Simulation method for material ablation effect based on synergistic action of atomic oxygen and ultraviolet
By obtaining atomic oxygen environment parameters and considering the synergistic effect of ultraviolet irradiation, the erosion thickness of spacecraft materials is calculated, solving the problem of simulation result deviation in existing technologies, realizing efficient and accurate material erosion simulation, and reducing costs and time.
Patent Information
- Application Number
- CN202210762547.X
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- Filing Date
- 2022-06-30
- Publication Date
- 2026-01-06
- Estimated Expiration
- 2042-06-30
AI Technical Summary
Most existing simulation software only performs numerical simulations of the single-atom oxygen effect, which leads to deviations between the simulation results and the actual spacecraft environment, affecting accuracy.
By obtaining parameters of the atomic oxygen environment, a three-dimensional model of the spacecraft is established, the atomic oxygen flux is calculated, and the synergistic effect of ultraviolet irradiation is considered to determine the material erosion response coefficient, and finally the erosion thickness of the material is obtained.
It enables accurate simulation of atomic oxygen flux and erosion thickness on material surfaces under different space environments, improving the accuracy of simulation results, reducing simulation costs and time, and providing an assessment basis for the material's resistance to space environment effects.
Smart Images
Figure CN115188438B_ABST
Abstract
Description
Technical Field
[0001] This invention relates to the field of spacecraft simulation and calculation technology, and more specifically, to a simulation method based on the material erosion effect under the synergistic effect of atomic oxygen and ultraviolet light. Background Technology
[0002] Spacecraft operating in low Earth orbit face a complex space environment, particularly atomic oxygen, which can cause severe erosion of materials. Current research methods for studying the effects of the space environment include costly and technically challenging flight tests, and costly and time-consuming ground simulations. Numerical simulations, on the other hand, are low-cost, time-efficient, and offer high accuracy. Currently, most simulation software for atomic oxygen effects only performs numerical simulations of the single atomic oxygen effect. These simulations focus more on the interaction mechanism between atomic oxygen and material surfaces, and the simulated environment is mostly a single atomic oxygen environment. This deviates significantly from the actual environment faced by spacecraft in low Earth orbit, affecting the accuracy of the simulation results. Summary of the Invention
[0003] The problem solved by this invention is that most simulation software in the prior art only performs numerical simulations of the single-atom oxygen effect, which deviates significantly from the actual environment faced by spacecraft in low Earth orbit, affecting the accuracy of the simulation results.
[0004] To address the above problems, this invention provides a simulation method for the material ablation effect based on the synergistic effect of atomic oxygen and ultraviolet light, comprising the following steps:
[0005] Step S1: Obtain atomic oxygen environment influence parameters, including: spacecraft speed, incoming flow direction, and atomic oxygen density;
[0006] Step S2: Establish a three-dimensional model of the spacecraft, input the atomic oxygen environment influence parameters into the three-dimensional model, and obtain the atomic oxygen flux on the spacecraft surface;
[0007] Step S3: Determine the ablation reaction coefficient of the spacecraft surface material based on the synergistic effect of atomic oxygen and ultraviolet radiation on the spacecraft surface.
[0008] Step S4: Obtain the erosion thickness of the spacecraft surface material by using the atomic oxygen flux on the spacecraft surface and the erosion reaction coefficient of the spacecraft surface material.
[0009] Preferably, in step S2, the atomic oxygen flux on the spacecraft surface includes the instantaneous atomic oxygen flux on the spacecraft surface and the cumulative atomic oxygen flux on the spacecraft surface.
[0010] Preferably, in step S2, inputting the atomic oxygen environment influence parameters into the three-dimensional model to obtain the atomic oxygen flux on the spacecraft surface includes:
[0011] Step S21: Input the atomic oxygen environment influence parameters into the three-dimensional model, calculate the polygonal mesh cells of the spacecraft surface that simulates atomic oxygen particle collisions, and obtain the instantaneous atomic oxygen flux on the spacecraft surface.
[0012] Step S22: Obtain the spacecraft's on-orbit flight time, and obtain the cumulative atomic oxygen flux on the spacecraft's surface based on the instantaneous atomic oxygen flux on the spacecraft's surface and the spacecraft's on-orbit flight time.
[0013] Preferably, in step S3, determining the ablation response coefficient of the spacecraft surface material based on the synergistic effect of atomic oxygen and ultraviolet radiation on the spacecraft surface includes:
[0014] When the spacecraft surface only comes into contact with atomic oxygen particles, the ablation reaction coefficient of the spacecraft surface material is the atomic oxygen reaction coefficient of the spacecraft surface material;
[0015] When the surface of a spacecraft is subjected to the combined effects of atomic oxygen and ultraviolet radiation, the ablation reaction coefficient of the spacecraft surface material is the combined reaction coefficient of atomic oxygen and ultraviolet radiation on the spacecraft surface material.
[0016] Preferably, the synergistic reaction coefficient of atomic oxygen and ultraviolet radiation on the spacecraft surface material is obtained by the ratio of the ultraviolet intensity received by the spacecraft surface to the total ultraviolet intensity received by the spacecraft during its on-orbit operation.
[0017] Preferably, in step S4, obtaining the erosion thickness of the spacecraft surface material using the atomic oxygen flux on the spacecraft surface and the erosion reaction coefficient of the spacecraft surface material includes:
[0018] The erosion thickness of the spacecraft surface material is obtained by multiplying the accumulated atomic oxygen flux on the spacecraft surface by the erosion reaction coefficient of the spacecraft surface material.
[0019] Preferably, in step S1, the spacecraft surface material includes a polyimide material or a polyimide material doped with a protective material.
[0020] Preferably, the protective material includes silicon dioxide or aluminum oxide.
[0021] Preferably, in step S1, the atomic oxygen density is obtained based on the solar activity level and the spacecraft's flight altitude.
[0022] Preferably, in step S1, the atomic oxygen environment influence parameters also include the spacecraft quaternion, the orbital hexagram, the orbital latitude and longitude altitude, and the position of the solar array.
[0023] The simulation method for material erosion effects based on the synergistic effect of atomic oxygen and ultraviolet radiation described in this invention has the advantage over existing technologies in that it can accurately calculate the atomic oxygen flux on the material surface under different space environments, obtain the erosion thickness of the material surface, and accurately express the synergistic effect of atomic oxygen and ultraviolet radiation, thereby achieving the goal of accurately predicting the erosion of the material surface under different atomic oxygen and ultraviolet radiation doses. This invention can autonomously adjust the space environment parameters of the material according to the actual irradiation conditions, achieving both accurate simulation and accelerated evaluation of the synergistic effect of atomic oxygen and ultraviolet radiation. The steps are simple and easy to operate, significantly reducing the time and cost of atomic oxygen and ultraviolet simulation experiments. It can also provide necessary basis for optimizing the material's resistance to space environment effects, and has significant implications for the study of the synergistic effect of materials in space environments. It has obvious advantages and broad application prospects in the study of the synergistic effect of atomic oxygen and ultraviolet radiation in materials and in the application of space environment hardening technology. Attached Figure Description
[0024] Figure 1 This is a flowchart of a simulation method for material ablation effect based on the synergistic effect of atomic oxygen and ultraviolet light in an embodiment of the present invention;
[0025] Figure 2 This is a schematic diagram illustrating the simulation effect of material ablation under the synergistic effect of atomic oxygen and ultraviolet light in an embodiment of the present invention;
[0026] Figure 3 This is a schematic diagram illustrating the simulation effect of material erosion under the single action of atomic oxygen in an embodiment of the present invention;
[0027] Figure 4 This is a material erosion curve diagram under the single action of atomic oxygen in an embodiment of the present invention;
[0028] Figure 5 This is a material ablation curve based on the synergistic effect of atomic oxygen and ultraviolet light in an embodiment of the present invention. Detailed Implementation
[0029] The technical solutions in the embodiments of this application will be clearly and thoroughly described below with reference to the accompanying drawings.
[0030] In the description of the embodiments in this application, the term "some embodiments" means that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of the present invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same implementation or instance. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples.
[0031] It should also be noted that, in the description of the embodiments of this application, the term "comprising" or any other variations thereof is intended to cover non-exclusive inclusion, such that a process, method, article, or terminal device that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or terminal device. Without further limitations, an element defined by the phrase "comprising..." does not exclude the presence of other identical elements in the process, method, article, or terminal device that includes said element.
[0032] like Figure 1 As shown, this embodiment of the invention provides a simulation method for the material ablation effect based on the synergistic effect of atomic oxygen and ultraviolet light, comprising the following steps:
[0033] Step S1: Obtain atomic oxygen environment influence parameters, including: spacecraft speed, incoming flow direction, and atomic oxygen density;
[0034] Step S2: Establish a three-dimensional model of the spacecraft, input the atomic oxygen environment influence parameters into the three-dimensional model, and obtain the atomic oxygen flux on the spacecraft surface;
[0035] Step S3: Determine the ablation reaction coefficient of the spacecraft surface material based on the synergistic effect of atomic oxygen and ultraviolet radiation on the spacecraft surface.
[0036] Step S4: Obtain the erosion thickness of the spacecraft surface material by using the atomic oxygen flux on the spacecraft surface and the erosion reaction coefficient of the spacecraft surface material.
[0037] It should be noted that in this embodiment, the erosion effect of atomic oxygen on the material surface mainly occurs in two aspects. On the one hand, high-energy atomic oxygen impacts the material surface, causing mechanical damage; on the other hand, the strong oxidizing atomic oxygen chemically corrodes the material. Ultimately, this leads to damage to the material surface, changes in performance, or even failure. The presence of ultraviolet radiation will affect the reaction or erosion rate of atomic oxygen with certain materials. This is because ultraviolet radiation can cause cross-linking of molecular chains and breakage of valence bonds in temperature-controlled coatings or organic polymers, thereby causing softening or fragmentation of the material surface, providing a channel for atomic oxygen erosion and exacerbating it. Therefore, the simulation method in this embodiment can accurately calculate the atomic oxygen flux on the material surface under different space environments, obtain the erosion thickness of the material surface under the synergistic effect of atomic oxygen and ultraviolet radiation, accurately express the synergistic effect of atomic oxygen and ultraviolet radiation, and achieve the goal of accurately predicting the erosion of the material surface under different atomic oxygen and ultraviolet radiation doses. This embodiment can also autonomously adjust the space environment parameters of the material according to the actual irradiation of the material, achieving both accurate simulation and accelerated evaluation of the erosion effect of the material under the synergistic effect of atomic oxygen and ultraviolet radiation.
[0038] In some embodiments, in step S2, the atomic oxygen flux on the spacecraft surface includes the instantaneous atomic oxygen flux and the cumulative atomic oxygen flux on the spacecraft surface. This provides more comprehensive data and more accurate simulations.
[0039] In this embodiment, the cumulative atomic oxygen flux on the spacecraft surface is the product of the instantaneous atomic oxygen flux on the surface at the orbital altitude during the spacecraft's on-orbit operation and the spacecraft's on-orbit flight time, which is convenient and accurate to calculate.
[0040] In some specific embodiments, step S2, which involves inputting the atomic oxygen environment influence parameters into the three-dimensional model to obtain the atomic oxygen flux on the spacecraft surface, includes:
[0041] Step S21: Input the atomic oxygen environment influence parameters into the three-dimensional model, calculate the polygonal mesh cells of the spacecraft surface that simulates atomic oxygen particle collisions, and obtain the instantaneous atomic oxygen flux on the spacecraft surface.
[0042] Step S22: Obtain the spacecraft's on-orbit flight time, and obtain the cumulative atomic oxygen flux on the spacecraft's surface based on the instantaneous atomic oxygen flux on the spacecraft's surface and the spacecraft's on-orbit flight time.
[0043] In some embodiments, step S3, determining the ablation response coefficient of the spacecraft surface material based on the synergistic effect of atomic oxygen and ultraviolet radiation on the spacecraft surface, includes:
[0044] When the spacecraft surface only comes into contact with atomic oxygen particles, the ablation reaction coefficient of the spacecraft surface material is the atomic oxygen reaction coefficient of the spacecraft surface material;
[0045] When the surface of a spacecraft is subjected to the combined effects of atomic oxygen and ultraviolet radiation, the ablation reaction coefficient of the spacecraft surface material is the combined reaction coefficient of atomic oxygen and ultraviolet radiation on the spacecraft surface material.
[0046] Therefore, the effect of ultraviolet irradiation on atomic oxygen ablation can be taken into account, making the simulation data more accurate.
[0047] In some embodiments, the synergistic reaction coefficient of atomic oxygen with ultraviolet radiation on the spacecraft surface material is obtained by the ratio of the ultraviolet intensity received by the spacecraft surface to the total ultraviolet intensity received by the spacecraft during its operation in orbit. This ensures accurate calculation.
[0048] In some preferred embodiments, the atomic oxygen reaction coefficient of the spacecraft surface material is (1 - the synergistic reaction coefficient of atomic oxygen and ultraviolet radiation of the spacecraft surface material). When the spacecraft surface only comes into contact with atomic oxygen particles, that is, when only a single atomic oxygen acts on the spacecraft surface, the synergistic reaction coefficient of atomic oxygen and ultraviolet radiation of the spacecraft surface material is zero. Therefore, when the spacecraft surface only comes into contact with atomic oxygen particles, the ablation reaction coefficient of the spacecraft surface material is the same as the atomic oxygen reaction coefficient of the spacecraft surface material, and the calculation is accurate.
[0049] In some embodiments, step S4, obtaining the erosion thickness of the spacecraft surface material using the atomic oxygen flux on the spacecraft surface and the erosion reaction coefficient of the spacecraft surface material, includes:
[0050] The erosion thickness of the spacecraft surface material is obtained by multiplying the accumulated atomic oxygen flux on the spacecraft surface by the erosion reaction coefficient of the spacecraft surface material.
[0051] In some specific embodiments, the erosion thickness of the spacecraft surface material is the product of the cumulative atomic oxygen flux on the spacecraft surface and the erosion reaction coefficient of the spacecraft surface material, which is convenient and accurate to calculate.
[0052] In some specific examples, in step S1, the spacecraft surface material includes a polyimide material or a polyimide material doped with a protective material.
[0053] In some preferred embodiments, the polyimide material is Kapton, a homopolymer polyimide film material developed and manufactured by DuPont. Kapton is widely used in spacecraft due to its excellent performance. Multiple on-orbit flights abroad have shown that its atomic oxygen erosion rate is relatively stable and not easily affected by other space environment factors. Therefore, it can be used as an ideal polymer material for monitoring atomic oxygen flux.
[0054] In some preferred embodiments, the protective material includes silicon dioxide or aluminum oxide. This is low-cost, readily available, and provides some protection to the material.
[0055] In some embodiments, in step S1, the atomic oxygen density is obtained based on the degree of solar activity and the spacecraft's flight altitude.
[0056] In some preferred embodiments, the manned spaceflight orbit is 360km. At this flight altitude, the solar activity index varies depending on the degree of solar activity, and the density of atomic oxygen gradually increases with the increase of the solar activity index.
[0057] In some specific embodiments, the solar activity level includes low solar activity years, medium solar activity years, and high solar activity years, and the solar activity index gradually increases in the order of low solar activity years, medium solar activity years, and high solar activity years.
[0058] In some specific embodiments, the incoming flow direction is used to describe the direction of the spacecraft's operation during orbital flight. In some specific embodiments, assuming the spacecraft is stationary and the atomic oxygen is in motion, the incoming flow direction refers to the direction from which the atomic oxygen contacts the spacecraft, indirectly describing the direction of the spacecraft's operation during orbital flight.
[0059] In some specific embodiments, the spacecraft rate is the spacecraft's on-orbit flight rate.
[0060] In some embodiments, in step S3, ultraviolet irradiation is related to ultraviolet irradiation intensity and ultraviolet irradiation direction. By changing the above-mentioned ultraviolet irradiation environmental influence parameters, the ultraviolet irradiation flux under different space environments can be obtained.
[0061] It should be noted that in this embodiment, the amount of ultraviolet radiation varies with solar activity; the shorter the wavelength, the greater the variation. The energy of ultraviolet radiation is mainly concentrated in the higher wavelength band, which exhibits smaller and more stable variations. Therefore, in this embodiment, the total ultraviolet radiation intensity is considered a constant for lifetime prediction.
[0062] In some embodiments, the ultraviolet irradiation direction is described by the angle between the solar ultraviolet radiation direction and the normal to the spacecraft surface. This allows for a more accurate reflection of the ultraviolet irradiation direction.
[0063] In some embodiments, the atomic oxygen environmental impact parameters and ultraviolet radiation environmental impact parameters also include the spacecraft's quaternion number, orbital hexagram number, orbital latitude and longitude, and solar array position. This fully considers the spacecraft's three-dimensional satellite structure and on-orbit operational status, resulting in more accurate data.
[0064] To verify the effectiveness of the simulation method based on the synergistic effect of atomic oxygen and ultraviolet light in this embodiment, the same mesh density, particle number, and particle reflectance number were used to simulate the material erosion effect under the single effect of atomic oxygen, for comparison. Figure 2-5 As shown, Figure 2 This is a schematic diagram illustrating the simulation effect of material ablation under the synergistic effect of atomic oxygen and ultraviolet light in this embodiment; Figure 3 This is a schematic diagram illustrating the simulation effect of material erosion under the single action of atomic oxygen in this embodiment;
[0065] Figure 4 This is a material erosion curve under the single action of atomic oxygen in this embodiment; Figure 5 This is a material ablation curve based on the synergistic effect of atomic oxygen and ultraviolet light in this embodiment. Figure 2 and Figure 3 In the figure, the thickness of the erosion is represented by the color intensity; the darker the color, the greater the erosion thickness and the more severe the erosion. As can be seen from the figure, the erosion effect based on the synergistic effect of atomic oxygen and ultraviolet light in this embodiment is stronger than the erosion effect based on the single effect of atomic oxygen in this embodiment, and is more consistent with the actual operating conditions of spacecraft.
[0066] Therefore, this embodiment can accurately calculate the atomic oxygen flux on the material surface under different space environments, obtain the surface erosion thickness under the synergistic effect of atomic oxygen and ultraviolet radiation, accurately express the synergistic effect of atomic oxygen and ultraviolet radiation, and achieve the goal of accurately predicting the surface erosion of materials under different atomic oxygen and ultraviolet radiation doses. Furthermore, this embodiment can autonomously adjust the space environment parameters of the material according to the actual irradiation conditions, achieving both accurate simulation and accelerated evaluation of the erosion effect of materials under the synergistic effect of atomic oxygen and ultraviolet radiation. The steps are simple and easy to operate, significantly reducing the time and cost of atomic oxygen and ultraviolet simulation experiments. It can also provide necessary basis for optimizing the material's resistance to space environment effects, and has significant implications for the study of the synergistic effect of materials in the space environment. It has obvious advantages and broad application prospects in the study of the synergistic effect of atomic oxygen and ultraviolet radiation in materials and in the application of hardening technology to resist space environment effects.
[0067] While the present invention has been disclosed above, its scope of protection is not limited thereto. Those skilled in the art can make various changes and modifications without departing from the spirit and scope of the present invention, and all such changes and modifications will fall within the scope of protection of the present invention.
Claims
1. A simulation method based on the synergistic effect of atomic oxygen and ultraviolet on material ablation, characterized in that, The method comprises the following steps: Step S1, obtaining atomic oxygen environmental influence parameters, the atomic oxygen environmental influence parameters comprising: a spacecraft speed, an incoming flow direction, and an atomic oxygen density; Step S2, establishing a three-dimensional model of the spacecraft, inputting the atomic oxygen environmental influence parameters into the three-dimensional model, and obtaining a spacecraft surface atomic oxygen flux; Step S3, determining a spacecraft surface material ablation reaction coefficient according to a situation in which the spacecraft surface is subjected to atomic oxygen and ultraviolet radiation, comprising: when the spacecraft surface only touches atomic oxygen particles, the spacecraft surface material ablation reaction coefficient is an atomic oxygen reaction coefficient of a spacecraft surface material; when the spacecraft surface is subjected to atomic oxygen and ultraviolet radiation simultaneously, the spacecraft surface material ablation reaction coefficient is an atomic oxygen and ultraviolet synergistic reaction coefficient of the spacecraft surface material, and the atomic oxygen and ultraviolet synergistic reaction coefficient is obtained through a ratio of an ultraviolet intensity received by the spacecraft surface to a total ultraviolet intensity received by the spacecraft during on-orbit operation; Step S4, obtaining an ablation thickness of a spacecraft surface material through the spacecraft surface atomic oxygen flux and the spacecraft surface material ablation reaction coefficient.
2. The simulation method based on the synergistic effect of atomic oxygen and ultraviolet on material ablation effect according to claim 1, characterized in that, In step S2, the spacecraft surface atomic oxygen flux comprises a spacecraft surface instantaneous atomic oxygen flux and a spacecraft surface cumulative atomic oxygen flux.
3. The simulation method based on the synergistic effect of atomic oxygen and ultraviolet on material ablation effect according to claim 2, characterized in that, In step S2, inputting the atomic oxygen environmental influence parameters into the three-dimensional model to obtain the spacecraft surface atomic oxygen flux comprises: Step S21, inputting the atomic oxygen environmental influence parameters into the three-dimensional model, calculating and simulating a polygonal grid unit of the spacecraft surface touched by atomic oxygen particles, and obtaining the spacecraft surface instantaneous atomic oxygen flux; Step S22, obtaining a spacecraft on-orbit flight time, and obtaining the spacecraft surface cumulative atomic oxygen flux according to the spacecraft surface instantaneous atomic oxygen flux and the spacecraft on-orbit flight time.
4. The simulation method based on the effect of atomic oxygen and ultraviolet synergistic material ablation according to claim 2 or 3, characterized in that, In step S4, obtaining the ablation thickness of the spacecraft surface material through the spacecraft surface atomic oxygen flux and the spacecraft surface material ablation reaction coefficient comprises: Obtaining the ablation thickness of the spacecraft surface material through a product of the spacecraft surface cumulative atomic oxygen flux and the spacecraft surface material ablation reaction coefficient.
5. The simulation method based on the synergistic effect of atomic oxygen and ultraviolet on material ablation effect according to claim 1, characterized in that, In step S1, the spacecraft surface material comprises a polyimide material or a polyimide material doped with a protective material.
6. The simulation method based on the synergistic effect of atomic oxygen and ultraviolet on material ablation effect according to claim 5, characterized in that, The protective material comprises silicon dioxide or aluminum oxide.
7. The simulation method based on the synergistic effect of atomic oxygen and ultraviolet on material ablation effect according to claim 1, characterized in that, In step S1, the atomic oxygen density is obtained according to a solar activity level and a spacecraft flight height.
8. The simulation method based on the synergistic effect of atomic oxygen and ultraviolet on material ablation effect according to claim 1, characterized in that, In step S1, the atomic oxygen environmental influence parameters further comprise a spacecraft quaternion, an orbit six-element number, an orbit longitude and latitude height, and a solar wing position.