Satellite orbit space environment disturbance coping method, equipment and computer program product

Abstract

The invention discloses a satellite orbit space environment disturbance coping method and device and a computer program product, and the method comprises the steps: obtaining the current position data and current space environment data of a target orbit, the current space environment data comprises a first high-energy particle integral flux at a high-energy particle flux target position and a first upper atmosphere daily average atmospheric density; according to the current position data, querying a second high-energy particle integral flux and a second upper atmosphere daily average atmospheric density at the high-energy particle flux target position when the target orbit environment is quiet; calculating the relative disturbance quantity of the high-energy particle radiation environment of the target orbit and the maximum relative disturbance quantity of the atmospheric density of the upper layer; determining the current high-energy particle radiation environment disturbance degree and the current atmospheric environment disturbance degree in combination with the disturbance degree judgment range; and generating risk coping suggestions. According to the invention, the operation environment disturbance condition of the spacecraft can be accurately known, and the in-orbit operation safety of the spacecraft is improved.

Description

Technical Field

[0001] The present application relates to the field of aerospace technology, and in particular to a method, device, electronic device, computer-readable storage medium and computer program product for responding to satellite orbit space environment disturbances. Background Art

[0002] The space environment is known as the fourth environment for human activities besides land, ocean and atmosphere. It includes three parts: solar atmosphere, interplanetary space and Earth space (which is further divided into magnetosphere, ionosphere and upper atmosphere). Solar activity is the main source of disturbance in the space environment, which may cause typical space environment events such as coronal mass ejections, solar flares, solar proton events, magnetic storms and high-energy electron storms. Different degrees of solar flare activities may cause different degrees of disturbance in the Earth's space environment. Harsh radiation, atmosphere and other environments may cause spacecraft operating in them to malfunction or even crash. It is crucial to understand the disturbance of the spacecraft's operating environment in real time and give corresponding response suggestions to ensure the on-orbit operation of spacecraft.

[0003] At present, a series of standards have been formulated in the field of space environment at home and abroad, but there is still a gap in the determination of the degree of disturbance in the satellite orbit space environment. With the continuous deepening of human exploration and utilization of space, it is crucial to accurately determine the degree of disturbance in the satellite orbit space environment and provide corresponding risk response suggestions for the design, operation guarantee and space environment research of spacecraft. Summary of the invention

[0004] In view of this, an embodiment of the present application provides a method, device, electronic device, computer-readable storage medium and computer program product for responding to satellite orbit space environment disturbances, which are used to solve at least one of the above-mentioned technical problems.

[0005] In a first aspect, an embodiment of the present application provides a method for coping with a satellite orbit space environment disturbance, including: obtaining current position data and current space environment data of a target orbit where a target spacecraft is located, the current space environment data including a first high-energy particle integrated flux and a first high-level atmospheric daily average atmospheric density at a high-energy particle flux target position; According to the current position data of the target orbit, query the second high-energy particle integrated flux at the high-energy particle flux target position when the target orbit environment is calm and the second high-level atmospheric daily average atmospheric density when the target orbit environment is calm; Calculate the relative disturbance of the high-energy particle radiation environment of the target orbit according to the first high-energy particle integrated flux and the second high-energy particle integrated flux; Calculate the maximum relative disturbance of the upper atmosphere density of the target orbit based on the daily average atmospheric density of the first upper atmosphere and the daily average atmospheric density of the second upper atmosphere; Determine the current disturbance degree of the high-energy particle radiation environment according to the relative disturbance amount of the high-energy particle radiation environment and the pre-set high-energy particle radiation environment disturbance degree discrimination range; Determine the current atmospheric environment disturbance degree according to the maximum relative disturbance amount of the upper atmospheric density and the preset atmospheric environment disturbance degree discrimination range; A first risk response suggestion corresponding to the current high-energy particle radiation environment disturbance level is generated, and a second risk response suggestion corresponding to the current atmospheric environment disturbance level is generated, and provided to maintenance personnel of the target spacecraft.

[0006] According to some embodiments of the present application, optionally, the high-energy particles include at least one of protons and electrons.

[0007] According to some embodiments of the present application, optionally, in the case where the high-energy particles include protons and electrons, the first high-energy particle integrated flux includes a first proton integrated flux at a proton flux target position and a first electron integrated flux at an electron flux target position, and the second high-energy particle integrated flux includes a second proton integrated flux at the proton flux target position when the target orbit environment is calm and a second electron integrated flux at the electron flux target position when the target orbit environment is calm; According to the first high-energy particle integrated flux and the second high-energy particle integrated flux, the relative disturbance amount of the high-energy particle radiation environment of the target orbit is calculated, including: calculating the ratio of the first proton integrated flux to the second proton integrated flux to obtain the relative disturbance amount of the proton radiation environment of the target orbit; calculating the ratio of the first electron integrated flux to the second electron integrated flux to obtain the relative disturbance amount of the electron radiation environment of the target orbit; the current high-energy particle radiation environment disturbance degree includes the current proton radiation environment disturbance degree and the current electron radiation environment disturbance degree, and the first risk response suggestion includes the risk response suggestion corresponding to the current proton radiation environment disturbance degree and the risk response suggestion corresponding to the current electron radiation environment disturbance degree.

[0008] According to some embodiments of the present application, optionally, determining the current high-energy particle radiation environment disturbance degree according to the high-energy particle radiation environment relative disturbance amount and a preset high-energy particle radiation environment disturbance degree discrimination range includes: If the relative disturbance of the high-energy particle radiation environment is less than 10, the current disturbance level of the high-energy particle radiation environment is determined to be calm; If the relative disturbance of the high-energy particle radiation environment is greater than or equal to 10 and less than 100, it is determined that the current disturbance degree of the high-energy particle radiation environment is slightly disturbed; If the relative disturbance of the high-energy particle radiation environment is greater than or equal to 100 and less than 1000, it is determined that the current disturbance degree of the high-energy particle radiation environment is medium disturbance; If the relative disturbance of the high-energy particle radiation environment is greater than or equal to 1000, the current disturbance level of the high-energy particle radiation environment is determined to be severe disturbance; Among them, the severity of multiple disturbance levels is from high to low: severe disturbance > moderate disturbance > slight disturbance > calm.

[0009] According to some embodiments of the present application, optionally, generating a first risk response suggestion corresponding to the current high-energy particle radiation environment disturbance degree includes: If the current high-energy particle radiation environment disturbance level is calm, the corresponding first risk response suggestion is to remind that the current high-energy particle radiation environment is safe and no action is taken; If the current high-energy particle radiation environment disturbance level is slight, the corresponding first risk response recommendation is to strengthen monitoring and pay attention to the potential risk of single-particle effects and / or deep charge and discharge in spacecraft; If the current high-energy particle radiation environment disturbance level is medium disturbance, the corresponding first risk response suggestion is to monitor the risk changes. When the current high-energy particle radiation environment disturbance level reaches severe disturbance, the single machine containing sensitive devices and / or the single machine affected by discharge enters a safe state; If the current high-energy particle radiation environment disturbance level is severe, the corresponding first risk response recommendation is to recommend that the single machine containing sensitive devices and / or the single machine affected by discharge enter a safe state.

[0010] According to some embodiments of the present application, optionally, calculating the maximum relative disturbance amount of the upper atmosphere density of the target orbit according to the first upper atmosphere daily average atmospheric density and the second upper atmosphere daily average atmospheric density includes: Calculate the difference between the daily average atmospheric density of the first upper atmosphere and the daily average atmospheric density of the second upper atmosphere; The percentage of the ratio of the difference to the second upper atmosphere daily average atmospheric density is calculated to obtain the maximum relative disturbance of the upper atmosphere density of the target orbit.

[0011] According to some embodiments of the present application, optionally, determining the current atmospheric environment disturbance degree according to the maximum relative disturbance amount of the high-level atmospheric density and a preset atmospheric environment disturbance degree discrimination range includes: If the maximum relative disturbance of the upper atmospheric density is less than 10%, the current atmospheric environment disturbance level is determined to be calm; If the maximum relative disturbance of the upper atmospheric density is greater than or equal to 10% and less than 40%, the current atmospheric environment disturbance level is determined to be slight disturbance; If the maximum relative disturbance of the upper atmospheric density is greater than or equal to 40% and less than 90%, the current atmospheric environment disturbance level is determined to be moderate; If the maximum relative disturbance of the upper atmospheric density is greater than or equal to 90%, the current atmospheric environment disturbance level is determined to be severe disturbance; Among them, the severity of multiple disturbance levels is from high to low: severe disturbance > moderate disturbance > slight disturbance > calm.

[0012] According to some embodiments of the present application, optionally, generating a second risk response suggestion corresponding to the current atmospheric environment disturbance degree includes: If the current atmospheric disturbance level is calm, the corresponding second response suggestion is to remind that the current atmospheric environment is safe and no action is taken; If the current atmospheric disturbance is slight, the corresponding second response suggestion is to strengthen monitoring and increase the frequency of orbit forecasts; If the current atmospheric environment disturbance level is medium, the corresponding second response suggestion is to recommend orbit raising. If the current level of atmospheric disturbance is severe, the corresponding second response suggestion is to perform orbit raising action and shut down a preset number of payloads.

[0013] In a second aspect, an embodiment of the present application provides a satellite orbit space environment disturbance response device, including: An acquisition module is used to acquire current position data and current space environment data of a target orbit where the target spacecraft is located, wherein the current space environment data includes a first high-energy particle integrated flux and a first high-level atmospheric daily average atmospheric density at a high-energy particle flux target position; A query module, used for querying the second high-energy particle integrated flux at the high-energy particle flux target position when the target orbit environment is calm and the second high-level atmospheric daily average atmospheric density when the target orbit environment is calm according to the current position data of the target orbit; A first calculation module is used to calculate a relative disturbance amount of a high-energy particle radiation environment of a target orbit according to the first high-energy particle integrated flux and the second high-energy particle integrated flux; A second calculation module is used to calculate the maximum relative disturbance of the upper atmosphere density of the target orbit according to the first upper atmosphere daily average atmospheric density and the second upper atmosphere daily average atmospheric density; The first determination module is used to determine the current disturbance degree of the high-energy particle radiation environment according to the relative disturbance amount of the high-energy particle radiation environment and a preset high-energy particle radiation environment disturbance degree discrimination range; The second determination module is used to determine the current atmospheric environment disturbance degree according to the maximum relative disturbance amount of the upper atmospheric density and a preset atmospheric environment disturbance degree discrimination range; The generation module is used to generate a first risk response suggestion corresponding to the current high-energy particle radiation environment disturbance level, and to generate a second risk response suggestion corresponding to the current atmospheric environment disturbance level, and provide them to the maintenance personnel of the target spacecraft.

[0014] In a third aspect, an embodiment of the present application provides an electronic device, comprising a processor and a memory storing computer program instructions; when the processor executes the computer program instructions, the steps of the method described above are implemented.

[0015] In a fourth aspect, an embodiment of the present application provides a computer-readable storage medium, on which computer program instructions are stored. When the computer program instructions are executed by a processor, the steps of the satellite orbit space environment disturbance response method as described above are implemented.

[0016] In a fifth aspect, an embodiment of the present application provides a computer program product, which includes computer program instructions. When the computer program instructions are executed by a processor, the steps of the satellite orbit space environment disturbance response method as described above are implemented.

[0017] The satellite orbit space environment disturbance response method, device, electronic device, computer-readable storage medium and computer program product provided by the embodiments of this application can accurately understand the disturbance of the spacecraft operating environment through real-time monitoring, quantitative evaluation and targeted suggestions, provide corresponding risk response suggestions, significantly improve the safety of spacecraft on-orbit operation, fill the gap in the satellite orbit space environment disturbance judgment standard, and provide data support for space environment research. It not only helps to ensure the safe operation of existing spacecraft, but also lays a solid foundation for future space exploration and utilization. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] In order to more clearly illustrate the technical solution of the embodiments of the present application, the following briefly introduces the drawings in the embodiments of the present application.

[0019] Figure 1 A flowchart of a method for coping with satellite orbit space environment disturbances provided in an embodiment of the present application.

[0020] Figure 2 A structural block diagram of a satellite orbit space environment disturbance response device provided in an embodiment of the present application.

[0021] Figure 3 A schematic diagram of the hardware structure of an electronic device according to an embodiment of the present application. DETAILED DESCRIPTION

[0022] The features and exemplary embodiments of various aspects of the present application will be described in detail below. In order to make the purpose, technical solutions and advantages of the present application clearer, the present application will be further described in detail below in conjunction with the accompanying drawings and specific embodiments. It should be understood that the specific embodiments described herein are only intended to explain the present application, rather than to limit the present application. For those skilled in the art, the present application can be implemented without the need for some of these specific details. The following description of the embodiments is only to provide a better understanding of the present application by illustrating the examples of the present application.

[0023] It should be noted that, in this article, relational terms such as first and second, etc. are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device. In the absence of further restrictions, the elements defined by the statement "include..." do not exclude the presence of other identical elements in the process, method, article or device including the elements.

[0024] It should be understood that the term "and / or" used in this article is only a description of the association relationship of associated objects, indicating that there can be three relationships. For example, A and / or B can represent: A exists alone, A and B exist at the same time, and B exists alone. In addition, the character " / " in this article generally indicates that the associated objects before and after are in an "or" relationship.

[0025] It is obvious to those skilled in the art that various modifications and changes can be made in this application without departing from the spirit or scope of this application. Therefore, this application is intended to cover modifications and changes of this application that fall within the scope of the corresponding claims (technical solutions claimed for protection) and their equivalents. It should be noted that the implementation methods provided in the embodiments of this application can be combined with each other without contradiction.

[0026] Before describing the technical solutions provided by the embodiments of the present application, in order to facilitate the understanding of the embodiments of the present application, the present application first specifically describes the problems existing in the related art: The space environment is known as the fourth environment for human activities besides land, ocean and atmosphere. It includes three parts: solar atmosphere, interplanetary space and Earth space (which is further divided into magnetosphere, ionosphere and upper atmosphere). Solar activity is the main source of disturbance in the space environment, which may cause typical space environment events such as coronal mass ejections, solar flares, solar proton events, magnetic storms and high-energy electron storms. Different degrees of solar flare activities may cause different degrees of disturbance in the Earth's space environment. Harsh radiation, atmosphere and other environments may cause spacecraft operating in them to malfunction or even crash. It is crucial to understand the disturbance of the spacecraft's operating environment in real time and give corresponding response suggestions to ensure the on-orbit operation of spacecraft.

[0027] At present, a series of standards have been formulated in the field of space environment at home and abroad, but there is still a gap in the determination of the degree of disturbance in the satellite orbit space environment. With the continuous deepening of human exploration and utilization of space, it is crucial to accurately determine the degree of disturbance in the satellite orbit space environment and provide corresponding risk response suggestions for the design, operation guarantee and space environment research of spacecraft.

[0028] In order to reduce the risks to satellites and other spacecraft caused by disturbances in the satellite orbit space environment, the embodiments of the present application provide a method, device, electronic device, computer-readable storage medium and computer program product for responding to disturbances in the satellite orbit space environment. By quantitatively judging the degree of disturbance in the satellite orbit space environment, it is possible to more accurately determine whether the current satellite orbit space environment poses a threat to satellites and other spacecraft, thereby taking corresponding response measures to ensure the safe operation of the spacecraft.

[0029] The following first introduces the satellite orbit space environment disturbance response method provided in the embodiment of the present application.

[0030] Figure 1 A schematic diagram of a flow chart of a method for coping with satellite orbit space environment disturbance provided in an embodiment of the present application. Figure 1 As shown, the satellite orbit space environment disturbance response method provided in the embodiment of the present application may include the following steps S101 to S107.

[0031] S101: Acquire the current position data and current space environment data of the target orbit where the target spacecraft is located. The current space environment data includes the first high-energy particle integrated flux and the first high-level atmospheric daily average atmospheric density at the high-energy particle flux target position.

[0032] For example, the target spacecraft includes but is not limited to a satellite or other spacecraft. In S101, data can be collected in real time by sensors and detectors on the target spacecraft, and the data can be transmitted to a data processing device at a ground station through a telemetry system.

[0033] For example, the current position data of the target orbit where the target spacecraft is located can be obtained by the navigation device or ground measurement and control system carried by the target spacecraft, which can obtain the precise position information of the target spacecraft in the target orbit in real time, including orbital altitude, inclination, latitude and other parameters.

[0034] For another example, a high-energy particle detector carried by a target spacecraft can be used to measure the target position of the high-energy particle flux on the target orbit, and the integrated flux at that position (i.e., the total number of high-energy particles passing through a unit area per unit time) can be calculated to obtain a first high-energy particle integrated flux.

[0035] For another example, the atmospheric density in the target orbit can be measured by an atmospheric density detection instrument carried by the target spacecraft, and its daily average value can be calculated to obtain the daily average atmospheric density of the first upper atmosphere.

[0036] S102: According to the current position data of the target orbit, query the second high-energy particle integrated flux at the high-energy particle flux target position when the target orbit environment is calm and the second high-level atmosphere daily average atmospheric density when the target orbit environment is calm.

[0037] In some embodiments, for example, according to the orbital altitude and latitude of the target orbit, the high-energy particle integrated flux data of the target orbit when the environment is calm (such as when the solar activity is low or there is no obvious solar eruption event) can be queried from a historical database or a space environment model to obtain the second high-energy particle integrated flux. Similarly, for example, according to the orbital altitude and latitude of the target orbit, the daily average density data of the upper atmosphere of the target orbit when the environment is calm can be queried from a historical database or a Mass Spectrometer and Incoherent Scatter Radar Extended Model (MSISE) model to obtain the second daily average atmospheric density of the upper atmosphere.

[0038] Taking the MSISE model as an example, the input parameters of the MSISE model usually include solar radiation flux (such as the F10.7 index) and geomagnetic activity index (such as the Kp or Ap index) to reflect the impact of solar activity and geomagnetic disturbances on the upper atmosphere.

[0039] In some specific embodiments, when the environment is calm, 1 / 5 of the historical monitoring data of a solar activity week is taken as the environmental calm data, and through statistical analysis of the historical monitoring data, it is obtained that when the environment is calm: the F10.7 value is below 75, and the Ap index is below 5. That is, through the MSISE model, for example, the upper atmosphere daily average density data of the target orbit with an F10.7 value below 75 and an Ap index below 5 is queried, and the second upper atmosphere daily average atmospheric density is obtained.

[0040] S103: Calculate the relative disturbance of the high-energy particle radiation environment of the target orbit according to the first high-energy particle integrated flux and the second high-energy particle integrated flux.

[0041] In S103, the relative disturbance of the high-energy particle radiation environment of the target orbit can be calculated according to the first high-energy particle integrated flux and the second high-energy particle integrated flux. The relative disturbance of the high-energy particle radiation environment reflects the disturbance degree of the current high-energy particle radiation environment relative to the calm environment.

[0042] S104: Calculate the maximum relative disturbance of the upper atmosphere density of the target orbit according to the first upper atmosphere daily average atmospheric density and the second upper atmosphere daily average atmospheric density.

[0043] In S104, the maximum relative disturbance of the upper atmosphere density of the target track can be calculated according to the first upper atmosphere daily average atmospheric density and the second upper atmosphere daily average atmospheric density. The maximum relative disturbance of the upper atmosphere density reflects the disturbance degree of the current upper atmosphere density relative to the calm environment.

[0044] By calculating the relative disturbance of the high-energy particle radiation environment and the maximum relative disturbance of the upper atmosphere density, the degree of disturbance in the space environment is quantified. This quantification method can make the assessment of environmental disturbance more scientific and objective, avoiding the errors caused by subjective judgment. Moreover, quantifying the degree of disturbance can provide a clear reference standard for the design and operation of spacecraft. By quantifying the degree of disturbance, it is possible to more accurately judge whether the current environment poses a threat to the spacecraft, and thus take corresponding countermeasures.

[0045] S105: Determine the current disturbance degree of the high-energy particle radiation environment according to the relative disturbance amount of the high-energy particle radiation environment and a preset high-energy particle radiation environment disturbance degree discrimination range.

[0046] According to the severity of the high-energy particle radiation environment disturbance, the high-energy particle radiation environment disturbance degree discrimination range can be divided into multiple levels. In S105, the calculated high-energy particle radiation environment relative disturbance amount can be compared with the pre-set high-energy particle radiation environment disturbance degree discrimination range to determine the current high-energy particle radiation environment disturbance degree.

[0047] S106: Determine the current atmospheric environment disturbance degree according to the maximum relative disturbance amount of the high-level atmospheric density and a preset atmospheric environment disturbance degree discrimination range.

[0048] Similarly, the atmospheric environment disturbance degree discrimination range can be divided into multiple levels according to the severity of the atmospheric environment disturbance. In S105, the calculated atmospheric environment relative disturbance amount can be compared with the preset atmospheric environment disturbance degree discrimination range to determine the current atmospheric environment disturbance degree.

[0049] S107: Generate a first risk response suggestion corresponding to the current high-energy particle radiation environment disturbance level, and generate a second risk response suggestion corresponding to the current atmospheric environment disturbance level, and provide them to maintenance personnel of the target spacecraft.

[0050] After determining the current high-energy particle radiation environmental disturbance degree and the current atmospheric environmental disturbance degree, for example, corresponding suggestions can be automatically matched from a preset response strategy library according to the disturbance degree level, including a first risk response suggestion corresponding to the current high-energy particle radiation environmental disturbance degree and a second risk response suggestion corresponding to the current atmospheric environmental disturbance degree. The first risk response suggestion and the second risk response suggestion can be generated in the form of text, code or instructions, and sent to the target satellite or maintenance personnel through a communication system, so that the maintenance personnel can refer to the risk response suggestions and execute corresponding response strategies, so that the target spacecraft can take timely measures before or when the environmental disturbance occurs to avoid or reduce the risk of failure and crash.

[0051] The satellite orbit space environment disturbance response method provided in the embodiments of the present application can, on the one hand, monitor the changes in high-energy particle flux and high-level atmospheric density in real time by acquiring the current position data and current space environment data of the orbit where the target satellite is located, thereby helping to promptly detect potential environmental risks and avoid spacecraft failures or crashes due to sudden environmental changes.

[0052] On the other hand, the degree of space environment disturbance is quantified by calculating the relative disturbance of the high-energy particle radiation environment and the maximum relative disturbance of the upper atmosphere density. This quantification method can make the assessment of environmental disturbance more scientific and objective, avoiding the errors caused by subjective judgment. Moreover, quantifying the degree of disturbance can provide a clear reference standard for the design and operation guarantee of spacecraft. By quantifying the degree of disturbance, it is possible to more accurately judge whether the current environment poses a threat to the spacecraft, so as to take corresponding countermeasures. In addition, by setting the range of judgment of the degree of high-energy particle radiation environment disturbance and the range of judgment of the degree of atmospheric environment disturbance, a unified quantitative standard is provided for the judgment of satellite orbit space environment disturbance. This standardized judgment method fills the gap in existing standards. Through standardized assessment, different spacecraft can take consistent countermeasures when facing the same environmental disturbance, which improves the reliability and safety of the overall system.

[0053] On the other hand, corresponding risk response suggestions are generated according to the degree of disturbance of the high-energy particle radiation environment and the degree of disturbance of the atmospheric environment. These suggestions can provide specific operational guidance for different degrees of disturbance, such as adjusting the orbit, shutting down sensitive equipment, etc. Targeted risk response suggestions can help spacecraft maintenance personnel make decisions quickly and reduce losses caused by environmental disturbances. This automated suggestion generation mechanism improves the efficiency of responding to emergencies, reduces delays and errors in human judgment, and helps spacecraft to operate more stably in the complex and changing space environment, extend their service life, and reduce maintenance costs.

[0054] According to some embodiments of the present application, optionally, the high-energy particles may include at least one of protons and electrons.

[0055] For example, in some specific embodiments, high-energy particles may include both protons and electrons. Accordingly, the first high-energy particle integrated flux may include a first proton integrated flux at a proton flux target position and a first electron integrated flux at an electron flux target position. The second high-energy particle integrated flux may include a second proton integrated flux at a proton flux target position when the target orbit environment is calm and a second electron integrated flux at an electron flux target position when the target orbit environment is calm. For the method of obtaining the first proton integrated flux and the first electron integrated flux, please refer to the method of obtaining the first high-energy particle integrated flux above, and for the method of obtaining the second proton integrated flux and the second electron integrated flux, please refer to the method of obtaining the second high-energy particle integrated flux above, which will not be repeated here.

[0056] Solar activity outbreaks or geomagnetic disturbances can cause a sharp increase in the high-energy particle flux in the Earth's orbit. Due to the protection of the geomagnetic field, the degree of radiation environment disturbance in different orbits is different. In some embodiments, based on high-energy particle data, the proton radiation environment can use ≥10MeV proton integrated flux, and the electron radiation environment can use ≥2MeV electron integrated flux to judge the degree of radiation environment disturbance.

[0057] Accordingly, S103: calculating the relative disturbance amount of the high-energy particle radiation environment of the target orbit according to the first high-energy particle integrated flux and the second high-energy particle integrated flux may include the following steps 1 and 2.

[0058] Step 1: Calculate the ratio of the first proton integrated flux to the second proton integrated flux to obtain the relative disturbance of the proton radiation environment of the target orbit.

[0059] The determination of the degree of disturbance of the satellite orbit space environment reflects the degree of change of the satellite orbit space environment relative to the background environment, and can indirectly understand the severity to which the spacecraft may be affected by the satellite orbit space environment.

[0060] In some examples, for example, for high orbits, medium orbits, and low orbit high latitude regions (above about 50° latitude), the relative perturbation of the proton radiation environment of the target orbit can be calculated according to the following expression (1): (1) in, represents the relative disturbance of the proton radiation environment of the target orbit, represents the first proton flux, Represents the second proton flux, unit: .

[0061] The above expression (1) can be applied to the proton radiation environment disturbance discrimination in high orbit, medium orbit and low orbit high latitude area (about 50° above latitude). The target position of the high-energy particle flux can be understood as the peak position of the high-energy particle flux or a position near the peak. For example, for protons, the target position of the proton flux in high orbit and medium orbit can be set as the equatorial position, while the target position of the proton flux in low orbit (including low orbit high latitude area) can be set as ±60° latitude position. The first proton integrated flux of high orbit and medium orbit is and the second proton flux It can be determined as the equatorial position using a proton flux of ≥10 MeV, the first proton flux of the low orbit and the second proton flux It can be determined that the proton flux of ≥10 MeV is used at ±60° latitude. For example, when the space environment is calm, the proton flux of ≥10 MeV in the equatorial position of high and medium orbits and the high latitude region of low orbit is usually less than 3 .

[0062] Step 2: Calculate the ratio of the first electron integrated flux to the second electron integrated flux to obtain the relative disturbance of the electron radiation environment of the target orbit.

[0063] In some examples, the relative disturbance of the electron radiation environment of the target orbit may be calculated according to the following expression (2): (2) in, Represents the relative disturbance of the electron radiation environment of the target orbit, represents the first electron integrated flux, Represents the second electron integrated flux, unit: .

[0064] For example, similar to protons, for electrons, the target position of the electron flux in high and medium orbits can be set at the equatorial position, and the target position of the electron flux in low orbits can be set at ±60° latitude. and the second electron flux It can be determined as the equatorial position using ≥2MeV electron integrated flux, the first electron integrated flux of the low orbit and the second electron flux It can be determined that the electron flux of ≥2MeV is used at ±60° latitude. For example, in a quiet space environment, such as at the equatorial position at an orbital altitude of 35786km, the electron flux of ≥2MeV is 300 Below, at 22000km orbit altitude, the electron flux of ≥2MeV at the equatorial position is 10 4 the following.

[0065] Accordingly, the current high-energy particle radiation environment disturbance degree may include the current proton radiation environment disturbance degree and the current electron radiation environment disturbance degree, and the first risk response suggestion may include a risk response suggestion corresponding to the current proton radiation environment disturbance degree and a risk response suggestion corresponding to the current electron radiation environment disturbance degree.

[0066] Protons (especially high-energy protons ≥10MeV) have high penetrating power and can cause serious damage to spacecraft electronic equipment, solar cells, astronaut health, etc. Depending on the degree of proton radiation disturbance, it can be recommended to shut down or shield sensitive equipment to reduce the damage of proton radiation to electronic components. In addition, by taking timely protective measures, the cumulative damage of proton radiation to solar cells and electronic equipment can be reduced, extending the service life of the spacecraft.

[0067] High-energy electrons can cause charging and discharging of spacecraft surface materials, triggering electrostatic discharge (ESD) events. Depending on the degree of disturbance, it may be recommended to shut down or shield susceptible equipment, or to enable redundant systems. When the electron radiation disturbance is high, it may be recommended to adjust the spacecraft trajectory to avoid areas of high electron flux (such as the South Atlantic Anomaly).

[0068] In this way, by providing risk response recommendations for the proton radiation environment disturbance degree and the electron radiation environment disturbance degree respectively, it is possible to respond to radiation threats in the space environment more accurately and efficiently, thereby ensuring the safe operation of spacecraft and the successful execution of missions.

[0069] According to some embodiments of the present application, optionally, by combining multiple space environment models and monitoring data of multiple satellites for statistical analysis, the degree of disturbance of the satellite orbit space environment is defined as four levels, namely: calm, slight disturbance, moderate disturbance, severe disturbance, and set the range of disturbance degree for each level. Among them, the severity of multiple disturbance degrees is from high to low: severe disturbance>medium disturbance>slight disturbance>calm.

[0070] Specifically, S105: determining the current disturbance degree of the high-energy particle radiation environment according to the relative disturbance amount of the high-energy particle radiation environment and a preset high-energy particle radiation environment disturbance degree discrimination range includes: If the relative disturbance of the high-energy particle radiation environment is less than 10, the current disturbance level of the high-energy particle radiation environment is determined to be calm; If the relative disturbance of the high-energy particle radiation environment is greater than or equal to 10 and less than 100, it is determined that the current disturbance degree of the high-energy particle radiation environment is slightly disturbed; If the relative disturbance of the high-energy particle radiation environment is greater than or equal to 100 and less than 1000, it is determined that the current disturbance degree of the high-energy particle radiation environment is medium disturbance; If the relative disturbance amount of the high-energy particle radiation environment is greater than or equal to 1000, it is determined that the current disturbance degree of the high-energy particle radiation environment is a severe disturbance.

[0071] For example, for protons, if the relative disturbance amount of the proton radiation environment is less than 10, the current proton radiation environment disturbance degree is determined to be calm; if the relative disturbance amount of the proton radiation environment is greater than or equal to 10 and less than 100, the current proton radiation environment disturbance degree is determined to be slightly disturbed; if the relative disturbance amount of the proton radiation environment is greater than or equal to 100 and less than 1000, the current proton radiation environment disturbance degree is determined to be moderately disturbed; if the relative disturbance amount of the proton radiation environment is greater than or equal to 1000, the current proton radiation environment disturbance degree is determined to be severely disturbed.

[0072] For example, for electrons, if the relative disturbance amount of the electron radiation environment is less than 10, the current disturbance degree of the electron radiation environment is determined to be calm; if the relative disturbance amount of the electron radiation environment is greater than or equal to 10 and less than 100, the current disturbance degree of the electron radiation environment is determined to be slightly disturbed; if the relative disturbance amount of the electron radiation environment is greater than or equal to 100 and less than 1000, the current disturbance degree of the electron radiation environment is determined to be moderately disturbed; if the relative disturbance amount of the electron radiation environment is greater than or equal to 1000, the current disturbance degree of the electron radiation environment is determined to be severely disturbed.

[0073] According to some embodiments of the present application, optionally, S107: generating a first risk response suggestion corresponding to the current high-energy particle radiation environment disturbance degree includes: If the current high-energy particle radiation environment disturbance level is calm, the corresponding first risk response suggestion is to remind that the current high-energy particle radiation environment is safe and no action is taken; If the current high-energy particle radiation environment disturbance level is slight, the corresponding first risk response recommendation is to strengthen monitoring and pay attention to the potential risk of single-particle effects and / or deep charge and discharge in spacecraft; If the current high-energy particle radiation environment disturbance level is medium disturbance, the corresponding first risk response suggestion is to monitor the risk changes. When the current high-energy particle radiation environment disturbance level reaches severe disturbance, the single machine containing sensitive devices and / or the single machine affected by discharge enters a safe state; If the current high-energy particle radiation environment disturbance level is severe, the corresponding first risk response recommendation is to recommend that the single machine containing sensitive devices and / or the single machine affected by discharge enter a safe state.

[0074] Taking protons as an example of high-energy particles, if the current proton radiation environment disturbance level is calm, the corresponding risk response suggestion is to remind the current proton radiation environment to be safe and no action is taken. If the current proton radiation environment disturbance level is slight disturbance, the corresponding risk response suggestion is to recommend enhanced monitoring and pay attention to the potential risk of single particle effects in spacecraft. If the current proton radiation environment disturbance level is moderate disturbance, the corresponding risk response suggestion is to recommend monitoring risk changes and, if necessary, single machines containing sensitive devices enter a safe state. If the current proton radiation environment disturbance level is severe disturbance, the corresponding risk response suggestion is to recommend single machines containing sensitive devices enter a safe state.

[0075] Taking electrons as high-energy particles as an example, if the current level of disturbance in the electron radiation environment is calm, the corresponding risk response recommendation is to remind that the current electron radiation environment is safe and no action is taken; if the current level of disturbance in the electron radiation environment is slight, the corresponding risk response recommendation is to recommend enhanced monitoring and pay attention to the potential risk of deep charging and discharging of spacecraft; if the current level of disturbance in the electron radiation environment is moderate, the corresponding risk response recommendation is to recommend monitoring changes in risks and, if necessary, to allow single machines affected by discharge to enter a safe state; if the current level of disturbance in the electron radiation environment is severe, the corresponding risk response recommendation is to recommend that single machines affected by discharge enter a safe state.

[0076] In this way, by providing targeted risk response suggestions for the current high-energy particle radiation environment, spacecraft maintenance personnel can make quick decisions and reduce losses caused by environmental disturbances. This automated suggestion generation mechanism improves the efficiency of responding to emergencies and reduces delays and errors in human judgment.

[0077] When solar activity erupts, a large amount of high-energy particles and strong electromagnetic radiation are released, which interact with the atmosphere, causing the density of the upper atmosphere to increase. Through the analysis of atmospheric density monitoring data and spacecraft trajectory positions, the following scheme for determining the degree of disturbance in the upper atmosphere environment has been developed.

[0078] According to some embodiments of the present application, optionally, S104: calculating the maximum relative disturbance amount of the upper atmosphere density of the target orbit according to the first upper atmosphere daily average atmospheric density and the second upper atmosphere daily average atmospheric density may include the following steps: Calculate the difference between the daily average atmospheric density of the first upper atmosphere and the daily average atmospheric density of the second upper atmosphere; The percentage of the ratio of the difference to the second highest daily average atmospheric density is calculated to obtain the maximum relative disturbance of the upper atmospheric density of the target orbit.

[0079] For example, in some examples, the maximum relative disturbance of the upper atmospheric density of the target orbit can be calculated according to the following expression (3): (3) in, Indicates the maximum relative disturbance of the upper atmospheric density of the target orbit, represents the daily average atmospheric density of the first upper atmosphere, Represents the daily average atmospheric density of the second upper atmosphere. As mentioned above, for example, the daily average atmospheric density of the second upper atmosphere can be obtained by the MSISE model. When the model is used to calculate the atmospheric density, the input parameter selection method for the calm period is as follows: 1 / 5 of the historical monitoring data of a solar activity week is taken as the environmental calm data. Through statistical analysis of the historical monitoring data, it is obtained that the F10.7 value is below 75 and the Ap index is below 5 when the environment is calm.

[0080] According to some embodiments of the present application, optionally, S106: determining the current atmospheric environment disturbance degree according to the maximum relative disturbance amount of the high-level atmospheric density and a preset atmospheric environment disturbance degree discrimination range may include the following steps: If the maximum relative disturbance of the upper atmospheric density is less than 10%, the current atmospheric environment disturbance level is determined to be calm; If the maximum relative disturbance of the upper atmospheric density is greater than or equal to 10% and less than 40%, the current atmospheric environment disturbance level is determined to be slight disturbance; If the maximum relative disturbance of the upper atmospheric density is greater than or equal to 40% and less than 90%, the current atmospheric environment disturbance level is determined to be moderate; If the maximum relative disturbance of the upper atmospheric density is greater than or equal to 90%, the current atmospheric environment disturbance level is determined to be severe disturbance; Among them, the severity of multiple disturbance levels is from high to low: severe disturbance > moderate disturbance > slight disturbance > calm.

[0081] Accordingly, S107: generating a second risk response suggestion corresponding to the current atmospheric environment disturbance degree may include the following steps: If the current atmospheric disturbance level is calm, the corresponding second response suggestion is to remind that the current atmospheric environment is safe and no action is taken; If the current atmospheric disturbance is slight, the corresponding second response suggestion is to strengthen monitoring and increase the frequency of orbit forecasts; If the current atmospheric environment disturbance level is medium, the corresponding second response suggestion is to recommend orbit raising. If the current level of atmospheric disturbance is severe, the corresponding second response suggestion is to perform orbit raising action and shut down a preset number of payloads.

[0082] In this way, this application provides hierarchical response suggestions according to the different degrees of atmospheric disturbance (calm, slight disturbance, moderate disturbance, severe disturbance). This hierarchical strategy can take appropriate measures for different levels of disturbances to avoid overreaction or underreaction. For example, under slight disturbances, potential risks can be discovered in advance by strengthening monitoring and increasing the frequency of orbit forecasts. In the case of moderate and severe disturbances, it is recommended to perform orbit raising actions at the right time. Orbit raising can offset the orbital attenuation caused by the increase in atmospheric density and prevent the spacecraft from crashing prematurely due to orbital descent. In the case of severe disturbances, it is recommended to shut down a preset number of payloads when necessary. Shutting down payloads can reduce the time the equipment is exposed to a high-density atmospheric environment and reduce the risk of equipment damage.

[0083] Based on the same technical concept as the satellite orbit space environment disturbance response method provided in the above embodiment, the present application also provides a satellite orbit space environment disturbance response device. Please refer to the following embodiment.

[0084] Figure 2 A structural block diagram of a satellite orbit space environment disturbance response device provided in an embodiment of the present application. Figure 2 As shown, the satellite orbit space environment disturbance response device 20 provided in the embodiment of the present application may include the following modules: An acquisition module 201 is used to acquire current position data and current space environment data of a target orbit where a target spacecraft is located, wherein the current space environment data includes a first high-energy particle integrated flux and a first high-level atmospheric daily average atmospheric density at a high-energy particle flux target position; A query module 202 is used to query the second high-energy particle integrated flux at the high-energy particle flux target position when the target orbit environment is calm and the second high-level atmospheric daily average atmospheric density when the target orbit environment is calm according to the current position data of the target orbit; A first calculation module 203 is used to calculate a relative disturbance amount of a high-energy particle radiation environment of a target orbit according to the first high-energy particle integrated flux and the second high-energy particle integrated flux; A second calculation module 204 is used to calculate the maximum relative disturbance of the upper atmosphere density of the target orbit according to the first upper atmosphere daily average atmospheric density and the second upper atmosphere daily average atmospheric density; The first determination module 205 is used to determine the current disturbance degree of the high-energy particle radiation environment according to the relative disturbance amount of the high-energy particle radiation environment and a preset high-energy particle radiation environment disturbance degree discrimination range; The second determination module 206 is used to determine the current atmospheric environment disturbance degree according to the maximum relative disturbance amount of the upper atmospheric density and a preset atmospheric environment disturbance degree discrimination range; The generation module 207 is used to generate a first risk response suggestion corresponding to the current high-energy particle radiation environment disturbance level, and to generate a second risk response suggestion corresponding to the current atmospheric environment disturbance level, and provide them to the maintenance personnel of the target spacecraft.

[0085] It should be noted that Figure 2 Each module / unit in the device shown has the function of implementing each step in the satellite orbit space environment disturbance response method provided in the above method embodiment, and can achieve its corresponding technical effect. For the sake of concise description, it will not be repeated here.

[0086] The satellite orbit space environment disturbance response device provided in the embodiments of the present application can, on the one hand, monitor the changes in high-energy particle flux and high-level atmospheric density in real time by acquiring the current position data and current space environment data of the orbit where the target satellite is located, thereby helping to timely discover potential environmental risks and avoid spacecraft failures or crashes due to sudden environmental changes.

[0087] On the other hand, the degree of space environment disturbance is quantified by calculating the relative disturbance of the high-energy particle radiation environment and the maximum relative disturbance of the upper atmosphere density. This quantification method can make the assessment of environmental disturbance more scientific and objective, avoiding the errors caused by subjective judgment. Moreover, quantifying the degree of disturbance can provide a clear reference standard for the design and operation guarantee of spacecraft. By quantifying the degree of disturbance, it is possible to more accurately judge whether the current environment poses a threat to the spacecraft, so as to take corresponding countermeasures. In addition, by setting the range of judgment of the degree of high-energy particle radiation environment disturbance and the range of judgment of the degree of atmospheric environment disturbance, a unified quantitative standard is provided for the judgment of satellite orbit space environment disturbance. This standardized judgment method fills the gap in existing standards. Through standardized assessment, different spacecraft can take consistent countermeasures when facing the same environmental disturbance, which improves the reliability and safety of the overall system.

[0088] On the other hand, corresponding risk response suggestions are generated according to the degree of disturbance of the high-energy particle radiation environment and the degree of disturbance of the atmospheric environment. These suggestions can provide specific operational guidance for different degrees of disturbance, such as adjusting the orbit, shutting down sensitive equipment, etc. Targeted risk response suggestions can help spacecraft maintenance personnel make decisions quickly and reduce losses caused by environmental disturbances. This automated suggestion generation mechanism improves the efficiency of responding to emergencies, reduces delays and errors in human judgment, and helps spacecraft to operate more stably in the complex and changing space environment, extend their service life, and reduce maintenance costs.

[0089] Based on the satellite orbit space environment disturbance response method provided in the above embodiment, the present application also provides a specific implementation method of the electronic device.

[0090] The electronic device in the embodiment of the present application may be a user terminal device, a server, other computing devices, or a cloud server. Figure 3 This is a hardware structure diagram of an electronic device of an embodiment of the present application. The electronic device may include a processor 301 and a memory 302 storing computer program instructions. When the processor 301 executes the computer program instructions, it implements the process or function of any of the above-mentioned embodiment methods.

[0091] Specifically, the processor 301 may include a central processing unit (CPU), or an application-specific integrated circuit (ASIC), or may be configured to implement one or more integrated circuits of the embodiment of the present application. The memory 302 may include a large-capacity memory for data or instructions. For example, the memory 302 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 tape, a universal serial bus (USB) drive, or other physical / tangible memory storage device. For another example, the memory 302 may include a removable or non-removable (or fixed) medium. For another example, the memory 302 may be inside or outside the integrated gateway disaster recovery device. The memory 302 may be a non-volatile solid-state memory. In other words, the memory 302 generally 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 method of the embodiment of the present application may be performed. The processor 301 implements the process or function of any one of the satellite orbit space environment disturbance response methods in the above-mentioned embodiments by reading and executing the computer program instructions stored in the memory 302 .

[0092] In one example, Figure 3 The electronic device shown may also include a communication interface 303 and a bus 310. Among them, the processor 301, the memory 302, and the communication interface 303 are connected through the bus 310 and complete the communication between each other. The communication interface 303 is mainly used to realize the communication between the modules, devices, units and / or devices in the embodiment of the present application. The bus 310 includes hardware, software or both, and can couple the components of the online data traffic billing device to each other. For example, the bus may include at least one of the following: an accelerated graphics port (AGP) or other graphics bus, an enhanced industrial standard architecture (EISA) bus, a front-end bus (FSB), a hypertransport (HT) interconnect, an industrial standard architecture (ISA) bus, an infinite bandwidth interconnect, a low pin count (LPC) bus, a memory bus, a micro channel architecture (MCA) bus, a peripheral component interconnect (PCI) bus, a PCI-Express (PCI-X) bus, a serial advanced technology attachment (SATA) bus, a video electronics standard association local (VLB) bus or other suitable buses. The bus 310 may include one or more buses. Although the embodiments of the present application describe or illustrate a specific bus, the embodiments of the present application may consider any suitable bus or interconnection method.

[0093] In combination with the methods in the above embodiments, an embodiment of the present application also provides a computer-readable storage medium, on which computer program instructions are stored. When the computer program instructions are executed by a processor, the process or function of any of the satellite orbit space environment disturbance response methods in the above embodiments is implemented.

[0094] In addition, an embodiment of the present application also provides a computer program product, which stores computer program instructions. When the computer program instructions are executed by a processor, they implement the process or function of any one of the satellite orbit space environment disturbance response methods in the above embodiments.

[0095] The above exemplarily describes the flowcharts and / or block diagrams of the methods, devices, systems and computer program products of the embodiments of the present application, and describes the relevant various aspects. It should be understood that each box or combination thereof in the flowchart and / or block diagram can be implemented by computer program instructions, or by dedicated hardware that performs a specified function or action, or by a combination of dedicated hardware and computer instructions. For example, these computer program instructions can be provided to a processor of a general-purpose computer, a special-purpose computer or other programmable data processing device to form a machine that enables these instructions executed by such a processor to enable the implementation of the functions / actions specified in each box or combination thereof in the flowchart and / or block diagram. Such a processor can be a general-purpose processor, a special-purpose processor, a special application processor or a field programmable logic circuit.

[0096] The functional blocks shown in the structural block diagram of the embodiment 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 function card, etc.; when implemented in software, it is a program or code segment used to perform the required task. The program or code segment can be stored in a memory, or transmitted on a transmission medium or a communication link via a data signal carried in a carrier. The code segment can be downloaded via a computer network such as the Internet, an intranet, etc.

[0097] 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 is only a specific implementation mode of the present application. Those skilled in the art can clearly understand that for the convenience and brevity of description, the specific working process of the described system, device, module or unit can refer to the corresponding process in the method embodiment without further description. It should be understood that the scope of protection of the present application is not limited to this. Any technician familiar with the technical field can think of various equivalent modifications or substitutions within the technical scope disclosed in the present application, and these modifications or substitutions should be included in the scope of protection of the present application.

Claims

1. A method for coping with satellite orbit space environment disturbance, characterized in that: include: Acquiring current position data and current space environment data of a target orbit where the target spacecraft is located, wherein the current space environment data includes a first high-energy particle integrated flux and a first high-level atmospheric daily average atmospheric density at a high-energy particle flux target position; According to the current position data of the target orbit, query the second high-energy particle integrated flux at the high-energy particle flux target position when the target orbit environment is calm and the second high-level atmospheric daily average atmospheric density when the target orbit environment is calm; Calculate the relative disturbance of the high-energy particle radiation environment of the target orbit according to the first high-energy particle integrated flux and the second high-energy particle integrated flux; Calculate the maximum relative disturbance of the upper atmosphere density of the target orbit based on the daily average atmospheric density of the first upper atmosphere and the daily average atmospheric density of the second upper atmosphere; Determine the current disturbance degree of the high-energy particle radiation environment according to the relative disturbance amount of the high-energy particle radiation environment and the pre-set high-energy particle radiation environment disturbance degree discrimination range; Determine the current atmospheric environment disturbance degree according to the maximum relative disturbance amount of the upper atmospheric density and the preset atmospheric environment disturbance degree discrimination range; A first risk response suggestion corresponding to the current high-energy particle radiation environment disturbance level is generated, and a second risk response suggestion corresponding to the current atmospheric environment disturbance level is generated, and provided to maintenance personnel of the target spacecraft.

2. The method according to claim 1, characterized in that: The high-energy particles include at least one of protons and electrons.

3. The method according to claim 1, characterized in that In the case where the high-energy particles include protons and electrons, the first high-energy particle integrated flux includes a first proton integrated flux at a proton flux target position and a first electron integrated flux at an electron flux target position, and the second high-energy particle integrated flux includes a second proton integrated flux at a proton flux target position when the target orbit environment is calm and a second electron integrated flux at an electron flux target position when the target orbit environment is calm; According to the first high-energy particle integrated flux and the second high-energy particle integrated flux, the relative disturbance of the high-energy particle radiation environment of the target orbit is calculated, including: Calculating the ratio of the first proton integrated flux to the second proton integrated flux to obtain the relative disturbance of the proton radiation environment of the target orbit; Calculating the ratio of the first electron integrated flux to the second electron integrated flux to obtain the relative disturbance of the electron radiation environment of the target orbit; The current high-energy particle radiation environment disturbance degree includes the current proton radiation environment disturbance degree and the current electron radiation environment disturbance degree, and the first risk response suggestion includes the risk response suggestion corresponding to the current proton radiation environment disturbance degree and the risk response suggestion corresponding to the current electron radiation environment disturbance degree.

4. The method according to claim 1, characterized in that: According to the relative disturbance amount of the high-energy particle radiation environment and the preset high-energy particle radiation environment disturbance degree discrimination range, the current high-energy particle radiation environment disturbance degree is determined, including: If the relative disturbance of the high-energy particle radiation environment is less than 10, the current disturbance level of the high-energy particle radiation environment is determined to be calm; If the relative disturbance of the high-energy particle radiation environment is greater than or equal to 10 and less than 100, it is determined that the current disturbance degree of the high-energy particle radiation environment is slightly disturbed; If the relative disturbance of the high-energy particle radiation environment is greater than or equal to 100 and less than 1000, it is determined that the current disturbance degree of the high-energy particle radiation environment is medium disturbance; If the relative disturbance of the high-energy particle radiation environment is greater than or equal to 1000, the current disturbance level of the high-energy particle radiation environment is determined to be severe disturbance; Among them, the severity of multiple disturbance levels is from high to low: severe disturbance > moderate disturbance > slight disturbance > calm.

5. The method according to claim 4, characterized in that Generate the first risk response recommendations corresponding to the current degree of high-energy particle radiation environment disturbance, including: If the current high-energy particle radiation environment disturbance level is calm, the corresponding first risk response suggestion is to remind that the current high-energy particle radiation environment is safe and no action is taken; If the current high-energy particle radiation environment disturbance level is slight, the corresponding first risk response recommendation is to strengthen monitoring and pay attention to the potential risk of single-particle effects and / or deep charge and discharge in spacecraft; If the current high-energy particle radiation environment disturbance level is medium disturbance, the corresponding first risk response suggestion is to monitor the risk changes. When the current high-energy particle radiation environment disturbance level reaches severe disturbance, the single machine containing sensitive devices and / or the single machine affected by discharge enters a safe state; If the current high-energy particle radiation environment disturbance level is severe, the corresponding first risk response recommendation is to recommend that the single machine containing sensitive devices and / or the single machine affected by discharge enter a safe state.

6. The method according to claim 1, characterized in that According to the daily average atmospheric density of the first upper atmosphere and the daily average atmospheric density of the second upper atmosphere, the maximum relative disturbance of the upper atmosphere density of the target orbit is calculated, including: Calculate the difference between the daily average atmospheric density of the first upper atmosphere and the daily average atmospheric density of the second upper atmosphere; The percentage of the ratio of the difference to the second upper atmosphere daily average atmospheric density is calculated to obtain the maximum relative disturbance of the upper atmosphere density of the target orbit.

7. The method according to claim 1, characterized in that According to the maximum relative disturbance of the upper atmospheric density and the preset atmospheric environment disturbance degree discrimination range, the current atmospheric environment disturbance degree is determined, including: If the maximum relative disturbance of the upper atmospheric density is less than 10%, the current atmospheric environment disturbance level is determined to be calm; If the maximum relative disturbance of the upper atmospheric density is greater than or equal to 10% and less than 40%, the current atmospheric environment disturbance level is determined to be slight disturbance; If the maximum relative disturbance of the upper atmospheric density is greater than or equal to 40% and less than 90%, the current atmospheric environment disturbance level is determined to be moderate; If the maximum relative disturbance of the upper atmospheric density is greater than or equal to 90%, the current atmospheric environment disturbance level is determined to be severe disturbance; Among them, the severity of multiple disturbance levels is from high to low: severe disturbance > moderate disturbance > slight disturbance > calm.

8. The method according to claim 1, characterized in that Generate the second risk response recommendations corresponding to the current level of atmospheric environmental disturbance, including: If the current atmospheric disturbance level is calm, the corresponding second response suggestion is to remind that the current atmospheric environment is safe and no action is taken; If the current atmospheric disturbance is slight, the corresponding second response suggestion is to strengthen monitoring and increase the frequency of orbit forecasts; If the current atmospheric environment disturbance level is medium, the corresponding second response suggestion is to recommend orbit raising. If the current level of atmospheric disturbance is severe, the corresponding second response suggestion is to perform orbit raising action and shut down a preset number of payloads.

9. An electronic device, characterized in that: The electronic device comprises: a processor and a memory storing computer program instructions; when the electronic device executes the computer program instructions, the method for coping with satellite orbit space environment disturbances as described in any one of claims 1-8 is implemented.

10. A computer program product, characterized in that It includes computer program instructions, which, when executed by a processor, implement the satellite orbit space environment disturbance response method as described in any one of claims 1-8.

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