A method and system for simulating and displaying the space environment effects of a spacecraft surface material

Abstract

The present invention provides a method and model for simulating and displaying the space environment effects of spacecraft surface materials, relating to the technical field of spacecraft simulation calculation. The method includes: establishing a three-dimensional model of the spacecraft and dividing the spacecraft surface into multiple polygon mesh units; inputting a first space environment parameter affecting the atomic oxygen flux on the outer surface of the spacecraft or a second space environment parameter affecting the ultraviolet irradiation intensity on the outer surface of the spacecraft into the three-dimensional model, calculating the polygon mesh units touched by atomic oxygen and / or ultraviolet irradiation simulation particles, obtaining the atomic oxygen and / or ultraviolet irradiation flux data on the spacecraft surface, and after data processing, obtaining the atomic oxygen and / or ultraviolet irradiation flux cloud map on the spacecraft surface and the erosion / etching depth change curve of the spacecraft surface material and / or the erosion / etching effect cloud map of the spacecraft surface material. The present invention is simple to operate, accurate in calculation, intuitive in display, and convenient for observation.

Description

Technical Field

[0001] The present invention relates to the technical field of spacecraft simulation calculation, and in particular, to a method and system for simulating and displaying the space environment effects of spacecraft surface materials. Background Art

[0002] In order to meet the growing demand for the development and utilization of space resources, higher requirements are put forward for the design life and reliability of modern spacecraft, and the impact of the space environment is becoming increasingly prominent. In addition to being affected by the main space environments such as vacuum, cold black, solar radiation, earth albedo, and the earth's own thermal radiation, some space environment effects that were originally considered weak can no longer be ignored, and their long-term cumulative effects need to be considered. Certain organic polymer materials are increasingly widely used as spacecraft surface materials and structural materials due to their high mechanical strength, good electrical properties, and desired thermal control properties. When a spacecraft flies in low earth orbit for a long time, these polymer materials will experience mass loss (erosion), surface oxidation, performance degradation, etc. under the action of atomic oxygen impact, ultraviolet radiation, and space debris impact, ultimately leading to material failure. However, in the prior art, in the simulation of the space environment effects of spacecraft surface materials, the influence of the satellite's three-dimensional structure and on-orbit operating state is not considered, and most of them only display the results through data, which is not accurate and intuitive enough. Summary of the Invention

[0003] The problem solved by the present invention is at least one aspect of the prior art that in the simulation of the space environment effects of spacecraft surface materials, the influence of the satellite's three-dimensional structure and on-orbit operating state is not considered, and most of them only display the results through data, which is not accurate and intuitive enough.

[0004] To solve the above problems, the present invention provides a method for simulating and displaying the space environment effects of spacecraft surface materials, which is characterized by including the following steps:

[0005] Step S1, establishing a three-dimensional model of the spacecraft and dividing the spacecraft surface into multiple polygon mesh units;

[0006] Step S2, inputting the first space environment parameter that affects the atomic oxygen flux on the outer surface of the spacecraft or the second space environment parameter that affects the ultraviolet radiation intensity on the outer surface of the spacecraft into the three-dimensional model, calculating the polygon mesh units touched by atomic oxygen and / or ultraviolet radiation simulation particles, obtaining the atomic oxygen and / or ultraviolet radiation flux data on the spacecraft surface, and after data processing, obtaining the atomic oxygen and / or ultraviolet radiation flux cloud map on the spacecraft surface;

[0007] Step S3: Obtain the spacecraft surface erosion effect data based on the atomic oxygen flux data on the spacecraft surface and the spacecraft surface material erosion reaction coefficient, and after data processing, obtain the spacecraft surface material erosion depth change curve and / or the spacecraft surface material erosion effect cloud map; and / or, obtain the spacecraft surface scooping erosion effect data based on the atomic oxygen flux data on the spacecraft surface and the spacecraft surface material scooping erosion reaction coefficient, and after data processing, obtain the spacecraft surface material scooping erosion depth change curve and / or the spacecraft surface material scooping erosion effect cloud map.

[0008] Preferably, the spacecraft surface material erosion depth change curve and / or the spacecraft surface material erosion effect cloud map, and / or, the spacecraft surface material scooping erosion depth change curve and / or the spacecraft surface material scooping erosion effect cloud map are all used to display the damage degree of the spacecraft surface material under the combined action of atomic oxygen and ultraviolet.

[0009] Preferably, the atomic oxygen and / or ultraviolet irradiation flux cloud map on the spacecraft surface includes the atomic oxygen and / or ultraviolet irradiation flux cloud map on the spacecraft surface based on point display or cell display.

[0010] Preferably, in step S2, the atomic oxygen and / or ultraviolet irradiation flux data on the spacecraft surface includes the instantaneous atomic oxygen or ultraviolet irradiation flux data on the spacecraft surface and the cumulative atomic oxygen or ultraviolet irradiation flux data on the spacecraft surface.

[0011] Preferably, in step S2, inputting the first space environment parameter affecting the atomic oxygen flux on the outer surface of the spacecraft or the second space environment parameter affecting the ultraviolet irradiation intensity on the outer surface of the spacecraft into the three-dimensional model to obtain the atomic oxygen and / or ultraviolet irradiation flux on the spacecraft surface includes:

[0012] Step S21: Input the first space environment parameter affecting the atomic oxygen flux on the outer surface of the spacecraft or the second space environment parameter affecting the ultraviolet irradiation intensity on the outer surface of the spacecraft into the three-dimensional model, calculate the polygon mesh cells touched by the atomic oxygen or ultraviolet irradiation simulation particles, and obtain the instantaneous atomic oxygen and / or ultraviolet irradiation flux on the spacecraft surface;

[0013] Step S22: Obtain the on-orbit flight time of the spacecraft, and obtain the cumulative atomic oxygen and / or ultraviolet irradiation flux on the spacecraft surface according to the instantaneous atomic oxygen or ultraviolet irradiation flux on the spacecraft surface and the on-orbit flight time of the spacecraft.

[0014] Preferably, in step S3, obtaining the spacecraft surface erosion effect data based on the atomic oxygen flux data on the spacecraft surface and the spacecraft surface material erosion reaction coefficient includes:

[0015] The erosion depth of the spacecraft surface material is obtained by multiplying the cumulative atomic oxygen flux on the spacecraft surface by the erosion reaction coefficient of the spacecraft surface material.

[0016] Preferably, in step S2, both the first space environment parameter and the second space environment parameter include the spacecraft quaternion, the six orbital elements, the longitude, latitude and altitude of the orbit, and the position of the solar array.

[0017] Preferably, in step S2, the first space environment parameter includes: the spacecraft velocity, the oncoming flow direction, and the atomic oxygen density.

[0018] Preferably, in step S2, the second space environment parameter includes: the ultraviolet irradiation intensity and the ultraviolet irradiation direction.

[0019] The advantage of the method for simulating and displaying the space environment effect of the spacecraft surface material according to the present invention compared with the prior art is that the method for simulating and displaying the space environment effect of the spacecraft surface material of the present invention takes into account the influence of the satellite three-dimensional structure and the on-orbit operation state, and can obtain the cloud maps of the atomic oxygen flux, ultraviolet intensity, surface erosion depth and pitting depth on the surface of the spacecraft or material as a whole and under the atomic oxygen and ultraviolet or comprehensive environment, and can also obtain the cloud maps of the atomic oxygen flux, ultraviolet intensity, surface erosion depth and pitting depth on the surface of a single grid cell under the atomic oxygen and ultraviolet or comprehensive environment. It is intuitive, accurate, and convenient to observe, provides a necessary basis for optimizing the ability of materials to resist space environment effects, has great significance for the research on the space environment synergy effect of materials, has obvious advantages and broad application prospects.

[0020] To solve the above technical problems, the present invention also provides a system for simulating and displaying the space environment effect of the spacecraft surface material, including:

[0021] A model establishment module, which is used to establish a three-dimensional model of the spacecraft and divide the spacecraft surface into a plurality of polygon grid cells;

[0022] An acquisition module, which is used to acquire the first space environment parameter affecting the atomic oxygen flux on the outer surface of the spacecraft and / or the second space environment parameter affecting the ultraviolet irradiation intensity on the outer surface of the spacecraft;

[0023] A calculation module, which is used to calculate the polygon grid cells touched by the atomic oxygen and / or ultraviolet irradiation simulation particles, and obtain the atomic oxygen and / or ultraviolet irradiation flux data on the spacecraft surface;

[0024] The calculation module is further used to obtain the erosion or pitting effect data on the spacecraft surface according to the atomic oxygen flux on the spacecraft surface and the erosion or pitting reaction coefficient of the spacecraft surface material;

[0025] A display module, which is used to display the erosion or gouging depth change curve of the spacecraft surface material and / or the erosion or gouging effect cloud map of the spacecraft surface material.

[0026] The advantages of the spacecraft surface material space environment effect simulation and display system and the spacecraft surface material space environment effect simulation and display method of the present invention are the same as those of the prior art, and will not be elaborated here. Description of the Drawings

[0027] Figure 1 It is a flowchart of the spacecraft surface material space environment effect simulation and display method in an embodiment of the present invention;

[0028] Figure 2 It is a cumulative atomic oxygen flux cloud map based on cell display obtained by using the spacecraft surface material space environment effect simulation and display method in an embodiment of the present invention;

[0029] Figure 3 It is a cumulative atomic oxygen flux cloud map based on point display obtained by using the spacecraft surface material space environment effect simulation and display method in an embodiment of the present invention;

[0030] Figure 4 It is a cumulative ultraviolet irradiation flux cloud map based on cell display obtained by using the spacecraft surface material space environment effect simulation and display method in an embodiment of the present invention;

[0031] Figure 5 It is a cumulative ultraviolet irradiation flux cloud map based on point display obtained by using the spacecraft surface material space environment effect simulation and display method in an embodiment of the present invention. Detailed Embodiments

[0032] Next, the technical solutions in the embodiments of the present application will be clearly and elaborately described with reference to the accompanying drawings.

[0033] In the description of the embodiments of the present application, the description of the term "some embodiments" means that the specific features, structures, materials, or characteristics described in connection with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic representation of the above terms does not necessarily refer to the same embodiment or instance. Moreover, the specific features, structures, materials, or characteristics described may be combined in any one or more embodiments or examples in a suitable manner.

[0034] It should also be noted that in the description of the embodiments of the present application, the term "including" or any other variant thereof is intended to cover non-exclusive inclusion, so that a process, method, article or terminal device including a series of elements not only includes those elements, but also includes other elements not expressly listed, or elements inherent to such a process, method, article or terminal device. Without further limitation, the elements defined by the statement "including..." do not exclude the existence of additional identical elements in the process, method, article or terminal device including the said elements.

[0035] As Figure 1 shown, an embodiment of the present invention provides a method for simulating and displaying the space environment effects of spacecraft surface materials, characterized by including the following steps:

[0036] Step S1, establish a three-dimensional model of the spacecraft and divide the spacecraft surface into multiple polygon mesh units;

[0037] Step S2, input the first space environment parameter affecting the atomic oxygen flux on the outer surface of the spacecraft or the second space environment parameter affecting the ultraviolet irradiation intensity on the outer surface of the spacecraft into the three-dimensional model, calculate the polygon mesh units touched by atomic oxygen and / or ultraviolet irradiation simulation particles, obtain the atomic oxygen and / or ultraviolet irradiation flux data on the spacecraft surface, and after data processing, obtain the atomic oxygen and / or ultraviolet irradiation flux cloud map on the spacecraft surface;

[0038] Step S3, according to the atomic oxygen flux data on the spacecraft surface and the ablation reaction coefficient of the spacecraft surface material, obtain the ablation effect data on the spacecraft surface, and after data processing, obtain the ablation depth change curve of the spacecraft surface material and / or the ablation effect cloud map of the spacecraft surface material; and / or, according to the atomic oxygen flux data on the spacecraft surface and the pitting reaction coefficient of the spacecraft surface material, obtain the pitting effect data on the spacecraft surface, and after data processing, obtain the pitting depth change curve of the spacecraft surface material and / or the pitting effect cloud map of the spacecraft surface material.

[0039] Thus, the method for simulating and displaying the space environment effects of spacecraft surface materials in this embodiment takes into account the influence of the satellite's three-dimensional structure and on-orbit operating state, and can obtain cloud maps of the atomic oxygen flux, ultraviolet intensity, surface ablation depth, and pitting depth on the surface of the spacecraft or material as a whole and under the atomic oxygen and ultraviolet or combined environment, and can also obtain cloud maps of the atomic oxygen flux, ultraviolet intensity, surface ablation depth, and pitting depth on the surface of a single mesh unit under the atomic oxygen and ultraviolet or combined environment. It is intuitive, accurate, and convenient to observe.

[0040] In some embodiments, the curve of the ablation depth change of the spacecraft surface material and / or the contour map of the ablation effect of the spacecraft surface material, and / or, the curve of the gouging depth change of the spacecraft surface material and / or the contour map of the gouging effect of the spacecraft surface material are all used to display the damage degree of the spacecraft surface material under the combined action of atomic oxygen and ultraviolet rays. Thus, it is possible to more intuitively display the damage degree of the spacecraft surface material under the combined action of atomic oxygen and ultraviolet rays, which is convenient for observation.

[0041] In some embodiments, the contour map of the atomic oxygen and / or ultraviolet irradiation flux on the spacecraft surface includes the contour map of the atomic oxygen and / or ultraviolet irradiation flux on the spacecraft surface based on point display or cell display. Among them, the cell display method can accurately display the atomic oxygen flux and ultraviolet flux on the cell, and the point display method can better display the flux relationship between different structures and the transition between different cells. The display method can be arbitrarily selected according to needs, which is more convenient.

[0042] In some embodiments, in step S2, the atomic oxygen and / or ultraviolet irradiation flux data on the spacecraft surface includes the instantaneous atomic oxygen or ultraviolet irradiation flux data on the spacecraft surface and the cumulative atomic oxygen or ultraviolet irradiation flux data on the spacecraft surface. The data is more comprehensive and the simulation is more accurate.

[0043] In some embodiments, in step S2, inputting the first space environment parameter affecting the atomic oxygen flux on the outer surface of the spacecraft or the second space environment parameter affecting the ultraviolet irradiation intensity on the outer surface of the spacecraft into the three-dimensional model to obtain the atomic oxygen and / or ultraviolet irradiation flux on the spacecraft surface includes:

[0044] Step S21: Input the first space environment parameter affecting the atomic oxygen flux on the outer surface of the spacecraft or the second space environment parameter affecting the ultraviolet irradiation intensity on the outer surface of the spacecraft into the three-dimensional model, calculate the polygon mesh cells touched by the atomic oxygen or ultraviolet irradiation simulation particles, and obtain the instantaneous atomic oxygen and / or ultraviolet irradiation flux on the spacecraft surface;

[0045] Step S22: Obtain the on-orbit flight time of the spacecraft, and obtain the cumulative atomic oxygen and / or ultraviolet irradiation flux on the spacecraft surface according to the instantaneous atomic oxygen or ultraviolet irradiation flux on the spacecraft surface and the on-orbit flight time of the spacecraft.

[0046] Thus, it is convenient to obtain the ablation effect data on the spacecraft surface subsequently. The steps are simple.

[0047] In some embodiments, in step S3, obtaining the ablation effect data on the spacecraft surface according to the atomic oxygen flux data on the spacecraft surface and the ablation reaction coefficient of the spacecraft surface material includes:

[0048] The erosion depth of the spacecraft surface material is obtained by multiplying the cumulative atomic oxygen flux on the spacecraft surface by the erosion reaction coefficient of the spacecraft surface material. The steps are simple and the calculation is accurate.

[0049] In this embodiment, the erosion reaction coefficient of the spacecraft surface material is determined according to the synergistic situation of atomic oxygen and ultraviolet irradiation on the spacecraft surface. Specifically:

[0050] When only atomic oxygen particles touch the spacecraft surface, the erosion reaction coefficient of the spacecraft surface material is the atomic oxygen reaction coefficient of the spacecraft surface material;

[0051] When the spacecraft surface is subjected to the synergy of atomic oxygen and ultraviolet irradiation, the erosion reaction coefficient of the spacecraft surface material is the atomic oxygen and ultraviolet synergistic reaction coefficient of the spacecraft surface material.

[0052] Thus, the influence of ultraviolet irradiation on the atomic oxygen erosion effect can be considered, making the simulation data more accurate.

[0053] In some embodiments, the atomic oxygen and ultraviolet synergistic reaction coefficient of the spacecraft surface material is obtained by the ratio of the ultraviolet intensity received by the spacecraft surface to the total ultraviolet intensity received during the spacecraft's on-orbit operation. Thus, the calculation is accurate.

[0054] In some preferred embodiments, the atomic oxygen reaction coefficient of the spacecraft surface material is (1 - the atomic oxygen and ultraviolet synergistic reaction coefficient of the spacecraft surface material). When only atomic oxygen particles touch the spacecraft surface, that is, when there is only a single atomic oxygen acting on the spacecraft surface, the atomic oxygen and ultraviolet synergistic reaction coefficient of the spacecraft surface material is zero. Therefore, when only atomic oxygen particles touch the spacecraft surface, the erosion reaction coefficient of the spacecraft surface material is the atomic oxygen reaction coefficient of the spacecraft surface material, and the calculation is accurate.

[0055] In some embodiments, in step S2, both the first space environment parameter and the second space environment parameter include the spacecraft quaternion, the six orbital elements, the longitude, latitude and altitude of the orbit, and the position of the solar wing. Thus, the three-dimensional satellite structure and the on-orbit operation state of the spacecraft are fully considered, and the data is more accurate.

[0056] In some embodiments, in step S2, the first space environment parameter includes: the spacecraft velocity, the oncoming flow direction, and the atomic oxygen density, and the second space environment parameter includes: the ultraviolet irradiation intensity and the ultraviolet irradiation direction. Thus, the influence of the atomic oxygen or ultraviolet space environment is fully considered, making the calculation more accurate.

[0057] To verify the effectiveness of the method for simulating and displaying the space environment effect of the spacecraft surface material in this embodiment, the same grid density, number of particles, number of particle reflections, and number of cores are used in this embodiment to simulate and display the space environment effect of the spacecraft surface material. AsFigures 2 - 5 As shown Figure 2 Figure 2 This is the cumulative atomic oxygen flux cloud map based on cell display obtained by the method for simulating and displaying the space environment effect of spacecraft surface materials in this embodiment, where the cell value is 7.31401e +19 ; Figure 3 Figure 3 This is the cumulative atomic oxygen flux cloud map based on point display obtained by the method for simulating and displaying the space environment effect of spacecraft surface materials in this embodiment; Figure 4 Figure 4 This is the cumulative ultraviolet irradiation flux cloud map based on cell display obtained by the method for simulating and displaying the space environment effect of spacecraft surface materials in this embodiment, where the cell value is 110.464; Figure 5 Figure 5 This is the cumulative ultraviolet irradiation flux cloud map based on point display obtained by the method for simulating and displaying the space environment effect of spacecraft surface materials in this embodiment. Among them, Figure 2 and Figure 3 Figure 3 In, the magnitude of the atomic oxygen flux is represented by the change in the depth of color. The darker the color, the greater the atomic oxygen flux; Figure 4 and Figure 5 Figure 5 In, the magnitude of the ultraviolet irradiation flux is represented by the change in the depth of color. The darker the color, the greater the ultraviolet irradiation flux. It can be seen from the figure that the cell display method in this embodiment can accurately display the atomic oxygen flux and ultraviolet flux on the cell, and the point display method can better display the flux relationship between different structures and the transition between different cells. The display method can be arbitrarily selected according to needs, which is more convenient.

[0058] Therefore, the method for simulating and displaying the space environment effect of the spacecraft surface material in this embodiment takes into account the influence of the satellite's three-dimensional structure and the on-orbit operating state, and can obtain cloud maps of the overall spacecraft or material and the surface atomic oxygen flux, ultraviolet intensity, surface erosion depth, and pitting depth under atomic oxygen and ultraviolet or combined environments. It can also obtain cloud maps of the surface atomic oxygen flux, ultraviolet intensity, surface erosion depth, and pitting depth of a single grid cell under atomic oxygen and ultraviolet or combined environments. It is intuitive, accurate, and convenient to observe, provides a necessary basis for optimizing the material's resistance to space environment effects, has great significance for the research on the space environment synergy effect of materials, and has obvious advantages and broad application prospects.

[0059] Another embodiment of the present invention also provides a system for simulating and displaying the space environment effect of spacecraft surface materials, including:

[0060] A model establishment module, which is used to establish a three-dimensional model of the spacecraft and divide the surface of the spacecraft into multiple polygon grid cells;

[0061] An acquisition module, which is used to acquire a first space environment parameter affecting the atomic oxygen flux on the outer surface of the spacecraft and / or a second space environment parameter affecting the ultraviolet irradiation intensity on the outer surface of the spacecraft;

[0062] A calculation module, which is used to calculate the polygon mesh cells touched by atomic oxygen and / or ultraviolet irradiation simulation particles, and obtain the atomic oxygen and / or ultraviolet irradiation flux data on the spacecraft surface;

[0063] The calculation module is further used to obtain the erosion or pitting effect data on the spacecraft surface according to the atomic oxygen flux on the spacecraft surface and the erosion or pitting reaction coefficient of the spacecraft surface material;

[0064] A display module, which is used to display the curve of the change in the erosion or pitting depth of the spacecraft surface material and / or the cloud map of the erosion or pitting effect of the spacecraft surface material.

[0065] The spacecraft surface material space environment effect simulation and display system described in this embodiment has the same advantages as the spacecraft surface material space environment effect simulation and display method compared with the prior art, and will not be elaborated here.

[0066] Although the present invention is disclosed as above, the protection scope of the present invention 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 these changes and modifications will all fall within the protection scope of the present invention.

Claims

1. A method for simulating and displaying the space environment effects of spacecraft surface materials, characterized in that, The method includes the following steps: Step S1: Establish a three-dimensional model of the spacecraft and divide the surface of the spacecraft into multiple polygon mesh cells; Step S2: Input the first space environment parameter affecting the atomic oxygen flux on the outer surface of the spacecraft or the second space environment parameter affecting the ultraviolet irradiation intensity on the outer surface of the spacecraft into the three-dimensional model, calculate the polygon mesh cells touched by atomic oxygen and / or ultraviolet irradiation simulation particles, obtain the atomic oxygen and / or ultraviolet irradiation flux data on the surface of the spacecraft, and after data processing, obtain the atomic oxygen and / or ultraviolet irradiation flux cloud map on the surface of the spacecraft; Step S3: According to the atomic oxygen flux data on the surface of the spacecraft and the ablation reaction coefficient of the spacecraft surface material, obtain the ablation effect data on the surface of the spacecraft, and after data processing, obtain the ablation depth change curve of the spacecraft surface material and / or the ablation effect cloud map of the spacecraft surface material; and / or, according to the atomic oxygen flux data on the surface of the spacecraft and the erosion reaction coefficient of the spacecraft surface material, obtain the erosion effect data on the surface of the spacecraft, and after data processing, obtain the erosion depth change curve of the spacecraft surface material and / or the erosion effect cloud map of the spacecraft surface material.

2. The method for simulating and displaying the space environment effects of the spacecraft surface material according to claim 1, wherein The ablation depth change curve of the spacecraft surface material and / or the ablation effect cloud map of the spacecraft surface material, and / or, the erosion depth change curve of the spacecraft surface material and / or the erosion effect cloud map of the spacecraft surface material are all used to display the damage degree of the spacecraft surface material under the combined action of atomic oxygen and ultraviolet light.

3. The method for simulating and displaying the space environment effects of the spacecraft surface material according to claim 1, wherein The atomic oxygen and / or ultraviolet irradiation flux cloud map on the surface of the spacecraft includes the atomic oxygen and / or ultraviolet irradiation flux cloud map on the surface of the spacecraft based on point display or cell display.

4. The method for simulating and displaying the space environment effects of the spacecraft surface material according to claim 1, characterized in that, In step S2, the atomic oxygen and / or ultraviolet irradiation flux data on the surface of the spacecraft includes the instantaneous atomic oxygen or ultraviolet irradiation flux data on the surface of the spacecraft and the cumulative atomic oxygen or ultraviolet irradiation flux data on the surface of the spacecraft.

5. The method for simulating and displaying the space environment effects of the spacecraft surface material according to claim 1, characterized in that, In step S2, the input of the first space environment parameter affecting the atomic oxygen flux on the outer surface of the spacecraft or the second space environment parameter affecting the ultraviolet irradiation intensity on the outer surface of the spacecraft into the three-dimensional model to obtain the atomic oxygen and / or ultraviolet irradiation flux on the surface of the spacecraft includes: Step S21: Input the first space environment parameter affecting the atomic oxygen flux on the outer surface of the spacecraft or the second space environment parameter affecting the ultraviolet irradiation intensity on the outer surface of the spacecraft into the three-dimensional model, calculate the polygon mesh cells touched by atomic oxygen or ultraviolet irradiation simulation particles, and obtain the instantaneous atomic oxygen and / or ultraviolet irradiation flux on the surface of the spacecraft; Step S22: Obtain the on-orbit flight time of the spacecraft, and obtain the cumulative atomic oxygen and / or ultraviolet irradiation flux on the surface of the spacecraft according to the instantaneous atomic oxygen or ultraviolet irradiation flux on the surface of the spacecraft and the on-orbit flight time of the spacecraft.

6. The method for simulating and displaying the space environment effects of the spacecraft surface material according to claim 5, characterized in that, In step S3, the obtaining of the ablation effect data on the surface of the spacecraft according to the atomic oxygen flux data on the surface of the spacecraft and the ablation reaction coefficient of the spacecraft surface material includes: Obtain the ablation depth of the spacecraft surface material by multiplying the cumulative atomic oxygen flux on the surface of the spacecraft by the ablation reaction coefficient of the spacecraft surface material.

7. The method for simulating and displaying the space environment effects of the spacecraft surface material according to claim 1, wherein In step S2, both the first space environment parameter and the second space environment parameter include the spacecraft quaternion, six orbital elements, the longitude, latitude and altitude of the orbit, and the position of the solar array.

8. The method for simulating and displaying the space environment effects of the spacecraft surface material according to claim 1, wherein In step S2, the first space environment parameter includes: the spacecraft velocity, the oncoming flow direction, and the atomic oxygen density.

9. The method for simulating and displaying the space environment effects of the spacecraft surface material according to claim 1, characterized in that, In step S2, the second space environment parameter includes: the ultraviolet irradiation intensity and the ultraviolet irradiation direction.

10. A simulation and display system for space environment effects of spacecraft surface materials, characterized in that, Comprising: A model establishment module, which is used to establish a three-dimensional model of the spacecraft and divide the spacecraft surface into multiple polygon mesh cells; An acquisition module, which is used to acquire the first space environment parameter affecting the atomic oxygen flux on the outer surface of the spacecraft and / or the second space environment parameter affecting the ultraviolet irradiation intensity on the outer surface of the spacecraft; A calculation module, which is used to calculate the polygon mesh cells touched by the atomic oxygen and / or ultraviolet irradiation simulation particles to obtain the atomic oxygen and / or ultraviolet irradiation flux data on the spacecraft surface; The calculation module is further used to obtain the ablation or erosion effect data on the spacecraft surface according to the atomic oxygen flux on the spacecraft surface and the ablation or erosion reaction coefficient of the spacecraft surface material; A display module, which is used to display the ablation or erosion depth change curve of the spacecraft surface material and / or the ablation or erosion effect nephogram of the spacecraft surface material.

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