Coordinated quantitative characterization simulation method and device for multi-orbit environment in the Earth's radiation belt

Abstract

The present invention provides a method and device for collaborative quantitative characterization and simulation of the multi-orbital environment of the Earth's radiation belt, which relates to the field of spacecraft simulation technology. The method for collaborative quantitative characterization and simulation of the multi-orbital environment of the Earth's radiation belt described in the present invention includes: initializing parameters, wherein the parameters include the mission start time, the mission end time, the simulation step length, the orbital parameters of the navigation satellite constellation, and the radiation belt model control parameters; from the mission start time to the mission end time, successively accumulating the simulation step lengths to obtain each simulation moment, traversing each navigation satellite in turn at each simulation moment, and updating the on-orbit motion state data of the navigation satellite; determining the corresponding radiation environment quantitative characterization data according to the spatial position data of the navigation satellite at each simulation moment and the radiation belt model control parameters. The present invention can quantitatively characterize the space radiation environment in which the navigation satellite is located.

Description

Technical Field

[0001] The present invention relates to the field of spacecraft simulation technology, and in particular to a method and device for collaborative quantitative characterization simulation of a multi-orbit environment in the Earth's radiation belt. Background Art

[0002] A space navigation satellite constellation, comprised of multiple artificial Earth satellites, provides navigation and positioning services to navigation receivers located on land, at sea, in the air, and in low-Earth orbit. Within a navigation satellite constellation, there are orbits of varying characteristics. Satellites in a constellation are located in low-Earth orbit, medium-high Earth orbit, and geosynchronous orbit. These satellites vary widely in distance from Earth, their orbital inclinations vary, and their ranges of operation vary significantly around the Earth.

[0003] Due to the Earth's magnetic field, a large number of relatively stable high-energy charged particles are formed around the Earth, known as the Earth's radiation belts. Navigation satellites carry a large number of electronic circuit systems to achieve navigation functions. These belts can affect or even damage the onboard electronic equipment of satellites orbiting the Earth. The damaging effects of space charged particle irradiation on spacecraft involve both radiation damage and deep dielectric charge and discharge. The latter occurs when high-energy electrons penetrate the interior of the spacecraft, depositing charge in electrical insulators and ultimately causing arc discharges. Radiation damage can be temporary or permanent. When the energy of charged particles is high enough, a single particle passing through can cause a change in the state of electronic devices, known as a single-event event. This can cause random memory cell flips, increase noise in CCD devices, and induce various erroneous signals. In severe cases, single-event events can cause integrator circuits to latch up or burn out, resulting in permanent damage.

[0004] Therefore, studying the space radiation environment of navigation satellite constellations is of great significance and value to the long-term stable operation of navigation satellites. Summary of the Invention

[0005] The problem solved by the present invention is how to quantitatively characterize the space radiation environment in which a navigation satellite is located.

[0006] To solve the above problems, the present invention provides a collaborative quantitative characterization simulation method for the multi-orbit environment of the Earth's radiation belt, including: initializing parameters, wherein the parameters include a mission start time, a mission end time, a simulation step, orbital parameters of the navigation satellite constellation, and radiation belt model control parameters; from the mission start time to the mission end time, accumulating the simulation step in sequence to obtain each simulation moment, traversing each navigation satellite in sequence at each simulation moment, and updating the on-orbit motion state data of the navigation satellite; determining the corresponding radiation environment quantitative characterization data according to the spatial position data of the navigation satellite at each simulation moment and the radiation belt model control parameters.

[0007] Optionally, the orbital parameters of the navigation satellite constellation include Kepler orbit parameters, and the Kepler orbit parameters include semi-major axis, eccentricity, inclination, right ascension of ascending node, argument of perigee and true anomaly.

[0008] Optionally, the method for collaborative quantitative characterization simulation of the Earth's radiation belt multi-orbit environment further includes: determining spatial position data at a next simulation moment based on a satellite orbit extrapolation model and spatial position data at a previous simulation moment.

[0009] Optionally, the satellite orbit extrapolation model includes a HPOP orbit calculation model, which embeds an earth gravity model, a solid tide and ocean tide model, an atmospheric resistance model, a solar radiation pressure model, and a sun and moon gravitational field model.

[0010] Optionally, the radiation belt models corresponding to the radiation belt model control parameters include AE-8 and AP-8 models.

[0011] Optionally, the radiation belt model control parameters include solar maximum and solar minimum year options, the number of particle energy levels calculated by the model and the corresponding particle energy levels, and the radiation integral flux or differential flux options of the model calculation results.

[0012] Optionally, the simulation time is expressed using Julian day.

[0013] The collaborative quantitative characterization simulation method for the multi-orbit environment of the Earth's radiation belt described in the present invention quantitatively characterizes the space radiation environment in which the navigation satellite is located based on time, which is beneficial to the long-term stable operation of the navigation satellite.

[0014] The present invention also provides a device for collaborative quantitative characterization and simulation of the multi-orbit environment of the Earth's radiation belt, comprising:

[0015] An initialization module, configured to initialize parameters, wherein the parameters include a mission start time, a mission end time, a simulation step size, orbital parameters of a navigation satellite constellation, and control parameters of a radiation belt model;

[0016] a traversal module, configured to accumulate the simulation step lengths in sequence from the task start time to the task end time to obtain each simulation moment, traverse each navigation satellite in sequence at each simulation moment, and update the on-orbit motion state data of the navigation satellite;

[0017] The characterization module is used to determine corresponding quantitative characterization data of the radiation environment according to the spatial position data of the navigation satellite and the control parameters of the radiation belt model at each simulation moment.

[0018] The advantages of the Earth radiation belt multi-orbit environment collaborative quantitative characterization simulation device and the above-mentioned Earth radiation belt multi-orbit environment collaborative quantitative characterization simulation method over the existing technology are the same, and will not be repeated here.

[0019] The present invention also provides a system for collaborative quantitative characterization and simulation of the Earth's radiation belt multi-orbit environment, 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 method for collaborative quantitative characterization and simulation of the Earth's radiation belt multi-orbit environment. The system and method offer the same advantages over the prior art, and are not further elaborated here.

[0020] 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 collaborative quantitative characterization and simulation of the Earth's radiation belt multi-orbit environment. The advantages of the computer-readable storage medium and the above-described method for collaborative quantitative characterization and simulation of the Earth's radiation belt multi-orbit environment over the prior art are the same and will not be further elaborated here. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 A schematic diagram of a collaborative quantitative characterization simulation method for the Earth's radiation belt multi-orbit environment according to an embodiment of the present invention;

[0022] Figure 2 A schematic diagram of the Earth's radiation belts according to an embodiment of the present invention;

[0023] Figure 3 A schematic diagram of a GPS constellation navigation system showing a three-dimensional view according to an embodiment of the present invention;

[0024] Figure 4 A schematic diagram of a GPS constellation navigation system with a two-dimensional map according to an embodiment of the present invention;

[0025] Figure 5 Schematic diagram of the instantaneous change curve of the integrated flux according to an embodiment of the present invention. DETAILED DESCRIPTION

[0026] 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.

[0027] like Figure 1 As shown, an embodiment of the present invention provides a method for collaborative quantitative characterization simulation of the multi-orbit environment of the Earth's radiation belt, including: initializing parameters, wherein the parameters include a mission start time, a mission end time, a simulation step, orbital parameters of the navigation satellite constellation, and radiation belt model control parameters; from the mission start time to the mission end time, accumulating the simulation step in sequence to obtain each simulation moment, traversing each navigation satellite in sequence at each simulation moment, and updating the on-orbit motion state data of the navigation satellite; determining the corresponding radiation environment quantitative characterization data according to the spatial position data of the navigation satellite at each simulation moment and the radiation belt model control parameters.

[0028] Specifically, combined Figure 2 As shown, radiation belt particles surround the Earth in an annular belt at mid- and low-latitudes. These particles are primarily composed of protons and electrons, with a small amount of heavy ions (such as O+). Earth's radiation belts are generally divided into two annular regions at different altitudes, known as the inner and outer belts. The inner belt extends from a few hundred kilometers to approximately 6,000 kilometers above the equator and is primarily composed of high-energy protons (up to tens of MeV) and high-energy electrons (1-10 MeV). The outer belt, reaching altitudes of up to 60,000 km, is primarily composed of high-energy electrons. Of particular concern for low-Earth orbit (LEO) is that the inner radiation belt extends to lower altitudes over the South Atlantic Ocean. The geomagnetic field strength in this region is relatively low, forming the South Atlantic Anomaly. Although geosynchronous orbit is located outside the center of the outer radiation belt, it still encounters a strong flux of high-energy electrons. The radiation belts surrounding Earth create a high-energy particle radiation environment for both humans and Earth satellites.

[0029] This embodiment aims to solve the space radiation environment in which each satellite in the navigation satellite constellation is located, and can quantitatively characterize the space radiation environment in which the navigation satellite is located to obtain first-hand data.

[0030] Considering that the position of a satellite in a navigation satellite constellation changes in real time with the passage of time during its space operation, and the radiation belt environment in which it is located also changes in real time, this embodiment designs a time-based real-time quantitative characterization method for the space radiation belt of a navigation satellite constellation (orbital altitude of 300 to 40,000 km) in order to be able to characterize the quantitative characterization data of the radiation belt environment of each satellite in the navigation satellite constellation.

[0031] Based on time, the user sets the task start and end times. Coordinated Universal Time (UTC) defines the user-set task time. The user can specify the simulation time range using the Gregorian calendar year, month, day, hour, minute, and second. Furthermore, the user must set the simulation time granularity, or simulation step size, in seconds. This method obtains each simulation moment according to the user-defined simulation step size and step time. Given that the simulation calculations in this method require a continuous time representation, the Julian day representation is introduced to convert the Gregorian calendar year, month, day, hour, minute, and second into integers for calculation. The conversion method is as follows.

[0032] Convert the Gregorian calendar year, month, day, hour, minute, and second to Julian day: Calculate the Julian day from the Gregorian calendar:

[0033]

[0034] Where: INT()—round down.

[0035] In order to solve the time-varying motion state of each satellite in the navigation constellation, it is first necessary to initialize the data of the initial orbital characteristics and positions of each satellite, using the six Kepler orbit elements: 1) semi-major axis, a, describes the orbit size. 2) eccentricity, e, describes the orbit shape. 3) inclination, i, describes the inclination angle of the orbital plane relative to the equatorial plane. 4) ascending node right ascension, Ω, describes the position of the ascending node relative to the vernal equinox. 5) argument of perigee, ω, describes the position of perigee relative to the ascending node. 6) true anomaly, f, describes the position of the satellite relative to perigee. In this embodiment, the extrapolation calculation of the satellite's spatial position starts from the satellite orbit elements at the start time of the initial simulation task to obtain the satellite's spatial position at the next simulation moment. Similarly, the spatial position at the next simulation moment is obtained by calculating the satellite's on-orbit spatial position at the previous simulation moment through the satellite orbit extrapolation model.

[0036] The satellite's orbital extrapolation model uses the HPOP (High-precision orbit propagator) orbit calculation model. This high-precision orbit prediction model, based on a two-body orbit calculation model, considers various orbital perturbations, such as Earth's gravitational pull, atmospheric perturbations, and solar radiation pressure. It can handle circular, elliptical, parabolic, and hyperbolic orbits ranging from the Earth's surface to the Moon's surface and beyond. The model incorporates the JGM-3 (70x70) Earth gravity model, solid and ocean tide models, atmospheric drag models, solar radiation pressure models, and solar and lunar gravitational field models, enabling accurate simulation of the satellite's orbital state.

[0037] After obtaining the spatial position data of the satellite corresponding to the simulation moment, the time data corresponding to the simulation moment, the spatial position data of the aircraft at that moment, and the model control parameter data set by the user are input into the model through the internal interface of the program for calculation, and finally the quantitative characterization data of the space radiation environment in which the current aircraft is located is obtained. In this embodiment, the radiation belt model uses the AE-8 / AP-8 model. The AE-8 / AP-8 model is a de facto standard model used internationally. When applied in engineering, the AE-8 / AP-8MIN or AE-8 / AP-8MAX model should be selected depending on the level of solar activity during the satellite's in-orbit service. If it is difficult to determine the ratio of solar low years to solar high years during the satellite's in-orbit mission period, the AE-8MAX / AP-8MIN model can be used to give a more conservative energy spectrum calculation result. The radiation belt model control parameters that need to be set in this embodiment are: the solar maximum year (MAX) and solar minimum year (MIN) options, the number of particle energy levels calculated by the model and the corresponding particle energy levels, in MeV, and the radiation integral flux or differential flux option of the model calculation results. The radiation belt model calculates the quantitative characterization data of the radiation environment, which is the flux value of particles at each energy level set by the user.

[0038] The complete navigation satellite constellation space radiation environment quantitative characterization process of this embodiment is as follows.

[0039] Initialize the mission start time, mission end time, simulation step size, and orbital parameters corresponding to the simulation start time of the navigation satellite constellation, as well as the control parameters of the radiation belt model AE-8 / AP-8 model. This embodiment starts the calculation, starting from the mission start time, and according to the simulation step size, steps the time to obtain the next simulation moment, and traverses each satellite in turn at this simulation moment. Update the on-orbit motion state data of each navigation satellite, and use the space radiation environment model to calculate the quantitative characterization data of the satellite's current radiation environment based on the current simulation moment and the latest spatial position data of the satellite and the control parameters of the radiation belt model. After traversing and calculating all satellites in the navigation constellation, obtain the next simulation moment according to the simulation step size, and complete the above work again until the simulation moment reaches or exceeds the mission end time, and stop the calculation.

[0040] Combine Figure 3 and Figure 4 The flight trajectory shown in the figure takes the GPS constellation navigation system as an example to characterize the real-time quantitative space radiation environment data of each position of each satellite in the navigation satellite constellation during its on-orbit operation mission. Figure 5 As shown in Figure 1, the space radiation environment in the constellation varies depending on the location of the satellite. Figure 5 The figure in the figure shows the instantaneous change curve of the integrated flux of 3MeV energy level of solar high annual radiation belt electrons received by satellites in different orbits and positions in the navigation satellite constellation.

[0041] In this embodiment, the space radiation environment in which the navigation satellite is located is quantitatively characterized based on time, which is beneficial to the long-term stable operation of the navigation satellite.

[0042] Optionally, the orbital parameters of the navigation satellite constellation include Kepler orbit parameters, and the Kepler orbit parameters include semi-major axis, eccentricity, inclination, right ascension of ascending node, argument of perigee and true anomaly.

[0043] Optionally, the method for collaborative quantitative characterization simulation of the Earth's radiation belt multi-orbit environment further includes: determining spatial position data at a next simulation moment based on a satellite orbit extrapolation model and spatial position data at a previous simulation moment.

[0044] Optionally, the satellite orbit extrapolation model includes a HPOP orbit calculation model, which embeds an earth gravity model, a solid tide and ocean tide model, an atmospheric resistance model, a solar radiation pressure model, and a sun and moon gravitational field model.

[0045] Optionally, the radiation belt models corresponding to the radiation belt model control parameters include AE-8 and AP-8 models.

[0046] Optionally, the radiation belt model control parameters include solar maximum and solar minimum year options, the number of particle energy levels calculated by the model and the corresponding particle energy levels, and the radiation integral flux or differential flux options of the model calculation results.

[0047] Optionally, the simulation time is expressed using Julian day.

[0048] Another embodiment of the present invention provides a device for collaborative quantitative characterization and simulation of the multi-orbit environment of the Earth's radiation belt, comprising:

[0049] An initialization module, configured to initialize parameters, wherein the parameters include a mission start time, a mission end time, a simulation step size, orbital parameters of a navigation satellite constellation, and control parameters of a radiation belt model;

[0050] a traversal module, configured to accumulate the simulation step lengths in sequence from the task start time to the task end time to obtain each simulation moment, traverse each navigation satellite in sequence at each simulation moment, and update the on-orbit motion state data of the navigation satellite;

[0051] The characterization module is used to determine corresponding quantitative characterization data of the radiation environment according to the spatial position data of the navigation satellite and the control parameters of the radiation belt model at each simulation moment.

[0052] Another embodiment of the present invention provides a collaborative quantitative characterization simulation system for the multi-orbit environment of the Earth's radiation belt, 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 collaborative quantitative characterization simulation method for the multi-orbit environment of the Earth's radiation belt is implemented as described above.

[0053] Another embodiment of the present invention provides a computer-readable storage medium storing a computer program. When the computer program is read and executed by a processor, the computer program implements the above-mentioned method for collaborative quantitative characterization and simulation of the multi-orbit environment of the Earth's radiation belt.

[0054] 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.

Claims

1. A collaborative quantitative characterization simulation method for the multi-orbit environment of the Earth's radiation belt, characterized by: include: Initialization parameters, including mission start time, mission end time, simulation step size, orbital parameters of the navigation satellite constellation, and radiation belt model control parameters. The radiation belt models corresponding to the radiation belt model control parameters include AE-8 and AP-8 models. The radiation belt model control parameters include solar maximum and solar minimum year options, the number of particle energy levels calculated by the model and the corresponding particle energy levels, and the radiation integral flux or differential flux options of the model calculation results; From the mission start time to the mission end time, successively accumulating the simulation step lengths to obtain respective simulation moments, traversing each navigation satellite in turn at each simulation moment, and updating the on-orbit motion state data of the navigation satellite; The corresponding quantitative characterization data of the radiation environment are determined based on the spatial position data of the navigation satellite at each simulation moment and the control parameters of the radiation belt model, wherein the method further includes: determining the spatial position data at the next simulation moment based on the satellite orbit extrapolation model and the spatial position data at the previous simulation moment; the satellite orbit extrapolation model includes a HPOP orbit calculation model, and the HPOP orbit calculation model has an embedded earth gravity model, a solid tide and an ocean tide model, an atmospheric resistance model, a solar light pressure model, and a solar and lunar gravitational field model.

2. The collaborative quantitative characterization simulation method for the multi-orbit environment of the Earth's radiation belt according to claim 1 is characterized in that: The orbital parameters of the navigation satellite constellation include Kepler orbit parameters, and the Kepler orbit parameters include semi-major axis, eccentricity, inclination, right ascension of ascending node, argument of perigee and true anomaly.

3. The collaborative quantitative characterization simulation method for the Earth radiation belt multi-orbit environment according to any one of claims 1 to 2, characterized in that: The simulation time is expressed in Julian day.

4. A collaborative quantitative characterization simulation device for the multi-orbit environment of the Earth's radiation belt, characterized by: include: an initialization module for initializing parameters, wherein the parameters include mission start time, mission end time, simulation step size, orbital parameters of the navigation satellite constellation, and radiation belt model control parameters, wherein the radiation belt models corresponding to the radiation belt model control parameters include AE-8 and AP-8 models, and the radiation belt model control parameters include solar maximum year, solar minimum year options, the number of particle energy levels calculated by the model and the corresponding particle energy levels, and the radiation integral flux or differential flux options of the model calculation results; a traversal module, configured to accumulate the simulation step lengths in sequence from the task start time to the task end time to obtain each simulation moment, traverse each navigation satellite in sequence at each simulation moment, and update the on-orbit motion state data of the navigation satellite; A characterization module is used to determine the corresponding quantitative characterization data of the radiation environment based on the spatial position data of the navigation satellite at each simulation moment and the control parameters of the radiation belt model, and to determine the spatial position data at the next simulation moment based on the satellite orbit extrapolation model and the spatial position data at the previous simulation moment; the satellite orbit extrapolation model includes a HPOP orbit calculation model, and the HPOP orbit calculation model has an embedded earth gravity model, solid tide and ocean tide models, atmospheric resistance model, solar radiation pressure model, and solar and lunar gravitational field models.

5. A collaborative quantitative characterization simulation system for the multi-orbit environment of the Earth's radiation belt, characterized by: 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 realizes the collaborative quantitative characterization simulation method of the multi-orbit environment of the Earth radiation belt according to any one of claims 1 to 3.

6. 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 collaborative quantitative characterization and simulation of the multi-orbit environment of the Earth's radiation belt according to any one of claims 1 to 3 is implemented.

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