Monte Carlo simulation method of atomic oxygen or ultraviolet flux based on solar wing activity posture

Abstract

The present invention provides a Monte Carlo simulation method of atomic oxygen or ultraviolet flux based on the active posture of a solar wing, and relates to the field of spacecraft simulation calculation technology. The method comprises: establishing or importing spacecraft geometric model data, dividing the components of the spacecraft into visible components and invisible components; meshing the geometric surface of each visible component to generate a corresponding polygonal mesh file; selecting solar wing reference point parameters on the spacecraft geometric model, and setting the solar wing rotation axis; reading the spacecraft motion orbit file, transforming quaternion parameters and / or solar wing rotation angle parameters according to the spacecraft body, generating each polygonal mesh data of the spacecraft motion orbit point, performing Monte Carlo simulation calculation of atomic oxygen flux or ultraviolet flux on the spacecraft surface, and obtaining atomic oxygen flux or ultraviolet flux on the spacecraft surface. The present invention can reduce the time of Monte Carlo simulation and improve calculation accuracy and efficiency.

Description

Technical Field

[0001] The invention relates to the technical field of spacecraft simulation calculation, and in particular to an atomic oxygen or ultraviolet flux Monte Carlo simulation method based on the activity posture of a solar wing. Background Art

[0002] At present, most simulation software in the prior art uses Monte Carlo simulation to calculate the atomic oxygen / ultraviolet radiation flux of each unit on the surface of the spacecraft. When the solar wing is fixed, the coordinates of the polygonal vertices of each subdivided unit on the surface of the spacecraft in the body coordinate system can be calculated based on the spacecraft orbit point parameters and the flight direction, and then the surface subdivided unit of the simulated particle collision is calculated. Although the overall calculation logic of this scheme is simple, it will cause a large deviation in the atomic oxygen / ultraviolet radiation flux of the solar wing and its surrounding surface units. This is because during the service of the spacecraft, the solar wing is always facing the direction of sunlight, that is, its posture relative to the body coordinate system is active. The active posture of the solar wing not only affects the atomic oxygen / ultraviolet radiation flux of each subdivided unit on the surface of the solar wing, but also affects the calculation of the atomic oxygen / ultraviolet radiation flux of the surface subdivided units of other components due to the occlusion relationship caused by the active posture. Therefore, ignoring the active posture of the solar wing will cause the numerical size and distribution law of the atomic oxygen / ultraviolet radiation flux of the spacecraft surface unit, thereby affecting the simulation calculation of the erosion / erosion effect, and ultimately affecting the optimization selection of the surface coating material. Summary of the invention

[0003] The problem solved by the present invention is that the method of using Monte Carlo simulation to calculate the atomic oxygen / ultraviolet radiation flux of each unit on the surface of a spacecraft in the prior art ignores the activity posture of the solar wing, which will affect the numerical size and distribution law of the atomic oxygen / ultraviolet radiation flux of the spacecraft surface unit, thereby affecting the simulation calculation of the erosion / etching effect, and ultimately affecting the optimal selection of the surface coating material.

[0004] To solve the above problems, the present invention provides a Monte Carlo simulation method of atomic oxygen or ultraviolet flux based on the activity posture of solar wings, comprising the following steps:

[0005] Step S1, establishing or importing spacecraft geometric model data, and dividing components of the spacecraft into visible components and invisible components according to the correlation with the spacecraft surface;

[0006] Step S2, meshing the geometric surface of each visible component to generate a corresponding polygon mesh file;

[0007] Step S3, selecting solar wing reference point parameters and setting the solar wing rotation axis on the spacecraft geometric model;

[0008] Step S4, reading the spacecraft motion orbit file, determining the spacecraft body transformation quaternion parameters according to the motion parameters of each orbit point and the sunlight direction, and determining the solar wing rotation angle parameters according to the solar wing rotation axis and the sunlight direction;

[0009] Step S5, generating polygonal mesh data of each spacecraft motion track point according to the spacecraft body transformation quaternion parameters and / or the solar wing rotation angle parameters;

[0010] Step S6, performing Monte Carlo simulation calculation of the atomic oxygen flux or ultraviolet flux on the surface of the spacecraft according to the polygonal mesh data of each point of the spacecraft's motion orbit, to obtain the atomic oxygen flux or ultraviolet flux on the surface of the spacecraft.

[0011] Preferably, in step S1, the components of the spacecraft are divided into visible components and invisible components according to the correlation with the surface of the spacecraft, including: if any component of the spacecraft is related to the surface of the spacecraft, then the component is determined to be a visible component; if any component of the spacecraft is not related to the surface of the spacecraft, then the component is determined to be a invisible component.

[0012] Preferably, in step S2, each mesh unit of the visible component surface segmentation is stored continuously in the polygonal mesh file, and the start and end numbers of the mesh units are recorded.

[0013] Preferably, in step S2, meshing the geometric surface of each visible component includes: meshing the geometric surface of each visible component according to a preset meshing unit size parameter.

[0014] Preferably, in step S4, the sunlight direction is determined by the right-hand rule.

[0015] Preferably, in step S5, before generating various polygonal mesh data of the spacecraft motion orbit points according to the quaternion parameters of the spacecraft body transformation and / or the solar wing rotation angle parameters, it includes: step S51, generating the body coordinate system coordinates of the spacecraft non-solar wing surface unit polygon vertices according to the quaternion parameters of the spacecraft body transformation.

[0016] Preferably, in step S5, the polygonal mesh data of each spacecraft motion orbit point is generated according to the quaternion parameters of the spacecraft body transformation and / or the solar wing rotation angle parameters, and also includes: step S52, generating the body coordinate system coordinates of the polygonal vertices of the spacecraft solar wing surface unit according to the quaternion parameters of the spacecraft body transformation and the solar wing rotation angle parameters.

[0017] Preferably, in step S52, the body coordinate system coordinates of the polygonal vertices of the solar wing surface unit are generated according to the quaternion parameters of the spacecraft body transformation and the solar wing rotation angle parameters, including: converting the solar wing reference point and the solar wing rotation axis according to the quaternion parameters of the spacecraft body transformation, and converting the polygonal vertices of the solar wing surface unit according to the quaternion parameters of the spacecraft body transformation and the solar wing rotation angle parameters, to generate the body coordinate system coordinates of the polygonal vertices of the spacecraft solar wing surface unit.

[0018] Preferably, between step S4 and step S5, the method further includes: reorganizing the grid files of the components of the spacecraft to generate a grid file of the initial attitude of the spacecraft.

[0019] Preferably, in step S5, the polygonal mesh data of each spacecraft motion orbit point is generated according to the spacecraft body transformation quaternion parameters and / or the solar wing rotation angle parameters, and also includes: step S53, assembling different polygonal mesh units according to the body coordinate system coordinates of the polygonal vertices of the spacecraft non-solar wing surface unit, the body coordinate system coordinates of the polygonal vertices of the spacecraft solar wing surface unit and the assembly order of the spacecraft initial attitude mesh file to generate each polygonal mesh data of the spacecraft motion orbit point.

[0020] The advantages of the Monte Carlo simulation method of atomic oxygen or ultraviolet flux based on the active posture of the solar wing in the present invention over the prior art are: the present invention deeply integrates elements such as spacecraft modeling, surface meshing and orbital data, reasonably arranges the calculation process, accurately and efficiently completes the Monte Carlo simulation of atomic oxygen / ultraviolet radiation flux on the surface of the spacecraft under the active posture of the solar wing, and achieves the purpose of improving the calculation accuracy of atomic oxygen / ultraviolet radiation flux and its distribution. Among them, the efficiency comes from the fact that the present invention does not modify the overall logic of the Monte Carlo simulation process, which is convenient for combining multi-core parallel and data pruning technology to complete the calculation process. The accuracy comes from the fact that the present invention effectively transforms the Monte Carlo simulation and calculation process, so that the posture data of each point of the spacecraft motion orbit in the body coordinate system can accurately reflect the current rotation angle and occlusion relationship of the solar wing, and the steps are simple and easy to implement, which improves the accuracy of atomic oxygen / ultraviolet radiation flux, reduces the calculation, use and research costs of atomic oxygen / ultraviolet radiation flux on the surface of the spacecraft, and has great significance. In the technical applications such as the promotion of spacecraft simulation software, teaching, demonstration and optimization selection of spacecraft surface coating materials, it has obvious advantages and broad application prospects. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 The flowchart of the Monte Carlo simulation method of atomic oxygen or ultraviolet flux based on the activity posture of the solar wing in the embodiment of the present invention;

[0022] Figure 2 It is a schematic diagram of calculation results of atomic oxygen flux Monte Carlo simulation method based on the activity posture of solar wings in an embodiment of the present invention;

[0023] Figure 3 This is a schematic diagram of calculation results of a Monte Carlo simulation method for atomic oxygen flux on the surface of a spacecraft without solar wings in an embodiment of the present invention;

[0024] Figure 4 It is a schematic diagram of calculation results of the ultraviolet flux Monte Carlo simulation method based on the activity posture of the solar wing in an embodiment of the present invention;

[0025] Figure 5 Schematic diagram of calculation results of the Monte Carlo simulation method for the ultraviolet flux on the surface of a spacecraft without solar wings in an embodiment of the present invention. DETAILED DESCRIPTION

[0026] The technical solutions in the embodiments of the present application will be described clearly and in detail below with reference to the accompanying drawings.

[0027] 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 conjunction 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 implementation or example. Moreover, the specific features, structures, materials or characteristics described can be combined in any one or more embodiments or examples in a suitable manner.

[0028] It should also be noted that in the description of the embodiments of the present application, the term "include" 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 includes not only those elements, but also includes other elements not explicitly listed, or also includes elements inherent to such process, method, article, or terminal device. In the absence of further restrictions, the elements defined by the sentence "include..." do not exclude the existence of other identical elements in the process, method, article, or terminal device including the elements.

[0029] like Figure 1 As shown, in order to solve the above technical problems, an embodiment of the present invention provides an atomic oxygen or ultraviolet flux Monte Carlo simulation method based on the activity posture of the solar wing, comprising the following steps:

[0030] Step S1, establishing or importing spacecraft geometric model data, and dividing components of the spacecraft into visible components and invisible components according to the correlation with the spacecraft surface;

[0031] Step S2, meshing the geometric surface of each visible component to generate a corresponding polygon mesh file;

[0032] Step S3, selecting solar wing reference point parameters and setting the solar wing rotation axis on the spacecraft geometric model;

[0033] Step S4, reading the spacecraft motion orbit file, determining the spacecraft body transformation quaternion parameters according to the motion parameters of each orbit point and the sunlight direction, and determining the solar wing rotation angle parameters according to the solar wing rotation axis and the sunlight direction;

[0034] Step S5, generating polygonal mesh data of each spacecraft motion track point according to the spacecraft body transformation quaternion parameters and / or the solar wing rotation angle parameters;

[0035] Step S6, performing Monte Carlo simulation calculation of the atomic oxygen flux or ultraviolet flux on the surface of the spacecraft according to the polygonal mesh data of each point of the spacecraft's motion orbit, to obtain the atomic oxygen flux or ultraviolet flux on the surface of the spacecraft.

[0036] In the preprocessing stage of the Monte Carlo simulation process, this embodiment reasonably integrates elements such as spacecraft modeling, surface mesh generation, and space orbit data to generate polygonal mesh data of each spacecraft motion orbit point without changing the overall logic of the Monte Carlo simulation process, and can efficiently and accurately complete the calculation of the atomic oxygen / ultraviolet radiation flux and its distribution on the spacecraft surface under the conditions of the active attitude of the solar wing. The steps are simple and easy to implement, which improves the accuracy of the atomic oxygen / ultraviolet radiation flux and reduces the cost of calculation, use, and research of the atomic oxygen / ultraviolet radiation flux on the spacecraft surface, which is of great significance. In technical applications such as the promotion of spacecraft simulation software, teaching, demonstration, and optimization and selection of spacecraft surface coating materials, it has obvious advantages and broad application prospects.

[0037] In some embodiments, in step S1, the components of the spacecraft are divided into visible components and invisible components according to the correlation with the surface of the spacecraft, including: if any component of the spacecraft is related to the surface of the spacecraft, the component is determined to be a visible component; if any component of the spacecraft is not related to the surface of the spacecraft, the component is determined to be an invisible component. Thus, each component of the spacecraft is reasonably modeled to facilitate subsequent calculations.

[0038] In some embodiments, in step S2, each mesh unit of the visible component surface is continuously stored in the polygonal mesh file, and the start and end numbers of the mesh units are recorded. This facilitates the rapid positioning of the positions of the various mesh units on the solar wing surface, so as to subsequently accurately determine the polygonal mesh data of the spacecraft motion orbit point and improve the calculation accuracy.

[0039] In some embodiments, in step S2, meshing the geometric surface of each visible component includes: meshing the geometric surface of each visible component according to a preset meshing unit size parameter, thereby saving space.

[0040] In some embodiments, in step S4, the sunlight direction is determined by the right-hand rule, which is simple and accurate.

[0041] It should be noted that in step S4, the motion parameters and sunlight direction of each orbit point are obtained by reading the motion orbit file of the spacecraft and parsing it, and the method is simple.

[0042] In some embodiments, in step S5, before generating polygonal mesh data of each spacecraft motion track point according to the spacecraft body transformation quaternion parameters and / or the solar wing rotation angle parameters, the method includes: step S51, generating the body coordinate system coordinates of the spacecraft non-solar wing surface unit polygon vertices according to the quaternion parameters of the spacecraft body transformation, so as to facilitate the subsequent data processing and transformation.

[0043] In some embodiments, in step S5, the step of generating polygonal mesh data of each spacecraft motion orbit point according to the quaternion parameters of the spacecraft body transformation and / or the solar wing rotation angle parameters also includes: step S52, generating the body coordinate system coordinates of the polygonal vertices of the surface unit of the spacecraft solar wing according to the quaternion parameters of the spacecraft body transformation and the solar wing rotation angle parameters. Thus, the calculation of the atomic oxygen / ultraviolet radiation flux and its distribution on the spacecraft surface under the condition of the solar wing active attitude can be completed efficiently and accurately.

[0044] In some embodiments, in step S52, the generating of the body coordinate system coordinates of the polygonal vertices of the solar wing surface unit according to the quaternion parameters of the spacecraft body transformation and the solar wing rotation angle parameters includes: converting the solar wing reference point and the solar wing rotation axis according to the quaternion parameters of the spacecraft body transformation, and converting the polygonal vertices of the solar wing surface unit according to the quaternion parameters of the spacecraft body transformation and the solar wing rotation angle parameters, to generate the body coordinate system coordinates of the polygonal vertices of the spacecraft solar wing surface unit. Thus, the method is simple and the calculation efficiency is improved.

[0045] In some embodiments, between step S4 and step S5, the method further includes: reorganizing the grid files of the components of the spacecraft to generate a grid file of the initial attitude of the spacecraft, thereby facilitating subsequent data statistics.

[0046] In some embodiments, in step S5, the step of generating polygonal mesh data of each spacecraft motion track point according to the spacecraft body transformation quaternion parameters and / or the solar wing rotation angle parameters also includes: step S53, assembling different polygonal mesh units according to the body coordinate system coordinates of the polygonal vertices of the spacecraft non-solar wing surface unit, the body coordinate system coordinates of the polygonal vertices of the spacecraft solar wing surface unit, and the assembly order of the spacecraft initial attitude mesh file, to generate each polygonal mesh data of the spacecraft motion track point. In this way, the Monte Carlo simulation results can accurately reflect the active attitude of the solar wing without changing the overall logic of the Monte Carlo simulation, and the calculation is accurate, which improves the calculation accuracy.

[0047] Therefore, this embodiment deeply integrates elements such as spacecraft modeling, surface meshing and orbital data, rationally arranges the calculation process, accurately and efficiently completes the Monte Carlo simulation of the atomic oxygen / ultraviolet radiation flux on the spacecraft surface under the active posture of the solar wing, and achieves the purpose of improving the calculation accuracy of the atomic oxygen / ultraviolet radiation flux and its distribution. Among them, the efficiency comes from the fact that the present invention does not modify the overall logic of the Monte Carlo simulation process, which is convenient for combining multi-core parallel and data pruning technology to complete the calculation process. The accuracy comes from the fact that the present invention effectively transforms the Monte Carlo simulation and calculation process, so that the posture data of each point of the spacecraft motion orbit in the body coordinate system can accurately reflect the current rotation angle and occlusion relationship of the solar wing, and the steps are simple and easy to implement, which improves the accuracy of the atomic oxygen / ultraviolet radiation flux and reduces the cost of calculation, use and research of the atomic oxygen / ultraviolet radiation flux on the spacecraft surface, which is of great significance. In the technical applications such as the promotion of spacecraft simulation software, teaching, demonstration and optimization selection of spacecraft surface coating materials, it has obvious advantages and broad application prospects.

[0048] In order to verify the effectiveness of the atomic oxygen or ultraviolet flux Monte Carlo simulation method based on the active posture of the solar wing in this embodiment, the same grid density, number of particles, and number of particle reflections are used in this embodiment to calculate the atomic oxygen or ultraviolet flux simulation method of Monte Carlo without solar wings, as a comparison. Figure 2-5 As shown, Figure 2 Schematic diagram of calculation results of atomic oxygen flux Monte Carlo simulation method based on the activity posture of solar wings in an embodiment of the present invention, Figure 3 Schematic diagram of calculation results of Monte Carlo simulation method for atomic oxygen flux on the surface of a spacecraft without solar wings in an embodiment of the present invention, Figure 4 Schematic diagram of calculation results of the ultraviolet flux Monte Carlo simulation method based on the activity posture of the solar wing in an embodiment of the present invention, Figure 5 is a schematic diagram of calculation results of the Monte Carlo simulation method for ultraviolet flux on the surface of a spacecraft without solar wings in an embodiment of the present invention, and Figure 2 and Figure 3In the figure, the size of the atomic oxygen flux is represented by the change in color depth. The darker the color, the greater the atomic oxygen flux. Figure 4 and Figure 5 In the figure, the size of the ultraviolet radiation flux is represented by the change in color depth. The darker the color, the greater the ultraviolet radiation flux. It can be seen that the atomic oxygen or ultraviolet flux Monte Carlo simulation method based on the active posture of the solar wing in this embodiment is more in line with reality than the atomic oxygen or ultraviolet flux simulation method of Monte Carlo without solar wings in this embodiment.

[0049] Although the present invention is disclosed as above, the protection scope of the present invention is not limited thereto. Those skilled in the art may make various changes and modifications without departing from the spirit and scope of the present invention, and these changes and modifications will fall within the protection scope of the present invention.

Claims

1. A Monte Carlo simulation method of atomic oxygen or ultraviolet flux based on the activity posture of solar wings, characterized in that: The steps include: Step S1, establishing or importing spacecraft geometric model data, and dividing components of the spacecraft into visible components and invisible components according to the correlation with the spacecraft surface; Step S2, meshing the geometric surface of each visible component to generate a corresponding polygon mesh file; Step S3, selecting solar wing reference point parameters and setting the solar wing rotation axis on the spacecraft geometric model; Step S4, reading the spacecraft motion orbit file, determining the spacecraft body transformation quaternion parameters according to the motion parameters of each orbit point and the sunlight direction, and determining the solar wing rotation angle parameters according to the solar wing rotation axis and the sunlight direction; Step S5, generating polygonal mesh data of each spacecraft motion track point according to the spacecraft body transformation quaternion parameters and / or the solar wing rotation angle parameters; include: Step S51, generating the body coordinate system coordinates of the spacecraft non-solar wing surface unit polygon vertices according to the quaternion parameters of the spacecraft body transformation, Step S52, converting the solar wing reference point and the solar wing rotation axis according to the quaternion parameters of the spacecraft body transformation, and converting the polygonal vertices of the solar wing surface unit according to the quaternion parameters of the spacecraft body transformation and the solar wing rotation angle parameters, to generate the body coordinate system coordinates of the spacecraft solar wing surface unit polygonal vertices, Step S53, assembling different polygonal mesh units according to the body coordinate system coordinates of the polygonal vertices of the spacecraft non-solar wing surface unit, the body coordinate system coordinates of the polygonal vertices of the spacecraft solar wing surface unit, and the assembly order of the spacecraft initial attitude mesh file, to generate each polygonal mesh data of the spacecraft motion orbit point; Step S6, performing Monte Carlo simulation calculation of the atomic oxygen flux or ultraviolet flux on the surface of the spacecraft according to the polygonal mesh data of each point of the spacecraft's motion orbit, to obtain the atomic oxygen flux or ultraviolet flux on the surface of the spacecraft.

2. The atomic oxygen or ultraviolet flux Monte Carlo simulation method based on the solar wing activity posture according to claim 1 is characterized in that: In step S1, the components of the spacecraft are divided into visible components and invisible components according to the correlation with the surface of the spacecraft, including: if any component of the spacecraft is related to the surface of the spacecraft, the component is determined to be a visible component; if any component of the spacecraft is not related to the surface of the spacecraft, the component is determined to be a invisible component.

3. The atomic oxygen or ultraviolet flux Monte Carlo simulation method based on the solar wing activity posture according to claim 1 is characterized in that: In step S2, each mesh unit of the visible component surface segmentation is stored continuously in the polygonal mesh file, and the start and end numbers of the mesh units are recorded.

4. The atomic oxygen or ultraviolet flux Monte Carlo simulation method based on the solar wing activity posture according to claim 1 is characterized in that: In step S2, meshing the geometric surface of each visible component includes: meshing the geometric surface of each visible component according to a preset meshing unit size parameter.

5. The atomic oxygen or ultraviolet flux Monte Carlo simulation method based on the solar wing activity posture according to claim 1 is characterized in that: In step S4, the sunlight direction is determined by the right-hand rule.

6. The atomic oxygen or ultraviolet flux Monte Carlo simulation method based on the solar wing activity posture according to claim 1 is characterized in that: Between step S4 and step S5, the method further includes: reorganizing the grid files of the components of the spacecraft to generate a grid file of the initial attitude of the spacecraft.

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