Method, device and simulator for displaying atomic oxygen erosion effect on spacecraft surface

Abstract

The present invention provides a method for displaying the atomic oxygen erosion effect on a spacecraft surface, relating to the field of spacecraft simulation and computing technology. The method comprises: generating a structured mesh file based on the number of polygonal meshes in each direction within a coordinate system; generating an initial crack file; generating an erosion mesh file; and displaying the atomic oxygen erosion effect on the spacecraft surface based on the data in the structured mesh file, the initial crack file, and the erosion mesh file. Compared with existing technologies, the present invention can intuitively display the atomic oxygen erosion effect on a spacecraft surface, achieving the goal of accurately predicting the erosion of atomic oxygen and the material surface under ultraviolet light. Furthermore, the method is simple in steps and easy to operate.

Description

Technical Field

[0001] The present invention relates to the field of spacecraft simulation computing technology, and in particular to a method, device and simulator for displaying atomic oxygen erosion effects on a spacecraft surface. Background Art

[0002] Low Earth orbit, 200 to 700 km above Earth's surface, is the primary operating orbit for high-resolution optical remote sensing satellites and space stations. Atomic oxygen, with its high energy and oxidizing properties, is one of the most significant factors affecting the lifespan of spacecraft in this orbit. Atomic oxygen primarily erodes the thermal control layer on spacecraft surfaces, causing failure. Adding protective layers such as SiO2 and Al2O3 to thermal control materials is a common method for protecting against atomic oxygen. However, due to impacts from space debris and collisions during spacecraft transportation, various defects often form in the protective layer. Atomic oxygen can still strike the thermal control material through these defects and react with it, causing failure of the thermal control layer. Numerous researchers have investigated this issue using a variety of methods, including space flight tests, ground-based simulations, and numerical simulations. Studies have shown that space flight tests remain the most direct and effective method for assessing the effects of atomic oxygen erosion. However, these methods are costly and time-consuming, and currently available software only displays surface cloud images of the erosion, which lacks accuracy and fidelity. Summary of the Invention

[0003] The problem solved by the present invention is that the space flight test method in the prior art is expensive and has a long research cycle, and the erosion results displayed by the software currently on the market are all surface cloud images, which are not accurate or realistic enough.

[0004] To solve the above problems, the present invention provides a method for displaying the atomic oxygen erosion effect on the surface of a spacecraft, comprising the following steps:

[0005] Step S1, generating a structured grid file according to the number of polygonal grids in each direction in the coordinate system;

[0006] Step S2, generating an initial crack file;

[0007] Step S3, generating an erosion grid file;

[0008] Step S4, completing the display of the atomic oxygen erosion effect on the surface of the spacecraft according to the data of the structured grid file, the data of the initial crack file and the data of the erosion grid file.

[0009] Optionally, in step S2, the display of the atomic oxygen etching effect on the spacecraft surface is completed based on the data of the structured grid file, the data of the initial crack file and the data of the erosion grid file, including: reading the data of the structured grid file, the data of the initial crack file and the data of the erosion grid file, and playing the data of the structured grid file, the data of the initial crack file and the data of the erosion grid file frame by frame through the playback control component to complete the display of the atomic oxygen etching effect on the spacecraft surface.

[0010] Optionally, in step S2, the method for generating an initial crack file includes: creating an initial crack unstructured grid file, reading an initial crack definition file and obtaining the corresponding number of the polygonal grid unit, and assigning the number of the polygonal grid unit to the initial crack unstructured grid file to form initial crack data.

[0011] Optionally, in step S3, generating the erosion grid file includes: establishing a thread class, and generating erosion data of different time steps using a loop in a preset function.

[0012] Optionally, the generating of erosion data of different time steps by looping in a preset function includes:

[0013] Step S31, reading the etching process record file and parsing it into the memory structure;

[0014] Step S32: creating an eroded unstructured grid file, and saving the data information in the eroded process record file to the eroded unstructured grid file to identify the number of eroded grid units.

[0015] Optionally, in step S31, the first column of the etching process record file records the etching steps corresponding to each etching time, and the second column of the etching process record file records the unit number of the polygonal mesh where the etching event occurs at each etching time.

[0016] Optionally, the data information in the etching process record file includes the unit number of the polygonal mesh where the etching event occurs at each etching time and the point information of the polygonal mesh unit where the etching event occurs at each etching time.

[0017] The advantage of the method for displaying the atomic oxygen etching effect on the surface of a spacecraft described in the present invention over the prior art is that the present invention can accurately obtain the internal etching depth of the material under the synergistic action of atomic oxygen and ultraviolet rays through this simulation method, and can intuitively display the atomic oxygen etching effect on the surface of the spacecraft, so as to achieve the purpose of accurately predicting the surface etching of the material under atomic oxygen and ultraviolet rays, and the method has simple steps and is easy to operate. In addition, the present invention can greatly reduce the time and cost of atomic oxygen and ultraviolet simulation tests, and can also provide the necessary basis for optimizing the ability of materials to resist space environment effects, which is of great significance to the study of the synergistic effect of space environment on materials. It has obvious advantages and broad application prospects in the study of the synergistic effect of atomic oxygen and ultraviolet rays on materials and the application of reinforcement technology for resistance to space environment effects.

[0018] In order to solve the above technical problems, the present invention further provides a display device for the atomic oxygen erosion effect on the surface of a spacecraft, comprising:

[0019] A structured grid file generation module, wherein the structured grid file generation module is used to generate a structured grid file according to the number of polygonal grids in each direction in the coordinate system;

[0020] An initial crack file generating module, wherein the initial crack file generating module is used to generate an initial crack file;

[0021] An erosion grid file generation module, wherein the erosion grid file generation module is used to generate an erosion grid file;

[0022] A display module is used to display the atomic oxygen erosion effect on the surface of the spacecraft based on the data of the structured grid file, the data of the initial crack file and the data of the erosion grid file.

[0023] The device for displaying the atomic oxygen etching effect on the surface of a spacecraft described in the present invention and the method for displaying the atomic oxygen etching effect on the surface of a spacecraft described in the present invention have the same advantages as those of the prior art and will not be described in detail here.

[0024] In order to solve the above technical problems, the present invention also provides a simulator of the atomic oxygen etching effect on the surface of a spacecraft, comprising a computer-readable storage medium storing a computer program and a processor. When the computer program is read and run by the processor, the method described above is implemented.

[0025] The simulator for atomic oxygen etching effect on the surface of a spacecraft and the method for displaying atomic oxygen etching effect on the surface of a spacecraft described in the present invention have the same advantages over the prior art and will not be described in detail here.

[0026] In order to solve the above technical problems, the present invention further provides a computer-readable storage medium, wherein the computer-readable storage medium stores a computer program, and when the computer program is read and executed by a processor, the method described above is implemented.

[0027] The advantages of the computer-readable storage medium and the method for displaying the atomic oxygen etching effect on the surface of a spacecraft described in the present invention are the same as those of the prior art and will not be repeated here. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] Figure 1 This is a flow chart of a method for displaying the atomic oxygen erosion effect on a spacecraft surface according to an embodiment of the present invention;

[0029] Figure 2 This is a schematic diagram showing the display results of the atomic oxygen erosion effect on the spacecraft surface in the zero-frame state in an embodiment of the present invention;

[0030] Figure 3 Schematic diagram showing the display results of atomic oxygen erosion effect on the spacecraft surface under ten frames in an embodiment of the present invention;

[0031] Figure 4 This is a schematic diagram showing the display results of the atomic oxygen erosion effect on the spacecraft surface under the fifty-frame state in an embodiment of the present invention;

[0032] Figure 5 This is a schematic diagram showing the display results of the atomic oxygen etching effect on the spacecraft surface in one hundred frames in an embodiment of the present invention. DETAILED DESCRIPTION

[0033] The technical solutions in the embodiments of the present application will be described clearly and in detail below with reference to the accompanying drawings.

[0034] In the description of the embodiments of this application, the term "some embodiments" means that the specific features, structures, materials, or characteristics described in conjunction with that 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 suitable manner in any one or more embodiments or examples.

[0035] 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 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 "comprising..." do not exclude the presence of other identical elements in the process, method, article, or terminal device including the elements.

[0036] like Figure 1 As shown, an embodiment of the present invention provides a method for displaying the atomic oxygen erosion effect on the surface of a spacecraft, comprising the following steps:

[0037] Step S1, generating a structured grid file according to the number of polygonal grids in each direction in the coordinate system;

[0038] Step S2, generating an initial crack file;

[0039] Step S3, generating an erosion grid file;

[0040] Step S4, completing the display of the atomic oxygen erosion effect on the surface of the spacecraft according to the data of the structured grid file, the data of the initial crack file and the data of the erosion grid file.

[0041] In some specific embodiments, the structured grid file is defined as structuredgrid.vtk to facilitate data storage.

[0042] In some embodiments, in step S2, the display of the atomic oxygen etching effect on the spacecraft surface is completed based on the data of the structured grid file, the data of the initial crack file, and the data of the erosion grid file, including: reading the data of the structured grid file, the data of the initial crack file, and the data of the erosion grid file, and playing the data of the structured grid file, the data of the initial crack file, and the data of the erosion grid file frame by frame through a playback control component to complete the display of the atomic oxygen etching effect on the spacecraft surface.

[0043] In some specific embodiments, in step S1, the coordinate system is a three-dimensional coordinate system. Accordingly, in step S4, completing the display of the atomic oxygen etching effect on the spacecraft surface is equivalent to completing the three-dimensional display of the atomic oxygen etching effect on the spacecraft surface, which is more intuitive.

[0044] In some embodiments, in step S2, the method for generating an initial crack file includes: creating an initial crack unstructured grid file, reading an initial crack definition file and obtaining the corresponding number of the polygonal grid unit, and assigning the number of the polygonal grid unit to the initial crack unstructured grid file to form initial crack data.

[0045] In some specific embodiments, the initial crack unstructured grid file is defined as crackgrid to facilitate data storage.

[0046] In some embodiments, in step S3, generating the erosion grid file includes: establishing a thread class, and generating erosion data of different time steps using a loop in a preset function.

[0047] It should be noted that the preset function in this embodiment is the run function, which makes the calculation more convenient and accurate. In addition, the erosion data in this embodiment is defined as steps*.vtk to facilitate data storage.

[0048] In some embodiments, the step of generating erosion data at different time steps by looping in a preset function includes:

[0049] Step S31, reading the etching process record file and parsing it into the memory structure;

[0050] Step S32: creating an eroded unstructured grid file, and saving the data information in the eroded process record file to the eroded unstructured grid file to identify the number of eroded grid units.

[0051] In some specific embodiments, in step S31, the first column of the etching process record file records the etching step corresponding to each etching time, and the second column of the etching process record file records the unit number of the polygonal mesh where the etching event occurs at each etching time.

[0052] Correspondingly, in step S32, the data information in the etching process record file includes the unit number of the polygonal mesh where the etching event occurs at each etching time and the point information of the polygonal mesh unit where the etching event occurs at each etching time.

[0053] Therefore, the advantage of the method for displaying the atomic oxygen etching effect on the surface of a spacecraft described in this embodiment over the prior art is that this embodiment can accurately obtain the internal etching depth of the material under the synergistic action of atomic oxygen and ultraviolet rays through this simulation method, and can intuitively display the atomic oxygen etching effect on the surface of the spacecraft, so as to achieve the purpose of accurately predicting the surface etching of the material under atomic oxygen and ultraviolet rays, and this method has simple steps and is easy to operate. In addition, this embodiment can greatly reduce the time and cost of atomic oxygen and ultraviolet simulation tests, and can also provide the necessary basis for optimizing the ability of materials to resist space environment effects, which is of great significance to the study of the synergistic effect of space environment on materials. In the study of the synergistic effect of atomic oxygen and ultraviolet rays in materials and the application of reinforcement technology for resistance to space environment effects, it has obvious advantages and broad application prospects.

[0054] Another embodiment of the present invention further provides a device for displaying the atomic oxygen erosion effect on a spacecraft surface, comprising:

[0055] A structured grid file generation module, the structured grid file generation module is used to generate a structured grid file according to the number of polygonal grids in each direction in the coordinate system;

[0056] An initial crack file generating module, wherein the initial crack file generating module is used to generate an initial crack file;

[0057] An erosion grid file generation module, wherein the erosion grid file generation module is used to generate an erosion grid file;

[0058] A display module is used to display the atomic oxygen erosion effect on the surface of the spacecraft based on the data of the structured grid file, the data of the initial crack file and the data of the erosion grid file.

[0059] The display device of the atomic oxygen etching effect on the surface of a spacecraft described in this embodiment and the display method of the atomic oxygen etching effect on the surface of a spacecraft described in this embodiment have the same advantages as those of the prior art and will not be repeated here.

[0060] Another embodiment of the present invention also provides a simulator for the atomic oxygen erosion effect on the surface of a spacecraft, comprising a computer-readable storage medium storing a computer program and a processor. When the computer program is read and executed by the processor, the method described above is implemented.

[0061] The simulator of the atomic oxygen etching effect on the surface of a spacecraft described in this embodiment and the method for displaying the atomic oxygen etching effect on the surface of a spacecraft described in this embodiment have the same advantages as those of the prior art and will not be described in detail here.

[0062] Yet another embodiment of the present invention provides a computer-readable storage medium storing a computer program. When the computer program is read and executed by a processor, the computer program implements the method described above.

[0063] The computer-readable storage medium described in this embodiment and the method for displaying the atomic oxygen etching effect on the surface of a spacecraft have the same advantages as those of the prior art and will not be described in detail here.

[0064] It should be noted that the computer-readable storage medium in this embodiment may be a tangible device that can hold and store instructions used by an instruction execution device. The computer-readable storage medium may be, for example, but not limited to, an electrical storage device, a magnetic storage device, an optical storage device, an electromagnetic storage device, a semiconductor storage device, or any suitable combination thereof. In some specific examples, the computer-readable storage medium includes: a portable computer disk, a hard disk, a random access memory (RAM), a read-only memory (ROM), an erasable programmable read-only memory (EPROM or flash memory), a static random access memory (SRAM), a portable compact disc read-only memory (CD-ROM), a digital versatile disk (DVD), a memory stick, a floppy disk, a mechanical encoding device, and any suitable combination thereof.

[0065] Although the present disclosure is disclosed as above, the protection scope of the present disclosure 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 disclosure, and these changes and modifications will fall within the protection scope of the present invention.

Claims

1. A method for displaying the atomic oxygen erosion effect on the surface of a spacecraft, characterized in that: The process includes the following steps: Step S1, generating a structured grid file according to the number of polygonal grids in each direction in the coordinate system; Step S2, generating an initial crack file, including creating an initial crack unstructured grid file, reading the initial crack definition file and obtaining the corresponding polygonal grid unit number, assigning the polygonal grid unit number to the initial crack unstructured grid file to form initial crack data; Step S3, generating an erosion grid file, includes: establishing a thread class, and using a loop to generate erosion data of different time steps in a preset function, wherein the method of using a loop to generate erosion data of different time steps in the preset function includes: Step S31, reading an etching process record file and parsing it into a memory structure, wherein the first column of the etching process record file records the etching step corresponding to each etching time, and the second column of the etching process record file records the cell number of the polygonal mesh where the etching event occurs at each etching time; Step S32: creating an eroded unstructured grid file, saving the data information in the eroded process record file to the eroded unstructured grid file to identify the number of grid cells eroded in each erosion step, wherein the data information in the eroded process record file includes the cell number of the polygonal grid where the erosion event occurs at each erosion time and the point information of the polygonal grid cell where the erosion event occurs at each erosion time; Step S4, completing the display of the atomic oxygen erosion effect on the surface of the spacecraft according to the data of the structured grid file, the data of the initial crack file and the data of the erosion grid file.

2. The method for displaying the atomic oxygen erosion effect on the surface of a spacecraft according to claim 1, characterized in that: In step S4, the display of the atomic oxygen etching effect on the spacecraft surface is completed based on the data of the structured grid file, the data of the initial crack file and the data of the erosion grid file, including: reading the data of the structured grid file, the data of the initial crack file and the data of the erosion grid file, and playing the data of the structured grid file, the data of the initial crack file and the data of the erosion grid file frame by frame through the playback control component to complete the display of the atomic oxygen etching effect on the spacecraft surface.

3. A display device for the atomic oxygen erosion effect on the surface of a spacecraft, based on the display method for the atomic oxygen erosion effect on the surface of a spacecraft as claimed in claim 1 or 2, characterized in that: include: A structured grid file generation module, wherein the structured grid file generation module is used to generate a structured grid file according to the number of polygonal grids in each direction in the coordinate system; An initial crack file generating module, wherein the initial crack file generating module is used to generate an initial crack file; An erosion grid file generation module, wherein the erosion grid file generation module is used to generate an erosion grid file; A display module is used to display the atomic oxygen erosion effect on the surface of the spacecraft based on the data of the structured grid file, the data of the initial crack file and the data of the erosion grid file.

4. A simulator for the atomic oxygen erosion effect on a spacecraft surface, characterized in that: The invention comprises a computer-readable storage medium storing a computer program and a processor, wherein the computer program implements the method according to claim 1 or 2 when read and executed by the processor.

5. A computer-readable storage medium, characterized in that The computer-readable storage medium stores a computer program, and when the computer program is read and executed by a processor, the method according to claim 1 or 2 is implemented.

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