Method and device for simulating the plasma environment of the earth's ionosphere in satellite orbit

Abstract

The present invention provides a method and device for simulating the plasma environment of the earth's ionosphere of a satellite in orbit, which relates to the technical field of computer simulation. The simulation method includes: obtaining the current state parameters of each satellite in a low-orbit constellation at the current simulation time, obtaining the communication link mission parameters of the satellite, obtaining the state parameters of multiple communication satellites for establishing a space communication link according to the communication link mission parameters and the current state parameters, establishing the ionosphere plasma environment model of the satellite according to the current simulation time and the current state parameters; and obtaining the ionosphere plasma environment characterization data of each communication satellite according to the ionosphere plasma environment model and the communication satellite state parameters. The present invention can calculate the quantitative characterization analysis of the space plasma environment in the earth's atmospheric ionosphere where each satellite is located while realizing the communication link simulation of the low-orbit communication satellite.

Description

Technical Field

[0001] The present invention relates to the field of computer simulation technology, and in particular to a method, device, computer equipment and computer-readable storage medium for simulating the plasma environment of the Earth's ionosphere when a satellite is in orbit. Background Art

[0002] The ionosphere is a quasi-neutral plasma region mainly produced by the ionization of part of the upper atmosphere by high-energy electromagnetic radiation from the sun. It is located in the altitude range of 50km to about 1000km, and the dominant neutral gases and ions are and Above 1000 km, the ion density begins to exceed that of the neutral gas, and H + and He + Gradually becoming the dominant ion component. The ionosphere has a lower temperature and a much higher number density than other space plasma regions. Except for the auroral belt region, the temperature of ionospheric plasma is generally 300K to 3500K (0.05-0.3eV).

[0003] The main energy source of the ionosphere comes from the solar extreme ultraviolet radiation. Since electrons are easily heated, their temperature is higher than that of ions and neutral atoms. The electron temperature is about 300K at an altitude of 100km, and increases to about 3500K at an altitude of 800km. Below 400km, the ion temperature is close to that of neutral gas. Below 150km, due to the high atmospheric density and collision frequency, the temperatures of electrons, ions and neutral gases are the same. Generally, the temperature of ionospheric plasma is lowest at the geomagnetic equator and increases with increasing latitude.

[0004] Satellite communication is an operating state of satellites in orbit. In the existing technology, communication simulation based on satellite constellations is the basic work of satellite communication payload design. Low-orbit communication satellites generally operate at an altitude in or near the ionosphere of the Earth's outer atmosphere. The effect of satellite communication will be affected by many factors, among which the Earth's ionosphere, a charged plasma layer, has a greater impact on the effect of satellite communication. Therefore, it is of great significance to be able to provide the plasma layer environment of the communication satellite while conducting research on the satellite communication simulation function. Summary of the invention

[0005] The problem solved by the present invention is to calculate quantitative characterization data of the space plasma environment in the ionosphere of the earth's atmosphere where each satellite is located while realizing the communication link simulation of the low-orbit communication satellite.

[0006] In order to solve the above problems, the present invention provides a satellite on-orbit earth ionosphere plasma environment simulation method, characterized in that it includes:

[0007] Get the current state parameters of each satellite in the low-orbit constellation at the current simulation time,

[0008] Get the satellite's communication link mission parameters,

[0009] According to the communication link mission parameters and the current state parameters, multiple communication satellite state parameters for establishing a space communication link are acquired,

[0010] Establishing an ionospheric plasma environment model of the satellite according to the current simulation time and the current state parameters;

[0011] According to the ionospheric plasma environment model and the communication satellite state parameters, the ionospheric plasma environment characterization data of each of the communication satellites is obtained.

[0012] Optionally, before obtaining the current state parameters of each satellite in the low-orbit constellation at the current simulation time, the method further includes:

[0013] Get the simulation time range and simulation step size,

[0014] The simulation time range is divided into a plurality of continuously distributed simulation moments according to the simulation step size.

[0015] Optionally, the simulation time range is obtained by calculating the simulation start time and the simulation end time.

[0016] Optionally, obtaining the current state parameters of each satellite in the low-orbit constellation at the current simulation moment includes: obtaining the orbital elements of each satellite at the start time of the simulation, starting from the start time of the simulation, calculating the current state parameters of each satellite at each simulation moment according to the orbital elements of each satellite at the start time of the simulation until the simulation ends.

[0017] Optionally, acquiring multiple communication satellite state parameters for establishing a space communication link according to the communication link mission parameters and the current state parameters includes:

[0018] Establishing a satellite topology structure according to the current state parameters of each of the satellites;

[0019] According to the communication link mission parameters, traverse the valid communication links in the satellite topology structure;

[0020] After screening the effective communication links, multiple communication satellite status parameters for establishing space communication links are obtained.

[0021] Optionally, the effective communication link screening includes: screening all the effective communication links based on the principle of shortest path.

[0022] Optionally, the ionospheric plasma environment characterization data of the communication satellite includes electron density or electron temperature.

[0023] The advantages of the satellite on-orbit earth ionosphere plasma environment simulation method described in the present invention over the prior art are: the present invention provides a satellite on-orbit earth ionosphere plasma environment simulation method, which can realize the communication link simulation of low-orbit communication satellites while calculating the quantitative characterization analysis of the space plasma environment in the earth's atmospheric ionosphere where each satellite is located. This helps my country's space satellite designers deal with the impact of the harsh space environment of communication satellites on the quality and reliability of satellite communications.

[0024] In order to solve the above problems, the present invention also provides a satellite on-orbit earth ionosphere plasma environment simulation device, comprising:

[0025] an acquisition unit, the acquisition unit being used to acquire current state parameters of each satellite in the low-orbit constellation at a current simulation time,

[0026] The acquisition unit is also used to acquire the communication link mission parameters of the satellite;

[0027] A model building unit, the model building unit is used to build an ionospheric plasma environment model of the satellite according to the current simulation time and the current state parameters;

[0028] a computing unit, the computing unit being used to obtain state parameters of a plurality of communication satellites for establishing a space communication link according to the communication link mission parameters and the current state parameters,

[0029] The calculation unit is also used to obtain ionospheric plasma environment characterization data of each of the communication satellites based on the ionospheric plasma environment model and the communication satellite state parameters.

[0030] The plasma environment simulation device for the ionosphere satellite communication process described in the present invention has the same advantages as the satellite on-orbit ionosphere plasma environment simulation method over the prior art, which will not be repeated here.

[0031] To solve the above problems, the present invention also provides a computer device, including a computer-readable storage medium storing a computer program and a processor. When the computer program is read and executed by the processor, the satellite in-orbit Earth ionosphere plasma environment simulation method is implemented.

[0032] The advantages of the computer device described in the present invention and the satellite on-orbit Earth ionosphere plasma environment simulation method over the prior art are the same and will not be repeated here.

[0033] To solve the above problems, the present invention also provides a computer-readable storage medium, which stores a computer program. When the computer program is read and executed by a processor, the method for simulating the plasma environment of the Earth's ionosphere when the satellite is in orbit is implemented.

[0034] The computer-readable storage medium described in the present invention and the satellite on-orbit Earth ionosphere plasma environment simulation method have the same advantages over the prior art, which will not be repeated here. BRIEF DESCRIPTION OF THE DRAWINGS

[0035] Figure 1 This is an application environment diagram of the satellite on-orbit Earth ionosphere plasma environment simulation method according to an embodiment of the present invention;

[0036] Figure 2 This is a flow chart of a method for simulating the plasma environment of the Earth's ionosphere when a satellite is in orbit according to an embodiment of the present invention;

[0037] Figure 3 A schematic diagram of the distribution and running trajectory of low-orbit constellations in the three-dimensional space around the earth in an embodiment of the present invention;

[0038] Figure 4 A real-time quantitative characterization data curve diagram of the ionospheric plasma environment experienced by a satellite of a low-orbit constellation marked as Iridium100 in an embodiment of the present invention;

[0039] Figure 5 It is a structural diagram of a satellite on-orbit earth ionosphere plasma environment simulation device in an embodiment of the present invention;

[0040] Figure 6 1 is a diagram showing the internal structure of a computer device in an embodiment of the present invention. DETAILED DESCRIPTION

[0041] The technical solutions in the embodiments of the present application will be described clearly and in detail below with reference to the accompanying drawings.

[0042] In the description of the embodiments of the present application, the description of the term "some embodiments" means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic representation of the above terms does not necessarily refer to the same implementation or example. Moreover, the specific features, structures, materials or characteristics described can be combined in any one or more embodiments or examples in a suitable manner.

[0043] Figure 1 This is an application environment diagram of the satellite on-orbit earth ionosphere plasma environment simulation method in the embodiment of this application. Figure 1The satellite on-orbit earth ionosphere plasma environment simulation method is applied to a plasma environment simulation system of an earth ionosphere satellite communication process. The plasma environment simulation system of an earth ionosphere satellite communication process includes a terminal 110 and a server 120. The terminal 110 and the server 120 are connected via a network. The terminal 110 can be a desktop terminal or a mobile terminal, and the mobile terminal can be at least one of a mobile phone, a tablet computer, a laptop computer, etc. The server 120 can be implemented by an independent server or a server cluster composed of multiple servers.

[0044] like Figure 2 As shown, in one embodiment, a method for simulating the plasma environment of the Earth ionosphere in a satellite orbit is provided. This embodiment mainly applies the method to the above Figure 1 The terminal 110 (or server 120) in FIG. Figure 2 The satellite on-orbit earth ionosphere plasma environment simulation method specifically includes the following steps:

[0045] Step 210, obtaining the current state parameters of each satellite in the low-orbit constellation at the current simulation time,

[0046] Step 220, obtaining the satellite's communication link mission parameters,

[0047] Step 230, acquiring state parameters of multiple communication satellites for establishing a space communication link according to the communication link mission parameters and the current state parameters,

[0048] Step 240, establishing an ionospheric plasma environment model of the satellite according to the current simulation time and the current state parameters;

[0049] Step 250, obtaining ionospheric plasma environment characterization data of each of the communication satellites according to the ionospheric plasma environment model and the communication satellite state parameters.

[0050] It should be noted that in this embodiment, the constellation refers to a satellite network composed of multiple satellites in accordance with certain rules and shapes that can provide certain coverage performance, and is the basic form of collaborative work of multiple satellites. The satellite constellation structure will affect the network coverage area, network latency and system cost, etc.

[0051] For satellites deployed in low orbit, an orbital altitude between 700km and 1500km is generally selected. When the altitude is below 700km, the satellite is susceptible to atmospheric damping and corrosion by oxygen atoms, and its life span is short. The altitude between 1500km and 5000km is the first Van Allen belt, which has a strong corrosive effect on celestial bodies. For communication functions, a higher orbit can expand the coverage area and increase the visible elevation angle, but a lower orbit is conducive to improving the signal detection capability and communication signal strength. Taking the above factors into consideration, the orbital altitude of the low-orbit constellation is set at 700km.

[0052] In some embodiments, before obtaining the current state parameters of each satellite in the low-orbit constellation at the current simulation time, the method further includes:

[0053] Get the simulation time range and simulation step size,

[0054] The simulation time range is divided into a plurality of continuously distributed simulation moments according to the simulation step size.

[0055] It should be noted that the simulation step size is generally in seconds.

[0056] In this embodiment, the simulation time range is obtained by calculating the simulation start time and the simulation end time.

[0057] In some embodiments, in step 210, obtaining the current state parameters of each satellite in the low-orbit constellation at the current simulation moment includes: obtaining the orbital elements of each satellite at the start time of the simulation, starting from the start time of the simulation, calculating the current state parameters of each satellite at each simulation moment according to the orbital elements of each satellite at the start time of the simulation, until the simulation ends.

[0058] In this embodiment, the orbital elements of the satellite include: the semi-major axis, which is used to describe the size of the orbit; the eccentricity, which is used to describe the shape of the orbit; the inclination, which is used to describe the inclination angle of the orbital plane relative to the equatorial plane; the right ascension of the ascending node, which is used to describe the position of the ascending node relative to the vernal equinox; the argument of perigee, which is used to describe the position of the perigee relative to the ascending node; and the true anomaly, which is used to describe the position of the satellite relative to the perigee.

[0059] In some embodiments, in step 230, acquiring multiple communication satellite state parameters for establishing a space communication link according to the communication link mission parameters and the current state parameters includes:

[0060] Establishing a satellite topology structure according to the current state parameters of each of the satellites;

[0061] According to the communication link mission parameters, traverse the valid communication links in the satellite topology structure;

[0062] After screening the effective communication links, multiple communication satellite status parameters for establishing space communication links are obtained, and a list is established.

[0063] The communication link task parameter is two satellites that need to establish a communication link. The effective communication link screening includes: screening all the effective communication links based on the principle of the shortest path, so as to make the communication fast.

[0064] In some embodiments, in step 240, the interface of the satellite's ionospheric plasma environment model is designed as: "input-data file path + input-time + input-spatial position + output-electron density + output-electron temperature, etc." wherein the input-data file path is used to specify the file location that the model needs to read; the input-time is the current simulation moment of each satellite, the input-spatial position is the spatial position of each satellite corresponding to the current simulation moment, and the output-electron density + output-electron temperature, etc. are all calculation output items of the model, which are the calculation results of the model.

[0065] In some embodiments, in step 250, the ionospheric plasma environment characterization data of the communication satellite includes electron density or electron temperature.

[0066] In a specific embodiment, the low-orbit constellation provided is an Iridium constellation, and the constellation is designed with 6 circular polar orbits, each of which has 11 satellites, and the orbit altitude is a low earth circular orbit of 765 km, forming a constellation configuration as follows: Figure 3 shown. Figure 4 A real-time quantitative characterization data curve chart of the ionospheric plasma environment experienced by a satellite in the Iridium constellation marked as Iridium100 in an embodiment of the present invention is shown.

[0067] Therefore, in this embodiment, the spatial positions of satellites in the constellation change in space with the passage of simulation time, the topological structure of the constellation in space also changes, the satellites on the communication link also changes, and the space ionospheric plasma environment in which the satellites are located also changes. For this reason, this embodiment provides a satellite in-orbit earth ionospheric plasma environment simulation method, which can calculate the quantitative characterization and analysis of the space plasma environment in the earth's atmospheric ionosphere where each satellite is located while realizing the communication link simulation of low-orbit communication satellites, thereby helping my country's space satellite designers to deal with the impact of the harsh space environment of communication satellites on the quality and reliability of satellite communications.

[0068] like Figure 5 As shown, another embodiment of the present invention further provides a satellite on-orbit earth ionosphere plasma environment simulation device, comprising:

[0069] An acquisition unit 710 is used to acquire current state parameters of each satellite in the low-orbit constellation at a current simulation time.

[0070] The acquisition unit 710 is also used to acquire the communication link mission parameters of the satellite;

[0071] A model building unit 720, the model building unit 720 is used to build an ionospheric plasma environment model of the satellite according to the current simulation time and the current state parameters;

[0072] A calculation unit 730, wherein the calculation unit 730 is used to obtain state parameters of multiple communication satellites for establishing a space communication link according to the communication link mission parameters and the current state parameters,

[0073] The calculation unit 730 is also used to obtain ionospheric plasma environment characterization data of each of the communication satellites based on the ionospheric plasma environment model and the communication satellite state parameters.

[0074] The advantages of the satellite on-orbit Earth ionosphere plasma environment simulation device and the satellite on-orbit Earth ionosphere plasma simulation method described in this embodiment are the same as those of the prior art, which will not be repeated here.

[0075] In one embodiment, a computer device is provided, including a memory, a processor, and a computer program stored in the memory and executable on the processor. When the processor executes the computer program, the steps of the above-mentioned satellite in-orbit Earth ionosphere plasma environment simulation method are implemented.

[0076] Figure 6 The internal structure diagram of a computer device in one embodiment is shown. The computer device may specifically be Figure 1 The terminal 110 (or server 120) in FIG. Figure 6 As shown, the computer device includes a processor, a memory, a network interface, an input device and a display screen connected through a system bus. Among them, the memory includes a non-volatile storage medium and an internal memory. The non-volatile storage medium of the computer device stores an operating system and may also store a computer program. When the computer program is executed by the processor, the processor can implement a satellite in-orbit earth ionosphere plasma environment simulation method. The internal memory may also store a computer program. When the computer program is executed by the processor, the processor can execute a satellite in-orbit earth ionosphere plasma environment simulation method. The display screen of the computer device may be a liquid crystal display screen or an electronic ink display screen, and the input device of the computer device may be a touch layer covered on the display screen, or a button, trackball or touchpad provided on the computer device housing, or an external keyboard, touchpad or mouse, etc.

[0077] In one embodiment, a computer-readable storage medium is provided, on which a computer program is stored. When the computer program is executed by a processor, the steps of the above-mentioned satellite in-orbit Earth ionosphere plasma environment simulation method are implemented.

[0078] Those skilled in the art can understand that all or part of the processes in the above-mentioned embodiment methods can be completed by instructing the relevant hardware through a computer program, and the program can be stored in a non-volatile computer-readable storage medium. When the program is executed, it can include the processes of the embodiments of the above-mentioned methods. Among them, any reference to memory, storage, database or other media used in the embodiments provided in this application may include non-volatile and / or volatile memory. Non-volatile memory may include read-only memory (ROM), programmable ROM (PROM), electrically programmable ROM (EPROM), electrically erasable programmable ROM (EEPROM) or flash memory. Volatile memory may include random access memory (RAM) or external cache memory. As an illustration and not limitation, RAM is available in many forms, such as static RAM (SRAM), dynamic RAM (DRAM), synchronous DRAM (SDRAM), double data rate SDRAM (DDRSDRAM), enhanced SDRAM (ESDRAM), synchronous link (Synchlink) DRAM (SLDRAM), memory bus (Rambus) direct RAM (RDRAM), direct memory bus dynamic RAM (DRDRAM), and memory bus dynamic RAM (RDRAM).

[0079] Although the present invention is disclosed as above, the protection scope of the present invention is not limited thereto. Those skilled in the art may make various changes and modifications without departing from the spirit and scope of the present invention, and these changes and modifications will fall within the protection scope of the present invention.

Claims

1. A satellite on-orbit Earth ionosphere plasma environment simulation method, characterized in that: include: Obtaining the current state parameters of each satellite in the low-orbit constellation at the current simulation time, including: obtaining the orbital elements of each satellite at the simulation start time, starting from the simulation start time, calculating the current state parameters of each satellite at each simulation time according to the orbital elements of each satellite at the simulation start time until the simulation end time is reached, Acquire the communication link mission parameters of the satellites, wherein the communication link mission parameters are for two satellites that need to establish a communication link, According to the communication link mission parameters and the current state parameters, a plurality of communication satellite state parameters for establishing a space communication link are obtained, including: establishing a satellite topology structure according to the current state parameters of each of the satellites, traversing valid communication links in the satellite topology structure according to the communication link mission parameters, and obtaining a plurality of communication satellite state parameters for establishing a space communication link after screening the valid communication links. Establishing an ionospheric plasma environment model of the satellite according to the current simulation time and the current state parameters; According to the ionospheric plasma environment model and the communication satellite state parameters, the ionospheric plasma environment characterization data of each of the communication satellites is obtained.

2. The satellite on-orbit earth ionosphere plasma environment simulation method according to claim 1, characterized in that: Before obtaining the current state parameters of each satellite in the low-orbit constellation at the current simulation time, the method further includes: Get the simulation time range and simulation step size, The simulation time range is divided into a plurality of continuously distributed simulation moments according to the simulation step size.

3. The satellite on-orbit earth ionosphere plasma environment simulation method according to claim 2, characterized in that: The simulation time range is obtained by calculating the simulation start time and the simulation end time.

4. The satellite on-orbit earth ionosphere plasma environment simulation method according to claim 1, characterized in that: The effective communication link screening includes: screening all the effective communication links based on the principle of the shortest path.

5. The satellite on-orbit earth ionosphere plasma environment simulation method according to claim 1, characterized in that: The ionospheric plasma environment characterization data of the communication satellite includes electron density or electron temperature.

6. A satellite on-orbit earth ionosphere plasma environment simulation device, used to execute the satellite on-orbit earth ionosphere plasma environment simulation method according to any one of claims 1 to 5, characterized in that: include: an acquisition unit, the acquisition unit being used to acquire current state parameters of each satellite in the low-orbit constellation at a current simulation time, The acquisition unit is also used to acquire the communication link mission parameters of the satellite; A model building unit, the model building unit is used to build an ionospheric plasma environment model of the satellite according to the current simulation time and the current state parameters; a computing unit, the computing unit being used to obtain state parameters of a plurality of communication satellites for establishing a space communication link according to the communication link mission parameters and the current state parameters, The calculation unit is also used to obtain ionospheric plasma environment characterization data of each of the communication satellites based on the ionospheric plasma environment model and the communication satellite state parameters.

7. A computer device, characterized in that: It comprises a computer-readable storage medium storing a computer program and a processor. When the computer program is read and executed by the processor, the satellite in-orbit earth ionosphere plasma environment simulation method as described in any one of claims 1 to 5 is implemented.

8. 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 for simulating the plasma environment of the Earth ionosphere of a satellite in orbit as described in any one of claims 1 to 5 is implemented.

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