Dynamic Adjustment Method of Spacecraft Model Parameters in Deep Charging Simulation

Abstract

The present invention relates to a method for dynamically adjusting spacecraft model parameters in a deep charging simulation, including: setting the default material density of each spacecraft component in the spacecraft model through a simulation platform; performing spatial grid division on the spacecraft model; setting multiple focus points in multiple cells, setting multiple rays along multiple directions with each focus point as the origin, and obtaining multiple ray vectors; determining the total number of ray vectors passing through each component; respectively determining the intersection length of each ray vector with each component passed through and the equivalent shielding surface density of each component; based on the equivalent shielding surface density of each component, calculating the average surface density of the spacecraft model; dynamically adjusting the material density value of each component in the spacecraft model until the difference between the average surface density and the reference value meets the requirements. The embodiments of the present application can realize automatic adjustment of the material density value of each component of the model, which can significantly improve the convenience of operation and simulation accuracy.

Description

Technical Field

[0001] The present application relates to the technical field of the influence of space radiation on spacecraft charging effect, and also to spacecraft deep charging simulation technology, and in particular to a method for dynamically adjusting spacecraft model parameters in deep charging simulation. Background Art

[0002] Deep charging of spacecraft refers to a charging phenomenon in which energetic charged particles penetrate the surface of a spacecraft and settle inside the spacecraft. The formation of deep charging is related to factors such as the high-energy electron environment and the properties of dielectric materials. Electrons with different energies deposit at different depths, eventually forming an interlayer charge structure in the dielectric and establishing an internal electric field. The establishment of this internal electric field will affect the operation of various components in the spacecraft. When the spacecraft is charged to a certain level, it may cause failures.

[0003] In the study of the impact of space radiation environment on the charging effect of on-orbit spacecraft, establishing a realistic three-dimensional model of the spacecraft is a key step. During the on-orbit operation of the spacecraft, the charge accumulation level of the internal devices affected by radiation is determined by many factors such as the extravehicular radiation environment, satellite structure, and materials.

[0004] The geometry and internal structure layout of the spacecraft 3D model can be designed based on drawings and related overall parameters. However, for high-energy particles that pass through the shield in the 4π direction and reach the cabin, the density of different model components on the traversal path is an important factor affecting the simulation results. Traditional manual configuration is not only inefficient but also inaccurate. Therefore, a more efficient and accurate parameter adjustment method is urgently needed to solve the above problems. Summary of the invention

[0005] In view of the technical problems existing in the prior art, the present application proposes a method for dynamically adjusting the parameters of a spacecraft model in a deep charging simulation, including: setting the material type and default material density value of each spacecraft component in the spacecraft model through a simulation platform, wherein the material type of the satellite platform is set to carbon fiber, the material type of the vacuum chamber is set to titanium, and the material type of the electrode cage is set to molybdenum alloy; performing spatial grid division on the spacecraft model to obtain a plurality of cells; setting a plurality of focus points in the plurality of cells, setting a plurality of rays along a plurality of directions with each focus point as the origin, to obtain a plurality of ray vectors, each ray vector passing through one or more components; determining the total number of ray vectors passing through each component, wherein the total number of rays passing through the i-th component is recorded as P. i; Based on the entity intersection method, combined with the default material density value of each component, the intersection length of each ray vector with each component passed through and the equivalent shielding surface density of each component are determined respectively; based on the equivalent shielding surface density of each component, the average surface density of the spacecraft model is calculated; the material density value of each component in the spacecraft model is dynamically adjusted, and the adjustment method is to increase or decrease the material density value according to a predetermined step size within a predetermined adjustment range, and the adjustment target is to reduce the difference between the average surface density of the spacecraft model and the reference value, and the reference value is determined by the actual material density value; wherein, during the dynamic adjustment process, if the absolute value of the difference between the average surface density and the reference value is greater than a first threshold value, the material density values ​​of all components are adjusted; if the absolute value of the difference is less than a second threshold value, the material density values ​​of all components are adjusted according to the P value of each component. i The material density values ​​of some or all components are adjusted in the order of small to large values, wherein the second threshold value is less than the first threshold value; if the absolute value of the difference is less than or equal to the first threshold value and greater than or equal to the second threshold value, then the ... i The material density values ​​of some or all components are adjusted in descending order until the difference between the average surface density and the reference value meets the requirement.

[0006] Optionally, the method further includes: taking the average surface density value closest to the reference value obtained during the dynamic adjustment process as the average surface density that meets the requirements.

[0007] Optionally, the entity intersection method is combined with the default material density value of each component to respectively determine the intersection length of each ray vector with each component passed through and the equivalent shielding surface density of each component, including: determining the intersection length of each ray vector with the spacecraft component passed through, determining the equivalent shielding surface density based on the intersection length and the default material density value of the spacecraft component, the equivalent shielding surface density is used to represent the attenuation ability of the spacecraft component to rays in the direction of the current ray vector; adding the equivalent shielding surface densities of each spacecraft component passed by multiple ray vectors, to obtain the total equivalent shielding surface density in the direction of each ray vector.

[0008] Optionally, the method also includes: calculating the spatial electron energy spectrum according to the total equivalent shielding surface density in each ray vector direction to obtain the spatial electron energy spectrum curve at the focus point in that direction; calculating the spatial electron energy spectrum curve of each ray vector at the focus point one by one, and summing the spatial electron energy spectra in all directions to obtain the spatial electron energy spectrum of the focus point.

[0009] Optionally, before determining the intersection length of each ray vector with the spacecraft component passed through, the method further includes: preprocessing the spacecraft model, wherein the preprocessing includes filtering out components or parts in the model that are not suitable for participating in the solid intersection method shielding analysis.

[0010] Optionally, when setting the default material density value, the default material density value of the satellite platform is set to 0.4 g / cm 3 , set the default material density value of the vacuum chamber material to 4.5g / cm 3 , set the default material density value of the electrode cage to 10g / cm 3 .

[0011] Optionally, during the dynamic adjustment process, at least one of the following operations is performed: the adjustment range of the metal material density value is set to ±10% of the default material density value; the adjustment range of the carbon fiber composite material density value is set to 0.3 g / cm 3 Up to 1.9g / cm 3 ; Set the adjustment step of the density value of the metal material and the density value of the carbon fiber composite material to 1% of the adjustment range; Set the initial density value of the carbon fiber composite material to 1g / cm 3 ; First, adjust the density value of the metal material.

[0012] Optionally, the first threshold is 10% of the default material density value, and the second threshold is 5% of the default material density value.

[0013] The embodiments of the present application are different from the previous simulation method of simulating the external radiation intake into the spacecraft model. Instead, the simulation results are calculated from the inside out with the internal components of the spacecraft model as the focus, so that the core components of concern can be set as the origin, so that the impact of the simulated radiation on the core components is closer to the actual situation, and the calculation results are closer to the ideal value; the embodiments of the present application can realize automatic adjustment of the material density values ​​of each component of the model, which can significantly improve the convenience of operation and simulation accuracy, and avoid the inefficiency and errors of manual settings; the combination of the entity intersection method and the dynamic adjustment strategy makes the shielding surface density calculation more accurate, ensuring that the model surface density is consistent with the real spacecraft parameters, so as to be closer to the actual effect. The embodiments of the present application can flexibly adapt to different material properties, facilitate further analysis and verification, and help to effectively improve the model after comparison with actual data, and improve the scientificity and reliability of radiation protection design. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Below, the preferred embodiments of the present application will be further described in detail with reference to the accompanying drawings, wherein:

[0015] Figure 1 It is a flowchart of a method for dynamically adjusting spacecraft model parameters in a deep charging simulation of an embodiment of the present application.

[0016] Figure 2 It is a schematic diagram of a three-dimensional satellite model after being imported into the OCC platform according to an embodiment of the present application.

[0017] Figure 3 It is a schematic diagram of the setting interface of the carbon fiber model material of an embodiment of the present application.

[0018] Figure 4 It is a schematic diagram of the focus point location and finite element division setting interface of an embodiment of the present application.

[0019] Figure 5 It is a schematic diagram of a flow chart of adjusting density parameters of various parts of a model according to an embodiment of the present application. DETAILED DESCRIPTION

[0020] In order to make the purpose, technical solution and advantages of the embodiments of the present application clearer, the technical solution in the embodiments of the present application will be clearly and completely described below in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of this application.

[0021] In the following detailed description, reference may be made to the various specification drawings that are part of the present application and are used to illustrate specific embodiments of the present application. In the accompanying drawings, similar reference numerals describe substantially similar components in different figures. The various specific embodiments of the present application are described below in sufficient detail so that a person of ordinary skill in the art with relevant knowledge and skills in the art can implement the technical solutions of the present application. It should be understood that other embodiments may also be used or structural, logical or electrical changes may be made to the embodiments of the present application.

[0022] Figure 1 A method for dynamically adjusting spacecraft model parameters in a deep charging simulation according to an embodiment of the present application includes:

[0023] Step S101: setting the material type and default material density value of each spacecraft component in the spacecraft model through the simulation platform, wherein the material type of the satellite platform is set to carbon fiber, the material type of the vacuum chamber is set to titanium, and the material type of the electrode cage is set to molybdenum alloy.

[0024] Step S102: Divide the spacecraft model into spatial grids to obtain a plurality of cells.

[0025] Step S103: multiple focus points are set in multiple cells, and multiple rays are set along multiple directions with each focus point as the origin to obtain multiple ray vectors, each ray vector passing through one or more components.

[0026] Step S104: Determine the total number of ray vectors passing through each component, where the total number of rays passing through the i-th component is recorded as Pi .

[0027] Step S105: Based on the entity intersection method and in combination with the default material density value of each component, the intersection length between each ray vector and each component passed through and the equivalent shielding surface density of each component are determined respectively.

[0028] Step S106: Based on the equivalent shielding surface density of each component, the average surface density of the spacecraft model is calculated.

[0029] Step S107: Dynamically adjust the material density value of each component in the spacecraft model, the adjustment method is to increase or decrease the material density value in a predetermined step within a predetermined adjustment range, and the adjustment target is to reduce the difference between the average surface density of the spacecraft model and the reference value, and the reference value is determined by the actual material density value. In the dynamic adjustment process, if the absolute value of the difference between the average surface density and the reference value is greater than a first threshold, the material density values ​​of all components are adjusted; if the absolute value of the difference is less than a second threshold, the material density values ​​of all components are adjusted according to the P value of each component. i The material density values ​​of some or all components are adjusted in the order of small to large values, wherein the second threshold value is less than the first threshold value; if the absolute value of the difference is less than or equal to the first threshold value and greater than or equal to the second threshold value, then the ... i The material density values ​​of some or all components are adjusted in descending order until the difference between the average surface density and the reference value meets the requirement.

[0030] The embodiment of the present application is different from the previous simulation of external radiation intake into the spacecraft model. Instead, it focuses on its internal components and calculates the simulation results from the inside out. In this way, the core component of concern can be directly set as the origin, the path of the simulated ray has a greater impact on the core component, and the calculation result is closer to the ideal value. The embodiment of the present application automatically adjusts the material density value of each component of the model, and the scheme significantly improves the convenience of operation and simulation accuracy, avoiding the inefficiency and error of manual setting. The combination of the entity intersection method and the dynamic adjustment strategy makes the shielding surface density calculation more accurate, ensuring that the model surface density is consistent with the real spacecraft parameters, so as to be closer to the actual effect. Finite element meshing combined with the uniform ray path in the 4π space can fully simulate the real space radiation environment and provide reliable data support for on-orbit protection design. The spacecraft model is spatially meshed, and the number of grids can be set. The increase in the number of grids will lead to an exponential increase in computing power requirements. Generally, the default number of grids is 1024. At the same time, by identifying the shielding effect of important components and flexibly adjusting the material density, the scheme optimizes the protection effect and improves the rationality of material selection and structural design. In addition, the embodiments of the present application can flexibly adapt to different material properties, facilitate further analysis and verification, and can effectively improve the model after comparison with actual data to ensure the scientificity and reliability of radiation protection design.

[0031] In some embodiments, the average surface density value closest to the reference value obtained during the dynamic adjustment process is used as the average surface density that meets the requirements.

[0032] Taking the average surface density value closest to the reference value obtained during the dynamic adjustment process as the standard that meets the requirements helps to find the optimal density configuration during the adjustment process. This measure ensures that the final surface density value is closest to the actual requirements, thereby improving the simulation accuracy and reliability of the model.

[0033] In some embodiments, the intersection length of each ray vector and the spacecraft component it passes through is determined, and the equivalent shielding surface density is determined based on the intersection length and the default material density value of the spacecraft component. The equivalent shielding surface density is used to represent the attenuation capability of the spacecraft component to rays in the direction of the current ray vector. The equivalent shielding surface densities of each spacecraft component passed by multiple ray vectors are added together to obtain the total equivalent shielding surface density in the direction of each ray vector.

[0034] Based on the solid intersection method, the intersection length of each ray vector and the component it passes through and the equivalent shielding surface density can be calculated to accurately evaluate the radiation attenuation capability of each component of the spacecraft. By combining these calculation results, the overall radiation protection capability of the spacecraft can be obtained, and the shielding effect of different components can be accurately described.

[0035] In some embodiments, the spatial electron energy spectrum is calculated based on the total equivalent shielding surface density in each ray vector direction to obtain the spatial electron energy spectrum curve at the focus point in that direction; the spatial electron energy spectrum curve of each ray vector at the focus point is calculated one by one, and the spatial electron energy spectra in all directions are summed to obtain the spatial electron energy spectrum of the focus point.

[0036] By calculating the total equivalent shielding surface density in each ray vector direction, further calculating the space electron energy spectrum, and combining the energy spectrum data in all directions, the space electron energy spectrum of the spacecraft at each point of interest is obtained. This can provide a comprehensive evaluation of the radiation protection capability of the spacecraft and make the data of the simulation model closer to the real value.

[0037] In some embodiments, before determining the intersection length between each ray vector and the spacecraft component it passes through, the spacecraft model is preprocessed, and the preprocessing includes filtering out components or parts in the model that are not suitable for participating in the solid intersection method shielding analysis.

[0038] Before performing shielding analysis, preprocessing can be used to remove components or parts that are not suitable for solid intersection analysis, which can reduce the complexity of calculations and improve efficiency. Filtering out irrelevant parts avoids unnecessary resource consumption during the calculation process, thereby improving simulation accuracy and calculation speed.

[0039] In some embodiments, when setting the default material density value, the default material density value of the satellite platform is set to 0.4 g / cm 3 Up to 0.6g / cm 3 , for example 0.4g / cm 3 Set the default material density value for the vacuum chamber material to 4.5g / cm 3 , set the default material density value of the electrode cage to 10g / cm 3 .

[0040] Setting a reasonable material density can effectively simulate the shielding effect of spacecraft. The density changes of different materials in the simulation will affect the penetration depth of the ray in the material, thereby changing the calculation results of the shielding surface density. Reasonable setting of default values ​​will help improve the efficiency of subsequent dynamic adjustments.

[0041] In some embodiments, during the dynamic adjustment process, at least one of the following operations is performed:

[0042] 1) Set the adjustment range of metal material density value to ±10% of the default material density value;

[0043] 2) The density value of the carbon fiber composite material is adjusted to 0.3g / cm 3 Up to 1.9g / cm 3 ;

[0044] 3) The adjustment step of the density value of the metal material and the density value of the carbon fiber composite material is set to 1% of the adjustment range;

[0045] 4) Set the initial density of the carbon fiber composite material to 1g / cm 3 ;

[0046] 5) First, adjust the density value of the metal material.

[0047] Reasonable setting of density variation range, adjustment step and initial value can improve the accuracy and efficiency of the adjustment process.

[0048] In some embodiments, the first threshold is 10% of the default material density value.

[0049] In some embodiments, the second threshold is 5% of the default material density value.

[0050] Dynamically adjusting the material density value achieves a shielding effect closer to reality by adjusting the density of each component in a hierarchical and prioritized manner. It can continuously optimize the density distribution of the model based on the simulation error, providing an important simulation basis for the protection design of spacecraft.

[0051] In some embodiments, when calculating the equivalent shielding surface density, in each direction, the intersection length and material density of each segment are used to convert the equivalent aluminum shielding length of each segment, and the equivalent aluminum shielding surface density in this direction is obtained by summing up. By setting the focus point and spatial resolution in the cabin, the total equivalent aluminum shielding length of the focus position is automatically calculated.

[0052] The advantage of using equivalent aluminum length is that it provides a unified comparison standard, simplifies the calculation process, and accurately evaluates the protection effect. The shielding performance of different materials varies due to different densities and thicknesses. By converting the shielding capabilities of various materials into equivalent aluminum thickness, a unified evaluation of the protection effect can be achieved, so that the shielding effects of different materials can be directly compared with the performance of aluminum, which is convenient for optimization and selection. At the same time, equivalent aluminum length simplifies the calculation, converting the shielding capabilities of various materials into equivalent aluminum thickness, facilitating the rapid calculation of the total shielding surface density and comparing it with the radiation protection standard. In addition, aluminum, as a commonly used standard material, has a wealth of protection performance data. The use of equivalent aluminum length helps to more accurately evaluate the shielding effect of complex structures in radiation environments, thereby optimizing material design and providing important support for the protection design and simulation of spacecraft.

[0053] In a specific embodiment, a spacecraft simulation model can be established based on a certain on-orbit satellite to describe the working process and verification results of the embodiment of the present application.

[0054] 1. Spacecraft Model Design

[0055] For example, the 3D modeling of spacecraft can be built using mainstream methods such as Pro / Engineer, which makes it easy to use the STEP format as an intermediate conversion file format to convert the 3D model file into a data stream file that can be used for simulation calculations. After the 3D model is established, a STEP format file is generated and imported into the geometric simulation platform. As an example, the geometric simulation platform can use the Open CASCADE (OCC) 3D design software platform. Simply put, OCC is a geometric modeling basic software platform that provides 3D surface modeling, solid modeling, data exchange, 3D visualization and other functions in the form of a C++ library. It can import model files such as Pro / E, automatically generate 3D models, position and move the models, etc., to achieve accurate modeling of the 3D structure of electromechanical products. Figure 2 The figure schematically shows the three-dimensional satellite model after being imported into the OCC platform, where the blue part is the three-dimensional satellite model and the model itself has been blurred.

[0056] (II) Spacecraft Component Material Setting

[0057] In the space radiation effect, there are two main methods for calculating the density of the shielding surface through which the ray is transmitted in the material: normal transmission (NORM) and linear transmission (SLANT). The shielding surface density calculated by normal transmission considers the transmission distance of the ray in the direction perpendicular to the surface of the shielding material, while linear transmission can intersect with any material surface at an angle. For complex shielding structures, normal transmission will overestimate the actual shielding surface density.

[0058] In the embodiment of the present application, the shielding surface density calculation for a specific direction inside the spacecraft uses the material surface density along the straight line in that direction as the shielding surface density. This simplification is reasonable because firstly, the primary components of the particles move in a straight line and contribute the most to the radiation effect. Secondly, the secondary components generated by high-energy particles in motion are also most densely distributed in the incident direction of the particles.

[0059] After converting the spacecraft 3D model file format, import it into the simulation platform and set the default material density value of the model. According to the embodiment of the present application, the satellite platform is set to composite carbon fiber material with a density of 0.4g / cm 3 ; Set the vacuum chamber material to titanium with a density of 4.5g / cm 3 ; The electrode cage is set to molybdenum alloy with a density of 10g / cm 3 . Figure 3 The setting interface of the carbon fiber model material is schematically shown, where the default material density value of satellite platform related components is set to 0.4g / cm 3 .

[0060] (III) Finite element division

[0061] After setting the default material density value of the spacecraft components, the spacecraft model is spatially meshed. The main purpose of spatial meshing is to establish a ray vector model and perform finite element meshing on the 4π solid space to prepare for the subsequent use of the entity intersection method to solve the three-dimensional shielding surface density. Currently, there are three main meshing forms: equal angle meshing, equal solid angle meshing, and optimized equal solid angle meshing. Spatial meshing should be able to quickly obtain the solid angle of the cell, the solid angles of each cell are similar, the cell shape is regular, and cells that are too narrow and long should be avoided.

[0062] (IV) Shielding surface density calculation

[0063] Next, we start to calculate the shielding surface density. First, in the model preprocessing, we use certain filtering methods to specify which components are involved in the shielding analysis calculation. We can filter out small parts such as fasteners and pins to improve the solution speed. Call the entity intersection function to perform entity intersection calculations between each component and the ray vector one by one to obtain the intersection length of the ray with each component. The equivalent shielding surface density of each component is obtained by multiplying by the material density and accumulating, and finally the total equivalent shielding surface density in one direction (or one ray vector) is obtained. The spatial electron energy spectrum corresponding to the total equivalent shielding surface density is calculated by difference in the spatial electron energy spectrum curve to obtain the final cabin space electron energy spectrum curve in that direction. Calculate the ray vector in each direction in a similar way to obtain the cabin electron energy spectrum curve in each direction, and sum the spatial electron energy spectra in all directions to obtain the spatial electron energy spectrum at the point of interest.

[0064] The algorithm of the entity intersection method is relatively simple, and there is no error caused by model simplification. The main task of the entity intersection method is to calculate the intersection length of the ray vector and the shielding plate, and by multiplying it with the material density, obtain the equivalent shielding surface density, and add up all the shielding surface densities to obtain the total shielding surface density in the direction of the ray vector. Combined with the dose-depth curve, the radiation dose encountered in this direction can be obtained. Finally, the doses in each direction are accumulated to obtain the total irradiation dose. The entity intersection method here mainly uses the calculation function provided by the OCC component 3D design software after the Pro / E software is converted into a STEP file to calculate the intersection length of a part model and a ray vector, that is, the equivalent surface density of the shielding layer of this part in the direction of this ray vector.

[0065] By setting the focus point and spatial resolution in the cabin, the three-dimensional omnidirectional equivalent shielding surface density of the focus point is automatically calculated. The equivalent shielding surface density is used to indicate the attenuation ability of the component to the ray in the direction of the current ray vector. The larger the equivalent shielding surface density, the stronger the attenuation of the ray in this direction. The three-dimensional rays are evenly distributed and emitted outward from the focus point, and the intersection length of each ray with each segment of the component it passes through is calculated. In addition, in each direction, the intersection length and density of each segment can be used to convert the equivalent aluminum shielding length of each segment, and the equivalent aluminum shielding thickness in this direction can be obtained by summing them up.

[0066] (V) Adjust the material density of each module of the spacecraft model

[0067] For each component in the spacecraft 3D model, the corresponding default density value is set after the material is set. However, since the density of most composite materials has a certain range, and composite components should not be set to the density value of a single material. Therefore, dynamic parameters are set for each component of the spacecraft 3D model to adjust the material density value of the component modules of the overall model. The schematic process is as follows:

[0068] (1) Spacecraft materials are divided into two categories: metal materials and carbon fiber composite materials. The density range of metal materials is relatively fixed. During the dynamic adjustment process, the density change range is set to ±10%. The density range of carbon fiber composite materials is 0.3g / cm 3 ~1.9 g / cm 3 .

[0069] (2) Divide the density range of metal materials and carbon fiber composite materials into 100 parts (default value, modifiable). The initial density value of carbon fiber composite materials can be 1 g / cm 3 Since metal materials have a high density, when making dynamic adjustments, the metal materials are adjusted first.

[0070] (3) During the deep charging simulation calculation process, the various components of the spacecraft play the role of shielding and dissipating the energy of the high-energy particles outside the cabin on the path of the incident to the point of interest. Since the high-energy particle radiation environment outside the spacecraft cabin is isotropic, the particle radiation effect on the analysis point is also uniformly distributed in the 4π space.

[0071] After calling the OCC platform to perform finite element settings on the spacecraft model (the default is 2048, that is, 2048 particle incident paths are evenly distributed in the omnidirectional space with the analysis point as the center), the number of rays passing through different components in the spacecraft model can be obtained. These components can effectively shield high-energy particle radiation. Therefore, the more components the rays pass through, the greater the impact of their density changes on the simulation calculation of spacecraft shielding protection. The components that are traversed by rays are recorded as P according to the number of rays passing through. i and press P i Sort the values ​​by size. Figure 4 The focus point locations and finite element mesh settings are schematically given, where values ​​such as 3D resolution can be set according to actual needs.

[0072] Figure 5 This is a schematic diagram of the process of adjusting the density parameters of each part of the model according to an embodiment of the present application. As shown in the figure, after the material is set, the corresponding default density value is available, and then the average surface density of the satellite model is calculated through the OCC platform. Then, based on the difference between it and the actual satellite surface density, choose how to dynamically adjust the weights of the model parameters of each component. Among them, the dynamic adjustment of the weights of the model parameters of each component can be adopted as follows:

[0073] a) When the surface density of the simulation model differs from the actual value of the satellite by more than ±10%, the density of all components of the satellite model is adjusted;

[0074] b) When the surface density of the simulation model differs from the true value of the satellite by ± (5% to 10%), the density of the satellite model components is adjusted from large to small according to the order of P;

[0075] c) When the surface density of the simulation model is less than ± (5%) of the actual value of the satellite, the density of the satellite components is adjusted in ascending order according to P;

[0076] d) Repeat the above steps until the closest adjustment value is obtained (compared with the actual satellite surface density).

[0077] By operating according to the above process of the embodiment of the present application, the simulation result of the satellite model can be obtained. Table 1 schematically lists part of the data of the model simulation result as follows:

[0078] Table 1

[0079] Finite element division (number) 2048 Average equivalent aluminum thickness (mm) 49.77 <![CDATA[Areal density (g / cm 2 ).]]> 13.44

[0080] The surface density of the satellite is known to be 13.8 g / cm 2 , then the error between the surface density of the satellite and the satellite model of the embodiment of the present application can be calculated as follows:

[0081] (13.44-13.8) / 13.8=-2.61%;

[0082] From the calculation results, we can see that the error is -2.61%, which meets the requirements of subsequent simulation tests (the specific required values ​​can be adjusted according to actual conditions). It can be determined that the spacecraft model is close to the structure and material density of the actual spacecraft, meets the actual use requirements, and can be used for subsequent simulation or calculation.

[0083] This scheme has shown many advantages in the simulation research of deep charging of spacecraft. By automatically adjusting the material density values ​​of each component of the model, the scheme significantly improves the convenience of operation and simulation accuracy, avoiding the inefficiency and errors of manual settings; the combination of the entity intersection method and the dynamic adjustment strategy makes the shielding thickness calculation more accurate, ensuring that the model surface density is consistent with the actual spacecraft parameters, thus closer to the actual effect. Finite element meshing combined with the uniform ray path of the 4π solid angle can fully simulate the real space radiation environment and provide reliable data support for on-orbit protection design. At the same time, by identifying the shielding effect of important components and flexibly adjusting the material density, the scheme optimizes the protection effect and improves the rationality of material selection and structural design. In addition, the scheme can flexibly adapt to different material properties, facilitate further analysis and verification, and can effectively improve the model after comparison with actual data to ensure the scientificity and reliability of radiation protection design.

[0084] The above is only a specific implementation of the present application. Those skilled in the art can clearly understand that for the convenience and simplicity of description, the specific working processes of the systems, modules and units described above can refer to the corresponding processes in the aforementioned method embodiments, and will not be repeated here. It should be understood that the protection scope of the present application is not limited to this. Any technician familiar with the technical field can easily think of various equivalent modifications or replacements within the technical scope disclosed in this application, and these modifications or replacements should be included in the protection scope of this application.

Claims

1. A method for dynamically adjusting spacecraft model parameters in deep charging simulation, characterized in that: include: The material type and default material density value of each spacecraft component in the spacecraft model are set through the simulation platform. The material type of the satellite platform is set to carbon fiber, the material type of the vacuum chamber is set to titanium, and the material type of the electrode cage is set to molybdenum alloy. The default material density value of the satellite platform is set to 0.4g / cm 3 Up to 0.6g / cm 3 ; Divide the spacecraft model into spatial grids to obtain multiple cells; A plurality of focus points are set in a plurality of cells, and a plurality of rays are set along a plurality of directions with each focus point as an origin to obtain a plurality of ray vectors, each ray vector passing through one or more components; Determine the total number of ray vectors that pass through each component, where the total number of rays passing through the i-th component is recorded as P i ; Based on the entity intersection method and combined with the default material density value of each component, the intersection length of each ray vector and each component it passes through and the equivalent shielding surface density of each component are determined respectively; Based on the equivalent shielding surface density of each component, the average surface density of the spacecraft model is calculated; The material density value of each component in the spacecraft model is dynamically adjusted by increasing or decreasing the material density value in a predetermined step within a predetermined adjustment range, and the adjustment target is to reduce the difference between the average surface density of the spacecraft model and a reference value, wherein the reference value is determined by the actual material density value; wherein, During the dynamic adjustment process, if the absolute value of the difference between the average surface density and the reference value is greater than a first threshold, the material density values ​​of all components are adjusted; If the absolute value of the difference is less than the second threshold, then the P i The material density values ​​of some or all components are adjusted in ascending order of value, wherein the second threshold value is less than the first threshold value; If the absolute value of the difference is less than or equal to the first threshold and greater than or equal to the second threshold, then the P i In descending order, the material density values ​​of some or all components are adjusted until the difference between the average surface density and the reference value meets the requirement; The first threshold is 10% of the default material density value, and the second threshold is 5% of the default material density value.

2. The method according to claim 1, characterized in that The method further includes: taking the average surface density value closest to the reference value obtained during the dynamic adjustment process as the average surface density that meets the requirements.

3. The method according to claim 1, characterized in that The entity intersection method is based on the default material density value of each component to determine the intersection length of each ray vector with each component passed through and the equivalent shielding surface density of each component, including: Determine the intersection length of each ray vector with the spacecraft component it passes through, and determine the equivalent shielding surface density based on the intersection length and the default material density value of the spacecraft component. The equivalent shielding surface density is used to represent the attenuation capability of the spacecraft component to the ray in the direction of the current ray vector. The equivalent shielding surface density of each spacecraft component passed by multiple ray vectors is added together to obtain the total equivalent shielding surface density in the direction of each ray vector.

4. The method according to claim 3, characterized in that The method further comprises: According to the total equivalent shielding surface density in each ray vector direction, the spatial electron energy spectrum is calculated to obtain the spatial electron energy spectrum curve at the focus point in the direction; The spatial electron energy spectrum curve of each ray vector at the focus point is calculated one by one, and the spatial electron energy spectrum in all directions is summed to obtain the spatial electron energy spectrum of the focus point.

5. The method according to claim 3 or 4, characterized in that: Before determining the intersection length of each ray vector with the spacecraft component passed through, the method further includes: The spacecraft model is preprocessed, and the preprocessing includes filtering out components or parts in the model that are not suitable for participating in the solid intersection method shielding analysis.

6. The method according to claim 1, characterized in that When setting the default material density value, the default material density value of the satellite platform is set to 0.4g / cm 3 , set the default material density value of the vacuum chamber material to 4.5g / cm 3 , set the default material density value of the electrode cage to 10g / cm 3 .

7. The method according to claim 1, characterized in that During the dynamic adjustment process, at least one of the following operations is performed: Set the adjustment range of metal material density value to ±10% of the default material density value; The density value of the carbon fiber composite material is adjusted to 0.3g / cm 3 Up to 1.9g / cm 3 ; The adjustment step of the density value of the metal material and the density value of the carbon fiber composite material is set to 1% of the adjustment range; The initial density of the carbon fiber composite material is set to 1g / cm 3 ; First, adjust the density value of the metal material.

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