A spacecraft surface charged potential acquisition method based on plasma energy spectrum

Abstract

The application provides a spacecraft surface charged potential acquisition method based on plasma energy spectrum, and relates to the field of space science and technology, and comprises the following steps: based on a spacecraft electrostatic simulation software, a double-layer flat plate model is obtained by simulating modeling according to an actual surface structure of a spacecraft; based on a Maxwell velocity distribution function, a plasma energy spectrum is obtained through plasma environment data; a spacecraft and electron plasma environment interaction model is obtained by model construction through the double-layer flat plate model and the plasma environment data; and the plasma energy spectrum is input into the spacecraft and electron plasma environment interaction model to obtain a spacecraft surface charged potential. The application realizes the reduction of time consumption while improving the calculation accuracy.

Description

Technical Field

[0001] This invention relates to the field of aerospace science and technology, and more specifically, to a method for obtaining the charged potential of a spacecraft surface based on plasma energy spectrum. Background Technology

[0002] With the rapid development of aerospace technology, the on-orbit reliability of spacecraft is receiving increasing attention. During their missions, spacecraft encounter complex space environments, including complex radiation environments composed of various particles that can damage them and affect their on-orbit lifespan. Among these, the surface charging effect can lead to spacecraft failure. Because the particle number density, temperature, and types vary in different orbital environments, the degree of charging on spacecraft differs, making accurate assessment of the surface charging potential of spacecraft crucial.

[0003] Currently, methods for obtaining the charged potential on the surface of spacecraft require first assuming a specific equilibrium potential value, substituting it into the current balance equation to determine if the net current is zero, and then iterating until the condition is met to determine the equilibrium potential. This method is relatively cumbersome and time-consuming. In addition, it does not consider the impact of space plasma environment analysis on the charged potential on the spacecraft surface, affecting the accuracy of the calculation. Summary of the Invention

[0004] The problem addressed by this invention is how to improve computational accuracy while reducing computational time.

[0005] To address the above problems, this invention provides a method for obtaining the charged potential of a spacecraft surface based on plasma energy spectrum.

[0006] In a first aspect, the present invention provides a method for obtaining the charged potential of a spacecraft surface based on plasma energy spectrum, comprising: Based on spacecraft electrostatic simulation software, a double-layer flat plate model was obtained by simulation modeling according to the actual surface structure of the spacecraft. Based on Maxwell's velocity distribution function, the plasma energy spectrum is obtained from plasma environment data. A model for the interaction between the spacecraft and the electron plasma environment is obtained by constructing a model using the double-layer flat plate model and the plasma environment data. The plasma energy spectrum is input into the interaction model between the spacecraft and the electron plasma environment to obtain the charged potential on the spacecraft surface.

[0007] Optionally, obtaining the plasma energy spectrum from plasma environment data includes: The plasma environment data is input into the Maxwell-Boltzmann distribution function to obtain the particle number distribution function in the velocity space; The particle flux is obtained through the particle number distribution function in the velocity space; The plasma energy spectrum is obtained based on the particle flux, wherein the plasma energy spectrum is used to represent the energy-flux density curve.

[0008] Optionally, the step of inputting the plasma environment data into the Maxwell-Boltzmann distribution function to obtain the particle number distribution function in the velocity space includes: The plasma environment data is input into the Maxwell-Boltzmann distribution function to obtain the particle number distribution function in the velocity space; The particle number distribution function in the velocity space includes: , Where f(v) is the particle number distribution function in the velocity space, v is the particle velocity, m is the particle mass, and n is the particle number density. Boltzmann's constant, For temperature.

[0009] Optionally, obtaining the particle flux through the particle number distribution function in the velocity space includes: The particle flux is obtained by inputting the particle number distribution function in the velocity space into the particle number distribution function formula in the velocity space and converting it. The particle flux includes: , Wherein, NF is the particle flux. This is the lower limit of particle velocity. This represents the upper limit of particle velocity.

[0010] Optionally, the plasma environment data includes particle types and energy distribution, and obtaining the plasma energy spectrum from the plasma environment data includes: The plasma energy spectrum is obtained by considering the particle types and the energy distribution.

[0011] Optionally, the process of obtaining the double-layer flat plate model through simulation modeling based on the actual surface structure of the spacecraft includes: A two-dimensional cross-sectional model is obtained by simplifying the actual surface structure of the spacecraft and then performing geometric modeling. The structured mesh is divided according to the two-dimensional cross-sectional model to obtain the double-layer plate model, wherein the double-layer plate model includes a shielding layer and a dielectric layer.

[0012] Optionally, the step of constructing a model of the interaction between the spacecraft and the electron plasma environment using the double-layer flat plate model and the plasma environment data includes: The double-layer flat plate model and the plasma environment data are used as parallel plate capacitors; The interaction model between the spacecraft and the electron plasma environment is obtained based on all the parallel plate capacitors.

[0013] Secondly, the present invention provides a spacecraft surface charged potential acquisition device based on plasma energy spectrum, comprising: a simulation modeling module, used to perform simulation modeling based on spacecraft electrostatic simulation software and the actual surface structure of the spacecraft to obtain a double-layer flat plate model; The plasma energy spectrum acquisition module is used to obtain the plasma energy spectrum based on Maxwell's velocity distribution function and plasma environment data. The model building module is used to build a model using the double-layer flat plate model and the plasma environment data to obtain a model of the interaction between the spacecraft and the electron plasma environment. The spacecraft surface charged potential acquisition module is used to input the plasma energy spectrum into the interaction model between the spacecraft and the electron plasma environment to obtain the charged potential of the spacecraft surface.

[0014] Thirdly, the present invention provides an electronic device, including a memory and a processor; The memory is used to store computer programs; The processor is configured to, when executing the computer program, implement the spacecraft surface charged potential acquisition method based on plasma energy spectrum as described in the first aspect.

[0015] Fourthly, the present invention provides a computer-readable storage medium storing a computer program that, when executed by a processor, implements the method for obtaining the charged potential of a spacecraft surface based on plasma energy spectrum as described in the first aspect.

[0016] The beneficial effects of the spacecraft surface charged potential acquisition method based on plasma energy spectrum of the present invention are as follows: A double-plate model is obtained by simulation modeling based on the actual surface structure of the spacecraft using spacecraft electrostatic simulation software. The particle number distribution function in the velocity space of the space plasma environment is derived based on Maxwell's velocity distribution function, and data is generated using software to plot the plasma energy spectrum. An interaction model between the spacecraft and the electron plasma environment is established using the double-plate model and plasma environment data, defining the concept of critical energy, considering the influence of space plasma environment analysis on the charged potential of the spacecraft surface, and improving calculation accuracy. The charged potential of the spacecraft surface is obtained by inputting the plasma energy spectrum into the model, thereby improving the calculation speed. Attached Figure Description

[0017] Figure 1This is a flowchart illustrating a method for obtaining the charged potential of a spacecraft surface based on plasma energy spectrum, according to an embodiment of the present invention. Figure 2 This is a schematic diagram of the interaction model between a spacecraft and an electron plasma environment according to an embodiment of the present invention; Figure 3 This is a schematic diagram of a spacecraft surface charged potential acquisition device based on plasma energy spectrum according to an embodiment of the present invention; Figure 4 This is a schematic diagram of the structure of an electronic device according to an embodiment of the present invention. Detailed Implementation

[0018] To make the above-mentioned objects, features, and advantages of the present invention more apparent and understandable, specific embodiments of the present invention will be described in detail below with reference to the accompanying drawings. Although some embodiments of the present invention are shown in the drawings, it should be understood that the present invention can be implemented in various forms and should not be construed as limited to the embodiments set forth herein. Rather, these embodiments are provided to provide a more thorough and complete understanding of the present invention. It should be understood that the accompanying drawings and embodiments of the present invention are for illustrative purposes only and are not intended to limit the scope of protection of the present invention.

[0019] It should be understood that the various steps described in the method embodiments of the present invention may be performed in different orders and / or in parallel. Furthermore, the method embodiments may include additional steps and / or omit the steps shown. The scope of the present invention is not limited in this respect.

[0020] The term "comprising" and its variations as used herein are open-ended, meaning "including but not limited to"; the term "based on" means "at least partially based on"; the term "one embodiment" means "at least one embodiment"; the term "another embodiment" means "at least one additional embodiment"; the term "some embodiments" means "at least some embodiments"; and the term "optionally" means "optional embodiments". Definitions of other terms will be given in the following description. It should be noted that the concepts of "first," "second," etc., mentioned in this invention are used only to distinguish different devices, modules, or units, and are not intended to limit the order of functions performed by these devices, modules, or units or their interdependencies.

[0021] It should be noted that the terms "one" and "more" used in this invention are illustrative rather than restrictive. Those skilled in the art should understand that, unless otherwise expressly indicated in the context, they should be understood as "one or more".

[0022] The names of the messages or information exchanged between the multiple devices in the embodiments of the present invention are for illustrative purposes only and are not intended to limit the scope of these messages or information.

[0023] like Figure 1 As shown in the figure, an embodiment of the present invention provides a method for obtaining the charged potential of a spacecraft surface based on plasma energy spectrum, comprising: Step 110: Based on spacecraft electrostatic simulation software, a double-layer flat plate model is obtained by simulation modeling according to the actual surface structure of the spacecraft.

[0024] Specifically, SPIS, a spacecraft electrostatic simulation software, was used to establish a simplified double-layer plate model based on the actual surface structure of the spacecraft. SPIS is an open-source, multiphysics coupled simulation software specifically designed for simulating the interaction between spacecraft and the space plasma environment. It is widely used in key space environment effect studies such as spacecraft surface / deep charging analysis, plasma sheath modeling, and electrostatic discharge (ESD) risk assessment. First, a list of materials required for this simulation was added, and the dielectric plate was configured, including the shielding layer thickness and material properties. Then, the number of dielectric layers after the shielding layer was set uniformly or individually, along with the thickness and material properties of the dielectric plate. The plate area was fixed at 1. .

[0025] Step 120: Based on Maxwell's velocity distribution function, obtain the plasma energy spectrum using plasma environment data.

[0026] Specifically, by substituting plasma environment data into the Maxwell-Boltzmann distribution function, the proportion of particles in different energy ranges is calculated through numerical integration. Combined with the particle number flux formula, the particle flux density per unit energy is obtained, and the energy spectrum is output as an energy-flux density curve.

[0027] Step 130: Using the double-layer flat plate model and the plasma environment data, a model is constructed to obtain the interaction model between the spacecraft and the electron plasma environment.

[0028] Specifically, such as Figure 2 As shown, the double-plate model and plasma environment data are considered as parallel plates, with the intermediate region representing a plasma sheath within the Debye length range. The interaction model between the spacecraft and the electron plasma environment is set according to the required particle type and energy range.

[0029] Step 140: Input the plasma energy spectrum into the interaction model between the spacecraft and the electron plasma environment to obtain the charged potential on the spacecraft surface.

[0030] Specifically, the core of the spacecraft-electron plasma environment interaction model follows dynamic equilibrium, only considering the contribution of electrons with velocities above the critical velocity to the surface charge, ignoring the effects of illumination and secondary electron emission, and finally solving for the charged potential on the spacecraft surface through the coupling of electric field and particle motion.

[0031] In some more specific embodiments, the current density distribution of the high-energy electron radiation dielectric layer is simulated. A 0.2 mm thick Kapton material flat dielectric is selected, and a single Maxwell plasma environment is chosen where both electron and ion number densities are [missing information]. Temperature is The electron number density in the dual Maxwell plasma environment is selected as follows: Temperature is The electron number density is The temperature is 1 eV; the ion number density is Temperature is ; Ion number density is The temperature is 1 eV.

[0032] In this embodiment, a double-layer flat plate model is obtained by simulation modeling based on the actual surface structure of the spacecraft using spacecraft electrostatic simulation software. The particle number distribution function in the velocity space of the space plasma environment is derived based on Maxwell's velocity distribution function, and data is generated using software to plot the plasma energy spectrum. An interaction model between the spacecraft and the electron plasma environment is established using the double-layer flat plate model and plasma environment data. The concept of critical energy is defined, and the influence of space plasma environment analysis on the charged potential of the spacecraft surface is considered to improve calculation accuracy. The plasma energy spectrum is input into the model to obtain the charged potential of the spacecraft surface, thereby improving the calculation speed.

[0033] Optionally, obtaining the plasma energy spectrum from plasma environment data includes: The plasma environment data is input into the Maxwell-Boltzmann distribution function to obtain the particle number distribution function in the velocity space; The particle flux is obtained through the particle number distribution function in the velocity space; The plasma energy spectrum is obtained based on the particle flux, wherein the plasma energy spectrum is used to represent the energy-flux density curve.

[0034] Specifically, plasma environment data includes particle types and energy distribution, from which particle flux is derived. The particle flux in the space plasma environment is derived from Maxwell's velocity distribution function. Software is used to generate corresponding data from the plasma environment data and particle flux, and an energy spectrum is plotted to obtain the plasma energy spectrum. Based on the physical meaning of particle flux and charge balance, an expression for the equilibrium potential containing particle flux is derived. Combined with the energy spectrum, the critical energy is determined, thus obtaining the equilibrium potential more quickly. The model is suitable for rough calculations of the potential. This method aims to improve computational efficiency while providing necessary analytical tools and theoretical guidance for the scientific evaluation of spacecraft on-orbit behavior.

[0035] Optionally, the step of inputting the plasma environment data into the Maxwell-Boltzmann distribution function to obtain the particle number distribution function in the velocity space includes: The plasma environment data is input into the Maxwell-Boltzmann distribution function to obtain the particle number distribution function in the velocity space; The particle number distribution function in the velocity space includes: , Where f(v) is the particle number distribution function in the velocity space, v is the particle velocity, m is the particle mass, and n is the particle number density. Boltzmann's constant, For temperature.

[0036] Optionally, obtaining the particle flux through the particle number distribution function in the velocity space includes: The particle flux is obtained by inputting the particle number distribution function in the velocity space into the particle number distribution function formula in the velocity space and converting it. The particle flux includes: , Wherein, NF is the particle flux. This is the lower limit of particle velocity. This represents the upper limit of particle velocity.

[0037] Specifically, the particle number distribution function formula in velocity space is essentially an integral of the particle velocity, where v is the velocity. This is the lower limit of particle velocity. This represents the upper limit of particle velocity. When a system composed of a large number of particles is in equilibrium or near equilibrium, the proportion of particles within each velocity range is definite, called the Maxwell velocity distribution function, or Maxwell-Boltzmann distribution function. A plasma environment where particle motion follows the Maxwell-Boltzmann distribution is called a Maxwell plasma environment. Based on the properties of the particles in the environment, it can be divided into single-Maxwell plasma and double-Maxwell plasma. As the name suggests, a single-Maxwell plasma environment macroscopically exhibits only one temperature and number density, while a double-Maxwell plasma environment contains two single-Maxwell plasma clusters, one cold and one hot, thus having two temperatures and number densities. Generally, the LEO orbit charging and discharging environment is a dense, low-temperature plasma, which can be considered a single-Maxwell plasma environment; the GEO orbit charging and discharging environment is mainly geomagnetic substorm plasma, usually considered a double-Maxwell plasma environment. Particle flux is an important parameter characterizing the space plasma environment.

[0038] Optionally, the plasma environment data includes particle types and energy distribution, and obtaining the plasma energy spectrum from the plasma environment data includes: The plasma energy spectrum is obtained by considering the particle types and the energy distribution.

[0039] Specifically, in a space plasma environment, the main types of plasma particles include electrons and ions. These particles do not possess a single energy level, but rather exist with a specific energy distribution function (or velocity distribution function). In different space regions (such as the solar wind, Earth's magnetosphere, and ionosphere), the energy distribution types of particles differ, directly affecting physical processes such as spacecraft charging, wave-particle interactions, and radiation belt dynamics.

[0040] Optionally, the process of obtaining the double-layer flat plate model through simulation modeling based on the actual surface structure of the spacecraft includes: A two-dimensional cross-sectional model is obtained by simplifying the actual surface structure of the spacecraft and then performing geometric modeling. The structured mesh is divided according to the two-dimensional cross-sectional model to obtain the double-layer plate model, wherein the double-layer plate model includes a shielding layer and a dielectric layer.

[0041] Specifically, the spacecraft electrostatic simulation software SPIS was used, with the actual surface structure of the spacecraft as the prototype, simplified into a double-layer flat plate model of "shielding layer + dielectric layer". The two-dimensional cross-section was delineated using the software's built-in geometric modeling tools, and a structured mesh was generated to ensure calculation accuracy. The shielding layer was made of aluminum alloy (thickness 0.1-0.5mm); the dielectric layer was made of Kapton material (thickness 0.2mm).

[0042] In this optional embodiment, the two-layer flat plate model of "shielding layer + dielectric layer" significantly reduces computational complexity, improves simulation efficiency, and retains the most critical electrical layering characteristics of the actual structure.

[0043] Optionally, the step of constructing a model of the interaction between the spacecraft and the electron plasma environment using the double-layer flat plate model and the plasma environment data includes: The double-layer flat plate model and the plasma environment data are used as parallel plate capacitors; The interaction model between the spacecraft and the electron plasma environment is obtained based on all the parallel plate capacitors.

[0044] Specifically, such as Figure 2As shown, if the spacecraft surface is considered as a flat plate, then the plasma environment and the spacecraft surface are approximately parallel-plate capacitors. The upper region represents the plasma environment S, typically a rarefied, high-temperature space plasma (such as the Earth's magnetosphere, solar wind, or auroral regions). The lower region represents the spacecraft surface, with a vacuum gap between them, the thickness of which is... That is, the Debye length. =0 represents the plasma potential, which is the reference potential and the average potential of the plasma region. A value less than 0 represents the spacecraft surface potential, indicating the spacecraft's potential relative to the plasma. This value is typically negative because electrons are more easily captured by the spacecraft than ions. E represents the electric field strength, and e represents the electron. Ignoring factors such as illumination and secondary electrons, we assume that an electron with velocity vc reaches the spacecraft surface at a velocity that drops to zero within a time interval tc, and is then accelerated away from the surface by the electric field. Dynamic equilibrium is reached when the number of electrons reaching and leaving the spacecraft surface is equal, at which point the spacecraft surface potential tends to a constant value, i.e., the equilibrium potential. Since electrons move at different velocities, only electrons with velocities higher than vc contribute to the charged potential of the spacecraft surface. Therefore, vc is defined as the critical velocity, and Ec as the corresponding critical energy. Ec is the standard energy value used to determine whether a particle contributes to the charged equilibrium potential of the spacecraft surface. The measured or simulated plasma energy spectrum (i.e., the relationship between particle energy and flux density) is used as a key input parameter in the interaction model between the spacecraft and the electron plasma environment. The influence of electrons with a speed higher than vc on the charged potential of the spacecraft surface is calculated. A total current balance equation is established, and the corresponding charged potential of the spacecraft surface can be obtained by iteratively solving it using numerical methods.

[0045] like Figure 3 As shown in the figure, an embodiment of the present invention provides a spacecraft surface charged potential acquisition device based on plasma energy spectrum, comprising: Simulation modeling module 10 is used to simulate and model the double-layer flat plate model based on the actual surface structure of the spacecraft using spacecraft electrostatic simulation software. Plasma energy spectrum acquisition module 20 is used to obtain plasma energy spectrum based on Maxwell velocity distribution function and plasma environment data; The model building module 30 is used to build a model using the double-layer flat plate model and the plasma environment data to obtain a model of the interaction between the spacecraft and the electron plasma environment. The spacecraft surface charged potential acquisition module 40 is used to input the plasma energy spectrum into the interaction model between the spacecraft and the electron plasma environment to obtain the charged potential of the spacecraft surface.

[0046] The spacecraft surface charged potential acquisition device based on plasma energy spectrum in this embodiment is used to realize the spacecraft surface charged potential acquisition method based on plasma energy spectrum as described above. Its advantages over the prior art are the same as the advantages of the spacecraft surface charged potential acquisition method based on plasma energy spectrum compared with the prior art, and will not be repeated here.

[0047] Optionally, the plasma energy spectrum acquisition module 20 is specifically used to: input the plasma environment data into the Maxwell-Boltzmann distribution function to obtain the particle number distribution function in the velocity space; The particle flux is obtained through the particle number distribution function in the velocity space; The plasma energy spectrum is obtained based on the particle flux, wherein the plasma energy spectrum is used to represent the energy-flux density curve.

[0048] Optionally, the plasma energy spectrum acquisition module 20 is specifically used to: input the plasma environment data into the Maxwell-Boltzmann distribution function to obtain the particle number distribution function in the velocity space; The particle number distribution function in the velocity space includes: , Where f(v) is the particle number distribution function in the velocity space, v is the particle velocity, m is the particle mass, and n is the particle number density. Boltzmann's constant, For temperature.

[0049] Optionally, the plasma energy spectrum acquisition module 20 is specifically used to: input the particle number distribution function in the velocity space into the particle number distribution function formula in the velocity space for conversion, and obtain the particle flux; The particle flux includes: , Wherein, NF is the particle flux. This is the lower limit of particle velocity. This represents the upper limit of particle velocity.

[0050] Optionally, the plasma energy spectrum acquisition module 20 is specifically used to: obtain the plasma energy spectrum by means of the particle type and the energy distribution.

[0051] Optionally, the simulation modeling module 10 is specifically used to: perform geometric modeling on the simplified actual surface structure of the spacecraft to obtain a two-dimensional cross-sectional model; The structured mesh is divided according to the two-dimensional cross-sectional model to obtain the double-layer plate model, wherein the double-layer plate model includes a shielding layer and a dielectric layer.

[0052] Optionally, the model building module 30 is specifically used to: use the double-layer flat plate model and the plasma environment data as a parallel plate capacitor; The interaction model between the spacecraft and the electron plasma environment is obtained based on all the parallel plate capacitors.

[0053] like Figure 4 As shown, an electronic device 400 provided in this embodiment of the invention includes a memory 410 and a processor 420; the memory 410 is used to store a computer program; the processor 420 is used to implement the method for obtaining the charged potential of a spacecraft surface based on plasma energy spectrum as described above when the computer program is executed.

[0054] Alternatively, an electronic device 400 includes a memory 410 and a processor 420 coupled to the memory 410; the memory 410 is configured to store a computer program; and the processor 420 is configured to perform the following operations when the computer program is executed: Based on spacecraft electrostatic simulation software, a double-layer flat plate model was obtained by simulation modeling according to the actual surface structure of the spacecraft. Based on Maxwell's velocity distribution function, the plasma energy spectrum is obtained from plasma environment data. A model for the interaction between the spacecraft and the electron plasma environment is obtained by constructing a model using the double-layer flat plate model and the plasma environment data. The plasma energy spectrum is input into the interaction model between the spacecraft and the electron plasma environment to obtain the charged potential on the spacecraft surface.

[0055] This invention provides a computer-readable storage medium storing a computer program. When the computer program is executed by a processor, it implements the method for obtaining the charged potential of a spacecraft surface based on plasma energy spectrum as described above.

[0056] Alternatively, a non-volatile computer-readable storage medium storing a computer program that, when executed by a processor, causes the processor to perform the following operations: Based on spacecraft electrostatic simulation software, a double-layer flat plate model was obtained by simulation modeling according to the actual surface structure of the spacecraft. Based on Maxwell's velocity distribution function, the plasma energy spectrum is obtained from plasma environment data. A model for the interaction between the spacecraft and the electron plasma environment is obtained by constructing a model using the double-layer flat plate model and the plasma environment data. The plasma energy spectrum is input into the interaction model between the spacecraft and the electron plasma environment to obtain the charged potential on the spacecraft surface.

[0057] The present invention will now be described an electronic device 400 that can serve as a server or client of the present invention, which is an example of a hardware device that can be applied to various aspects of the present invention. Electronic device 400 is intended to represent various forms of digital electronic computer devices, such as laptop computers, desktop computers, workstations, personal digital assistants, servers, blade servers, mainframe computers, and other suitable computers. Electronic device 400 can also represent various forms of mobile devices, such as personal digital processors, cellular phones, smartphones, wearable devices, and other similar computing devices. The components shown herein, their connections and relationships, and their functions are merely illustrative and are not intended to limit the implementation of the invention described and / or claimed herein.

[0058] Electronic device 400 includes a computing unit that can perform various appropriate actions and processes based on a computer program stored in read-only memory (ROM) or a computer program loaded from a storage unit into random access memory (RAM). The RAM may also store various programs and data required for device operation. The computing unit, ROM, and RAM are interconnected via a bus. Input / output (I / O) interfaces are also connected to the bus.

[0059] Those skilled in the art will understand that all or part of the processes in the above embodiments can be implemented by a computer program instructing related hardware. The program can be stored in a computer-readable storage medium, and when executed, it can include the processes of the embodiments of the above methods. The storage medium can be a magnetic disk, optical disk, read-only memory (ROM), or random access memory (RAM), etc. In this application, the units described as separate components may or may not be physically separate. The components shown as units may or may not be physical units; that is, they may be located in one place or distributed across multiple network units. Some or all of the units can be selected to achieve the purpose of the embodiments of the present invention according to actual needs. Furthermore, the functional units in the various embodiments of the present invention can be integrated into one processing unit, or each unit can exist physically separately, or two or more units can be integrated into one unit. The integrated units can be implemented in hardware or as software functional units.

[0060] 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 method for obtaining the charged potential of a spacecraft surface based on plasma energy spectrum, characterized in that, include: Based on spacecraft electrostatic simulation software, a double-layer flat plate model was obtained by simulation modeling according to the actual surface structure of the spacecraft. Based on Maxwell's velocity distribution function, the plasma energy spectrum is obtained from plasma environment data. A model for the interaction between the spacecraft and the electron plasma environment is obtained by constructing a model using the double-layer flat plate model and the plasma environment data. The plasma energy spectrum is input into the interaction model between the spacecraft and the electron plasma environment to obtain the charged potential on the spacecraft surface.

2. The method for obtaining the charged potential of a spacecraft surface based on plasma energy spectrum according to claim 1, characterized in that, The process of obtaining the plasma energy spectrum from plasma environment data includes: The plasma environment data is input into the Maxwell-Boltzmann distribution function to obtain the particle number distribution function in the velocity space; The particle flux is obtained through the particle number distribution function in the velocity space; The plasma energy spectrum is obtained based on the particle flux, wherein the plasma energy spectrum is used to represent the energy-flux density curve.

3. The method for obtaining the charged potential of a spacecraft surface based on plasma energy spectrum according to claim 2, characterized in that, The step of inputting the plasma environment data into the Maxwell-Boltzmann distribution function to obtain the particle number distribution function in the velocity space includes: The plasma environment data is input into the Maxwell-Boltzmann distribution function to obtain the particle number distribution function in the velocity space; The particle number distribution function in the velocity space includes: ， Where f(v) is the particle number distribution function in the velocity space, v is the particle velocity, m is the particle mass, and n is the particle number density. Boltzmann's constant, For temperature.

4. The method for obtaining the charged potential of a spacecraft surface based on plasma energy spectrum according to claim 2, characterized in that, The process of obtaining particle flux through the particle number distribution function in the velocity space includes: The particle flux is obtained by inputting the particle number distribution function in the velocity space into the particle number distribution function formula in the velocity space and converting it. The particle flux includes: ， Wherein, NF is the particle flux. This is the lower limit of particle velocity. This represents the upper limit of particle velocity.

5. The method for obtaining the charged potential of a spacecraft surface based on plasma energy spectrum according to claim 1, characterized in that, The plasma environment data includes particle types and energy distribution, and obtaining the plasma energy spectrum from the plasma environment data includes: The plasma energy spectrum is obtained by considering the particle types and the energy distribution.

6. The method for obtaining the charged potential of a spacecraft surface based on plasma energy spectrum according to claim 1, characterized in that, The process of simulating and modeling the double-layer flat plate based on the actual surface structure of the spacecraft to obtain the model includes: A two-dimensional cross-sectional model is obtained by simplifying the actual surface structure of the spacecraft and then performing geometric modeling. The structured mesh is divided according to the two-dimensional cross-sectional model to obtain the double-layer plate model, wherein the double-layer plate model includes a shielding layer and a dielectric layer.

7. The method for obtaining the charged potential of a spacecraft surface based on plasma energy spectrum according to claim 6, characterized in that, The process of constructing a model based on the double-layer flat plate model and the plasma environment data to obtain a model of the interaction between the spacecraft and the electron plasma environment includes: The double-layer flat plate model and the plasma environment data are used as parallel plate capacitors; The interaction model between the spacecraft and the electron plasma environment is obtained based on all the parallel plate capacitors.

8. A device for obtaining the charged potential of a spacecraft surface based on plasma energy spectrum, characterized in that, include: The simulation modeling module is used to simulate and model the double-layer flat plate model based on the actual surface structure of the spacecraft using spacecraft electrostatic simulation software. The plasma energy spectrum acquisition module is used to obtain the plasma energy spectrum based on Maxwell's velocity distribution function and plasma environment data. The model building module is used to build a model using the double-layer flat plate model and the plasma environment data to obtain a model of the interaction between the spacecraft and the electron plasma environment. The spacecraft surface charged potential acquisition module is used to input the plasma energy spectrum into the interaction model between the spacecraft and the electron plasma environment to obtain the charged potential of the spacecraft surface.

9. An electronic device, characterized in that, Including memory and processor; The memory is used to store computer programs; The processor is configured to, when executing the computer program, implement the method for obtaining the charged potential of a spacecraft surface based on plasma energy spectrum as described in any one of claims 1 to 7.

10. A computer-readable storage medium, characterized in that, The storage medium stores a computer program, which, when executed by a processor, implements the method for obtaining the charged potential of a spacecraft surface based on plasma energy spectrum as described in any one of claims 1 to 7.

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