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

Abstract

The application discloses a satellite orbit space environment disturbance coping method, equipment and computer program product. The method comprises the following steps: acquiring current position data and current space environment data of a target orbit, wherein the current space environment data comprises a first high-energy particle integrated flux at a target position of a high-energy particle flux and a first high-altitude atmospheric daily average atmospheric density; querying a second high-energy particle integrated flux at the target position of the high-energy particle flux and a second high-altitude atmospheric daily average atmospheric density when the target orbit environment is calm according to the current position data; calculating a high-energy particle radiation environment relative disturbance amount and a high-altitude atmospheric density maximum relative disturbance amount of the target orbit; determining a current high-energy particle radiation environment disturbance degree and a current atmospheric environment disturbance degree in combination with a disturbance degree discrimination range; and generating a risk coping suggestion. The application can accurately understand the disturbance situation of a spacecraft operating environment and improve the safety of the spacecraft in-orbit operation.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aerospace technology, and in particular to a satellite orbit space environment disturbance response method and device, an electronic device, a computer readable storage medium and a computer program product. BACKGROUND

[0002] The space environment is referred to as the fourth environment of human activities in addition to land, sea and atmosphere, including solar atmosphere, interplanetary and Earth space (further divided into magnetosphere, ionosphere and upper atmosphere). Solar activity is the main disturbance source of the space environment, which can cause typical space environment events such as coronal mass ejection, solar flare, solar proton event, magnetic storm and high-energy electron storm. Different degrees of solar eruption activity can cause different degrees of disturbance of the Earth's space environment, and severe radiation, atmospheric and other environments can cause the risk of failure or even crash of a spacecraft running in the environment. Real-time understanding of the disturbance of the spacecraft operating environment and giving corresponding response suggestions are crucial for the on-orbit operation of the 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 blank in the aspect of satellite orbit space environment disturbance degree discrimination. With the continuous deepening of human exploration and utilization of space, it is crucial to accurately discriminate the satellite orbit space environment disturbance degree and provide corresponding risk response suggestions for the design, operation guarantee and space environment research of the spacecraft. SUMMARY

[0004] Therefore, the embodiments of the present application provide a satellite orbit space environment disturbance response method and device, an electronic device, a computer readable storage medium and a computer program product to solve the above at least one technical problem.

[0005] In a first aspect, the embodiments of the present application provide a satellite orbit space environment disturbance response method, comprising: acquiring current position data and current space environment data of a target orbit where a target spacecraft is located, the current space environment data comprising a first high-energy particle integral flux at a target position of high-energy particle flux and a first high-altitude atmospheric daily average atmospheric density;

[0006] According to the current position data of the target orbit, the second high-energy particle integral flux at the target position of high-energy particle flux when the target orbit environment is calm and the second high-altitude atmospheric daily average atmospheric density when the target orbit environment is calm are queried;

[0007] According to the first high-energy particle integral flux and the second high-energy particle integral flux, the relative disturbance amount of the high-energy particle radiation environment of the target orbit is calculated;

[0008] According to the first high-altitude atmospheric daily average atmospheric density and the second high-altitude atmospheric daily average atmospheric density, a maximum relative disturbance amount of high-altitude atmospheric density of the target orbit is calculated;

[0009] According to the high-energy particle radiation environment relative disturbance amount and a pre-set high-energy particle radiation environment disturbance degree discrimination range, a current high-energy particle radiation environment disturbance degree is determined.

[0010] According to the maximum relative disturbance amount of high-altitude atmospheric density and a pre-set atmospheric environment disturbance degree discrimination range, a current atmospheric environment disturbance degree is determined.

[0011] A first risk response suggestion corresponding to the current high-energy particle radiation environment disturbance degree is generated, and a second risk response suggestion corresponding to the current atmospheric environment disturbance degree is generated, and provided to a maintenance personnel of the target spacecraft.

[0012] According to some embodiments of the present application, optionally, the high-energy particles include at least one of protons and electrons.

[0013] 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 integral flux includes a first proton integral flux at a proton flux target position and a first electron integral flux at an electron flux target position, and the second high-energy particle integral flux includes a second proton integral flux at the proton flux target position when the target orbit environment is calm and a second electron integral flux at the electron flux target position when the target orbit environment is calm.

[0014] According to the first high-energy particle integral flux and the second high-energy particle integral flux, a high-energy particle radiation environment relative disturbance amount of the target orbit is calculated, including: calculating a ratio of the first proton integral flux and the second proton integral flux to obtain a proton radiation environment relative disturbance amount of the target orbit; and calculating a ratio of the first electron integral flux and the second electron integral flux to obtain an electron radiation environment relative disturbance amount of the target orbit; the current high-energy particle radiation environment disturbance degree includes a current proton radiation environment disturbance degree and a current electron radiation environment disturbance degree, and the first risk response suggestion includes 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.

[0015] According to some embodiments of the present application, optionally, according to the high-energy particle radiation environment relative disturbance amount and the pre-set high-energy particle radiation environment disturbance degree discrimination range, the current high-energy particle radiation environment disturbance degree is determined, including:

[0016] If the high-energy particle radiation environment relative disturbance amount is less than 10, it is determined that the current high-energy particle radiation environment disturbance degree is calm.

[0017] 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 high-energy particle radiation environment disturbance degree is slight disturbance.

[0018] 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 high-energy particle radiation environment disturbance degree is moderate disturbance.

[0019] If the relative disturbance of the high-energy particle radiation environment is greater than or equal to 1000, it is determined that the current high-energy particle radiation environment disturbance degree is severe disturbance.

[0020] Among them, the severity of the plurality of disturbance degrees is in turn from high to low: severe disturbance > moderate disturbance > slight disturbance > calm.

[0021] According to some embodiments of the present application, optionally, a first risk response suggestion corresponding to the current high-energy particle radiation environment disturbance degree is generated, including:

[0022] If the current high-energy particle radiation environment disturbance degree is calm, the corresponding first risk response suggestion is to prompt that the current high-energy particle radiation environment is safe and no treatment is needed.

[0023] If the current high-energy particle radiation environment disturbance degree is slight disturbance, the corresponding first risk response suggestion is to suggest strengthening monitoring and paying attention to the potential risks of single event effect and / or deep charging and discharging of the spacecraft.

[0024] If the current high-energy particle radiation environment disturbance degree is moderate disturbance, the corresponding first risk response suggestion is to suggest monitoring the risk change and entering the safe state of the single machine containing sensitive devices and / or the single machine affected by discharge when the current high-energy particle radiation environment disturbance degree reaches severe disturbance.

[0025] If the current high-energy particle radiation environment disturbance degree is severe disturbance, the corresponding first risk response suggestion is to suggest entering the safe state of the single machine containing sensitive devices and / or the single machine affected by discharge.

[0026] According to some embodiments of the present application, optionally, according to the first high-altitude atmospheric daily average atmospheric density and the second high-altitude atmospheric daily average atmospheric density, the maximum relative disturbance of the high-altitude atmospheric density of the target orbit is calculated, including:

[0027] The difference between the first high-altitude atmospheric daily average atmospheric density and the second high-altitude atmospheric daily average atmospheric density is calculated.

[0028] The percentage of the ratio of the difference to the second high-altitude atmospheric daily average atmospheric density is calculated to obtain the maximum relative disturbance of the high-altitude atmospheric density of the target orbit.

[0029] According to some embodiments of the present application, optionally, the current atmospheric environment disturbance degree is determined according to the maximum relative disturbance of high-altitude atmospheric density and a preset atmospheric environment disturbance degree judgment range, and the method comprises the following steps:

[0030] If the maximum relative disturbance of high-altitude atmospheric density is less than 10%, the current atmospheric environment disturbance degree is determined to be calm;

[0031] If the maximum relative disturbance of high-altitude atmospheric density is greater than or equal to 10% and less than 40%, the current atmospheric environment disturbance degree is determined to be slight disturbance;

[0032] If the maximum relative disturbance of high-altitude atmospheric density is greater than or equal to 40% and less than 90%, the current atmospheric environment disturbance degree is determined to be moderate disturbance;

[0033] If the maximum relative disturbance of high-altitude atmospheric density is greater than or equal to 90%, the current atmospheric environment disturbance degree is determined to be severe disturbance.

[0034] Among them, the severity of the plurality of disturbance degrees is in descending order: severe disturbance > moderate disturbance > slight disturbance > calm.

[0035] According to some embodiments of the present application, optionally, a second risk response suggestion corresponding to the current atmospheric environment disturbance degree is generated, and the method comprises the following steps:

[0036] If the current atmospheric environment disturbance degree is calm, the corresponding second response suggestion is to prompt that the current atmospheric environment is safe and no treatment is needed;

[0037] If the current atmospheric environment disturbance degree is slight disturbance, the corresponding second response suggestion is to suggest strengthening monitoring and increasing the frequency of orbit prediction;

[0038] If the current atmospheric environment disturbance degree is moderate disturbance, the corresponding second response suggestion is to suggest performing an orbit-raising action;

[0039] If the current atmospheric environment disturbance degree is severe disturbance, the corresponding second response suggestion is to suggest performing an orbit-raising action and closing a preset number of loads.

[0040] In a second aspect, the embodiments of the present application provide a satellite orbit space environment disturbance response device, which comprises:

[0041] An acquisition module is configured to acquire current position data of a target orbit where a target spacecraft is located and current space environment data, and the current space environment data comprises a first high-energy particle integrated flux at a target position of high-energy particle flux and a first high-altitude atmospheric daily average atmospheric density;

[0042] The query module is configured to query, according to the current position data of the target orbit, the second high-energy particle integrated flux at the target position of the high-energy particle flux when the target orbit environment is calm and the second high-altitude atmospheric daily average atmospheric density when the target orbit environment is calm.

[0043] The first calculation module is configured to calculate, according to the first high-energy particle integrated flux and the second high-energy particle integrated flux, a relative disturbance amount of the high-energy particle radiation environment of the target orbit.

[0044] The second calculation module is configured to calculate, according to the first high-altitude atmospheric daily average atmospheric density and the second high-altitude atmospheric daily average atmospheric density, a maximum relative disturbance amount of the high-altitude atmospheric density of the target orbit.

[0045] The first determination module is configured to determine, according to the relative disturbance amount of the high-energy particle radiation environment and a pre-set disturbance degree discrimination range of the high-energy particle radiation environment, a current disturbance degree of the high-energy particle radiation environment.

[0046] The second determination module is configured to determine, according to the maximum relative disturbance amount of the high-altitude atmospheric density and a pre-set disturbance degree discrimination range of the atmospheric environment, a current disturbance degree of the atmospheric environment.

[0047] The generation module is configured to generate a first risk response suggestion corresponding to the current disturbance degree of the high-energy particle radiation environment and a second risk response suggestion corresponding to the current disturbance degree of the atmospheric environment, and provide the first risk response suggestion and the second risk response suggestion to a maintenance personnel of the target spacecraft.

[0048] In a third aspect, an electronic device is provided, which includes a processor and a memory storing computer program instructions; the processor executes the computer program instructions to implement the steps of the method described above.

[0049] In a fourth aspect, a computer readable storage medium is provided, which stores computer program instructions; the computer program instructions are executed by a processor to implement the steps of the satellite orbit space environment disturbance response method described above.

[0050] In a fifth aspect, a computer program product is provided, which includes computer program instructions; the computer program instructions are executed by a processor to implement the steps of the satellite orbit space environment disturbance response method described above.

[0051] The satellite orbit space environment disturbance coping method, device, electronic equipment, computer readable storage medium and computer program product provided by the embodiments of the present application can accurately understand the disturbance situation of the spacecraft operating environment, provide corresponding risk response suggestions, significantly improve the safety of the spacecraft in-orbit operation, fill the blank of the satellite orbit space environment disturbance discrimination standard, and provide data support for space environment research. 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 DRAWINGS

[0052] 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.

[0053] Figure 1 A flowchart of the satellite orbit space environment disturbance coping method provided by the embodiments of the present application.

[0054] Figure 2 A structural block diagram of the satellite orbit space environment disturbance coping device provided by the embodiments of the present application.

[0055] Figure 3 A hardware structure schematic diagram of the electronic equipment of the embodiments of the present application. DETAILED DESCRIPTION

[0056] The features and exemplary embodiments of various aspects of the present application will be described in detail below, in order to make the purposes, technical solutions and advantages of the present application more clear and apparent, the present application will be further described in detail below. It should be understood that the specific embodiments described herein are intended to explain the present application, not to limit the present application. The present application can be implemented without some of these specific details. The following description of the embodiments is merely to provide a better understanding of the present application by showing examples of the present application.

[0057] It should be noted that the relative terms, such as first and second, and the like, are used herein only to distinguish one entity or operation from another, and do not necessarily require or imply any actual such relationship or order between such entities or operations. Moreover, the terms "comprises", "comprising", or any other variations thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but can include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by an "includes" statement does not exclude the existence of additional elements of the same nature as those included in the process, method, article, or apparatus.

[0058] It should be understood that the term "and / or" used herein only describes an association relationship of associated objects, which means that there can be three relationships, for example, A and / or B can represent three cases of A alone, A and B together, and B alone. In addition, the character " / " herein generally represents an "or" relationship between the front and rear associated objects.

[0059] Various modifications and changes can be made to the present application in light of the foregoing without departing from the spirit or scope of the application. Accordingly, the present application is intended to embrace all modifications and alterations to this application that fall within the scope of the corresponding claims (technical solutions claimed to be protected) and their equivalents. It should be noted that the embodiments provided by the present application can be combined with each other as long as they do not conflict.

[0060] 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:

[0061] The space environment is referred to as the fourth environment of human activities in addition to land, sea and atmosphere, including solar atmosphere, interplanetary and Earth space (further divided into magnetosphere, ionosphere and upper atmosphere). Solar activity is the main disturbance source of space environment, which may cause typical space environment events such as coronal mass ejection, solar flare, solar proton event, magnetic storm and high-energy electron storm. Different degrees of solar burst activity may cause different degrees of disturbance of the Earth's space environment, and severe radiation, atmospheric environment and the like may cause the risk of failure and even crash of the spacecraft running therebetween. Real-time understanding of the disturbance of the spacecraft running environment and giving corresponding response suggestions are crucial for the on-orbit operation guarantee of the spacecraft.

[0062] At present, a series of standards have been formulated in the field of space environment at home and abroad, but there is still a blank in the aspect of judging the disturbance degree of satellite orbit space environment. With the continuous deepening of human exploration and utilization of space, it is very important to accurately judge the disturbance degree of satellite orbit space environment and provide corresponding risk response suggestions for the design, operation guarantee and space environment research of spacecraft.

[0063] In order to reduce the risk of satellite and other spacecraft caused by satellite orbit space environment disturbance, the embodiments of the present application provide a satellite orbit space environment disturbance response method, device, electronic equipment, computer readable storage medium and computer program product. By quantitatively judging the disturbance degree of satellite orbit space environment, it can be more accurately judged whether the current satellite orbit space environment constitutes a threat to the satellite and other spacecraft, so as to take corresponding response measures to guarantee the safe operation of the spacecraft.

[0064] Firstly, the satellite orbit space environment disturbance response method provided by the embodiments of the present application is introduced.

[0065] Figure 1 A flowchart of the satellite orbit space environment disturbance response method provided by the embodiments of the present application is shown in FIG. 1. Figure 1 As shown in FIG. 1, the satellite orbit space environment disturbance response method provided by the embodiments of the present application can include the following steps S101 to S107.

[0066] S101: Obtain the current position data and current space environment data of the target orbit where the target spacecraft is located, and the current space environment data includes the first high-energy particle integrated flux of the target position of high-energy particle flux and the first high-altitude average atmospheric density of the day.

[0067] For example, the target spacecraft includes but is not limited to satellite or other spacecraft. In S101, the data can be collected in real time by the sensors and detectors on the target spacecraft, and the data can be transmitted to the data processing equipment of the ground station through the telemetry system.

[0068] For example, the current position data of the target orbit where the target spacecraft is located can be obtained by the navigation device carried by the target spacecraft or the ground measurement and control system, and the accurate position information of the target spacecraft in the target orbit can be obtained, including the parameters such as orbit height, inclination, latitude, etc.

[0069] For another example, the high-energy particle detector carried by the target spacecraft can be used to measure the target position of high-energy particle flux on the target orbit, and the integrated flux (i.e. the total number of high-energy particles passing through a unit area per unit time) of the position can be calculated to obtain the first high-energy particle integrated flux.

[0070] For another example, the atmospheric density on the target orbit can be measured by an atmospheric density detection instrument carried by the target spacecraft, and a first high-altitude atmospheric daily average atmospheric density can be obtained by calculating a daily average of the atmospheric density.

[0071] S102: According to the current position data of the target orbit, query a second high-energy particle integrated flux of the target position of the high-energy particle flux when the target orbit environment is calm and a second high-altitude atmospheric daily average atmospheric density when the target orbit environment is calm.

[0072] In some embodiments, the second high-energy particle integrated flux can be obtained by querying the high-energy particle integrated flux data of the target orbit when the environment is calm (e.g., during a solar activity low year or without a significant solar burst event) from a historical database or a space environment model, for example, according to the orbital altitude and latitude of the target orbit. Similarly, the second high-altitude atmospheric daily average atmospheric density can be obtained by querying the high-altitude atmospheric daily average density data of the target orbit when the environment is calm from a historical database or a Mass Spectrometer and Incoherent Scatter Radar Extended Model (MSISE) model, for example, according to the orbital altitude and latitude of the target orbit.

[0073] Taking the MSISE model as an example, the input parameters of the MSISE model generally include solar radiation flux (e.g., F10.7 index) and geomagnetic activity index (e.g., Kp or Ap index) to reflect the influence of solar activity and geomagnetic disturbance on the high-altitude atmosphere.

[0074] 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 environment 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, by the MSISE model, the second high-altitude atmospheric daily average atmospheric density can be obtained by querying the high-altitude atmospheric daily average density data of the target orbit when the F10.7 value is below 75 and the Ap index is below 5.

[0075] S103: Calculate 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.

[0076] In S103, the relative disturbance amount 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 amount of the high-energy particle radiation environment reflects the disturbance degree of the current high-energy particle radiation environment relative to the environment when it is calm.

[0077] S104: Calculate the maximum relative disturbance of high-altitude atmospheric density of the target orbit according to the first high-altitude atmospheric daily average atmospheric density and the second high-altitude atmospheric daily average atmospheric density.

[0078] In S104, the maximum relative disturbance of high-altitude atmospheric density of the target orbit can be calculated according to the first high-altitude atmospheric daily average atmospheric density and the second high-altitude atmospheric daily average atmospheric density. The maximum relative disturbance of high-altitude atmospheric density reflects the disturbance degree of the current high-altitude atmospheric density relative to the environment.

[0079] By calculating the relative disturbance of high-energy particle radiation environment and the maximum relative disturbance of high-altitude atmospheric density, the disturbance degree of space environment is quantified. This quantification method can make the evaluation of environmental disturbance more scientific and objective, avoiding the error caused by subjective judgment. Moreover, quantifying the disturbance degree can provide a clear reference standard for the design and operation of spacecraft. By quantifying the disturbance degree, it can be more accurately judged whether the current environment poses a threat to the spacecraft, so that appropriate measures can be taken.

[0080] S105: Determine the current high-energy particle radiation environment disturbance degree according to the relative disturbance of high-energy particle radiation environment and the pre-set high-energy particle radiation environment disturbance degree discrimination range.

[0081] Among them, according to the severity of 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 relative disturbance of high-energy particle radiation environment 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.

[0082] S106: Determine the current atmospheric environment disturbance degree according to the maximum relative disturbance of high-altitude atmospheric density and the pre-set atmospheric environment disturbance degree discrimination range.

[0083] Similarly, according to the severity of atmospheric environment disturbance, the atmospheric environment disturbance degree discrimination range can be divided into multiple levels. In S105, the calculated relative disturbance of atmospheric environment can be compared with the pre-set atmospheric environment disturbance degree discrimination range to determine the current atmospheric environment disturbance degree.

[0084] S107: Generate the first risk response suggestion corresponding to the current high-energy particle radiation environment disturbance degree, and generate the second risk response suggestion corresponding to the current atmospheric environment disturbance degree, and provide it to the maintenance personnel of the target spacecraft.

[0085] After determining the current high-energy particle radiation environment disturbance degree and the current atmospheric environment disturbance degree, a corresponding suggestion can be automatically matched from a preset coping strategy library according to the disturbance degree level, including a first risk coping suggestion corresponding to the current high-energy particle radiation environment disturbance degree and a second risk coping suggestion corresponding to the current atmospheric environment disturbance degree. The first risk coping suggestion and the second risk coping 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 coping suggestion to perform a corresponding coping strategy, 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.

[0086] The satellite orbit space environment disturbance coping method provided by the embodiments of the present application can monitor the changes of high-energy particle flux and high-altitude atmospheric density in real time by obtaining the current position data and current space environment data of the target satellite, which helps to discover potential environmental risks in time and avoid spacecraft failure or crash caused by environmental mutation.

[0087] On the other hand, the space environment disturbance degree is quantified by calculating the relative disturbance amount of the high-energy particle radiation environment and the maximum relative disturbance amount of the high-altitude atmospheric density. This quantification method can make the evaluation of environmental disturbance more scientific and objective, avoiding errors caused by subjective judgment. Moreover, the quantification of disturbance degree provides a clear reference standard for the design and operation of spacecraft. By quantifying the disturbance degree, it can be more accurately judged whether the current environment poses a threat to the spacecraft, so that appropriate measures can be taken. In addition, by setting the high-energy particle radiation environment disturbance degree discrimination range and the atmospheric environment disturbance degree discrimination range, a unified quantification standard is provided for the discrimination of satellite orbit space environment disturbance. This standardized discrimination method fills the gap in existing standards. Through standardized evaluation, different spacecrafts can take consistent measures when facing the same environmental disturbance, improving the reliability and safety of the overall system.

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

[0089] According to some embodiments of the present application, the high-energy particles can include at least one of protons and electrons.

[0090] For example, in some specific embodiments, the high-energy particles can include both protons and electrons. Accordingly, the first high-energy particle integrated flux can include a first proton integrated flux at the proton flux target location and a first electron integrated flux at the electron flux target location. The second high-energy particle integrated flux can include a second proton integrated flux at the proton flux target location when the target orbit environment is calm and a second electron integrated flux at the electron flux target location when the target orbit environment is calm. The first proton integrated flux and the first electron integrated flux can be obtained in the manner described above for the first high-energy particle integrated flux, and the second proton integrated flux and the second electron integrated flux can be obtained in the manner described above for the second high-energy particle integrated flux, which will not be described again here.

[0091] Solar activity bursts or geomagnetic disturbances and other phenomena can cause the high-energy particle flux of the Earth's orbit to increase sharply. Due to the protection of the geomagnetic field, the disturbance degree of different orbit radiation environments is different. In some embodiments, based on the high-energy particle data, the proton radiation environment can use the ≥10 MeV proton integrated flux, and the electron radiation environment can use the ≥2 MeV electron integrated flux to distinguish the disturbance degree of the radiation environment.

[0092] 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 can include the following steps one and two.

[0093] Step one: calculating the ratio of the first proton integrated flux and the second proton integrated flux to obtain the relative disturbance amount of the proton radiation environment of the target orbit.

[0094] The satellite orbit space environment disturbance degree discrimination reflects the change degree of the satellite orbit space environment relative to the background environment, and can indirectly understand the severity of the possible influence of the satellite orbit space environment on the spacecraft.

[0095] In some examples, for example, for high orbits, medium orbits, and high-latitude regions (about latitude 50° or more) of low orbits, the relative disturbance amount of the proton radiation environment of the target orbit can be calculated according to the following expression (1):

[0096] (1)

[0097] Wherein, represents the relative disturbance amount of the proton radiation environment of the target orbit, represents the first proton integrated flux, represents the second proton integrated flux, unit: .

[0098] The above expression (1) can be applied to the proton radiation environment disturbance discrimination of high orbit, medium orbit and low orbit high latitude region (about latitude 50° or above), for example. The target position of high energy particle flux can be understood as the peak position of high energy particle flux or a position near the peak, for example, for protons, the target position of proton flux of high orbit and medium orbit can be set as the equatorial position, and the target position of proton flux of low orbit (including low orbit high latitude region) can be set as the ±60° latitude position. The first proton integral flux and the second proton integral flux of high orbit and medium orbit can be set as the equatorial position using ≥10 MeV proton integral flux, and the first proton integral flux and the second proton integral flux of low orbit can be set as the ±60° latitude position using ≥10 MeV proton integral flux. For example, when the space environment is calm, the ≥10 MeV proton integral flux of equatorial position of high orbit and medium orbit and the ≥10 MeV proton integral flux of low orbit high latitude region are usually lower than 3 .

[0099] Step two: calculate the ratio of the first electron integral flux to the second electron integral flux to obtain the relative disturbance of the electron radiation environment of the target orbit.

[0100] In some examples, the relative disturbance of the electron radiation environment of the target orbit can be calculated according to the following expression (2), for example:

[0101] (2)

[0102] wherein, represents the relative disturbance of the electron radiation environment of the target orbit, represents the first electron integral flux, represents the second electron integral flux, and the unit is: .

[0103] For example, similar to protons, for electrons, the target position of electron flux of high orbit and medium orbit can be set as the equatorial position, and the target position of electron flux of low orbit can be set as the ±60° latitude position. The first electron integral flux and the second electron integral flux of high orbit and medium orbit can be set as the equatorial position using ≥2 MeV electron integral flux, and the first electron integral flux and the second electron integral flux of low orbit can be set as the ±60° latitude position using ≥2 MeV electron integral flux. For example, when the space environment is calm, the ≥2 MeV electron integral flux of equatorial position of 35786 km orbit height is 300 In the following, the 22000km orbital altitude equatorial position ≥2MeV electron integral flux is 10 4 In the following.

[0104] Correspondingly, the current high-energy particle radiation environment disturbance degree can include a current proton radiation environment disturbance degree and a current electron radiation environment disturbance degree, and the first risk response suggestion can 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.

[0105] Protons, especially high-energy protons ≥10MeV, have high penetration ability and can cause serious damage to electronic devices, solar cells, and astronaut health of the spacecraft. According to the degree of proton radiation disturbance, it can be suggested to close or shield sensitive devices to reduce the damage of proton radiation to electronic components. In addition, by taking protective measures in time, the cumulative damage of proton radiation to solar cells and electronic devices can be reduced, and the service life of the spacecraft can be prolonged.

[0106] High-energy electrons can cause charging and discharging of spacecraft surface materials, triggering electrostatic discharge (ESD) events. According to the disturbance degree, it can be suggested to close or shield vulnerable devices, or enable redundant systems. When the electron radiation disturbance is high, it can be suggested to adjust the spacecraft orbit to avoid high electron flux areas (such as the South Atlantic Anomaly).

[0107] In this way, by respectively providing risk response suggestions for the degree of proton radiation environment disturbance and the degree of electron radiation environment disturbance, the radiation threat in the space environment can be more accurately and efficiently responded to, thereby ensuring the safe operation of the spacecraft and the successful execution of the mission.

[0108] According to some embodiments of the present application, optionally, by combining statistical analysis of multiple space environment models and monitoring data of multiple satellites, the satellite orbit space environment disturbance degree is divided into four levels: calm, slight disturbance, moderate disturbance, and severe disturbance, and the disturbance degree discrimination range of each level is set. Among them, the severity of multiple disturbance degrees from high to low is: severe disturbance > moderate disturbance > slight disturbance > calm.

[0109] Specifically, S105: determining the current high-energy particle radiation environment disturbance degree according to the high-energy particle radiation environment relative disturbance amount and the pre-set high-energy particle radiation environment disturbance degree discrimination range, including:

[0110] If the high-energy particle radiation environment relative disturbance amount is less than 10, the current high-energy particle radiation environment disturbance degree is determined to be calm;

[0111] If the relative disturbance quantity of the high-energy particle radiation environment is greater than or equal to 10 and less than 100, it is determined that the current high-energy particle radiation environment disturbance degree is slight disturbance.

[0112] If the relative disturbance quantity of the high-energy particle radiation environment is greater than or equal to 100 and less than 1000, it is determined that the current high-energy particle radiation environment disturbance degree is moderate disturbance.

[0113] If the relative disturbance quantity of the high-energy particle radiation environment is greater than or equal to 1000, it is determined that the current high-energy particle radiation environment disturbance degree is severe disturbance.

[0114] For example, for protons, if the relative disturbance quantity of the proton radiation environment is less than 10, it is determined that the current proton radiation environment disturbance degree is calm; if the relative disturbance quantity of the proton radiation environment is greater than or equal to 10 and less than 100, it is determined that the current proton radiation environment disturbance degree is slight disturbance; if the relative disturbance quantity of the proton radiation environment is greater than or equal to 100 and less than 1000, it is determined that the current proton radiation environment disturbance degree is moderate disturbance; and if the relative disturbance quantity of the proton radiation environment is greater than or equal to 1000, it is determined that the current proton radiation environment disturbance degree is severe disturbance.

[0115] For example, for electrons, if the relative disturbance quantity of the electron radiation environment is less than 10, it is determined that the current electron radiation environment disturbance degree is calm; if the relative disturbance quantity of the electron radiation environment is greater than or equal to 10 and less than 100, it is determined that the current electron radiation environment disturbance degree is slight disturbance; if the relative disturbance quantity of the electron radiation environment is greater than or equal to 100 and less than 1000, it is determined that the current electron radiation environment disturbance degree is moderate disturbance; and if the relative disturbance quantity of the electron radiation environment is greater than or equal to 1000, it is determined that the current electron radiation environment disturbance degree is severe disturbance.

[0116] According to some embodiments of the present application, S107: generating a first risk response suggestion corresponding to the current high-energy particle radiation environment disturbance degree, comprising:

[0117] If the current high-energy particle radiation environment disturbance degree is calm, the corresponding first risk response suggestion is to prompt that the current high-energy particle radiation environment is safe and no processing is required.

[0118] If the current high-energy particle radiation environment disturbance degree is slight disturbance, the corresponding first risk response suggestion is to suggest to strengthen monitoring and pay attention to potential risks of single event effects and / or deep charging and discharging of the spacecraft.

[0119] If the current high-energy particle radiation environment disturbance degree is moderate disturbance, the corresponding first risk response suggestion is to suggest to monitor the risk change and to enter a safe state for a single machine containing sensitive devices and / or a single machine affected by discharge when the current high-energy particle radiation environment disturbance degree reaches severe disturbance.

[0120] If the current high-energy particle radiation environment disturbance degree is severe disturbance, the corresponding first risk response suggestion is to suggest that the single machine containing sensitive devices and / or the single machine affected by discharge enters a safe state.

[0121] Taking protons as an example, if the current proton radiation environment disturbance degree is calm, the corresponding risk response suggestion is to prompt that the current proton radiation environment is safe and no treatment is needed. If the current proton radiation environment disturbance degree is slight disturbance, the corresponding risk response suggestion is to suggest that monitoring be strengthened and attention be paid to the potential risk of single event effect of the spacecraft. If the current proton radiation environment disturbance degree is moderate disturbance, the corresponding risk response suggestion is to suggest that the risk change condition be monitored and, if necessary, the single machine containing sensitive devices enters a safe state. If the current proton radiation environment disturbance degree is severe disturbance, the corresponding risk response suggestion is to suggest that the single machine containing sensitive devices enters a safe state.

[0122] Taking electrons as an example, if the current electron radiation environment disturbance degree is calm, the corresponding risk response suggestion is to prompt that the current electron radiation environment is safe and no treatment is needed. If the current electron radiation environment disturbance degree is slight disturbance, the corresponding risk response suggestion is to suggest that monitoring be strengthened and attention be paid to the potential risk of deep charging and discharging of the spacecraft. If the current electron radiation environment disturbance degree is moderate disturbance, the corresponding risk response suggestion is to suggest that the risk change condition be monitored and, if necessary, the single machine affected by discharge enters a safe state. If the current electron radiation environment disturbance degree is severe disturbance, the corresponding risk response suggestion is to suggest that the single machine affected by discharge enters a safe state.

[0123] In this way, for the current high-energy particle radiation environment, the risk response suggestion provided can help the spacecraft maintenance personnel to make a quick decision and reduce the loss caused by environmental disturbance. This automatic suggestion generation mechanism improves the efficiency of responding to emergencies and reduces the delay and errors of human judgment.

[0124] When a solar activity burst occurs, a large amount of high-energy particles and strong electromagnetic radiation will be released, which will increase the density of the upper atmosphere by acting on the atmosphere. Through analysis of the atmospheric density monitoring data and the position of the spacecraft orbit, the following high-altitude atmospheric environment disturbance degree discrimination scheme is formulated.

[0125] According to some embodiments of the present application, optionally, S104: calculating the maximum relative disturbance amount of the high-altitude atmospheric density of the target orbit according to the first high-altitude atmospheric daily average atmospheric density and the second high-altitude atmospheric daily average atmospheric density, can include the following steps:

[0126] calculating the difference between the first high-altitude atmospheric daily average atmospheric density and the second high-altitude atmospheric daily average atmospheric density;

[0127] The percentage of the ratio of the difference value to the second high-altitude atmospheric daily average atmospheric density is calculated to obtain the maximum relative disturbance of the high-altitude atmospheric density of the target orbit.

[0128] For example, in some examples, the maximum relative disturbance of the high-altitude atmospheric density of the target orbit can be calculated according to the following expression (3):

[0129] (3)

[0130] wherein, represents the maximum relative disturbance of the high-altitude atmospheric density of the target orbit, represents the first high-altitude atmospheric daily average atmospheric density, represents the second high-altitude atmospheric daily average atmospheric density. As described above, the second high-altitude atmospheric daily average atmospheric density can be obtained by the MSISE model, and the input parameter selection method for calculating the atmospheric density in the quiet period is: taking 1 / 5 of the historical monitoring data of a solar activity week as the environmental quiet data, and 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 in the environmental quiet period.

[0131] According to some embodiments of the present application, S106: determining the current atmospheric environment disturbance degree according to the maximum relative disturbance of the high-altitude atmospheric density and the pre-set atmospheric environment disturbance degree judgment range can include the following steps:

[0132] If the maximum relative disturbance of the high-altitude atmospheric density is less than 10%, it is determined that the current atmospheric environment disturbance degree is quiet;

[0133] If the maximum relative disturbance of the high-altitude atmospheric density is greater than or equal to 10% and less than 40%, it is determined that the current atmospheric environment disturbance degree is slight disturbance;

[0134] If the maximum relative disturbance of the high-altitude atmospheric density is greater than or equal to 40% and less than 90%, it is determined that the current atmospheric environment disturbance degree is moderate disturbance;

[0135] If the maximum relative disturbance of the high-altitude atmospheric density is greater than or equal to 90%, it is determined that the current atmospheric environment disturbance degree is severe disturbance;

[0136] Wherein, the severity of the multiple disturbance degrees is in descending order: severe disturbance > moderate disturbance > slight disturbance > quiet.

[0137] Correspondingly, S107: generating a second risk response suggestion corresponding to the current atmospheric environment disturbance degree can include the following steps:

[0138] If the current atmospheric environment disturbance degree is calm, the corresponding second response suggestion is to prompt the current atmospheric environment safety, and no processing is performed.

[0139] If the current atmospheric environment disturbance degree is slight disturbance, the corresponding second response suggestion is to suggest to strengthen monitoring and increase the orbit prediction frequency.

[0140] If the current atmospheric environment disturbance degree is moderate disturbance, the corresponding second response suggestion is to suggest to perform the orbit-raising action.

[0141] If the current atmospheric environment disturbance degree is severe disturbance, the corresponding second response suggestion is to suggest to perform the orbit-raising action and to close a preset number of loads.

[0142] In this way, the application provides hierarchical response suggestions according to different atmospheric environment disturbance degrees (calm, slight disturbance, moderate disturbance, and severe disturbance). This hierarchical strategy can take corresponding measures for different levels of disturbance to avoid overreaction or insufficient reaction. For example, under slight disturbance, potential risks can be discovered in advance by strengthening monitoring and increasing the orbit prediction frequency. Under moderate and severe disturbance, the orbit-raising action is suggested to be performed in a timely manner. Orbit-raising can offset the orbit decay caused by the increase in atmospheric density, avoiding the premature crash of the spacecraft due to the descent of the orbit. Under severe disturbance, it is suggested to close a preset number of loads if necessary. Closing the loads can reduce the time for which the equipment is exposed to the high-density atmospheric environment, reducing the risk of equipment damage.

[0143] Based on the same technical concept as the satellite orbit space environment disturbance response method provided in the above embodiment, correspondingly, the application also provides a satellite orbit space environment disturbance response device. Please refer to the following embodiments.

[0144] Figure 2 A structural block diagram of the satellite orbit space environment disturbance response device provided in the embodiments of the application is shown in FIG. 2. As shown in FIG. 2, the satellite orbit space environment disturbance response device 20 provided in the embodiments of the application can include the following modules: Figure 2

[0145] The acquisition module 201 is configured to acquire current position data of a target orbit where a target spacecraft is located and current space environment data, and the current space environment data includes a first high-energy particle integrated flux at a target position of high-energy particle flux and a first high-altitude atmospheric daily average atmospheric density.

[0146] The query module 202 is configured to query, according to the current position data of the target orbit, a second high-energy particle integrated flux at the target position of high-energy particle flux when the target orbit environment is calm and a second high-altitude atmospheric daily average atmospheric density when the target orbit environment is calm.

[0147] ​The first calculation module 203 is configured to calculate a high-energy particle radiation environment relative disturbance amount of the target orbit according to the first high-energy particle integrated flux and the second high-energy particle integrated flux.

[0148] The second calculation module 204 is configured to calculate a high-altitude atmosphere density maximum relative disturbance amount of the target orbit according to the first high-altitude atmosphere daily average atmospheric density and the second high-altitude atmosphere daily average atmospheric density.

[0149] The first determination module 205 is configured to determine a current high-energy particle radiation environment disturbance degree according to the high-energy particle radiation environment relative disturbance amount and a pre-set high-energy particle radiation environment disturbance degree discrimination range.

[0150] The second determination module 206 is configured to determine a current atmosphere environment disturbance degree according to the high-altitude atmosphere density maximum relative disturbance amount and a pre-set atmosphere environment disturbance degree discrimination range.

[0151] The generation module 207 is configured to generate a first risk response suggestion corresponding to the current high-energy particle radiation environment disturbance degree, and generate a second risk response suggestion corresponding to the current atmosphere environment disturbance degree, and provide the first risk response suggestion and the second risk response suggestion to a maintenance personnel of the target spacecraft.

[0152] It should be noted that, Figure 2 Each module / unit in the device has the function of implementing each step in the satellite orbit space environment disturbance response method provided by the above method embodiments, and can achieve its corresponding technical effects. For the sake of brevity, it will not be described here.

[0153] The satellite orbit space environment disturbance response device provided by the embodiments of the present application can, on the one hand, by acquiring the current position data and the current space environment data of the target satellite, monitor the changes of the high-energy particle flux and the high-altitude atmosphere density in real time, which helps to discover potential environmental risks in time and avoid spacecraft failures or crashes caused by environmental mutations.

[0154] In another aspect, the degree of disturbance of the space environment is quantified by calculating the relative disturbance of the high-energy particle radiation environment and the maximum relative disturbance of the high-altitude atmospheric density. This quantification method can make the evaluation of environmental disturbance more scientific and objective, avoiding 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 can be more accurately determined whether the current environment poses a threat to the spacecraft, and appropriate measures can be taken. In addition, by setting the high-energy particle radiation environment disturbance degree discrimination range and the atmospheric environment disturbance degree discrimination range, a unified quantification standard for satellite orbit space environment disturbance discrimination is provided. This standardized discrimination method fills the gap in existing standards. Through standardized evaluation, different spacecraft can take consistent measures to respond to the same environmental disturbance, improving the reliability and safety of the overall system.

[0155] In yet another aspect, according to the degree of disturbance of the high-energy particle radiation environment and the degree of disturbance of the atmospheric environment, corresponding risk response suggestions are generated. These suggestions can provide specific operational guidance for different degrees of disturbance, such as adjusting the orbit, turning off sensitive equipment, etc. Targeted risk response suggestions can help spacecraft maintenance personnel make quick decisions 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 operate more stably in complex and changing space environments, extending their service life and reducing maintenance costs.

[0156] Based on the satellite orbit space environment disturbance response method provided in the above embodiments, the present application also provides a specific implementation of an electronic device.

[0157] The electronic device in the embodiments of the present application can be a user terminal device, a server, or other computing devices, or a cloud server. Figure 3 A hardware structure diagram of the electronic device of the embodiments of the present application is provided. The electronic device can include a processor 301 and a memory 302 storing computer program instructions. When the processor 301 executes the computer program instructions, the flow or function of the method of any of the above embodiments is implemented.

[0158] In particular, the processor 301 can include a central processing unit (CPU), or an application-specific integrated circuit (ASIC), or can be configured as one or more integrated circuits to implement the embodiments of the present application. The memory 302 can include a mass storage for data or instructions. For example, the memory 302 can be at least one of a hard disk drive (HDD), a read-only memory (ROM), a random access memory (RAM), a floppy disk drive, a flash drive, an optical disk, a magneto-optical disk, a magnetic tape, a universal serial bus (USB) drive, or other physical / tangible memory storage device. Also, the memory 302 can include a removable or non-removable (or fixed) medium. Further, the memory 302 can be internal or external to the integrated gateway disaster recovery device. The memory 302 can be a non-volatile solid-state memory. In other words, generally the memory 302 includes a tangible (non-transitory) computer-readable storage medium (such as a memory device) encoded with computer-executable instructions that, when executed (by one or more processors), perform the operations described in the method of the embodiments of the present application. The processor 301 implements the flow or function of any of the satellite orbit space environment perturbation coping methods in the above-described embodiments by reading and executing computer program instructions stored in the memory 302.

[0159] In one example, Figure 3 The electronic device shown can also include a communication interface 303 and a bus 310. The processor 301, the memory 302, and the communication interface 303 are connected through the bus 310 and complete communication with each other. The communication interface 303 is mainly used to realize the communication between the modules, devices, units, and / or equipment in the embodiments of the present application. The bus 310 includes hardware, software, or both, which can couple the components of the online data traffic billing device to each other. For example, the bus can include at least one of an accelerated graphics port (AGP) or other graphics bus, an enhanced industry standard architecture (EISA) bus, a frontside bus (FSB), a hypertransport (HT) interconnect, an industry standard architecture (ISA) bus, an infiniband interconnect, a low pin count (LPC) bus, a memory bus, a microchannel architecture (MCA) bus, a peripheral component interconnect (PCI) bus, a PCI-Express (PCI-X) bus, a serial advanced technology attachment (SATA) bus, a video electronics standards association local (VLB) bus, or other suitable bus. The bus 310 can include one or more buses. Although the embodiments of the present application describe or show a specific bus, the embodiments of the present application can consider any suitable bus or interconnection method.

[0160] In combination with the method in the above embodiments, the embodiments of the present application further provide a computer-readable storage medium, which has stored thereon computer program instructions, and the computer program instructions are executed by a processor to implement the flow or function of any one of the satellite orbit space environment disturbance coping methods in the above embodiments.

[0161] In addition, the embodiments of the present application further provide a computer program product, which has stored thereon computer program instructions, and the computer program instructions are executed by a processor to implement the flow or function of any one of the satellite orbit space environment disturbance coping methods in the above embodiments.

[0162] The flowcharts and / or block diagrams of the methods, apparatuses, systems and computer program products of the embodiments of the present application are described above by way of example, and related aspects are described. It should be understood that each block in the flowcharts and / or block diagrams, or a combination thereof, can be implemented by computer program instructions, or by special-purpose hardware that performs specified functions or actions, or by a combination of special-purpose 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 apparatus, to form a machine, so that the instructions executed by the processor can enable the implementation of the functions / actions specified in each block or a combination thereof in the flowcharts and / or block diagrams. The processor can be a general-purpose processor, a special-purpose processor, a special application processor, or a field programmable logic circuit.

[0163] 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, and the like; when implemented in software, it is a program or a code segment used to perform the required tasks. The program or code segment can be stored in a memory, or transmitted on a transmission medium or a communication link by a data signal carried in a carrier wave. The code segment can be downloaded via a computer network such as the Internet, an intranet, and the like.

[0164] It should be noted that the present application is not limited to the specific configurations and processes described above or shown in the drawings. The above description is merely a specific implementation of the present application, and those skilled in the art can clearly understand that, for the convenience and brevity of description, the specific working processes of the described systems, devices, modules or units can refer to the corresponding processes in the method embodiments, which need not be described again. It should be understood that the protection scope of the present application is not limited thereto, and any skilled person in the art can think of various equivalent modifications or replacements within the technical scope disclosed in the present application, and these modifications or replacements should be covered within the protection scope of the present application.

Claims

1. A method for assessing the degree of disturbance in the space environment of a satellite orbit, characterized in that, include: Step 1: Obtain the current integrated proton flux value at the proton flux peak position of the orbit of the spacecraft to be evaluated, and obtain the current integrated electron flux value at the electron flux peak position of the orbit of the spacecraft to be evaluated. Step 2: Calculate the proton radiation disturbance d in the orbit of the spacecraft to be evaluated based on the following expressions (1) and (2). p and electron radiation disturbance d I : d p =p c / p q (1) d I =I c / I q (2) Where, p c The current integrated proton flux value at the proton flux peak position of the orbit of the spacecraft to be evaluated; p q This represents the proton integral flux value when the orbit of the spacecraft to be evaluated is in a calm environment. The peak proton flux location for high or medium orbits is at the equator, while the peak proton flux location for low orbits is at ±60° latitude. c and p q All use a proton integral flux of ≥10MeV; Among them, I c The current integrated electron flux value at the peak position of the electron flux in the orbit of the spacecraft to be evaluated; I q I represents the electron integral flux value when the orbit of the spacecraft to be evaluated is in a quiescent environment; c and I q All use ≥2MeV electron integral flux; Step 3: Based on the daily average atmospheric density value of the orbit of the spacecraft to be evaluated and the daily average atmospheric density value when the orbit of the spacecraft to be evaluated is in a calm environment, calculate the amount of upper atmospheric density disturbance in the orbit of the spacecraft to be evaluated. Step 4: Based on the proton radiation disturbance d present in the orbit of the spacecraft to be evaluated. p Electron radiation disturbance quantity d I The pre-defined ranges for judging the disturbance levels of proton radiation environment and electron radiation environment determine the disturbance level of the high-energy particle radiation environment in the orbit of the spacecraft to be evaluated, and generate corresponding risk response suggestions. Step 5: Based on the upper atmospheric density disturbance in the orbit of the spacecraft to be evaluated. Based on the pre-defined range for judging atmospheric disturbance levels, the degree of atmospheric disturbance in the orbit of the spacecraft to be evaluated is determined, and corresponding risk response suggestions are generated and provided to spacecraft maintenance personnel. For regions above 60° latitude in high orbit, medium orbit, and low orbit, the discrimination ranges F for proton radiation environment disturbance and electron radiation environment disturbance are F<10, 10≤F<100, 100≤F<1000, and F>1000, respectively, corresponding to the levels of radiation environment disturbance: calm, slight disturbance, moderate disturbance, and severe disturbance. The discrimination range f for atmospheric environment disturbance is f<10%, 10%≤f<40%, 40%≤f<90%, and f>90%, corresponding to the levels of atmospheric environment disturbance: calm, slight disturbance, moderate disturbance, and severe disturbance.

2. The method according to claim 1, characterized in that, Risk mitigation recommendations corresponding to the degree of disturbance in the high-energy particle radiation environment in space include: If the current high-energy particle radiation environment is calm, the risk response recommendation is to indicate that the current high-energy particle radiation environment is safe. If the current disturbance level of the high-energy particle radiation environment is slight, the risk response recommendation is to strengthen monitoring and pay attention to the potential risks of single-event effects and / or deep charging and discharging of spacecraft. If the current high-energy particle radiation environment disturbance level is moderate, the risk response recommendation is to monitor the risk changes and, when the current high-energy particle radiation environment disturbance level reaches severe disturbance, the individual units containing sensitive devices and / or the individual units affected by discharge should enter a safe state. If the current high-energy particle radiation environment is subject to severe disturbance, the risk response recommendation is to have individual units containing sensitive devices and / or units affected by discharge enter a safe state.

3. The method according to claim 1, characterized in that, Risk response recommendations corresponding to the degree of disturbance in the space atmospheric environment include: If the current atmospheric disturbance level is calm, the recommended response is to indicate that the current atmospheric environment is safe. If the current atmospheric disturbance is minor, the recommended response is to strengthen monitoring and increase the frequency of orbit forecasts. If the current atmospheric disturbance level is moderate, then the recommendation should be to perform an orbital ascent. If the current atmospheric disturbance level is severe, the recommended action is to perform an orbital ascent and shut down a preset number of payloads.

4. An electronic device, characterized in that, The electronic device includes a processor and a memory storing computer program instructions; when the electronic device executes the computer program instructions, it implements the method for assessing the degree of disturbance in the satellite orbital space environment as described in any one of claims 1-3.

5. A computer program product, characterized in that, It includes computer program instructions that, when executed by a processor, implement the method for assessing the degree of disturbance in the satellite orbital space environment as described in any one of claims 1-3.

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