Method and apparatus for plasma model analysis of space charge effects

Abstract

This application discloses a plasma model analysis method and apparatus for space charging and discharging effects. The method includes: determining the orbit type and the space region traversed during on-orbit operation; determining the plasma model of the outer space plasma fusion model in the traversed space region; obtaining plasma parameters of the traversed space region based on data from the current solar activity period and / or the current geomagnetic activity period; analyzing the charging and discharging effects occurring on the spacecraft surface based on the plasma parameters; using an intrinsic plasma model in the intrinsic region and a transitional fusion model in the transition region, determining the range of the transition region based on the boundary between two adjacent intrinsic regions; dividing the transition region into multiple sub-regions based on the range and division strategy of the transition region; determining the fusion mode of each sub-region for each sub-region, obtaining a transitional fusion model corresponding to the transition region. The plasma parameters obtained through plasma model analysis are more accurate.

Description

Technical Field

[0001] This application relates to the technical field of spacecraft space environment design and effect analysis, and in particular to a plasma model analysis method and apparatus for space charging and discharging effects. Background Technology

[0002] Space plasma is partially or completely ionized gas in the space environment, primarily originating from solar activity and the capture of low-energy charged particles by the Earth's magnetic field. Near-Earth space plasma mainly includes solar wind plasma, magnetospheric plasma, and ionospheric plasma. During spaceflight missions, spacecraft inevitably traverse the space plasma environment. Charged particles in this environment can cause varying degrees of damage to the spacecraft's surface and interior, and space plasma can also impact spaceflight activities, even affecting spacecraft safety. Therefore, there is an urgent need to develop an analytical method based on plasma models to facilitate accurate analysis of space plasma. Summary of the Invention

[0003] The purpose of this invention is to provide a plasma model analysis method and apparatus for space charging and discharging effects.

[0004] Embodiments of this application provide a plasma model analysis method for space charging and discharging effects, including: The orbit type and the space region traversed during on-orbit operation are determined based on the spacecraft's operational plan; Based on the spacecraft's orbital type and the space regions it traverses during its on-orbit operation, determine one or more plasma models for the outer space plasma fusion model in the traversed space regions. Based on data from the current solar activity period and / or the current geomagnetic activity period, plasma parameters for the space region traversed are obtained according to the plasma model; and The charging and discharging effects occurring on the spacecraft surface are analyzed based on the plasma parameters; wherein... The spatial region traversed includes multiple intrinsic regions and at least one transition region located between two adjacent intrinsic regions. The plasma model includes an intrinsic plasma model and a transition fusion model. In the multiple intrinsic regions, the intrinsic plasma model corresponding to each intrinsic region is used. In the at least one transition region, a transition fusion model based at least on the intrinsic plasma models corresponding to adjacent intrinsic regions is used. Determining the transition fusion model includes: The extent of the transition zone is determined based on the boundary between two adjacent intrinsic regions; Based on the scope and division strategy of the transition zone, the transition zone is divided into multiple sub-partitions; For each sub-partition, a fusion mode is determined to obtain the transition fusion model corresponding to the transition zone.

[0005] Furthermore, the method further includes: using a multi-model fusion strategy to combine the intrinsic plasma model corresponding to the intrinsic region with the transition fusion model corresponding to the transition region to obtain the outer space plasma fusion model.

[0006] Furthermore, based on the range and partitioning strategy of the transition zone, the transition zone is divided into multiple sub-partitions, including: Based on the physical field gradient threshold of the transition region, the transition region is divided into multiple sub-regions; or, Based on the level of solar or geomagnetic activity in the transition zone, the transition zone is divided into multiple sub-regions; or, The thickness of the transition zone is determined based on its range, and the transition zone is divided into multiple sub-regions based on its thickness and an exponential decay function; or, If a physical boundary exists within the transition zone, the transition zone is divided into multiple sub-zones based on the physical boundary.

[0007] Further, determining the fusion mode for each sub-partition to obtain the transition fusion model corresponding to the transition zone includes: Extract the model parameters of the intrinsic plasma model corresponding to the intrinsic regions on both sides of the transition region boundary; The thickness and interpolation weight function of each sub-partition are determined based on the range of the transition region; wherein, the interpolation weight function is used to determine the fusion ratio of the model parameters of the intrinsic plasma models on both sides in each sub-partition; Interpolation calculations are performed on the theoretical parameters of the plasma environment within each sub-region using the corresponding interpolation weight function to obtain preliminary fusion results of the transition region parameters. The preliminary fusion results include the continuous distribution of each parameter in the transition region. The theoretical parameters of the plasma environment include at least one of the following: plasma density, temperature, flow rate, and magnetic field parameters. At least one plasma physics process model is invoked to calculate additional correction terms for the preliminary fusion results to correct the interpolation results and obtain the corrected plasma parameters; wherein, the plasma physics process model includes a magnetic reconnection model or a transport model.

[0008] Furthermore, the step of determining the fusion mode for each sub-partition to obtain the transition fusion model corresponding to the transition zone further includes: Obtain the actual measurement results of the plasma environment parameters in the transition region; The pre-constructed initial transition fusion model is trained using actual measurement results of plasma environment parameters, and the corrected plasma parameters are input into the initial transition fusion model to enable it to learn and update its model parameters; and The plasma parameters of the transition region output by the updated transition fusion model are compared with the actual measurement results of the plasma environment parameters to obtain the error between the two. If the error is found to be unacceptable, the model parameters of the initial transition fusion model are iteratively adjusted until the error meets the requirements, thus obtaining the optimized transition fusion model.

[0009] Furthermore, the plasma parameters of the space region traversed, obtained based on data from the current solar activity period and / or the current geomagnetic activity period and according to the outer space plasma fusion model, include: Acquire solar activity and geomagnetic activity data of the space region traversed at the time of spacecraft transit; The solar activity data and / or the geomagnetic activity data are input into the outer space plasma fusion model to calculate the space plasma parameters of the space region being traversed.

[0010] Furthermore, the intrinsic plasma model corresponding to the intrinsic region includes at least one of the following: Ionospheric plasma environment model, inner magnetosphere plasma model, outer magnetosphere plasma environment model, plasmasphere environment model, magnetosheath plasma model, solar wind plasma model, and polar layer plasma environment model.

[0011] Furthermore, the orbital type of the spacecraft includes at least one of the following: Low-inclination orbits, high-inclination orbits, MEO circular orbits, geosynchronous orbits, Lagrange point orbits, high apogee elliptical orbits, planetary orbits, and interplanetary cruise orbits.

[0012] This application provides a spacecraft outer space plasma environment analysis device, comprising: A space region determination module is used to determine the orbit type and the space regions traversed during on-orbit operation based on the spacecraft's operation plan; wherein the traversed space regions include multiple intrinsic regions and at least one transition region located between two adjacent intrinsic regions; A plasma model determination module is used to determine one or more plasma models of the outer space plasma fusion model in the space regions traversed by the spacecraft, based on the spacecraft's orbital type and the space regions it passes through during its on-orbit operation; wherein, the plasma models include intrinsic plasma models and transition fusion models; The transition fusion model determination module, used to determine the transition fusion model, includes: A transition region unit is defined, which is used to determine the extent of the transition region based on the boundary of two adjacent intrinsic regions; A sub-partitioning unit is used to divide the transition area into multiple sub-partitions based on the range and partitioning strategy of the transition area; A fusion mode determination unit is used to determine the fusion mode of each sub-partition for each sub-partition, so as to obtain the transition fusion model corresponding to the transition area; A model module is selected, which is used to apply the intrinsic plasma model corresponding to each of the plurality of intrinsic regions, and in the at least one transition region, to use a transition fusion model based at least on the intrinsic plasma models corresponding to the adjacent intrinsic regions. A plasma parameter determination module, used to determine plasma parameters of the space region traversed based on data from the current solar activity period and / or the current geomagnetic activity period, according to the plasma model; and An analysis module is used to analyze the charging and discharging effects occurring on the spacecraft surface based on the plasma parameters.

[0013] This application provides an electronic device, which includes a processor and a memory storing computer program instructions; when the processor executes the computer program instructions, it implements the steps of the method described above.

[0014] This application provides a computer-readable storage medium storing computer program instructions, which, when executed by a processor, implement the steps of the method described above.

[0015] This application provides a computer program product, which includes computer program instructions that, when executed by a processor, implement the steps of the method described above.

[0016] The above-mentioned technical solution of this application has the following beneficial technical effects: In this embodiment, the orbital type of the spacecraft and the space region through which the spacecraft passes during its orbital operation can be determined based on the orbital altitude of the spacecraft during its orbital operation. In the outer space plasma fusion model, an intrinsic plasma model that conforms to the orbital type of the spacecraft and the intrinsic region through which the spacecraft passes during its orbital operation will be selected. If the spacecraft passes through multiple intrinsic regions during its orbital operation, a transition fusion model corresponding to the transition region will also be selected. By inputting solar activity data and / or geomagnetic activity data into the corresponding plasma model, the corresponding plasma parameters can be obtained. Analysis using a plasma model that matches the actual operating environment of the spacecraft, and considering the influence of the geomagnetic field and solar activity on the intensity of space plasma, yields more accurate and timely plasma parameters. Furthermore, selecting the appropriate plasma model based on the actual operating environment of the spacecraft can better utilize its performance or provide corresponding typical plasma parameters, facilitating the analysis of the space plasma environment. Accurate space plasma parameters obtained through analysis can provide a basis for optimizing the redundancy design and fault tolerance mechanisms of spacecraft materials, electronic components, or optoelectronic devices. They can also assess the impact on space activities, such as communication quality, the occurrence of charge-discharge effects, and orbit maintenance. In particular, they provide accurate and reliable data for analyzing charge-discharge effects occurring on the spacecraft surface, thereby ensuring the safety of the spacecraft's on-orbit operation. Attached Figure Description

[0017] Figure 1 This is a flowchart of the plasma model analysis method for space charging and discharging effects according to the first embodiment of this application; Figure 2 This is a flowchart illustrating the determination of the transition fusion model in the second embodiment of this application; Figure 3 This is a schematic diagram of the spatial region distribution around the Earth according to the third embodiment of this application; Figure 4 This is a schematic diagram of the spatial region distribution around the Earth according to the fourth embodiment of this application; Figure 5 This is a schematic diagram of the spatial region distribution around the Earth according to the fifth embodiment of this application; Figure 6 This is a schematic diagram of the structure of the plasma model analysis device for space charging and discharging effects according to the sixth embodiment of this application; Figure 7 This is a schematic diagram of the structure of the determination transition fusion model module in the seventh embodiment of this application; Figure 8 This is a schematic diagram of an electronic device used to implement the plasma model analysis method for space charging and discharging effects according to the embodiments of this application. Detailed Implementation

[0018] The principles and spirit of this application will be described below with reference to several exemplary embodiments. It should be understood that these embodiments are provided to make the principles and spirit of this application clearer and more thorough, enabling those skilled in the art to better understand and implement the principles and spirit of this application. The exemplary embodiments provided herein are only a part of the embodiments of this application, and not all of them. All other embodiments obtained by those skilled in the art based on the embodiments described herein without inventive effort are within the scope of protection of this application.

[0019] In this document, terms such as first, second, and third are used only to distinguish one entity (or operation) from another entity (or operation), and are not intended to require or imply any order or relationship between these entities (or operations).

[0020] This application provides a flowchart illustrating a plasma model analysis method for space charging and discharging effects, referring to... Figure 1 and Figure 2 The method includes the following specific steps: S110: Determine the orbit type and the space region traversed during on-orbit operation based on the spacecraft's operational plan; wherein the space region includes multiple intrinsic regions and at least one transition region located between two adjacent intrinsic regions.

[0021] Specifically, spacecraft operation planning data can be retrieved from the server-side database. This data may include, for example, the spacecraft's orbital altitude, launch date, and time. Based on the spacecraft's orbital altitude, corresponding orbital classification standards can be established. Following these standards, the spacecraft's orbital type can be identified. Combining the orbital type with information such as orbital inclination and orbital period, the specific space regions traversed by the spacecraft during its operation can be further clarified. If the space regions traversed by the spacecraft include multiple intrinsic regions, there is a transition zone between adjacent intrinsic regions.

[0022] S120: Determine one or more plasma models for the outer space plasma fusion model in the space regions traversed by the spacecraft based on the spacecraft's orbit type and the space regions it passes through during its on-orbit operation; wherein the plasma models include intrinsic plasma models and transition fusion models.

[0023] Specifically, the intrinsic plasma model of each intrinsic region can be seamlessly integrated with the transition fusion model of the adjacent transition region to form a plasma fusion model covering the entire outer space. Intrinsic regions can be, for example, the ionosphere, inner magnetosphere, outer magnetosphere, solar wind region, polar region, or planetary environment region. The intrinsic plasma models corresponding to each intrinsic region mainly include ionospheric plasma environment models such as IRI, inner magnetosphere plasma models such as GCPM, outer magnetosphere plasma environment models, solar wind plasma models, auroral plasma environment models, and planetary plasma environment models. These intrinsic plasma models are dedicated analysis models for different intrinsic regions. Therefore, the corresponding intrinsic plasma model can be selected according to the spacecraft's orbital type and the space region traversed during its on-orbit operation. The transition fusion model is matched to the corresponding transition region. In this way, the plasma model matches the actual operating environment of the spacecraft, avoiding analysis errors caused by incompatible model application areas.

[0024] S130: Determine the transition fusion model.

[0025] Step S130: Determining the transition fusion model may include the following specific steps: S131: Determine the extent of the transition zone based on the boundary between two adjacent intrinsic regions; S132: Based on the range and division strategy of the transition zone, the transition zone is divided into multiple sub-partitions; S133: Determine the fusion mode for each sub-partition to obtain the transition fusion model corresponding to the transition area.

[0026] Specifically, by subdividing the spatial region into intrinsic region and transition region, and performing precise modeling for each sub-region, the transition region is divided into multiple sub-regions. Multiple methods are used to fuse each sub-region to obtain a transition fusion model corresponding to the transition region, thereby improving the rationality and accuracy of the plasma parameters output by the transition fusion model.

[0027] S140: In the plurality of intrinsic regions, the intrinsic plasma model corresponding to each intrinsic region is used; in the at least one transition region, a transition fusion model based at least on the intrinsic plasma model corresponding to the adjacent intrinsic regions is used.

[0028] S150: Based on data from the current solar activity period and / or the current geomagnetic activity period, plasma parameters of the space region traversed are obtained according to the plasma model.

[0029] Specifically, based on the spacecraft's launch date and time, data on the solar and / or geomagnetic activity periods during the spacecraft's on-orbit operation can be determined. Inputting the current solar and / or geomagnetic activity period data into the target space plasma model can output corresponding plasma parameters. Plasma parameters may include, for example, particle type, particle temperature, particle density, and plasma drift velocity. Particle types may include, for example, electrons and ions. Among these, for the continuous spectrum of all charged particles, if the energy of a charged particle is below 50 keV, then the charged particle can be identified as plasma.

[0030] S160: Analyze the charging and discharging effects occurring on the spacecraft surface based on the plasma parameters.

[0031] In this embodiment, the orbital type of the spacecraft and the space region through which the spacecraft passes during its orbital operation can be determined based on the orbital altitude of the spacecraft during its orbital operation. In the outer space plasma fusion model, an intrinsic plasma model that conforms to the orbital type of the spacecraft and the intrinsic region through which the spacecraft passes during its orbital operation will be selected. If the spacecraft passes through multiple intrinsic regions during its orbital operation, a transition fusion model corresponding to the transition region will also be selected. By inputting solar activity data and / or geomagnetic activity data into the corresponding plasma model, the corresponding plasma parameters can be obtained. Analysis using a plasma model that matches the actual operating environment of the spacecraft, and considering the influence of the geomagnetic field and solar activity on the intensity of space plasma, yields more accurate and timely plasma parameters. Furthermore, selecting the appropriate plasma model based on the actual operating environment of the spacecraft can better utilize its performance or provide corresponding typical plasma parameters, facilitating the analysis of the space plasma environment. Accurate space plasma parameters obtained through analysis can provide a basis for optimizing the redundancy design and fault tolerance mechanisms of spacecraft materials, electronic components, or optoelectronic devices. They can also assess the impact on space activities, such as communication quality, the occurrence of charge-discharge effects, and orbit maintenance. In particular, they provide accurate and reliable data for analyzing charge-discharge effects occurring on the spacecraft surface, thereby ensuring the safety of the spacecraft's on-orbit operation.

[0032] In some embodiments, the transition fusion model corresponding to the transition region is used to output plasma parameters that match the transition region; the method further includes: The intrinsic plasma model corresponding to the intrinsic region and the transition fusion model corresponding to the transition region are combined using a multi-model fusion strategy to obtain the outer space plasma fusion model.

[0033] Specifically, intrinsic plasma models corresponding to each intrinsic region include ionospheric plasma environment models such as IRI, inner magnetosphere plasma models such as GCPM, outer magnetosphere plasma environment models, solar wind plasma models, auroral plasma environment models, and planetary plasma environment models, covering a variety of typical intrinsic plasma regions. Transition fusion models, on the other hand, match corresponding transition regions, demonstrating strong model adaptability. Based on the spatial applicability of each intrinsic plasma model and transition fusion model, the plasma models are spatially layered and spliced ​​together to form a spatially integrated model, resulting in an outer space plasma fusion model. By seamlessly integrating the intrinsic plasma model of each intrinsic region with the transition fusion model of adjacent transition regions, a plasma fusion model covering the entire outer space is formed. Inputting solar activity or geomagnetic activity data into the corresponding plasma models can improve the timeliness and accuracy of the plasma parameters output by the models.

[0034] In some embodiments, step S150: obtaining plasma parameters of the space region traversed based on data from the current solar activity period and / or the current geomagnetic activity period, according to the outer space plasma fusion model, includes the following specific steps: S151: Obtain solar activity data and geomagnetic activity data of the space region being traversed at the time of spacecraft transit; S152: Input the solar activity data and / or the geomagnetic activity data into the outer space plasma fusion model to calculate the plasma parameters of the space region being traversed.

[0035] The current geomagnetic activity period and solar activity data are determined based on the spacecraft's on-orbit operation time. Solar activity data may include, for example, local solar magnetic time, solar magnetic latitude, and the Kp index. Geomagnetic activity level data may include, for example, the Dst index, and whether a geomagnetic storm has occurred. The spacecraft's orbital altitude during its on-orbit operation determines its orbital type and the space region it will traverse. In the outer space plasma fusion model, an intrinsic plasma model matching the spacecraft's orbital type and the intrinsic region it will traverse will be selected. If the space region traversed by the spacecraft includes multiple intrinsic regions and a transition region between adjacent intrinsic regions, a transition fusion model corresponding to the transition region will also be selected. Solar activity data and / or geomagnetic activity data are input into the corresponding plasma model to calculate the plasma parameters of the traversed space region. If the spacecraft does not traverse other intrinsic regions during its on-orbit operation, the parameters in the intrinsic plasma models and transition fusion models for the untraversed intrinsic regions will be set to 0, i.e., the corresponding plasma model will not be selected.

[0036] In some embodiments, step S132: dividing the transition region into multiple sub-partitions based on the range and partitioning strategy of the transition region includes the following specific steps: S1321: Divide the transition region into multiple sub-regions based on the physical field gradient threshold of the transition region; or, S1322: Based on the solar activity level or geomagnetic activity level of the transition zone, the transition zone is divided into multiple sub-regions; or, S1323: Determine the thickness of the transition region based on its range, and divide the transition region into multiple sub-regions based on its thickness and an exponential decay function; or, S1324: If there is a physical boundary within the range of the transition zone, the transition zone is divided into multiple sub-zones based on the physical boundary.

[0037] Specifically, dividing the transition area into multiple sub-partitions can include the following processing methods: 1. Physical field gradient thresholding method The gradients of key parameters in the intrinsic regions on both sides of the transition region are calculated. These gradients can be, for example, electron density gradients or magnetic field gradients. When the absolute value of the gradient of a key parameter exceeds a preset threshold, a partitioning request is triggered. For example, there is a transition region between the ionosphere and the magnetosheath. If the magnetic field gradient of a certain region within the transition region is higher than 5 nT / km, then that region can be divided into an independent sub-region. Therefore, the transition region can be divided into multiple sub-regions.

[0038] 2. Dynamic partition adjustment mechanism Based on real-time solar activity and geomagnetic activity data, it can be determined whether the transition zone can be divided into multiple sub-regions. Real-time solar activity data can be, for example, based on the F10.7 solar index, and geomagnetic activity data can be, for example, based on the Dst index. The granularity and extent of the sub-region division can be dynamically adjusted based on the real-time solar activity and geomagnetic activity data. When the Dst index is < -200 nT, indicating a strong geomagnetic storm, the transition zone between the ionosphere and magnetosheath can be subdivided into three sub-regions, for example, to capture the rapid evolution of the shock structure.

[0039] 3. Adaptive spatial scale partitioning Based on the thickness δ of the transition zone, according to the exponential decay function The transition area can be divided into multiple sub-partitions:

[0040] Until

[0041] In the formula, δ is the thickness of the transition region in kilometers. For example, the thickness of the transition region between the inner magnetosphere and the plasmasphere extends for hundreds of kilometers. According to the exponential decay function, the transition region can be divided into 5–8 sub-regions.

[0042] 4. Partitioning driven by physical processes If there are regions with significant physical boundaries within the transition zone, such as magnetic reconnection interfaces or plasmapauses, the transition zone can be divided into multiple sub-regions based on these physical boundaries. Alternatively, the transition zone can be divided using magnetic field topology analysis, such as by locating the magnetic reconnection interface using the Minimum Variance Analysis (MVA) method, with the magnetic reconnection interface serving as the boundary.

[0043] In some embodiments, the transition zone is divided into multiple sub-regions, and multi-dimensional feature clustering analysis can also be used. Specifically, the following processing can be performed: extracting the spatiotemporal features of the transition zone, which may include, for example, solar wind speed, geomagnetic index, plasma β value, etc., and using the K-means clustering algorithm for unsupervised clustering to automatically identify the number and boundaries of sub-regions. For example, during a solar storm, the transition zone can be divided into a "high-density near-Earth side region" and a "low-density far-Earth side region".

[0044] In some embodiments, step S133: determining the fusion mode for each sub-partition to obtain the transition fusion model corresponding to the transition area includes the following specific steps: S1331: Extract the model parameters of the intrinsic plasma model corresponding to the intrinsic regions on both sides of the transition region boundary; S1332: Determine the thickness and interpolation weight function of each sub-partition based on the range of the transition region; wherein, the interpolation weight function is used to determine the fusion ratio of the model parameters of the intrinsic plasma models on both sides in each sub-partition; S1333: The theoretical parameters of the plasma environment within each of the sub-regions are interpolated using the corresponding interpolation weight function to obtain the preliminary fusion results of the transition region parameters. The preliminary fusion results include the continuous distribution of each parameter in the transition region. The theoretical parameters of the plasma environment include at least one of the following: plasma density, temperature, flow rate, and magnetic field parameters. S1334: Call at least one plasma physics process model to calculate additional correction terms for the preliminary fusion results to correct the interpolation results and obtain the corrected plasma parameters; wherein, the plasma physics process model includes a magnetic reconnection model or a transport model.

[0045] Specifically, the model parameters P of the intrinsic plasma model corresponding to the intrinsic regions on both sides of the transition region boundary are extracted. A and P BThe interpolation weighting function can be, for example, the inverse distance weighting function and / or the Kriging interpolation function. The model parameters P are determined based on the range of each sub-partition and the interpolation weighting function. A and P B The fusion ratio of each sub-region is determined; theoretical parameters such as plasma density, temperature, flow rate, and magnetic field parameters are interpolated using corresponding interpolation weight functions to obtain the corresponding interpolation results, thereby obtaining the continuous distribution of each parameter in the transition region. The interpolation results are then corrected using the plasma physics process model to obtain the corrected complete plasma parameters corresponding to the transition region.

[0046] In some embodiments, step S133: determining the fusion mode for each sub-partition to obtain the transition fusion model corresponding to the transition area further includes the following specific steps: S1335: Obtain the actual measurement results of the plasma environment parameters in the transition region; S1336: The pre-constructed initial transition fusion model is trained using actual measurement results of plasma environment parameters, and the corrected plasma parameters are input into the initial transition fusion model to enable the initial transition fusion model to learn and update the model parameters of the initial transition fusion model; and, S1337: Compare the plasma parameters of the transition region output by the updated transition fusion model with the actual measurement results of the plasma environment parameters to obtain the error between the two. If the error between the two is not satisfactory, iteratively adjust the model parameters of the initial transition fusion model until the error meets the requirements, and obtain the optimized transition fusion model.

[0047] Specifically, using plasma environment parameters of the transition zone measured by satellite during the same period as training samples, a pre-constructed initial transition fusion model is trained. This initial transition fusion model can be constructed using a spatiotemporal convolutional network (ST-ConvNet) or a long short-term memory network (LSTM). The corrected plasma parameters are then input into the initial transition fusion model for machine reinforcement learning, continuously updating the model parameters. The plasma parameters of the transition zone output by the updated transition fusion model are compared with the actual measured plasma environment parameters to determine the error between the two. If the error does not meet the requirements, the model parameters of the initial transition fusion model are iteratively adjusted until the error meets the requirements, at which point the iterative optimization stops, resulting in an optimized transition fusion model. Therefore, the plasma parameters of the transition zone output by the optimized transition fusion model are highly accurate.

[0048] In this embodiment, the transition region is subdivided into multiple sub-regions, and a hybrid algorithm of weighting and interpolation is used for each sub-region. The physical process model is used to calculate correction terms to correct the interpolation results. The actual measurement results of plasma environment parameters and the corrected parameters are used to train and learn the model, thereby realizing a closed-loop optimization model. This solves the multi-scale coupling problem in transition region plasma parameter modeling and improves the accuracy, efficiency, and generalization of the model output parameters. It provides highly reliable data support for the safety of spacecraft in orbit.

[0049] In an exemplary embodiment, the intrinsic plasma model corresponding to the intrinsic region includes at least one of the following: Ionospheric plasma environment model, inner magnetosphere plasma model, outer magnetosphere plasma environment model, plasmasphere environment model, magnetosheath plasma model, solar wind plasma model, and polar layer plasma environment model.

[0050] In an exemplary embodiment, the orbit type of the spacecraft includes at least one of the following: Low-inclination orbits, high-inclination orbits, MEO circular orbits, geosynchronous orbits, Lagrange point orbits, high apogee elliptical orbits, planetary orbits, and interplanetary cruise orbits.

[0051] The following describes in detail the specific processing procedure of the embodiments of this application, using specific examples.

[0052] In this embodiment of the application, the orbit type and the space region traversed by the spacecraft during its on-orbit operation can be determined based on the obtained orbital altitude of the spacecraft, as shown in Table 1.

[0053] Table 1. Plasma regions encountered by engineering missions of different orbital types

[0054] As shown in Table 1, depending on the orbital type of the spacecraft during its on-orbit operation, engineering missions of different orbital types may encounter plasma regions that include one or more intrinsic regions. When multiple intrinsic regions are encountered, there is a corresponding transition region between two adjacent intrinsic regions. (Reference) Figure 3-5 The plasma region encountered can be determined based on the spacecraft's location or orbit type during its on-orbit operation as follows: 1) The space region with an altitude between 60km and 2000km can be defined as ionosphere 12.

[0055] 2) Space regions with an orbital inclination greater than 50° and an altitude between 80km and 2000km encountered by the spacecraft during its on-orbit operation are designated as Polar Region 11.

[0056] 3) The space region with an altitude higher than 2000km and lower than L=7 (approximately L=1.3 at the equator) can be identified as plasmasphere 18.

[0057] 4) All spatial regions corresponding to L values ​​above L and within the magnetic apex can be identified as the outer magnetic layer, and spatial regions corresponding to L = 1.2-3 can be identified as the inner magnetic layer. Both the outer and inner magnetic layers belong to magnetic layer 13.

[0058] 5) The space region outside the magnetic apex and inside the bow shock 16 can be defined as the magnetosheath region; wherein, the bow shock 16 is the shock wave formed in front of the Earth's magnetosphere when the solar wind plasma flow interacts with the Earth's magnetosphere.

[0059] 6) The space region outside the magnetic apex and bow shock can be identified as the solar wind region 14.

[0060] 7) The spatial region located within the bow shock 16 and beyond a distance of 30Re (Re is the Earth's radius) from Earth on the opposite side can be defined as the magnetotail region 17 and the distal magnetosheath region; wherein, the magnetotail region 17 is the magnetospheric extension region formed on the opposite side by the interaction of the solar wind and the magnetosphere 13; the magnetosheath region is the region between the magnetopause and the lateral shock. The magnetotail region 17 includes a plasma sheet region and a neutral sheet region.

[0061] 8) The space region within the planetary bow shock or the planetary magnetotope or the top of the planetary ionosphere can be identified as the planetary environment region.

[0062] Figure 3 The white dashed lines in the image represent the flow paths of the solar wind and solar particles. Figure 4 The diagram shows the locations of polar region 11, ionosphere 12, magnetosphere 13, and solar wind region 14. Polar gap region 15 consists of two funnel-shaped magnetic field gaps in magnetosphere 13 located near the magnetic noon of 75° latitude at the north and south poles. The magnetic field strength of polar gap region 15 is close to zero, allowing the solar wind to enter the upper atmosphere of polar region 11 almost unimpeded. Figure 5 The location of magnetotail region 17 and plasma layer 18 is shown in the figure; other plasma regions are not shown in the figure.

[0063] This application also provides another plasma model analysis method for space charging and discharging effects, which may include the following specific steps: S201: If the spacecraft's orbit type is a low-inclination orbit, a high-inclination orbit, or a MEO circular orbit, and the space region that the spacecraft passes through during its on-orbit operation is the ionosphere, then the ionospheric IRI model will be invoked. S202: Input the data of the current geomagnetic activity period into the ionospheric IRI model to output plasma parameters; wherein, the data of the current geomagnetic activity period includes longitude and latitude in the geomagnetic coordinate system, the date of geomagnetic activity, local time, and the altitude range of the start and end of geomagnetic activity.

[0064] Specifically, the space region between 60 km and 2000 km in altitude can be defined as the ionosphere; the ionospheric IRI model can calculate the density, temperature, and composition of plasma in the non-auroral region of the ionosphere. Input parameters for the ionospheric IRI model may include, for example: 1) Selection of geographical or geomagnetic coordinate system; 2) Latitude; 3) Longitude; 4) The date of the geomagnetic activity; 5) Local or world time; 6) The altitude range at which geomagnetic activity begins and ends (start and end ranges and step lengths).

[0065] The client can send data requests to the server, which may include, for example, the spacecraft's orbital altitude, launch date, and time. Based on the obtained launch date and time, the geomagnetic activity period during the spacecraft's orbital operation can be determined. The ionospheric IRI model can output the densities of O+, H+, He+, NO+, O2+, N+, and complex ions. The external drivers of the IRI model are the sunspot number and the ionospheric index IG, both of which require a 12-month average index.

[0066] S203: If the spacecraft's orbit type is a high-inclination orbit, and the space region it traverses during its orbital operation is a polar region, then the aurora plasma environment model is invoked; the aurora plasma environment model includes an electron distribution function; and the parameters of the worst-case scenario in the aurora charging environment are applied to the electron distribution function for calculation to obtain the plasma parameters; When E ≤ 17.44 keV, the electron distribution function is given by the following condition:

[0067] When E > 17.44 keV, the electron distribution function is given by the following condition:

[0068] In the formula: f(v) is the distribution function, in units of s. 3 m -6 N0 is the electron density, in m³. -3 ;m ekT0 is the electron mass in kg; kT0 is the thermal energy in J; E0 is the electron energy threshold that can generate a charging potential in J; E is the electron energy in J. The worst-case parameters for aurora charging are as follows: N0 = 1.13E 6 m -3 kT0 = 3.96 keV; E0 = 17.44 keV; using a thermionic density of 125 cm⁻¹ -3 The temperature is 0.2 eV.

[0069] Among them, the aurora charging environment determined by the aurora plasma environment model has a corresponding impact on orbital inclination angles greater than 50° and orbital altitudes between 80km and 2000km when the spacecraft is in orbit.

[0070] S204: If the spacecraft's orbit type is geosynchronous orbit, and the space region it traverses during its orbital operation is the exomagnetic layer, then the exomagnetic plasma environment model is selected. This model includes a typical parameter set for geosynchronous orbit plasma. Within this set, plasma parameters are determined based on data from the current geomagnetic activity period. If the current geomagnetic activity is in a quiescent phase, the plasma density is approximately 0.1-10 cm³. -3 Ion energy is 1-1000 eV, electron energy is 1-1000 eV, and Debye length λ D Approximately 50m; if the current geomagnetic activity is in a substorm phase, the plasma density is 0.1-1cm³. -3 The ion energy is 10-300 keV, the electron energy is approximately 0.1-10 keV, and the Debye length λ... D Approximately 500m. Comparing substorm and quiescent periods of geomagnetic activity, the Debye length λ... D It increased tenfold.

[0071] Specifically, data on the current geomagnetic activity period are determined based on the spacecraft's on-orbit operation time, such as whether a geomagnetic storm has occurred. Based on the data of the geomagnetic activity period, corresponding plasma parameters are selected from the typical plasma parameter group in geosynchronous orbit to analyze the charging and discharging effects on the spacecraft surface; for example, the specific typical plasma parameters in geosynchronous orbit can be found in Table 2.

[0072] Table 2 Typical parameters of plasma in geosynchronous orbit

[0073] S205: If the spacecraft's orbit type is geosynchronous orbit or MEO circular orbit, and the space region the spacecraft passes through during its on-orbit operation is the plasmasphere, then the plasma GCPM model is selected; and the data of the current solar activity period is input into the plasma GCPM model to output plasma parameters; the data of the current solar activity period includes solar magnetic local time, solar magnetic latitude, and Kp index.

[0074] Specifically, the region where a spacecraft operates at an orbital altitude higher than 2000 km but lower than L=7 (approximately L=1.3 at the equator) can be defined as the plasmasphere. Input parameters for the plasma GCPM model include, for example, the spacecraft's orbital time, geocentric radial distance (spacecraft's orbital altitude), solar magnetic local time, solar magnetic latitude, and the Kp exponent. Output parameters include the densities of electrons, protons, helium ions, and oxygen ions. These output parameters can be used to analyze the charging and discharging effects on the spacecraft surface and its impact on communication signal attenuation. For the analysis of the spacecraft charging effect, the plasma GCPM model can use a Kp exponent of 9 to represent the worst-case scenario; where Kp=9 indicates the strongest solar activity and a high charging potential on the spacecraft surface.

[0075] S206: If the spacecraft's orbit type is geosynchronous orbit or MEO circular orbit, and the space region traversed by the spacecraft during its orbital operation is a magnetosheath region, then the typical parameter set of magnetosheath plasma will be used as the target space plasma model; among which, the plasma parameters are determined according to the latitude traversed by the spacecraft and the local time of the observed spacecraft. If the local time of the observed spacecraft is 12 noon, the plasma velocity is 50 km / s. -1 The ion temperature is 2×10 6 K, electron temperature is 2×10 6 K, plasma density is 35 cm⁻¹ -3 If the local time for observing the spacecraft is 6:00 AM, the plasma velocity is 500 km / s. -1 The ion temperature is 1×10 6 K, electron temperature is 1×10 6 K, plasma density is 20 cm⁻¹ -3 .

[0076] Specifically, plasma parameters are selected from the typical parameter set of magnetosheath plasma, which varies according to the latitude of the spacecraft and the local time of observation, in order to analyze the charging and discharging effects on the spacecraft surface; for example, the specific typical parameters of magnetosheath plasma can be found in Table 3.

[0077] Table 3 Typical parameters of magnetosheath plasma

[0078] S207: If the spacecraft's orbit type is MEO circular orbit, and the space region traversed by the spacecraft during its orbital operation is the exomagnetism, then the exomagnetic plasma environment model is selected. The exomagnetic plasma environment model also includes a worst-case environmental parameter set based on a dual Maxwell distribution. This set includes a first component parameter set and a second component parameter set. The first component parameter set includes one or more of the following: electron density of 0.1-100 cm⁻¹. -3 The electron energy is 0.1-10 keV, and the ion density is 0.5-50 cm⁻¹. -3 The ion energy is 1-300 eV; the second component parameter set includes one or more of the following: electron density is 0.1-10 cm⁻¹. -3 The electron energy is 100 eV-100 keV, and the ion density is 0.01-5 cm⁻¹. -3 The ion energy is 1-100 keV.

[0079] Specifically, the outer magnetosphere is a region where plasma density and temperature dynamically change. For assessing the surface charging effect of a spacecraft operating in orbit within the outer magnetosphere, worst-case environmental parameters of a double Maxwell distribution can be used as inputs for simulating or calculating the surface charging effect. For example, specific worst-case environmental parameters of a double Maxwell distribution can be found in Table 4.

[0080] Table 4. Worst-case environmental parameters for the double Maxwell distribution

[0081] S208: If the spacecraft's orbit type is L1, L2, L4, or L5 Lagrange point orbit or interplanetary cruise orbit, and the space region traversed by the spacecraft during its orbital operation is a solar wind region, then the interplanetary solar wind prediction model shall be selected; among which, If the spacecraft is located at the L1 or L2 Lagrange points, the solar wind it experiences will have the same average plasma parameters and range as the solar wind encountered on Earth. The average and range of solar wind density at locations within the heliosphere of the ecliptic plane are given by r. -2 The change is plotted using , where r is the distance from the heliocenter; The average and range of electron temperatures at locations within the heliosphere of the ecliptic plane are given by r. -0.64 The changes are used to draw the image.

[0082] Specifically, the interplanetary solar wind prediction model (PFSS-WSA-Cone model-modified HAF) in this embodiment can simulate the propagation process of background and disturbed solar wind in interplanetary space based on the extrapolation model of the solar photosphere magnetic field potential, the empirical model of solar wind velocity at the source surface, and the modified solar wind dynamics propagation model, combined with the cone model of solar coronal mass ejections. It can predict the basic parameters of interplanetary magnetic field polarity and solar wind plasma. Typical values ​​of solar wind velocity, density, and temperature predicted by the interplanetary solar wind prediction model are shown in Table 5.

[0083] Table 5 Solar wind parameters

[0084] S209: If the spacecraft's orbit type is an L2 Lagrange point orbit, and the space region it traverses during its orbital operation is the magnetotail region and the far magnetosheath region, then the typical plasma parameter set around L2 will be used as the target space plasma model; among which, If the spacecraft is located in the Earth's magnetosheath region, the plasma density is 1–30 cm⁻¹. -3 The ion temperature is 1×10 5 –1×10 7 K, electron energy 10–100 eV, plasma velocity 200–500 km·s -1 If the spacecraft is located in the magnetosheath region of another planet, the plasma density is 1–10 cm³. -3 The temperature of electrons and ions decreases with increasing heliocentric distance; If the spacecraft is located in the magnetic lobe region, the plasma density is 0.01–0.1 cm³. -3 The ion temperature is 1×10 6 –1×10 7 K, electron energy 100–500 eV, plasma velocity 10–100 km·s -1 ; If the spacecraft is located in a plasma region, the plasma density is 0.1-1 cm³. -3 The ion temperature is 1×10 7 –5×10 8 K, electron energy 0.1–10 keV, plasma velocity 50–300 km·s -1 .

[0085] Table 6 shows typical plasma parameters that may be encountered in the far magnetotail and far magnetosheath regions near the L2 Lagrange point.

[0086] Table 6 Typical plasma parameters around L2

[0087] The ion energy can be converted into ion temperature, for example, 100 eV–500 eV corresponds to 1 × 10⁻⁶ eV. 6 K~5×10 6 K.

[0088] S210: If the spacecraft's orbit type is a planetary orbit and the space region it passes through during its orbital operation is a planetary environment region, then the planetary plasma environment parameter set will be used as the target space plasma model; among which, the planetary plasma environment parameter set includes the worst-case environment parameter set for solar eclipse charging near Jupiter and Saturn. In the worst-case environmental parameter set for eclipse charging near Jupiter and Saturn, if encountering Jupiter, the combined rotational speed of the spacecraft and Jupiter is 10. 4 km·s -1 At that time, the proton flux was 1.11 × 10⁻⁶. 5 m -2 ·s -1 The combined rotational speed of the spacecraft and Jupiter is 1.0 km / s. -1 At that time, the proton flux was 0.458·m. -2 ·s -1 The combined rotational speed of the spacecraft and Jupiter is 2.0 km / s. -1 At that time, the proton flux was 1.7·m -2 ·s -1 ; In the worst-case environmental parameter set for eclipse charging near Jupiter and Saturn, if encountering Saturn, the combined rotational speed of the spacecraft and Saturn is 10. 4 km·s -1 At that time, the proton flux was 3.0 × 10⁻⁶. 3 m -2 ·s -1 The combined rotational speed of the spacecraft and Saturn is 1.0 km / s. -1 At that time, the proton flux was 30.8·m. -2 ·s -1 The combined rotational speed of the spacecraft and Saturn is 2.0 km / s. -1 At that time, the proton flux was 8.5·m. -2 ·s -1 .

[0089] Table 7 provides information on the worst charging environments near Jupiter and Saturn.

[0090] Table 7. Worst-case scenarios for solar eclipse charging near Jupiter and Saturn.

[0091] S211: If the spacecraft's orbit type is an elliptical orbit with a high apogee, and the space region that the spacecraft passes through during its orbital operation is one or more of the following: ionosphere, plasmasphere, exomagnetic sphere, magnetosheath region, polar region, solar wind region, and planetary environment region, then the intrinsic plasma model corresponding to the intrinsic region shall be selected. If the spacecraft passes through multiple intrinsic regions during its orbital operation, the transition fusion model of the corresponding transition region may also be selected to obtain plasma parameters.

[0092] S212: Based on the charging effect induced on the spacecraft surface by plasma generated during spacecraft operation in orbit, determine the induced plasma environment parameter set; among which, the induced plasma environment parameter set includes: plasma energy of 3eV, photoelectron current of 1×10 -5 A / m 2 The surface electron density is 1×10 8 m -3 .

[0093] Corresponding to the method in the embodiments of this application, the embodiments of this application also provide a spacecraft outer space plasma environment analysis device, with reference to... Figures 6-7 ,include: The space region determination module 510 is used to determine the orbit type and the space regions traversed during on-orbit operation based on the spacecraft's operation plan; wherein the traversed space regions include multiple intrinsic regions and at least one transition region located between two adjacent intrinsic regions; The plasma model determination module 520 is used to determine one or more plasma models of the outer space plasma fusion model in the space region traversed by the spacecraft based on the spacecraft's orbit type and the space region it passes through during its on-orbit operation; wherein, the plasma model includes an intrinsic plasma model and a transition fusion model; Transition fusion model determination module 530, which is used to determine the transition fusion model, the transition fusion model determination module 530 includes: A transition region unit 531 is defined, which is used to determine the extent of the transition region based on the boundary of two adjacent intrinsic regions; Sub-partitioning unit 532 is used to divide the transition area into multiple sub-partitions based on the range and partitioning strategy of the transition area; The fusion mode determination unit 533 is used to determine the fusion mode of each sub-partition for each sub-partition, so as to obtain the transition fusion model corresponding to the transition area; Model module 540 is selected, which is used to use the intrinsic plasma model corresponding to each of the plurality of intrinsic regions, and in the at least one transition region, to use a transition fusion model based at least on the intrinsic plasma models corresponding to the adjacent intrinsic regions. Plasma parameter determination module 550 is used to determine plasma parameters of the space region traversed based on data from the current solar activity period and / or the current geomagnetic activity period, according to the plasma model; and Analysis module 560 is used to analyze the charging and discharging effects occurring on the spacecraft surface based on the plasma parameters.

[0094] The electronic device in this application embodiment may be a user terminal device, a server, other computing devices, or a cloud server. Figure 8 The diagram illustrates the hardware structure of an electronic device according to an embodiment of this application. The electronic device may include a processor 601 and a memory 602 storing computer program instructions. When the processor 601 executes the computer program instructions, it implements the process or function of any of the methods described above.

[0095] Specifically, processor 601 may include a central processing unit (CPU), or an application-specific integrated circuit (ASIC), or one or more integrated circuits configured to implement the embodiments of this application. Memory 602 may include a mass storage device for data or instructions. For example, memory 602 may be at least one of the following: a hard disk drive (HDD), read-only memory (ROM), random access memory (RAM), floppy disk drive, flash memory, optical disk, magneto-optical disk, magnetic tape, universal serial bus (USB) drive, or other physical / tangible memory storage device. Alternatively, memory 602 may include removable or non-removable (or fixed) media. Furthermore, memory 602 may be internal or external to the integrated gateway disaster recovery device. Memory 602 may be non-volatile solid-state memory. In other words, typically memory 602 includes a tangible (non-transitory) computer-readable storage medium (such as a memory device) encoded with computer-executable instructions, and when the software is executed (e.g., by one or more processors), it can perform the operations described in the methods of the embodiments of this application. The processor 601 implements the process or function of any of the methods described in the above embodiments by reading and executing computer program instructions stored in the memory 602.

[0096] In one example Figure 8The illustrated electronic device may also include a communication interface 603 and a bus 610. The processor 601, memory 602, and communication interface 603 are connected via bus 610 and communicate with each other. Communication interface 603 is primarily used to enable communication between modules, devices, units, and / or equipment in the embodiments of this application. Bus 610 may include hardware, software, or both, and can couple components of the online data traffic billing device together. For example, the bus may include at least one of the following: Accelerated Graphics Port (AGP) or other graphics bus, Enhanced Industry Standard Architecture (EISA) bus, Front Side Bus (FSB), HyperTransport (HT) Interconnect, Industry Standard Architecture (ISA) bus, Infinite Bandwidth Interconnect, Low Pin Count (LPC) bus, memory bus, Microchannel Architecture (MCA) bus, Peripheral Component Interconnect (PCI) bus, PCI-Express (PCI-X) bus, Serial Advanced Technology Attachment (SATA) bus, Video Electronics Standards Association Local (VLB) bus, or other suitable buses. Bus 610 may include one or more buses. Although specific buses are described or illustrated in the embodiments of this application, any suitable bus or interconnection method may be considered in the embodiments of this application.

[0097] In conjunction with the methods in the above embodiments, this application also provides a computer-readable storage medium storing computer program instructions, which, when executed by a processor, implement the process or function of any of the methods in the above embodiments.

[0098] In addition, this application also provides a computer program product that stores computer program instructions, which, when executed by a processor, implement the process or function of any of the methods described above.

[0099] The flowcharts and / or block diagrams of methods, apparatuses, systems, and computer program products according to embodiments of this application have been exemplarily described above, and related aspects have been described. It should be understood that each block or combination thereof in the flowcharts and / or block diagrams may be implemented by computer program instructions, by dedicated hardware performing a specified function or action, or by a combination of dedicated hardware and computer instructions. For example, these computer program instructions may be provided to a processor of a general-purpose computer, a special-purpose computer, or other programmable data processing apparatus to form a machine that enables the implementation of the function / action specified in each block or combination thereof in the flowcharts and / or block diagrams, executable via such processor. Such a processor may be a general-purpose processor, a dedicated processor, a special-purpose application processor, or a field-programmable logic circuit.

[0100] The functional blocks shown in the structural block diagrams of this application can be implemented as hardware, software, firmware, or a combination thereof. When implemented in hardware, they can be, for example, electronic circuits, application-specific integrated circuits (ASICs), appropriate firmware, plug-ins, function cards, etc.; when implemented in software, they are programs or code segments used to perform the required tasks. Programs or code segments can be stored in memory or transmitted over a transmission medium or communication link via data signals carried on a carrier wave. Code segments can be downloaded via computer networks such as the Internet or intranets.

[0101] It should be noted that this application is not limited to the specific configurations and processes described above or shown in the figures. The above descriptions are merely specific embodiments of this application. Those skilled in the art will clearly understand that, for the sake of convenience and brevity, the specific working processes of the described systems, devices, modules, or units can be referred to the corresponding processes in the method embodiments, and need not be repeated here. It should be understood that the scope of protection of this application is not limited thereto. Any person skilled in the art can conceive of various equivalent modifications or substitutions within the scope of the technology disclosed in this application, and these modifications or substitutions should all be covered within the scope of protection of this application.

Claims

1. A method for plasma model analysis of space charge and discharge effects, characterized in that, include: The orbit type and the space regions traversed during on-orbit operation are determined based on the spacecraft's operation plan; wherein, the space regions traversed include multiple intrinsic regions and at least one transition region located between two adjacent intrinsic regions; Based on the spacecraft's orbital type and the space regions it traverses during its on-orbit operation, one or more plasma models for the outer space plasma fusion model are determined for the traversed space regions; wherein, the plasma models include intrinsic plasma models and transition fusion models; Determining the transition fusion model includes: The extent of the transition zone is determined based on the boundary between two adjacent intrinsic regions; Based on the scope and division strategy of the transition zone, the transition zone is divided into multiple sub-partitions; For each sub-partition, a fusion mode is determined to obtain the transition fusion model corresponding to the transition zone; In the plurality of intrinsic regions, an intrinsic plasma model corresponding to each intrinsic region is used; in the at least one transition region, a transition fusion model based at least on the intrinsic plasma models corresponding to the adjacent intrinsic regions is used. Based on data from the current solar activity period and / or the current geomagnetic activity period, plasma parameters for the space region traversed are obtained according to the plasma model; and The charging and discharging effects occurring on the spacecraft surface are analyzed based on the plasma parameters.

2. The method of claim 1, wherein, Also includes: The intrinsic plasma model corresponding to the intrinsic region and the transition fusion model corresponding to the transition region are combined using a multi-model fusion strategy to obtain the outer space plasma fusion model.

3. The method of claim 2, wherein, Based on the range and partitioning strategy of the transition zone, the transition zone is divided into multiple sub-partitions, including: Based on the physical field gradient threshold of the transition region, the transition region is divided into multiple sub-regions; or, Based on solar activity data or geomagnetic activity data of the transition zone, the transition zone is divided into multiple sub-regions; or, The thickness of the transition zone is determined based on its range, and the transition zone is divided into multiple sub-regions based on its thickness and an exponential decay function; or, If a physical boundary exists within the transition zone, the transition zone is divided into multiple sub-zones based on the physical boundary.

4. The method of claim 3, wherein, The step of determining the fusion mode for each sub-partition to obtain the transition fusion model corresponding to the transition zone includes: Extract the model parameters of the intrinsic plasma model corresponding to the intrinsic regions on both sides of the transition region boundary; The thickness and interpolation weight function of each sub-partition are determined based on the range of the transition region; wherein, the interpolation weight function is used to determine the fusion ratio of the model parameters of the intrinsic plasma models on both sides in each sub-partition; Interpolation calculations are performed on the theoretical parameters of the plasma environment within each sub-region using the corresponding interpolation weight function to obtain preliminary fusion results of the transition region parameters. The preliminary fusion results include the continuous distribution of each parameter in the transition region. The theoretical parameters of the plasma environment include at least one of the following: plasma density, temperature, flow rate, and magnetic field parameters. At least one plasma physics process model is invoked to calculate additional correction terms for the preliminary fusion results to correct the interpolation results and obtain the corrected plasma parameters; wherein, the plasma physics process model includes a magnetic reconnection model or a transport model.

5. The method according to claim 4, characterized in that, The step of determining the fusion mode for each sub-partition to obtain the transition fusion model corresponding to the transition zone further includes: Obtain the actual measurement results of the plasma environment parameters in the transition region; The pre-constructed initial transition fusion model is trained using actual measurement results of plasma environment parameters, and the corrected plasma parameters are input into the initial transition fusion model to enable it to learn and update its model parameters; and The plasma parameters of the transition region output by the updated transition fusion model are compared with the actual measurement results of the plasma environment parameters to obtain the error between the two. If the error is found to be unacceptable, the model parameters of the initial transition fusion model are iteratively adjusted until the error meets the requirements, thus obtaining the optimized transition fusion model.

6. The method according to claim 1, characterized in that, The plasma parameters of the space regions traversed are obtained based on the data from the current solar activity period and / or the current geomagnetic activity period, according to the outer space plasma fusion model, including: Acquire solar activity and geomagnetic activity data of the space region traversed at the time of spacecraft transit; The solar activity data and / or the geomagnetic activity data are input into the outer space plasma fusion model to calculate the space plasma parameters of the space region being traversed.

7. The method according to claim 1, characterized in that, The intrinsic plasma model corresponding to the intrinsic region includes at least one of the following: Ionospheric plasma environment model, inner magnetosphere plasma model, outer magnetosphere plasma environment model, plasmasphere environment model, magnetosheath plasma model, solar wind plasma model, and polar layer plasma environment model.

8. The method according to any one of claims 1 to 7, characterized in that, The orbital type of the spacecraft includes at least one of the following: Low-inclination orbits, high-inclination orbits, MEO circular orbits, geosynchronous orbits, Lagrange point orbits, high apogee elliptical orbits, planetary orbits, and interplanetary cruise orbits.

9. A spacecraft outer space plasma environment analysis device, characterized in that, include: A space region determination module is used to determine the orbit type and the space regions traversed during on-orbit operation based on the spacecraft's operation plan; wherein the traversed space regions include multiple intrinsic regions and at least one transition region located between two adjacent intrinsic regions; A plasma model determination module is used to determine one or more plasma models of the outer space plasma fusion model in the space regions traversed by the spacecraft, based on the spacecraft's orbit type and the space regions it passes through during its on-orbit operation; wherein, the plasma models include intrinsic plasma models and transition fusion models; A transition fusion model determination module, used to determine the transition fusion model, the transition fusion model determination module comprising: A transition region unit is defined, which is used to determine the extent of the transition region based on the boundary of two adjacent intrinsic regions; A sub-partitioning unit is used to divide the transition area into multiple sub-partitions based on the range and partitioning strategy of the transition area; A fusion mode determination unit is used to determine the fusion mode of each sub-partition for each sub-partition, so as to obtain the transition fusion model corresponding to the transition area; A model module is selected, which is used to use the intrinsic plasma model corresponding to each intrinsic region in the plurality of intrinsic regions, and in the at least one transition region, a transition fusion model based at least on the intrinsic plasma model corresponding to the adjacent intrinsic regions is used. A plasma parameter determination module, used to determine plasma parameters of the space region traversed based on data from the current solar activity period and / or the current geomagnetic activity period, according to the plasma model; and An analysis module is used to analyze the charging and discharging effects occurring on the spacecraft surface based on the plasma parameters.

10. 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 as described in any one of claims 1 to 8.

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