A method, device and system for real-time characterization of space plasma

Abstract

The present invention provides a method, device, and system for real-time characterization of space plasma, relating to the field of aerospace technology. The method for real-time characterization of space plasma described in the present invention includes: initializing parameters; determining real-time position data and real-time velocity data of a spacecraft based on orbital parameters, and determining real-time space attitude data of the spacecraft based on attitude parameters; determining temperature and density parameters of the plasma environment based on the real-time position data, determining the plasma energy spectrum through Maxwell plasma energy distribution, and determining real-time space plasma environment data based on the temperature parameters, density parameters, and plasma energy spectrum; and determining real-time characterization simulation data based on the real-time position data, real-time velocity data, real-time space attitude data, and real-time space plasma environment data. The technical solution described in the present invention accurately describes the effects of space plasma on spacecraft, thereby improving spacecraft flight safety.

Description

Technical Field

[0001] The present invention relates to the field of aerospace technology, and in particular to a method, device and system for real-time characterization of space plasma. Background Art

[0002] There are a large number of charged particles in the space near the earth. These charged particles form a large space plasma environment in the area near the earth. Plasmas of different properties are distributed in different regions of the geomagnetic layer according to different energies and densities, including: ionosphere, plasmasphere, plasma sheet, magnetospheric tail lobe and magnetospheric top boundary layer.

[0003] During space flight missions, spacecraft will inevitably pass through the space plasma environment. The charged particles in the space plasma environment will cause varying degrees of damage to the surface and interior of the spacecraft, affecting the safety of the spacecraft. Summary of the Invention

[0004] The problem solved by the present invention is how to improve the safety of spacecraft.

[0005] To solve the above problems, the present invention provides a real-time characterization method for space plasma, comprising: initializing parameters, wherein the parameters include orbital parameters and attitude parameters, the orbital parameters being used to describe the orbital motion state of a spacecraft, and the attitude parameters being used to describe the attitude motion state of the spacecraft; determining real-time position data and real-time velocity data of the spacecraft based on the orbital parameters, and determining real-time space attitude data of the spacecraft based on the attitude parameters; determining temperature parameters and density parameters of a plasma environment based on the real-time position data, determining a plasma energy spectrum through Maxwell plasma energy distribution, and determining real-time space plasma environment data based on the temperature parameters, the density parameters, and the plasma energy spectrum; and determining real-time characterization simulation data based on the real-time position data, the real-time velocity data, the real-time space attitude data, and the real-time space plasma environment data.

[0006] Optionally, the spatial plasma real-time characterization method further includes establishing a time system and a space coordinate system, wherein the time system is used to simulate the passage of time, and the space coordinate system is used to calculate the spatial motion state.

[0007] Optionally, determining the real-time position data and real-time velocity data of the spacecraft based on the orbital parameters includes: performing orbit calculations in the spatial coordinate system according to the passage of the simulation time to determine the real-time position data and the real-time velocity data.

[0008] Optionally, determining the real-time space attitude data of the spacecraft according to the attitude parameters includes: performing attitude calculation in the space coordinate system according to the passage of simulation time to determine the real-time space attitude data.

[0009] Optionally, determining the temperature parameter and the density parameter of the plasma environment according to the real-time position data includes: acquiring the temperature parameter and the density parameter corresponding to the real-time position data from historical detection data.

[0010] Optionally, determining the plasma energy spectrum by Maxwell plasma energy distribution includes: determining the corresponding single Maxwell plasma energy spectrum according to the Maxwell plasma energy distribution of the single Maxwell plasma; and determining the corresponding dual Maxwell plasma energy spectrum according to the Maxwell plasma energy distribution of the dual Maxwell plasma.

[0011] Optionally, the dual Maxwell plasma includes isotropic dual Maxwell plasma and anisotropic dual Maxwell plasma.

[0012] The space plasma real-time characterization method described in the present invention uses simulation technology to determine real-time characterization simulation data based on real-time position data, real-time velocity data, real-time space attitude data, and real-time space plasma environment data, thereby accurately describing the effects of space plasma on spacecraft, and further reducing the degree of damage caused to the surface and interior of the spacecraft by charged particles in the space plasma environment, thereby improving spacecraft flight safety.

[0013] The present invention also provides a space plasma real-time characterization device, comprising: an initialization module for initializing parameters, wherein the parameters include orbital parameters and attitude parameters, the orbital parameters are used to describe the orbital motion state of the spacecraft, and the attitude parameters are used to describe the attitude motion state of the spacecraft; an orbital attitude module for determining the real-time position data and real-time velocity data of the spacecraft based on the orbital parameters, and determining the real-time space attitude data of the spacecraft based on the attitude parameters; a plasma environment module for determining the temperature parameters and density parameters of the plasma environment based on the real-time position data, determining the plasma energy spectrum through Maxwell plasma energy distribution, and determining the real-time space plasma environment data based on the temperature parameters, the density parameters, and the plasma energy spectrum; and a characterization simulation module for determining real-time characterization simulation data based on the real-time position data, the real-time velocity data, the real-time space attitude data, and the real-time space plasma environment data. The space plasma real-time characterization device has the same advantages as the above-mentioned space plasma real-time characterization method over the prior art, and will not be repeated here.

[0014] The present invention also provides a system for real-time characterization of space plasma, comprising a computer-readable storage medium storing a computer program and a processor. When the computer program is read and executed by the processor, the system implements the above-described method for real-time characterization of space plasma. The system and the above-described method have the same advantages over the prior art and are not further elaborated here.

[0015] The present invention also provides a computer-readable storage medium storing a computer program. When read and executed by a processor, the computer program implements the above-described method for real-time characterization of space plasma. The advantages of the computer-readable storage medium and the above-described method for real-time characterization of space plasma over the prior art are the same and will not be further elaborated here. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 Schematic diagram of the process of a method for real-time characterization of space plasma according to an embodiment of the present invention;

[0017] Figure 2 A simulation calculation framework for a real-time characterization method of space plasma according to an embodiment of the present invention;

[0018] Figure 3 Schematic diagram of the WGS-84 coordinate system according to an embodiment of the present invention;

[0019] Figure 4 is a schematic diagram of an Earth-centered Earth-fixed coordinate system according to an embodiment of the present invention;

[0020] Figure 5 is a schematic diagram of an epoch geocentric inertial coordinate system according to an embodiment of the present invention;

[0021] Figure 6 Schematic diagram of the dual Maxwell plasma energy spectrum according to an embodiment of the present invention. DETAILED DESCRIPTION

[0022] A plasma environment pervasive in Earth's vicinity. Plasma of varying energy and density is distributed across different regions of the Earth's magnetosphere, encompassing various properties: the ionosphere, plasmasphere, plasma sheet, magnetospheric tail lobe, and magnetopause boundary layer. The ionosphere and plasmasphere, located in the atmosphere and inner magnetosphere, respectively, are closer to Earth and serve as the primary operating areas for artificial satellites. The latter three regions, comprising the outer magnetospheric plasma, are located further from Earth. However, as human exploration of space continues, deep space activities are bound to increase.

[0023] The plasma environment in space can have multiple effects on man-made spacecraft, directly or indirectly causing operational safety issues. The primary impact of the plasma environment on man-made spacecraft is the induction of currents onto exposed surfaces, leading to charge accumulation. The electric fields generated by high-voltage power systems exposed to the space environment significantly affect this current flow. The accumulated charge can generate potential differences between different electrically insulating surfaces on the spacecraft, leading to destructive arcing or the formation of micro-arcing that generates electromagnetic noise and ablation. This surface ablation, in turn, contributes to the formation of a gas and dust environment around the spacecraft. The plasma environment in low-Earth orbit can induce arcing in high-voltage solar arrays (greater than 100V). Even at lower voltages, solar array design must minimize micro-arcing and the resulting electromagnetic interference.

[0024] Typically, the operating voltage of a solar array should be below 200V (the empirical threshold for arcing voltage), which significantly increases the weight of the spacecraft's power distribution system. Under geosynchronous orbit conditions, the high energy of the plasma creates a charging environment far more severe than that of low-Earth orbit plasma. This can create potential differences of several thousand volts between the spacecraft structure and the space plasma, or between different surfaces. The resulting arc discharge can directly cause spacecraft failure. The accumulated charge on the spacecraft surface also tends to attract charged contaminant gas molecules to sensitive surfaces, causing changes in their properties. To study the effects of space plasma on spacecraft, computer simulation methods are necessary.

[0025] In order to make the above-mentioned objects, features and advantages of the present invention more obvious and easy to understand, specific embodiments of the present invention are described in detail below with reference to the accompanying drawings.

[0026] like Figure 1 As shown, an embodiment of the present invention provides a real-time characterization method for space plasma, comprising: initializing parameters, wherein the parameters include orbital parameters and attitude parameters, the orbital parameters are used to describe the orbital motion state of the spacecraft, and the attitude parameters are used to describe the attitude motion state of the spacecraft; determining real-time position data and real-time velocity data of the spacecraft according to the orbital parameters, and determining real-time space attitude data of the spacecraft according to the attitude parameters; determining temperature parameters and density parameters of the plasma environment according to the real-time position data, determining a plasma energy spectrum through Maxwell plasma energy distribution, and determining real-time space plasma environment data according to the temperature parameters, the density parameters, and the plasma energy spectrum; and determining real-time characterization simulation data according to the real-time position data, the real-time velocity data, the real-time space attitude data, and the real-time space plasma environment data.

[0027] Specifically, combined Figure 2 As shown, in order to obtain the spacecraft motion state data and plasma environment data during operation required for the calculation of spacecraft plasma effects, after starting the calculation, the parameters must be initialized first, such as the satellite's initial orbital parameters, which are used to define the satellite's motion state, so as to facilitate the subsequent calculation of the satellite's on-orbit motion state as the simulation time goes by, and the satellite's initial attitude parameters, which are used to define the satellite's attitude motion state, so as to facilitate the subsequent calculation of the satellite's on-orbit attitude motion state as the simulation time goes by.

[0028] After initializing the various parameters in the scene, calculations and representations are performed in the time system and the space coordinate system. Therefore, it is necessary to establish the time system and the space coordinate system in advance, use the time system to simulate the passage of time, and use the space coordinate system to calculate the spatial motion state (including spatial position, spatial motion speed, and attitude in space). For example, according to the passage of simulation time, satellite orbit calculations are performed to obtain the real-time position and speed of the orbit, that is, real-time position data and real-time speed data. At the same time, satellite attitude calculations are performed to obtain real-time change data of the satellite attitude quaternion, that is, real-time space attitude data. Among them, calculations involving time can be performed using the Julian day, and calculations involving spatial coordinate position and speed can be performed using the geocentric inertial coordinate system.

[0029] When studying the operating status of spacecraft flying near the earth, the definition method of the three-dimensional rectangular Cartesian coordinate system is usually used to analyze and describe the quantitative representation of the spacecraft's on-orbit position, speed, attitude and other states.

[0030] In order to transform the latitude and longitude of the pointing point to the epoch coordinate system of the satellite, the coordinates of the target point in the geocentric earth coordinate system must first be transformed to the geocentric earth-fixed coordinate system. Figure 3 As shown, WGS-84 is a barycentric coordinate system. The origin coincides with the center of mass of the earth. Its Z axis points to the agreed polar direction defined by the International Time Bureau in 1984.0. The X axis points to the intersection of the agreed meridian plane and the agreed magnitude with the equator. The Y axis, X axis and Z axis form a right-handed rectangular coordinate. The geodetic coordinates (lon, lat, alt) in the WGS-84 coordinate system are the longitude and latitude of the target in the WGS-84 coordinate system. The geodetic longitude lon is the angle between the geodetic meridian plane and the prime meridian plane of the target point, the geodetic latitude lat is the angle between the normal of the WGS-84 ellipsoid passing through the target point and the equatorial plane, and alt is the normal distance between the target point and the WGS-84 ellipsoid surface. The WGS-84 coordinate system corresponds to the WGS-84 ellipsoid. The parameters are shown in Table 1 below, where a represents the major radius, b represents the minor radius, c represents the polar radius, and the unit is m. f represents the flattening, and e represents the normal distance between the target point and the WGS-84 ellipsoid. 2 represents the first eccentricity squared, e ’2represents the square of the second eccentricity, and J2 represents the second-order spherical harmonic coefficient of the Earth's gravity field.

[0031] Table 1

[0032]

[0033] Combine Figure 4 As shown, the origin of the Earth-centered Earth-fixed coordinate system coincides with the Earth's center of mass, the Z axis points to the Earth's North Pole, the X axis points to the intersection of the equator and the Greenwich meridian plane, and the Y axis, X axis and Z axis form a right-handed rectangular coordinate system.

[0034] Combine Figure 5 As shown, the epoch inertial coordinate system uses the J2000 coordinate system. The celestial reference coordinate system is defined using the celestial equator and equinox at J2000 (12:00, January 1, 2000). The J2000 coordinate system's origin coincides with the Earth's center of mass, with the X-axis pointing to the mean equinox at J2000, the Z-axis pointing to the North Pole, and the Y-axis, X-axis, and Z-axis forming a right-handed rectangular coordinate system. This is an inertial coordinate system.

[0035] The origin of the satellite's coordinate system is located at the satellite's center of mass. The X, Y, and Z axes are the satellite's three principal axes of inertia. In the absence of attitude deviation, the three axes of the satellite's coordinate system coincide with the satellite's orbital coordinate system. At this point, the satellite's Z axis points toward the Earth's center, the X axis coincides with the satellite's motion direction, and the Y axis points toward the negative normal of the satellite's orbital plane, forming a right-handed rectangular coordinate system with the X and Z axes.

[0036] The time scale standard is introduced below.

[0037] (1) Sidereal time

[0038] Sidereal time is based on the Earth's true rotation. A sidereal day is the time it takes for the vernal equinox to pass through the local meridian (23 hours, 56 minutes, 4.09 seconds). Greenwich Mean Sidereal Time is the hour angle of the vernal equinox relative to the Greenwich meridian. When the vernal equinox passes through the Greenwich meridian, it is Greenwich Sidereal Time zero. Because the vernal equinox has a true equinox and a mean equinox, Greenwich Sidereal Time is divided into Greenwich True Sidereal Time (GAST) and Greenwich Mean Sidereal Time (GMST).

[0039] Conversion relationship between Greenwich Mean Sidereal Time and Greenwich Mean Sidereal Time:

[0040] GAST=GMST+ΔψCOSε;

[0041] Where: ΔψCOSε—right ascension nutation.

[0042] The expression for Greenwich mean sidereal time is as follows:

[0043] GMST=6h 41 m 50 s .54841+8640184 s .812866T

[0044] +0 s .093104T 2 -6 s .2×10 -6 T 3 ;

[0045] Where T is the Julian century starting from the epoch J2000.

[0046] T=(JD(t)-2451545.0) / 36525.0;

[0047] This embodiment uses GMST to calculate the Earth's rotation angle since the J2000 epoch.

[0048] (2) Universal Time

[0049] Universal Time is Greenwich Mean Solar Time. Starting from mean midnight on the prime meridian, the difference between local time and Universal Time in different regions is equal to the longitude of that location. One Universal Time consists of 86,400 mean solar seconds and 24 mean solar hours. Initially, the initial value of Universal Time, UT0, was obtained by observing stars at observatories. Subsequently, considering the uneven rotation of the Earth and the influence of polar motion, the polar motion correction Δλ and the rotation speed ΔTS were added to obtain UT1 and UT2. The relationship between the two is:

[0050] UT1=UT0+Δλ

[0051] UT2=UT1+ΔTS=UT0+Δλ+ΔTS;

[0052] (3) Coordinated Universal Time

[0053] Coordinated Universal Time (UTC), also known as the world's single time, is based on the length of the atomic second and is intended to be as close to UT1 as possible. To ensure that UTC does not deviate from UT1 by more than 0.9 seconds, the International Central Bureau for Earth Rotation and Expansion (ICER) in Paris decides when necessary to add leap seconds to UTC.

[0054] During the orbit calculation process of this embodiment, the launch time and current position of the satellite both use UTC time as input.

[0055] (4) Julian Day

[0056] The Julian day is the number of days starting at 12:00 a.m. on January 1, 4573 BC. Converting the Gregorian year, month, and day to Julian day allows for a unified description of the difference between two Gregorian calendar moments, facilitating the definition of simulation step sizes. Similarly, Julian day is also applicable to the calculation of the Earth's rotation angle.

[0057] Calculate Julian day from the Gregorian calendar:

[0058]

[0059] Where: INT()—round down.

[0060] In this embodiment, the calculation of the spacecraft's motion state is primarily used to describe the spacecraft's operating position and velocity during its in-orbit operation. The satellite orbit design utilizes the SGP4 and HPOP orbit calculation models, enabling high-precision orbit predictions for over 24 hours. A parallel computing framework is employed to achieve accurate and high-speed satellite orbit calculations, obtaining three-dimensional data on the satellite's position and velocity in the inertial frame based on kinematic and dynamic equations. The time processing component inputs internal clock update information into the Earth's rotation state model for calculation, deriving the time-varying Earth rotation position. This information, combined with the satellite's time-varying on-orbit position derived from the satellite orbit simulation module, is then input into the sub-satellite point calculation algorithm to determine the satellite's sub-satellite point variation.

[0061] The satellite rigid-body attitude dynamics model used in this embodiment is primarily used to describe the relative attitude of a satellite in space during on-orbit operation, using attitude quaternions. This embodiment allows for customizing the aircraft's attitude reference coordinate system and attitude description coordinate system; it can describe attitude using the commonly used four-element method, Euler angle method, and YPR description method; it can input the attitude of various aircraft in the form of files, and can perform attitude parameter conversion and prediction based on various rotation sequences and multiple attitude operating modes.

[0062] This embodiment uses an object-oriented programming framework to represent a space plasma model of spacecraft flight velocity and on-orbit attitude in a scenario-based manner. Using the scenario as the object, the spacecraft object is instantiated within the scenario, and satellite environmental parameters are set within the scenario. The scenario uses a time step as the unit, performing time extrapolation on a time-by-time basis, traversing each satellite object and sequentially extrapolating orbital position and velocity data, space attitude data, and space plasma environment data. As time progresses, real-time simulation data is generated that takes into account the spacecraft's flight velocity, on-orbit attitude, and on-orbit plasma environment.

[0063] In addition, the calculation method for the space Maxwell plasma environment in this embodiment is as follows:

[0064] The Maxwell-Boltzmann distribution can be the simplest description of space plasma. The Maxwell velocity distribution law is expressed by f(v):

[0065]

[0066] According to the orbital environment of different spacecraft, Maxwell plasma is divided into three cases:

[0067] 1. Single Maxwellian (single Maxwell plasma)

[0068] 2. Double Maxwellian (Double Maxwell Plasma - Isotropic)

[0069] 3. Bi-Maxwellian (Bi-Maxwell Plasma-Anisotropy)

[0070] The above three Maxwell plasma environment flux expressions are implemented separately with C++ to further analyze the influence of spacecraft speed and flight attitude on plasma flux.

[0071] (1)Single Maxwellian

[0072] According to the physical meaning and formula of particle number flux, the expression of particle number flux is:

[0073]

[0074]

[0075] Where f(v): Maxwell velocity distribution rate

[0076] n: particle number density (cm -3 ---Convert the unit to m -3 ×1e6)

[0077] m: particle mass (kg)

[0078] T: Temperature (eV)

[0079] q: particle charge (C)

[0080] E: particle energy (eV)

[0081] <nf>: Particle volume fraction flux (n / m 2 ·sec·Sr)

[0082] F: Particle differential flux (n / m 2 ·sec·Sr·eV).

[0083] The single Maxwell velocity distribution is suitable for calculating the flux of charged particles of different energies in a single Maxwell plasma. For example, in LEO orbits, the particles are mainly dense low-temperature plasma.

[0084] (2)Double Maxwellian

[0085] In fact, in some cases, space plasma is not a single Maxwell distribution, but a double Maxwell distribution. In particular, when new high-energy particles enter the low-temperature plasma region, the plasma velocity distribution shows a double Maxwell distribution. For isotropic plasma, when the temperature is different, the double Maxwell plasma is usually obtained by directly adding two single Maxwell velocity distributions. That is:

[0086] <nf>= <NF h >+ <NF c >

[0087] F=F h +F c ;

[0088] The subscripts represent: h (hot): hot plasma; v (cold): cold plasma.

[0089] The isotropic double Maxwell velocity distribution is suitable for GEO orbit, where the main charging and discharging environment is geomagnetic substorm plasma and high-energy electrons.

[0090] (3) Bi-Maxwellian

[0091] For anisotropic plasma, the Maxwell velocity distribution law is expressed as:

[0092]

[0093]

[0094] Where: v ⊥ (velocity perpendicular to the background magnetic field)

[0095] v || (velocity parallel to the background magnetic field)

[0096] θ ⊥ (Thermal velocity perpendicular to the background magnetic field):

[0097] θ || (Thermal velocity parallel to the background magnetic field):

[0098] E ⊥ (Energy perpendicular to the background magnetic field):

[0099] E || (Energy parallel to the background magnetic field):

[0100]

[0101] Anisotropic double Maxwell is applicable to PEO orbits and dust plasmas. The environment in which the charge and discharge effects of PEO orbits are caused is mainly auroral precipitation electrons.

[0102] In the constructed near-Earth space, according to the time-space system mentioned above, a geosynchronous orbit spacecraft is calculated, taking into account its flight speed and on-orbit attitude of space plasma real-time characterization technology. Initialize the spacecraft attitude and orbit parameters. The six initial orbit numbers of the spacecraft are: major axis 42166.3km, eccentricity 0 degrees, inclination 0 degrees, ascending node right ascension 0 degrees, perigee argument 0 degrees, and perigee angle 0 degrees. The mission started at 12:00:00 on January 1, 2017. The initial attitude orbit quaternion of the spacecraft is described as 1, 0, 0, 0. Through the GEO orbit plasma electron parameters density 7.8E-1 temperature 5.5E2, density 3.1E-1 temperature 8.68E3, we get the following Figure 6 The energy spectrum of the dual Maxwell plasma is shown.

[0103] In this embodiment, simulation technology is used to determine real-time characterization simulation data based on real-time position data, real-time velocity data, real-time space attitude data, and real-time space plasma environment data, thereby accurately describing the effects of space plasma on the spacecraft, and further reducing the degree of damage caused by charged particles in the space plasma environment to the surface and interior of the spacecraft, thereby improving the flight safety of the spacecraft.

[0104] Optionally, the spatial plasma real-time characterization method further includes establishing a time system and a space coordinate system, wherein the time system is used to simulate the passage of time, and the space coordinate system is used to calculate the spatial motion state.

[0105] Optionally, determining the real-time position data and real-time velocity data of the spacecraft based on the orbital parameters includes: performing orbit calculations in the spatial coordinate system according to the passage of the simulation time to determine the real-time position data and the real-time velocity data.

[0106] Optionally, determining the real-time space attitude data of the spacecraft according to the attitude parameters includes: performing attitude calculation in the space coordinate system according to the passage of simulation time to determine the real-time space attitude data.

[0107] Optionally, determining the temperature parameter and the density parameter of the plasma environment according to the real-time position data includes: acquiring the temperature parameter and the density parameter corresponding to the real-time position data from historical detection data.

[0108] Optionally, determining the plasma energy spectrum by Maxwell plasma energy distribution includes: determining the corresponding single Maxwell plasma energy spectrum according to the Maxwell plasma energy distribution of the single Maxwell plasma; and determining the corresponding dual Maxwell plasma energy spectrum according to the Maxwell plasma energy distribution of the dual Maxwell plasma.

[0109] Optionally, the dual Maxwell plasma includes isotropic dual Maxwell plasma and anisotropic dual Maxwell plasma.

[0110] Another embodiment of the present invention provides a real-time characterization device for space plasma, comprising: an initialization module for initializing parameters, wherein the parameters include orbital parameters and attitude parameters, the orbital parameters being used to describe the orbital motion state of a spacecraft, and the attitude parameters being used to describe the attitude motion state of the spacecraft; an orbital attitude module for determining real-time position data and real-time velocity data of the spacecraft based on the orbital parameters, and determining real-time space attitude data of the spacecraft based on the attitude parameters; a plasma environment module for determining temperature parameters and density parameters of the plasma environment based on the real-time position data, determining a plasma energy spectrum through Maxwell plasma energy distribution, and determining real-time space plasma environment data based on the temperature parameters, the density parameters, and the plasma energy spectrum; and a characterization simulation module for determining real-time characterization simulation data based on the real-time position data, the real-time velocity data, the real-time space attitude data, and the real-time space plasma environment data.

[0111] Another embodiment of the present invention provides a space plasma real-time characterization system, comprising a computer-readable storage medium storing a computer program and a processor. When the computer program is read and executed by the processor, the above space plasma real-time characterization method is implemented.

[0112] Another embodiment of the present invention provides a computer-readable storage medium, wherein the computer-readable storage medium stores a computer program. When the computer program is read and executed by a processor, the above-mentioned method for real-time characterization of spatial plasma is implemented.

[0113] Although the present invention is disclosed as above, the scope of protection disclosed by 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 scope of protection of the present invention.< / nf> < / nf>

Claims

1. A method for real-time characterization of space plasma, characterized in that: include: Initialization parameters, wherein the parameters include orbital parameters and attitude parameters, the orbital parameters are used to describe the orbital motion state of the spacecraft, and the attitude parameters are used to describe the attitude motion state of the spacecraft; Determine the real-time position data and real-time velocity data of the spacecraft according to the orbital parameters, and determine the real-time space attitude data of the spacecraft according to the attitude parameters; Determine temperature parameters and density parameters of the plasma environment according to the real-time position data, determine a plasma energy spectrum through Maxwell plasma energy distribution, and determine real-time spatial plasma environment data according to the temperature parameters, the density parameters, and the plasma energy spectrum; Real-time characterization simulation data is determined according to the real-time position data, the real-time velocity data, the real-time spatial attitude data, and the real-time spatial plasma environment data.

2. The method for real-time characterization of space plasma according to claim 1, characterized in that: It also includes establishing a time system and a space coordinate system. The time system is used to simulate the passage of time, and the space coordinate system is used to calculate the spatial motion state.

3. The method for real-time characterization of space plasma according to claim 2, characterized in that: Determining the real-time position data and real-time velocity data of the spacecraft according to the orbital parameters includes: According to the passage of the simulation time, orbit calculation is performed in the space coordinate system to determine the real-time position data and the real-time speed data.

4. The method for real-time characterization of space plasma according to claim 2, characterized in that: Determining the real-time space attitude data of the spacecraft according to the attitude parameters includes: According to the passage of the simulation time, posture calculation is performed in the spatial coordinate system to determine the real-time spatial posture data.

5. The method for real-time characterization of space plasma according to claim 1, characterized in that: Determining the temperature parameter and density parameter of the plasma environment according to the real-time position data includes: acquiring the temperature parameter and the density parameter corresponding to the real-time position data from historical detection data.

6. The method for real-time characterization of space plasma according to claim 1, characterized in that: Determining the plasma energy spectrum by using the Maxwell plasma energy distribution includes: determining a corresponding single Maxwell plasma energy spectrum according to the Maxwell plasma energy distribution of the single Maxwell plasma; The corresponding double Maxwell plasma energy spectrum is determined according to the Maxwell plasma energy distribution of the double Maxwell plasma.

7. The method for real-time characterization of space plasma according to claim 6, characterized in that: The dual Maxwell plasma includes isotropic dual Maxwell plasma and anisotropic dual Maxwell plasma.

8. A space plasma real-time characterization device, characterized in that: include: An initialization module, configured to initialize parameters, wherein the parameters include orbital parameters and attitude parameters, wherein the orbital parameters are used to describe the orbital motion state of the spacecraft, and the attitude parameters are used to describe the attitude motion state of the spacecraft; An orbit attitude module, configured to determine real-time position data and real-time velocity data of the spacecraft according to the orbit parameters, and to determine real-time space attitude data of the spacecraft according to the attitude parameters; a plasma environment module, configured to determine temperature parameters and density parameters of the plasma environment according to the real-time position data, determine a plasma energy spectrum through Maxwell plasma energy distribution, and determine real-time spatial plasma environment data according to the temperature parameters, the density parameters, and the plasma energy spectrum; The characterization simulation module is used to determine real-time characterization simulation data according to the real-time position data, the real-time velocity data, the real-time space posture data and the real-time space plasma environment data.

9. A space plasma real-time characterization system, characterized in that: The method comprises a computer-readable storage medium storing a computer program and a processor, wherein when the computer program is read and executed by the processor, the method for real-time characterization of space plasma according to any one of claims 1 to 7 is implemented.

10. 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 real-time characterization of spatial plasma according to any one of claims 1 to 7 is implemented.

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