental parameter calculation module, which is used to input the target moment, equipment position parameters, solar activity data, atmospheric data, and geomagnetic activity data into the corresponding space environment models according to the input data requirements of various space environment models, and calculate the equipment or mission-related environmental parameters by combining the monitoring data and the model output data; A risk assessment module, which is used to evaluate the effect risk index of the mission risk affected by the space environment. The mission risk includes the spacecraft body risk and the related equipment mission risk; The spacecraft body risk is based on the equipment position parameters, equipment performance parameters, and environmental parameters to determine multiple effect risk indexes under the influence of various environmental effects; The related equipment mission risk is based on the equipment position parameters, signal frequency, and ionospheric parameters of the signal transmission path to determine the effect risk index under the influence of the related mission environmental effects; A decision support module, which is used to give suggestions on countermeasures for mission risks; for any effect risk with an effect risk index greater than or equal to the preset risk threshold in the mission risk, query the historical cases with the same equipment, the same mission type, and the same effect risk type from the case database; and calculate the similarity between the current mission and the historical cases according to the effect risk index and its corresponding target sub-environmental parameters; if there is a target historical case with a similarity greater than or equal to the similarity threshold, generate an effect risk decision suggestion by referring to the disposal measures of the target historical case.

2. The system according to claim 1, wherein The effect risk index of the target historical case is greater than or equal to the effect risk index of the current mission; The decision support module is also used to, if there is no target historical case, query the target risk disposal measure suggestion corresponding to the effect risk index from the pre-established decision suggestion expert database as the effect risk decision suggestion.

3. The system according to claim 1, characterized in that The multiple environmental effects include single event upset effect, deep dielectric charging effect, surface charging effect, displacement damage effect, ionization damage effect, orbit decay effect, and debris collision effect. Correspondingly, the multiple effect risk indexes include single event risk index E1, deep dielectric charging risk index E2, surface charging risk index E3, displacement damage risk index E4, ionization damage risk index E5, orbit decay risk index E6, and debris collision risk index E7.

4. The system according to claim 3, wherein The target sub-environmental parameters corresponding to the single event risk index E1 at least include the proton flux of the orbit where the spacecraft is located; When the single event risk index E1 is equal to x1, the effect risk decision suggestion is to pay attention to the changes in the space environment; When the single event risk index E1 is equal to x2, the effect risk decision suggestion is to strengthen the monitoring and increase the monitoring arc segment; When the single event risk index E1 is equal to x3, the effect risk decision suggestion is to collect telemetry data in real time, monitor the function changes of the vulnerable devices, and when necessary, the single machine containing the sensitive devices enters the safe state; When the single-particle risk index E1 is equal to x4, the effect risk decision recommendation is that some single machines containing sensitive devices enter the safe state, where x4 > x3 > x2 > x1 and all are positive numbers.

5. The system according to claim 3 or 4, characterized in that, The target sub-environment parameters corresponding to the deep charging and discharging risk index E2 include at least the electron flux of the orbit where the spacecraft is located; The target sub-environment parameters corresponding to the surface charging and discharging risk index E3 include at least the geomagnetic index; The target sub-environment parameters corresponding to the displacement damage risk index E4 include at least the proton flux of the orbit where the spacecraft is located; The target sub-environment parameters corresponding to the ionization damage risk index E5 include at least the proton flux and electron flux of the orbit where the spacecraft is located; The target sub-environment parameters corresponding to the orbit decay risk index E6 include at least the atmospheric density; The target sub-environment parameters corresponding to the debris collision risk index E7 include at least the orbital elements of the space debris and the orbital elements of the spacecraft.

6. The system according to claim 1, wherein The relevant mission environment effects include the Faraday rotation effect, the ionospheric dispersion effect, the ionospheric time delay effect, the ionospheric scintillation effect, and the ionospheric absorption effect. The effect risk indices affected by the relevant mission environment effects include the ionosphere affecting satellite communication risk index R1, the ionosphere affecting satellite navigation risk index R2, the ionosphere affecting SAR imaging risk index R3, the ionosphere affecting shortwave communication risk index R4, and the ionosphere affecting ground-based radar risk index R5; The target sub-environment parameters corresponding to the ionosphere affecting satellite communication risk index R1, the ionosphere affecting satellite navigation risk index R2, the ionosphere affecting SAR imaging risk index R3, the ionosphere affecting shortwave communication risk index R4, and the ionosphere affecting ground-based radar risk index R5 include at least the ionospheric electron density.

7. The system according to claim 3 or 4, characterized in that The risk assessment module is further configured to calculate a comprehensive risk index Er, and use the maximum risk index among the comprehensive risk index Er, the surface charging and discharging risk index E3, the orbit decay risk index E6, and the debris collision risk index E7 as the overall risk index of the spacecraft; Among them, the comprehensive risk index Er represents the comprehensive risk index caused by four environmental effects of different devices of the spacecraft. The four environmental effects include: single-event upset effect, deep charging and discharging effect, displacement damage effect, and ionization damage effect; The decision support module is further configured to, when the overall risk index of the spacecraft is one of the effect risk indices of the surface charging and discharging risk index E3, the orbit decay risk index E6, or the debris collision risk index E7, use the effect risk decision recommendation corresponding to the effect risk index as the overall decision recommendation of the spacecraft.

8. The system according to claim 7, wherein The decision support module is further configured to, when the overall risk index of the spacecraft is the comprehensive risk index Er, use the effect risk decision recommendations corresponding to the single-particle risk index E1, the deep charging and discharging risk index E2, the displacement damage risk index E4, and the ionization damage risk index E5 as the overall decision recommendation of the spacecraft.

9. The system according to claim 1, wherein The single event upset risk index, deep dielectric charging risk index, surface charging risk index, displacement damage risk index, ionization damage risk index, orbit decay risk index, and debris collision risk index of the spacecraft body are determined by calculating the number of single event upsets of multiple sensitive devices in the spacecraft, the charging electric field at multiple sensitive devices, the surface charging potential of the spacecraft, the displacement damage dose of multiple sensitive devices, the ionization damage dose of multiple sensitive devices, the orbit decay amount, and the probability of the spacecraft colliding with space debris, respectively; The ionosphere impact on satellite communication risk index, ionosphere impact on satellite navigation risk index, ionosphere impact on SAR imaging risk index, ionosphere impact on shortwave communication risk index, and ionosphere impact on ground-based radar risk index of related equipment missions are determined by calculating the signal-to-noise ratio / bit error rate, navigation positioning error, imaging resolution, shortwave communication reliability / compatibility, range error / angle error, respectively.

10. The system according to claim 1, characterized in that, Multiple space environment models include the International Geomagnetic Reference Field model, the Earth radiation belt model, the atmospheric model, and the ionosphere model; The environmental parameter calculation module includes: A geomagnetic parameter calculation unit, which inputs the target time, the longitude of the spacecraft, the latitude of the spacecraft, and the altitude of the spacecraft into the International Geomagnetic Reference Field model to obtain the target geomagnetic parameters at the location of the spacecraft. The target geomagnetic parameters include at least the magnetic shell parameters and the magnetic field strength at the location of the spacecraft in the Earth's magnetic field; A proton flux calculation unit. For low-orbit satellites, when in the mid-low latitudes, the target geomagnetic parameters are input into the Earth radiation belt model to obtain the proton flux in the orbit where the spacecraft is located; for the high-latitude regions of low-orbit satellites and medium-high orbit satellites during solar proton events, the flux refers to the high-energy proton detection results of geosynchronous operational environmental satellites; An electron flux calculation unit. For low-orbit satellites, the target geomagnetic parameters are input into the Earth radiation belt model to obtain the electron flux in the orbit where the spacecraft is located; for medium-high orbit satellites, the high-energy electron detection data of geosynchronous orbits need to be referred to; An atmospheric parameter calculation unit, which inputs the target time, the longitude of the spacecraft, the latitude of the spacecraft, the altitude of the spacecraft, the solar radiation intensity, and the geomagnetic activity index into the atmospheric model to obtain atmospheric parameters. The atmospheric parameters include atmospheric temperature, atmospheric density, and the content of each element in the atmosphere; An ionosphere parameter calculation unit, which inputs the longitude of the spacecraft, the latitude of the spacecraft, the altitude of the spacecraft, the solar activity data, and the geomagnetic activity index into the ionosphere model to obtain the ionosphere parameters of the signal transmission path. The ionosphere parameters of the signal transmission path include the critical frequency of each layer, the electron density of each layer, the peak height of each layer, and TEC.

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