A calculation method for atomic oxygen or ultraviolet irradiation flux under simulated space environment

Abstract

The present invention provides a calculation method for atomic oxygen or ultraviolet irradiation flux under a simulated space environment, which relates to the technical field of spacecraft simulation calculation. The method includes: obtaining first space environment parameters affecting the atomic oxygen flux on the outer surface of the spacecraft or second space environment parameters affecting the ultraviolet irradiation intensity on the outer surface of the spacecraft; establishing a three-dimensional model of the spacecraft and dividing the surface of the spacecraft into multiple polygon mesh units; inputting the first space environment parameters or the second space environment parameters into the three-dimensional model, calculating the polygon mesh units touched by the atomic oxygen or ultraviolet irradiation simulation particles, and obtaining the atomic oxygen or ultraviolet irradiation flux on the surface of the spacecraft. The calculation method for atomic oxygen or ultraviolet irradiation flux under the simulated space environment of the present invention is simple to operate, can accurately and quickly calculate the atomic oxygen or ultraviolet irradiation flux on the surface of materials under different environmental conditions, and has a wide application prospect.

Description

Technical Field

[0001] The present invention relates to the technical field of spacecraft simulation calculation, and more specifically, to a calculation method for simulating atomic oxygen or ultraviolet irradiation flux in a space environment. Background Art

[0002] To control temperature, the outer surface of a satellite is covered with a thermal control coating, which is an important part of the spacecraft thermal control system. The quality of its performance directly determines the lifespan of the satellite. Since it is in direct contact with the outer space environment, it is more vulnerable to being affected. According to the survey data, among multiple spacecraft accidents that occurred, many were directly caused by the damage to the spacecraft thermal control system. Therefore, the performance of the thermal control system has always affected the development of the space industry in various countries. Among the many factors affecting the performance of the spacecraft thermal control system, the degradation factor of the thermal control coating material on the spacecraft surface plays a decisive role, and atomic oxygen or ultraviolet irradiation has a very serious impact on the thermal control coating material on the spacecraft surface. The fluence of atomic oxygen received by the outer surface of the satellite is affected by the actual in-orbit state of the satellite. However, in the existing technology, the calculation models for space atomic oxygen fluence or ultraviolet irradiation do not consider the influence of the satellite's three-dimensional structure and in-orbit operating state. Therefore, it is impossible to accurately calculate the atomic oxygen fluence or the external irradiation flux, resulting in the inability to accurately predict the lifespan of the satellite. Summary of the Invention

[0003] The problem solved by the present invention is that in the existing technology, the calculation models for space atomic oxygen fluence or ultraviolet irradiation do not consider the influence of the satellite's three-dimensional structure and in-orbit operating state. Therefore, it is impossible to accurately calculate the atomic oxygen fluence or the ultraviolet irradiation flux, resulting in the inability to accurately predict the lifespan of the satellite in at least one aspect.

[0004] To solve the above problems, the present invention provides a calculation method for simulating atomic oxygen or ultraviolet irradiation flux in a space environment, including the following steps:

[0005] Step S1, obtain 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;

[0006] Step S2, establish a three-dimensional model of the spacecraft and divide the spacecraft surface into multiple polygon mesh units;

[0007] Step S3, input the first space environment parameter or the second space environment parameter into the three-dimensional model, calculate the polygon mesh units touched by the atomic oxygen or ultraviolet irradiation simulation particles, and obtain the atomic oxygen or ultraviolet irradiation flux on the spacecraft surface.

[0008] Preferably, in step S3, the atomic oxygen or ultraviolet radiation flux on the surface of the spacecraft includes the instantaneous atomic oxygen or ultraviolet radiation flux and the cumulative atomic oxygen or ultraviolet radiation flux on the surface of the spacecraft.

[0009] Preferably, in step S3, the first space environment parameter or the second space environment parameter is input into the three-dimensional model, and the polygon mesh cells touched by the atomic oxygen or ultraviolet radiation simulation particles are calculated to obtain the atomic oxygen or ultraviolet radiation flux on the surface of the spacecraft, including:

[0010] Step S31, input the first space environment parameter or the second space environment parameter into the three-dimensional model, calculate the polygon mesh cells touched by the atomic oxygen or ultraviolet radiation simulation particles, and obtain the instantaneous atomic oxygen or ultraviolet radiation flux on the surface of the spacecraft;

[0011] Step S32, obtain the on-orbit flight time of the spacecraft, and obtain the cumulative atomic oxygen or ultraviolet radiation flux on the surface of the spacecraft according to the instantaneous atomic oxygen or ultraviolet radiation flux on the surface of the spacecraft and the on-orbit flight time of the spacecraft.

[0012] Preferably, both the first space environment parameter and the second space environment parameter include the spacecraft quaternion, six orbital elements, the latitude, longitude and altitude of the orbit, and the position of the solar wing.

[0013] Preferably, in step S1, the first space environment parameter further includes: the spacecraft speed, the oncoming flow direction, and the atomic oxygen density.

[0014] Preferably, in step S1, the atomic oxygen density is obtained according to the solar activity level and the flight altitude of the spacecraft.

[0015] Preferably, the solar activity level includes the solar minimum, the solar median, and the solar maximum.

[0016] Preferably, the oncoming flow direction is used to describe the running direction of the spacecraft during on-orbit flight.

[0017] Preferably, in step S1, the second space environment parameter includes: the ultraviolet radiation intensity and the ultraviolet radiation direction.

[0018] Preferably, the ultraviolet radiation direction is described by the angle between the solar ultraviolet radiation direction and the normal of the spacecraft surface.

[0019] The advantages of the method for calculating the atomic oxygen or ultraviolet irradiation flux in a simulated space environment according to the present invention compared with the prior art are as follows. The method for calculating the atomic oxygen or ultraviolet irradiation flux in a simulated space environment according to the present invention takes into account the influence of the three-dimensional structure of the satellite and its on-orbit operating state, and can accurately calculate the instantaneous atomic oxygen or ultraviolet irradiation flux on the surface of materials in different space environments, so as to achieve the purpose of accurately predicting the atomic oxygen or ultraviolet irradiation flux on the surface of materials in different space environments. Moreover, the method for calculating the atomic oxygen or ultraviolet irradiation flux in a simulated space environment according to the present invention is simple to operate, can accurately and quickly calculate the atomic oxygen or ultraviolet irradiation flux on the surface of materials under different environmental conditions, 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 synergistic effect of materials, has obvious advantages and broad application prospects. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 It is a flowchart of the method for calculating the atomic oxygen or ultraviolet irradiation flux in a simulated space environment in an embodiment of the present invention;

[0021] Figure 2 It is a schematic diagram of the instantaneous atomic oxygen flux obtained by using the method for calculating the atomic oxygen or ultraviolet irradiation flux in a simulated space environment in an embodiment of the present invention;

[0022] Figure 3 It is a schematic diagram of the cumulative atomic oxygen flux obtained by using the method for calculating the atomic oxygen or ultraviolet irradiation flux in a simulated space environment in an embodiment of the present invention;

[0023] Figure 4 It is a table of the instantaneous atomic oxygen flux obtained by using the method for calculating the atomic oxygen or ultraviolet irradiation flux in a simulated space environment in an embodiment of the present invention;

[0024] Figure 5 It is a table of the cumulative atomic oxygen flux obtained by using the method for calculating the atomic oxygen or ultraviolet irradiation flux in a simulated space environment in an embodiment of the present invention;

[0025] Figure 6 It is a curve of the cumulative atomic oxygen flux obtained by using the method for calculating the atomic oxygen or ultraviolet irradiation flux in a simulated space environment in an embodiment of the present invention;

[0026] Figure 7 It is a schematic diagram of the instantaneous ultraviolet irradiation flux obtained by using the method for calculating the atomic oxygen or ultraviolet irradiation flux in a simulated space environment in an embodiment of the present invention;

[0027] Figure 8 It is a schematic diagram of the cumulative ultraviolet irradiation flux obtained by using the method for calculating the atomic oxygen or ultraviolet irradiation flux in a simulated space environment in an embodiment of the present invention. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0028] The technical solutions in the embodiments of the present application will be clearly and elaborately described below with reference to the accompanying drawings.

[0029] 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 example. Moreover, the specific features, structures, materials, or characteristics described may be combined in any one or more embodiments or examples in a suitable manner.

[0030] It should also be noted that in the description of the embodiments of the present application, the term "comprising" or any other variant thereof is intended to cover a non-exclusive inclusion, such that a process, method, article, or terminal device comprising a series of elements includes not only those elements but also other elements that are not explicitly listed, or further includes elements that are inherent to such process, method, article, or terminal device. Without further limitation, the elements defined by the statement "comprising..." do not exclude the presence of additional identical elements in the process, method, article, or terminal device comprising the said elements.

[0031] As Figure 1 shown, the embodiments of the present invention provide a method for calculating the atomic oxygen or ultraviolet irradiation flux in a simulated space environment, including the following steps:

[0032] Step S1, obtaining a first space environment parameter that affects the atomic oxygen flux on the outer surface of the spacecraft or a second space environment parameter that affects the ultraviolet irradiation intensity on the outer surface of the spacecraft;

[0033] Step S2, establishing a three-dimensional model of the spacecraft and dividing the surface of the spacecraft into a plurality of polygon mesh units;

[0034] Step S3, inputting the first space environment parameter or the second space environment parameter into the three-dimensional model, calculating the polygon mesh units touched by the atomic oxygen or ultraviolet irradiation simulation particles, and obtaining the atomic oxygen or ultraviolet irradiation flux on the surface of the spacecraft.

[0035] Thus, this embodiment can accurately calculate the instantaneous atomic oxygen or ultraviolet irradiation flux on the surface of materials in different space environments, achieving the purpose of accurately predicting the atomic oxygen or ultraviolet irradiation flux on the surface of materials in different space environments.

[0036] In some embodiments, in step S3, the atomic oxygen or ultraviolet irradiation flux on the surface of the spacecraft includes the instantaneous atomic oxygen or ultraviolet irradiation flux on the surface of the spacecraft and the cumulative atomic oxygen or ultraviolet irradiation flux on the surface of the spacecraft. The data is more comprehensive and the simulation is more accurate.

[0037] In some embodiments, in step S3, inputting the first space environment parameter or the second space environment parameter into the three-dimensional model, calculating the polygon mesh cells touched by the atomic oxygen or ultraviolet irradiation simulation particles, and obtaining the atomic oxygen or ultraviolet irradiation flux on the spacecraft surface, including:

[0038] Step S31, inputting the first space environment parameter or the second space environment parameter into the three-dimensional model, calculating the polygon mesh cells touched by the atomic oxygen or ultraviolet irradiation simulation particles, and obtaining the instantaneous atomic oxygen or ultraviolet irradiation flux on the spacecraft surface;

[0039] Step S32, obtaining the on-orbit flight time of the spacecraft, and obtaining the cumulative atomic oxygen 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.

[0040] In this embodiment, the cumulative atomic oxygen or ultraviolet irradiation flux on the spacecraft surface is the product of the instantaneous atomic oxygen or ultraviolet irradiation flux on the surface at the orbital altitude during the on-orbit operation of the spacecraft and the on-orbit flight time of the spacecraft, which is convenient and accurate to calculate.

[0041] In some embodiments, a calculation method for the atomic oxygen or ultraviolet irradiation flux in a simulated space environment

[0042] further includes:

[0043] Step S4, after obtaining the atomic oxygen or ultraviolet irradiation flux on the spacecraft surface, performing data output, where the data includes cloud map files, curve files, and table files of the instantaneous atomic oxygen or ultraviolet irradiation flux on the spacecraft surface and / or the cumulative atomic oxygen or ultraviolet irradiation flux on the spacecraft surface.

[0044] Thereby, the data of the simulated instantaneous atomic oxygen or ultraviolet irradiation flux on the spacecraft surface and / or the cumulative atomic oxygen or ultraviolet irradiation flux on the spacecraft surface can be observed from multiple angles, and the effect is more intuitive.

[0045] In some embodiments, in step S1, 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 structure of the spacecraft and its on-orbit operation state are fully considered, and the data is more accurate.

[0046] In some embodiments, in step S1, the first space environment parameter includes: the spacecraft speed, the oncoming flow direction, and the atomic oxygen density. Thus, different atomic oxygen fluxes in different space environments can be obtained through the change of the first space environment parameter.

[0047] In some specific embodiments, the atomic oxygen density is obtained according to the degree of solar activity and the flight altitude of the spacecraft.

[0048] In some preferred embodiments, the manned space orbit is 360 km. At this flight altitude, the solar activity degree indices are different under different solar activity levels, and as the solar activity degree index increases, the density of atomic oxygen gradually increases.

[0049] In some specific embodiments, the solar activity level includes the low solar activity years, the medium solar activity years, and the high solar activity years, and the solar activity degree index gradually increases in the order of the low solar activity years, the medium solar activity years, and the high solar activity years.

[0050] In some specific embodiments, the oncoming flow direction is used to describe the running direction of the spacecraft during on-orbit flight. In some specific embodiments, assuming that the spacecraft is in a stationary state and the atomic oxygen is in a moving state, the oncoming flow direction is the direction from which the atomic oxygen contacts the spacecraft, indirectly describing the running direction of the spacecraft during on-orbit flight.

[0051] In some specific embodiments, the spacecraft speed is the on-orbit flight speed of the spacecraft.

[0052] In some embodiments, in step S1, the second space environment parameter includes: the ultraviolet irradiation intensity and the ultraviolet irradiation direction. Thus, different ultraviolet irradiation fluxes under different space environments can be obtained through the change of the second space environment parameter.

[0053] It should be noted that in this embodiment, with the change of solar activity, the radiation amount of ultraviolet radiation has a certain change. The shorter the wavelength, the greater the change amplitude. The energy of ultraviolet radiation is mainly concentrated in the higher wavelength band, and the change amplitude of the higher wavelength band is small and relatively stable. Therefore, in the life prediction of this embodiment, the total ultraviolet radiation intensity is determined as a constant.

[0054] In some embodiments, the ultraviolet irradiation direction is described by the angle between the solar ultraviolet radiation direction and the normal of the spacecraft surface. Thus, the ultraviolet irradiation direction can be more accurately reflected.

[0055] To verify the effectiveness of the calculation method of atomic oxygen or ultraviolet irradiation flux in the simulated space environment in this embodiment, the same grid density, number of particles, number of particle reflections, and number of nuclei are used in this embodiment to calculate the atomic oxygen or ultraviolet irradiation flux in the space environment. As Figures 2 - 8 shown, Figure 2 is a schematic diagram of the instantaneous atomic oxygen flux obtained by using the calculation method of atomic oxygen or ultraviolet irradiation flux in the simulated space environment in this embodiment; Figure 3 is a schematic diagram of the cumulative atomic oxygen flux obtained by using the calculation method of atomic oxygen or ultraviolet irradiation flux in the simulated space environment in this embodiment; Figure 4The instantaneous atomic oxygen flux table obtained by the calculation method of atomic oxygen or ultraviolet irradiation flux in the simulated space environment in this embodiment; Figure 5 The cumulative atomic oxygen flux table obtained by the calculation method of atomic oxygen or ultraviolet irradiation flux in the simulated space environment in this embodiment; Figure 6 The cumulative atomic oxygen flux curve obtained by the calculation method of atomic oxygen or ultraviolet irradiation flux in the simulated space environment in this embodiment; Figure 7 The schematic diagram of instantaneous ultraviolet irradiation flux obtained by the calculation method of atomic oxygen or ultraviolet irradiation flux in the simulated space environment in this embodiment; Figure 8 The schematic diagram of cumulative ultraviolet irradiation flux obtained by the calculation method of atomic oxygen or ultraviolet irradiation flux in the simulated space environment in this embodiment. Among them, Figure 2 and 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 7 and Figure 8 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 calculation method of atomic oxygen or ultraviolet irradiation flux in the simulated space environment in this embodiment can accurately simulate the atomic oxygen or ultraviolet irradiation flux during the on-orbit operation of the spacecraft.

[0056] Therefore, the advantage of the calculation method of atomic oxygen or ultraviolet irradiation flux in the simulated space environment described in this embodiment compared with the prior art is that the calculation method of atomic oxygen or ultraviolet irradiation flux in the simulated space environment in this embodiment takes into account the influence of the satellite's three-dimensional structure and on-orbit operation state, and can accurately calculate the instantaneous flux of atomic oxygen or ultraviolet irradiation on the material surface in different space environments, so as to achieve the purpose of accurately predicting the atomic oxygen or ultraviolet irradiation flux on the material surface in different space environments. Moreover, the calculation method of atomic oxygen or ultraviolet irradiation flux in the simulated space environment in this embodiment is simple to operate, can accurately and quickly calculate the atomic oxygen or ultraviolet irradiation flux on the material surface under different environmental conditions, 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 synergistic effect of materials, and has obvious advantages and broad application prospects.

[0057] 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 calculation method for atomic oxygen or ultraviolet irradiation flux under simulated space environment, characterized in that, It includes the following steps: Step S1, obtaining 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; Step S2, establishing a three-dimensional model of the spacecraft and dividing the spacecraft surface into multiple polygon mesh cells; Step S3, inputting the first space environment parameter or the second space environment parameter into the three-dimensional model, calculating the polygon mesh cells touched by atomic oxygen or ultraviolet irradiation simulation particles, and obtaining the atomic oxygen or ultraviolet irradiation flux on the spacecraft surface.

2. The calculation method of atomic oxygen or ultraviolet irradiation flux under the simulated space environment according to claim 1, characterized in that, In step S3, the atomic oxygen or ultraviolet irradiation flux on the spacecraft surface includes the instantaneous atomic oxygen or ultraviolet irradiation flux on the spacecraft surface and the cumulative atomic oxygen or ultraviolet irradiation flux on the spacecraft surface.

3. The calculation method of atomic oxygen or ultraviolet irradiation flux under simulated space environment according to claim 2, characterized in that In step S3, inputting the first space environment parameter or the second space environment parameter into the three-dimensional model, calculating the polygon mesh cells touched by atomic oxygen or ultraviolet irradiation simulation particles, and obtaining the atomic oxygen or ultraviolet irradiation flux on the spacecraft surface, including: Step S31, inputting the first space environment parameter or the second space environment parameter into the three-dimensional model, calculating the polygon mesh cells touched by atomic oxygen or ultraviolet irradiation simulation particles, and obtaining the instantaneous atomic oxygen or ultraviolet irradiation flux on the spacecraft surface; Step S32, obtaining the on-orbit flight time of the spacecraft, and obtaining the cumulative atomic oxygen 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.

4. The calculation method of atomic oxygen or ultraviolet irradiation flux under simulated space environment according to claim 1, wherein 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 wing.

5. The calculation method of atomic oxygen or ultraviolet irradiation flux in a simulated space environment according to claim 1, characterized in that, In step S1, the first space environment parameter further includes: the spacecraft speed, the oncoming flow direction, and the atomic oxygen density.

6. The calculation method of atomic oxygen or ultraviolet irradiation flux under the simulated space environment according to claim 5, characterized in that, In step S1, the atomic oxygen density is obtained according to the solar activity level and the flight altitude of the spacecraft.

7. The calculation method of atomic oxygen or ultraviolet irradiation flux under the simulated space environment according to claim 6, characterized in that The solar activity level includes the solar minimum, the solar median, and the solar maximum.

8. The calculation method of atomic oxygen or ultraviolet irradiation flux under simulated space environment according to claim 5, characterized in that The oncoming flow direction is used to describe the running direction of the spacecraft during on-orbit flight.

9. The calculation method of atomic oxygen or ultraviolet irradiation flux under simulated space environment according to claim 1, characterized in that In step S1, the second space environment parameter includes: the ultraviolet irradiation intensity and the ultraviolet irradiation direction.

10. The calculation method of atomic oxygen or ultraviolet irradiation flux under a simulated space environment according to claim 9, characterized in that, The ultraviolet irradiation direction is described by the angle between the solar ultraviolet radiation direction and the normal of the spacecraft surface.

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