A Monte Carlo simulation method for atomic oxygen or ultraviolet flux on spacecraft surface
By dividing the spacecraft surface mesh into two structural units, the problem of low accuracy and efficiency in Monte Carlo simulation calculations of spacecraft surface flux in existing technologies is solved, achieving efficient and accurate flux calculation and supporting the optimization of spacecraft surface coating materials.
Patent Information
- Application Number
- CN202210762501.8
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- Filing Date
- 2022-06-30
- Publication Date
- 2025-10-31
- Estimated Expiration
- 2042-06-30
AI Technical Summary
Existing Monte Carlo simulation methods for calculating atomic oxygen/ultraviolet radiation flux on spacecraft surfaces result in reduced accuracy or low efficiency, primarily due to neglecting the positional relationships between spacecraft components, leading to excessively high grid computation complexity.
The spacecraft surface mesh is divided into two structural units. The first structural unit is used to organize the mesh array, and the second structural unit is used to set the bounding box. The mesh units that simulate particle collisions are calculated through these structural units, and irrelevant mesh calculations are removed to keep the overall logic of the Monte Carlo simulation unchanged.
It significantly reduces the computation time of Monte Carlo simulations, improves the accuracy and efficiency of throughput calculations, provides accurate input data for the simulation of erosion and scouring of spacecraft surface coating materials, and supports spacecraft simulation experiments and design optimization.
Smart Images
Figure CN115204023B_ABST
Abstract
Description
Technical Field
[0001] This invention relates to the field of spacecraft simulation and calculation technology, and more specifically, to a Monte Carlo simulation method for atomic oxygen or ultraviolet flux on the surface of a spacecraft. Background Technology
[0002] Currently, most existing simulation software uses Monte Carlo simulation to calculate the atomic oxygen / ultraviolet radiation flux of each cell on the spacecraft surface. This method divides the spacecraft surface into grid cells and then calculates the flux of each grid cell by counting the number of simulated particles that collide with each grid cell in a given total number of experiments. In each random experiment, atomic oxygen particles / simulated ultraviolet radiation particles are generated at random locations, and their final velocities are synthesized based on the spacecraft's flight velocity and the thermodynamic velocity of atomic oxygen. The grid cells that the simulated particles collide with during their motion, as well as the grid cells they collide with after specular or diffuse reflection, are calculated. This method ignores the positional relationships between spacecraft components when dividing the grid, requiring each random experiment to traverse all grid cells on the spacecraft surface, causing the complexity of the flux calculation process to increase more than linearly. Therefore, an effective flux calculation process needs to limit both the number of grid cells and the total number of random experiments, but both approaches reduce the accuracy of the calculation results, causing a large deviation between the calculated results and the actual flux, and also reducing computational efficiency. Summary of the Invention
[0003] The problem addressed by this invention is that the existing method of using Monte Carlo simulation to calculate the atomic oxygen / ultraviolet irradiation flux of each unit on the spacecraft surface reduces the accuracy of the calculation results, causing a large deviation between the calculated results and the actual flux, or reducing the calculation efficiency in at least one aspect.
[0004] To address the above problems, this invention provides a Monte Carlo simulation method for atomic oxygen or ultraviolet flux on the surface of a spacecraft, comprising the following steps:
[0005] Step S1: Divide the spacecraft surface into multiple polygonal mesh units, obtain random experimental parameters at each motion trajectory point of the spacecraft, and unify the random experimental parameters into the body coordinate system of the spacecraft.
[0006] Step S2: Divide all the polygonal mesh units into first structural units and second structural units according to the structural relationship of the spacecraft components;
[0007] Step S3: Obtain the total number of simulated particles and their orientation at each point on the motion trajectory, and use the spatial environment parameters to obtain the position coordinates and relative motion direction of the simulated particles at the said orientation.
[0008] Step S4: Based on the position coordinates and relative motion direction of the simulated particles, calculate the polygonal mesh unit that each simulated particle touches using the first structural unit and the second structural unit;
[0009] Step S5: Based on the calculation results in step S4 and the total number of simulated particles, obtain the atomic oxygen flux or ultraviolet flux on the spacecraft surface.
[0010] Preferably, in step S4, the polygonal mesh cells touched by each simulated particle are calculated using the first structural unit and the second structural unit, including calculating the polygonal mesh cells touched by each simulated particle during its motion and the polygonal mesh cells touched after specular reflection or diffuse reflection.
[0011] Preferably, in step S1, the random experimental parameters are the subdivision nodes of the multiple polygonal mesh units.
[0012] Preferably, in step S2, the first structural unit is used to organize all the polygonal mesh units into an array, and each polygonal mesh unit is stored consecutively in the array.
[0013] Preferably, in step S2, the second structural unit is used to set the bounding box of each component and to store the start / end positions of the polygonal mesh units set in each bounding box in the array.
[0014] Preferably, at each trajectory point of the spacecraft, the bounding box vertices in the first structural unit and the polygonal mesh unit vertices in the second structural unit are updated according to the motion parameters of the spacecraft.
[0015] Preferably, in step S3, obtaining the total number of simulated particles and their orientation at each point on the motion track includes: obtaining the total number of simulated particles and their orientation at each point on the motion track based on the total number of random experiments.
[0016] Preferably, in step S4, the polygonal mesh element touched by each simulated particle is calculated based on the position and relative motion direction of the simulated particle, using the first structural unit and the second structural unit, including:
[0017] Step S41: Determine the bounding boxes that the simulated particles may collide with, and calculate the distance from the simulated particles to the collision point on each bounding box, so as to remove the calculations on the polygonal mesh cells on the surface of other components.
[0018] Step S42: Enumerate the polygonal mesh cells of one of the possible bounding box components that may be touched, and calculate the first polygonal mesh cell that the simulated particle touches during its movement and the distance from the simulated particle to the first polygonal mesh cell;
[0019] Step S43: Based on the distance of the simulated particle to the first polygonal mesh cell and the distance of the simulated particle to the collision point on the other bounding boxes, determine to stop enumerating the polygonal mesh cells of the other possible touching bounding box components, so as to prune the calculations on the polygonal mesh cells on the surfaces of other components.
[0020] Preferably, in step S43, determining the polygonal mesh cells to stop enumerating other potentially touched components within the bounding box based on the distance between the simulated particle and the first polygonal mesh cell and the distance between the simulated particle and the collision points on the other bounding boxes includes:
[0021] When the distance from the simulated particle to the collision point on another bounding box is greater than the distance from the simulated particle to the first polygonal mesh cell, the enumeration of polygonal mesh cells of other possible touching bounding box components is stopped.
[0022] Preferably, in step S4, based on the position and relative motion direction of the simulated particles, and by calculating the polygonal mesh element touched by each simulated particle using the first structural unit and the second structural unit, the method further includes:
[0023] Step S44: After the simulated particle undergoes specular or diffuse reflection at the collision point with the first polygonal mesh unit or the collision point with the bounding box, the motion process of the simulated particle repeats steps S41-S43 until the number of specular or diffuse reflections reaches a set upper limit, thus obtaining the polygonal mesh unit touched by the simulated particle.
[0024] The Monte Carlo simulation method for atomic oxygen or ultraviolet flux on spacecraft surfaces described in this invention has the advantage of utilizing the positional relationships between spacecraft components to organize the meshed structure of the spacecraft surface into a two-layer structure, namely a first structural unit and a second structural unit. This hierarchical structure significantly reduces the number of meshes involved in each random experiment without altering the overall logic of existing Monte Carlo simulations. The steps are simple and easy to operate. Furthermore, the accelerated Monte Carlo simulation method proposed in this invention can significantly reduce the time required for large-scale Monte Carlo simulations, providing accurate input data for optimizing the erosion and scouring simulation of spacecraft surface coating materials. This is of great significance for spacecraft simulation experiments and design optimization. It has obvious advantages and broad application prospects in the study of atomic oxygen / ultraviolet radiation flux effects on spacecraft surfaces and in the application of radiation hardening technology. Attached Figure Description
[0025] Figure 1 This is a flowchart of the Monte Carlo simulation method for atomic oxygen or ultraviolet flux on the spacecraft surface in an embodiment of the present invention;
[0026] Figure 2 This is a schematic diagram of the Monte Carlo simulation results of the atomic oxygen flux on the spacecraft surface without considering the structural relationships of spacecraft components in this embodiment of the invention.
[0027] Figure 3 This is a schematic diagram of the Monte Carlo simulation results of the atomic oxygen flux on the spacecraft surface considering the structural relationships of spacecraft components in an embodiment of the present invention.
[0028] Figure 4 This is a schematic diagram of the Monte Carlo simulation results of the ultraviolet intensity on the surface of a spacecraft without considering the structural relationships of spacecraft components in an embodiment of the present invention.
[0029] Figure 5 This is a schematic diagram of the Monte Carlo simulation results of the ultraviolet intensity on the spacecraft surface considering the structural relationship of spacecraft components in an embodiment of the present invention. Detailed Implementation
[0030] The technical solutions in the embodiments of this application will be clearly and thoroughly described below with reference to the accompanying drawings.
[0031] In the description of the embodiments in this application, the term "some embodiments" means that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of the present invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same implementation or instance. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples.
[0032] It should also be noted that, in the description of the embodiments of this application, the term "comprising" or any other variations thereof is intended to cover non-exclusive inclusion, such that a process, method, article, or terminal device that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or terminal device. Without further limitations, an element defined by the phrase "comprising..." does not exclude the presence of other identical elements in the process, method, article, or terminal device that includes said element.
[0033] like Figure 1 As shown, this embodiment of the invention provides a Monte Carlo simulation method for atomic oxygen or ultraviolet flux on a spacecraft surface, comprising the following steps:
[0034] Step S1: Divide the spacecraft surface into multiple polygonal mesh units, obtain random experimental parameters at each motion trajectory point of the spacecraft, and unify the random experimental parameters into the body coordinate system of the spacecraft.
[0035] Step S2: Divide all the polygonal mesh units into first structural units and second structural units according to the structural relationship of the spacecraft components;
[0036] Step S3: Obtain the total number of simulated particles and their orientation at each point on the motion trajectory, and use the spatial environment parameters to obtain the position coordinates and relative motion direction of the simulated particles at the said orientation.
[0037] Step S4: Based on the position coordinates and relative motion direction of the simulated particles, calculate the polygonal mesh unit that each simulated particle touches using the first structural unit and the second structural unit;
[0038] Step S5: Based on the calculation results in step S4 and the total number of simulated particles, obtain the atomic oxygen flux or ultraviolet flux on the spacecraft surface.
[0039] Therefore, this embodiment organizes the meshed surface of the spacecraft into a two-layer structure—a first structural unit and a second structural unit—based on the positional relationships of the spacecraft component structures. This hierarchical structure is used to remove irrelevant meshes, accelerating computation. This significantly reduces computation time while maintaining consistent results, provided the input mesh and the total number of random experiments remain the same. Furthermore, within the same computation time, the accuracy of atomic oxygen / ultraviolet irradiation flux calculations can be improved by refining the mesh or increasing the total number of random experiments. This invention shortens the response time of the Monte Carlo method and provides users with flexibility in selecting mesh density and the total number of random experiments.
[0040] It should be noted that in this embodiment, the first structural unit is located at the bottom layer of the spacecraft structure, and the second structural unit is located at the top layer of the spacecraft structure. Thus, the positional relationship of the spacecraft component structures organizes the mesh of the spacecraft surface into a two-layer structure, which is simple and facilitates subsequent calculations.
[0041] In some embodiments, step S4, calculating the polygonal mesh cells touched by each of the simulated particles using the first structural unit and the second structural unit, includes calculating the polygonal mesh cells touched by each of the simulated particles during motion and the polygonal mesh cells touched after specular reflection or diffuse reflection using the first structural unit and the second structural unit.
[0042] In some embodiments, in step S1, the random experimental parameters are the subdivision nodes of the plurality of polygonal mesh cells. This determines the position of each polygonal mesh cell.
[0043] In some embodiments, in step S2, the first structural unit is used to organize all the polygonal mesh units into an array, and each polygonal mesh unit is stored consecutively in the array. This facilitates subsequent ordered calculations.
[0044] In some embodiments, in step S2, the second structural unit is used to define the bounding box of each component and to store the start / end positions of the polygonal mesh cells set within each bounding box in the array. This facilitates subsequent calculations.
[0045] In some embodiments, at each trajectory point of the spacecraft, the bounding box vertices within the first structural unit and the polygonal mesh unit vertices within the second structural unit are updated according to the spacecraft's motion parameters. This makes the calculation more accurate and precise.
[0046] In some embodiments, step S3, obtaining the total number of simulated particles and their orientation at each point on the motion trajectory, includes: obtaining the total number of simulated particles and their orientation at each point on the motion trajectory based on the total number of random experiments. This makes the calculation simple and accurate.
[0047] In some embodiments, step S4, calculating the polygonal mesh cells touched by each simulated particle based on the position and relative motion direction of the simulated particle, using the first structural unit and the second structural unit, includes:
[0048] Step S41: Determine the bounding boxes that the simulated particles may collide with, and calculate the distance from the simulated particles to the collision point on each bounding box, so as to remove the calculations on the polygonal mesh cells on the surface of other components.
[0049] Step S42: Enumerate the polygonal mesh cells of one of the possible bounding box components that may be touched, and calculate the first polygonal mesh cell that the simulated particle touches during its movement and the distance from the simulated particle to the first polygonal mesh cell;
[0050] Step S43: Based on the distance of the simulated particle to the first polygonal mesh cell and the distance of the simulated particle to the collision point on the other bounding boxes, determine to stop enumerating the polygonal mesh cells of the other possible touching bounding box components, so as to prune the calculations on the polygonal mesh cells on the surfaces of other components.
[0051] Therefore, by performing two pruning operations, the speed of Monte Carlo simulation is greatly accelerated, and the computational efficiency is improved.
[0052] It should be noted that step S4 is equivalent to the motion process of each simulated particle, which is equivalent to a random experiment.
[0053] In some embodiments, step S43, determining whether to stop enumerating polygonal mesh cells of other potentially touched bounding box components based on the distance of the simulated particle to the first polygonal mesh cell and the distance of the simulated particle to collision points on other bounding boxes, includes:
[0054] When the distance from the simulated particle to the collision point on another bounding box is greater than the distance from the simulated particle to the first polygonal mesh cell, enumeration of polygonal mesh cells of other potentially collided components within the bounding box is stopped. This prunes the calculations on polygonal mesh cells on the surfaces of other components, thus speeding up Monte Carlo simulations and improving computational efficiency.
[0055] In some embodiments, step S4, which calculates the polygonal mesh cell touched by each simulated particle based on the position and relative motion direction of the simulated particle and using the first structural unit and the second structural unit, further includes:
[0056] Step S44: After the simulated particle undergoes specular or diffuse reflection at the collision point with the first polygonal mesh unit or the collision point with the bounding box, the motion process of the simulated particle repeats steps S41-S43 until the number of specular or diffuse reflections reaches a set upper limit, thus obtaining the polygonal mesh unit touched by the simulated particle.
[0057] Therefore, the specular or diffuse reflection that occurs during the motion of simulated particles is fully considered, making the calculation more accurate and improving the calculation precision.
[0058] It should be noted that, in this embodiment, the specular or diffuse reflection that the simulated particles undergo during motion is determined by the properties of the coating materials on the surfaces of various spacecraft components. Different properties result in different numbers of specular or diffuse reflections.
[0059] In this embodiment, step S5, based on the calculation results in step S4 and the total number of simulated particles, obtains the atomic oxygen flux or ultraviolet flux on the spacecraft surface, including: based on the calculation results in step S4 and the total number of simulated particles, obtaining the number of simulated particles that collide with each grid cell in a given total number of experiments, and then obtaining the atomic oxygen flux or ultraviolet flux on the spacecraft surface.
[0060] Therefore, the Monte Carlo simulation method for atomic oxygen or ultraviolet flux on spacecraft surfaces described in this embodiment has the advantage over existing technologies in that it utilizes the positional relationships between spacecraft components to organize the meshed structure of the spacecraft surface into a two-layer structure, namely a first structural unit and a second structural unit. This hierarchical structure significantly reduces the number of meshes involved in each random experiment without altering the overall logic of existing Monte Carlo simulations. The steps are simple and easy to operate. Furthermore, the Monte Carlo simulation acceleration method proposed in this embodiment can significantly reduce the time required for large-scale Monte Carlo simulations, providing accurate input data for optimizing the erosion and scouring simulation of spacecraft surface coating materials. This is of great significance for spacecraft simulation experiments and design optimization. It has obvious advantages and broad application prospects in the study of atomic oxygen / ultraviolet radiation flux effects on spacecraft surfaces and in the application of radiation-resistant hardening technologies.
[0061] Example 1
[0062] This invention provides a Monte Carlo simulation method for atomic oxygen or ultraviolet flux on a spacecraft surface, comprising the following steps:
[0063] (1) Divide the spacecraft surface into multiple polygonal mesh units, obtain random experimental parameters at each motion trajectory point of the spacecraft, and unify the subdivision nodes of all the polygonal mesh units at each motion trajectory point of the spacecraft to the body coordinate system of the spacecraft.
[0064] (2) According to the structural relationship of the spacecraft components, all the polygonal mesh units are divided into a first structural unit at the bottom and a second structural unit at the top. The first structural unit is used to organize all the polygonal mesh units into an array, and each polygonal mesh unit is stored continuously in the array. The second structural unit is used to set the bounding box of each component and to store the start / end position of the polygonal mesh unit set in each bounding box in the array. At each trajectory point of the spacecraft, the vertices of the bounding box in the first structural unit and the vertices of the polygonal mesh unit in the second structural unit are updated according to the motion parameters of the spacecraft.
[0065] (3) Obtain the total number of simulated particles and their orientation at each point on the motion track based on the total number of random experiments, and use the spatial environment parameters to obtain the position coordinates and relative motion direction of the simulated particles at the said orientation.
[0066] (4) Based on the position coordinates and relative motion direction of the simulated particles, and using the first and second structural units, calculate the polygonal mesh elements touched by each simulated particle, specifically including:
[0067] First, determine the bounding boxes that the simulated particles may collide with, and calculate the distance from the simulated particles to the collision point on each bounding box, so as to remove the calculations on the polygonal mesh cells on the surface of other components.
[0068] Then enumerate the polygonal mesh cells of one of the possible bounding box components, and calculate the first polygonal mesh cell that the simulated particle touches during its movement and the distance from the simulated particle to the first polygonal mesh cell;
[0069] Furthermore, based on the distance between the simulated particle and the first polygonal mesh cell and the distance between the simulated particle and the collision point on the other bounding boxes, it is determined to stop enumerating the polygonal mesh cells of the other possible touching bounding box components, so as to prune the calculations on the polygonal mesh cells on the surface of other components.
[0070] Finally, after the simulated particle undergoes specular or diffuse reflection at the collision point with the first polygonal mesh cell or the collision point with the bounding box, the motion process of the simulated particle repeats the above steps until the number of specular or diffuse reflections reaches a set upper limit, thus obtaining the polygonal mesh cell touched by the simulated particle.
[0071] (5) Based on the calculation results in step S4 and the total number of simulated particles, the number of simulated particles that touch each grid cell in the given total number of experiments is obtained, and then the atomic oxygen flux or ultraviolet flux on the spacecraft surface is obtained.
[0072] Example 2
[0073] To verify the effectiveness of the Monte Carlo simulation method for spacecraft surface atomic oxygen or ultraviolet flux based on the structural relationships of spacecraft components in Example 1, this example uses the same mesh density, particle number, particle reflection number, and nucleus number to calculate the Monte Carlo simulation method for atomic oxygen / ultraviolet flux without considering the structural relationships of spacecraft components, for comparison. Figure 2-5 As shown, Figure 2This is a schematic diagram of the Monte Carlo simulation results of the atomic oxygen flux on the spacecraft surface without considering the structural relationships of spacecraft components in this embodiment. The calculation time is 666.234. Figure 3 This is a schematic diagram of the Monte Carlo simulation results of the spacecraft surface atomic oxygen flux considering the structural relationships of spacecraft components in Example 1. The calculation time is 121.653 seconds. Figure 4 This is a schematic diagram of the Monte Carlo simulation results of the ultraviolet intensity on the spacecraft surface without considering the structural relationships of spacecraft components in this embodiment. The calculation time is 251.648. Figure 5 This is a schematic diagram illustrating the Monte Carlo simulation results of the spacecraft surface ultraviolet intensity considering the structural relationships of spacecraft components in Example 1. The calculation time was 42.537 seconds. Figure 2 and Figure 3 In this system, the amount of atomic oxygen flux is represented by variations in color intensity; the darker the color, the greater the atomic oxygen flux. Figure 4 and Figure 5 In the figure, the magnitude of ultraviolet irradiance flux is represented by variations in color intensity; the darker the color, the greater the ultraviolet irradiance flux. As can be seen from the figure, the Monte Carlo simulation method for atomic oxygen or ultraviolet flux on the spacecraft surface based on the structural relationships of spacecraft components in Example 1 has significantly improved computational efficiency compared to the Monte Carlo simulation method for atomic oxygen / ultraviolet flux in this example, which does not consider the structural relationships of spacecraft components.
[0074] While the present invention has been disclosed above, its scope of protection is not limited thereto. Those skilled in the art can make various changes and modifications without departing from the spirit and scope of the present invention, and all such changes and modifications will fall within the scope of protection of the present invention.
Claims
1. A Monte Carlo simulation method for atomic oxygen or ultraviolet flux on the surface of a spacecraft, characterized in that, Includes the following steps: Step S1: Divide the spacecraft surface into multiple polygonal mesh units, obtain random experimental parameters at each motion trajectory point of the spacecraft, and unify the random experimental parameters into the body coordinate system of the spacecraft. Step S2: According to the structural relationship of the spacecraft components, all the polygonal mesh units are divided into a first structural unit and a second structural unit. The first structural unit is used to organize all the polygonal mesh units into an array, and each polygonal mesh unit is stored continuously in the array. The second structural unit is used to set the bounding box of each component and to store the start / end position of the polygonal mesh units set in each bounding box in the array. Step S3: Obtain the total number of simulated particles and their orientation at each point on the motion trajectory, and use the spatial environment parameters to obtain the position coordinates and relative motion direction of the simulated particles at the said orientation. Step S4, based on the position coordinates and relative motion direction of the simulated particles, and using the first structural unit and the second structural unit, calculates the polygonal mesh unit that each simulated particle touches, including: Step S41: Determine the bounding boxes that the simulated particles may touch, and calculate the distance from the simulated particles to the collision point on each bounding box to remove calculations on the polygonal mesh cells on the surfaces of other components. Step S42: Enumerate the polygonal mesh cells of one of the possible bounding box components that may be touched, and calculate the first polygonal mesh cell that the simulated particle touches during its movement and the distance from the simulated particle to the first polygonal mesh cell; Step S43: Based on the distance of the simulated particle to the first polygonal mesh cell and the distance of the simulated particle to the collision point on the other bounding boxes, determine to stop enumerating the polygonal mesh cells of the other possible touching bounding box components, so as to prune the calculations on the polygonal mesh cells on the surface of other components. Step S5: Based on the calculation results in step S4 and the total number of simulated particles, obtain the atomic oxygen flux or ultraviolet flux on the spacecraft surface.
2. The Monte Carlo simulation method for atomic oxygen or ultraviolet flux on the spacecraft surface according to claim 1, characterized in that, In step S4, the polygonal mesh cells touched by each simulated particle are calculated using the first structural unit and the second structural unit. This includes calculating the polygonal mesh cells touched by each simulated particle during its motion and the polygonal mesh cells touched after specular or diffuse reflection.
3. The Monte Carlo simulation method for atomic oxygen or ultraviolet flux on the spacecraft surface according to claim 1, characterized in that, In step S1, the random experimental parameters are the subdivision nodes of the multiple polygonal mesh units.
4. The Monte Carlo simulation method for atomic oxygen or ultraviolet flux on the spacecraft surface according to claim 1, characterized in that, At each trajectory point of the spacecraft, the bounding box vertices in the second structural unit and the polygonal mesh unit vertices in the first structural unit are updated according to the motion parameters of the spacecraft.
5. The Monte Carlo simulation method for atomic oxygen or ultraviolet flux on the spacecraft surface according to claim 4, characterized in that, In step S3, obtaining the total number of simulated particles and their orientation at each point on the motion track includes: obtaining the total number of simulated particles and their orientation at each point on the motion track based on the total number of random experiments.
6. The Monte Carlo simulation method for atomic oxygen or ultraviolet flux on the spacecraft surface according to claim 5, characterized in that, In step S43, determining the polygonal mesh cells to stop enumerating other potentially touched components within the bounding box based on the distance between the simulated particle and the first polygonal mesh cell and the distance between the simulated particle and the collision points on the other bounding boxes includes: When the distance from the simulated particle to the collision point on another bounding box is greater than the distance from the simulated particle to the first polygonal mesh cell, the enumeration of polygonal mesh cells of other possible touching bounding box components is stopped.
7. The Monte Carlo simulation method for atomic oxygen or ultraviolet flux on the spacecraft surface according to claim 6, characterized in that, In step S4, based on the position and relative motion direction of the simulated particles, and by calculating the polygonal mesh element that each simulated particle touches using the first structural unit and the second structural unit, the method further includes: Step S44: After the simulated particle undergoes specular or diffuse reflection at the collision point with the first polygonal mesh unit or the collision point with the bounding box, the motion process of the simulated particle repeats steps S41-S43 until the number of specular or diffuse reflections reaches a set upper limit, thus obtaining the polygonal mesh unit touched by the simulated particle.