A method, device and system for real-time quantitative characterization of spatial comprehensive environment

Abstract

The present invention provides a method, device and system for real-time quantitative characterization of a space comprehensive environment, and relates to the field of aerospace technology. The method for real-time quantitative characterization of a space comprehensive environment described in the present invention includes: setting simulation parameters, wherein the simulation parameters include a simulation start time, a simulation end time and a simulation step time; from the simulation start time to the simulation end time, accumulating the simulation step time in sequence according to the simulation step time, and determining the space comprehensive environment of the aircraft at each simulation time one by one; selecting a corresponding quantitative characterization model according to the space comprehensive environment, so as to determine the real-time quantitative characterization data of the space comprehensive environment corresponding to different simulation times. The technical solution described in the present invention can solve the problem of real-time quantitative characterization of the space comprehensive environment and ensure 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 quantitative characterization of a space comprehensive environment. Background Art

[0002] The space above the earth's surface is usually the main space for human activities. In the process of extending outward, the space above the earth's surface passes through the earth's atmosphere, the earth's radiation belt, solar cosmic rays and galactic cosmic rays in sequence. Different environments are cross-coupled with each other in space. The complex and harsh environment of space can easily cause on-orbit failures of spacecraft. Therefore, establishing a technology that can comprehensively simulate the complex environment of space plays a vital role in the high-reliability operation of spacecraft on orbit and ensuring the successful completion of the spacecraft mission. Summary of the invention

[0003] The problem solved by the present invention is how to achieve real-time quantitative representation of the space comprehensive environment to ensure flight safety.

[0004] To solve the above problems, the present invention provides a method for real-time quantitative characterization of a space comprehensive environment, comprising: setting simulation parameters, wherein the simulation parameters include a simulation start time, a simulation end time and a simulation step time; from the simulation start time to the simulation end time, accumulating the simulation step time in sequence according to the simulation step time, and determining the space comprehensive environment of the aircraft at each simulation time one by one; selecting a corresponding quantitative characterization model according to the space comprehensive environment, so as to determine the real-time quantitative characterization data of the space comprehensive environment corresponding to different simulation times.

[0005] Optionally, the comprehensive space environment includes an upper atmosphere environment, a geomagnetic field environment, an ionospheric plasma environment and a charged particle radiation environment.

[0006] Optionally, the quantitative characterization model corresponding to the high-altitude atmospheric environment includes the NRLMSISE-00 model, and the environmental output types of the NRLMSISE-00 model include the number density of helium atoms, the number density of oxygen atoms, the number density of nitrogen molecules, the number density of oxygen molecules, the number density of argon atoms, the total mass density, the number density of hydrogen atoms, the number density of nitrogen atoms, the abnormal number density of oxygen, the temperature of the outer atmosphere and the temperature at the target altitude.

[0007] Optionally, the quantitative characterization model corresponding to the geomagnetic field environment includes the International Reference Geomagnetic Field Model IGRF, and the environmental output types of the International Reference Geomagnetic Field Model IGRF include magnetic declination, magnetic inclination, horizontal intensity, north intensity, east intensity, vertical intensity and total intensity.

[0008] Optionally, the quantitative characterization model corresponding to the ionospheric plasma environment includes an international reference ionosphere model, and the environmental output types of the international reference ionosphere model include electron density, electron temperature, ion density, ion temperature and ion ratio of ionospheric plasma.

[0009] Optionally, the charged particle radiation environment includes an earth radiation belt electron radiation environment and an earth radiation belt proton radiation environment.

[0010] Optionally, the quantitative characterization model corresponding to the electron radiation environment of the Earth radiation belt includes the AE-8 electron model, and the environmental output types of the AE-8 electron model include the Earth radiation belt electron integral flux and the Earth radiation belt electron differential flux; the quantitative characterization model corresponding to the Earth radiation belt proton radiation environment includes the AP-8 proton model, and the environmental output types of the AP-8 proton model include the Earth radiation belt proton integral flux and the Earth radiation belt proton differential flux.

[0011] The method for real-time quantitative characterization of the spatial comprehensive environment described in the present invention determines the spatial comprehensive environment of the aircraft at each simulation moment, and then selects a corresponding quantitative characterization model based on the spatial comprehensive environment to determine the real-time quantitative characterization data of the spatial comprehensive environment corresponding to different simulation moments. This can solve the problem of real-time quantitative characterization of the spatial comprehensive environment and ensure flight safety.

[0012] The present invention also provides a space comprehensive environment real-time quantitative characterization device, including: a parameter module, used to set simulation parameters, wherein the simulation parameters include simulation start time, simulation end time and simulation step time; an environment module, used to determine the space comprehensive environment of the aircraft at each simulation time one by one by accumulating the simulation step length in sequence according to the simulation step time from the simulation start time to the simulation end time; a quantitative characterization module, used to select a corresponding quantitative characterization model according to the space comprehensive environment, so as to determine the space comprehensive environment real-time quantitative characterization data corresponding to different simulation times. The space comprehensive environment real-time quantitative characterization device described in the present invention has the same advantages as the above-mentioned space comprehensive environment real-time quantitative characterization method over the prior art, which will not be repeated here.

[0013] The present invention also provides a spatial comprehensive environment real-time quantitative characterization system, comprising a computer-readable storage medium storing a computer program and a processor, wherein the computer program is read and executed by the processor to implement the above spatial comprehensive environment real-time quantitative characterization method. The spatial comprehensive environment real-time quantitative characterization system has the same advantages as the above spatial comprehensive environment real-time quantitative characterization method over the prior art, which will not be described in detail here.

[0014] The present invention also provides a computer-readable storage medium, wherein the computer-readable storage medium stores a computer program, and when the computer program is read and executed by a processor, the above-mentioned spatial comprehensive environment real-time quantitative characterization method is implemented. The advantages of the computer-readable storage medium and the above-mentioned spatial comprehensive environment real-time quantitative characterization method over the prior art are the same, and will not be repeated here. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 A schematic diagram of a method for real-time quantitative characterization of a spatial comprehensive environment according to an embodiment of the present invention;

[0016] Figure 2 A schematic diagram of a J2000 inertial coordinate system according to an embodiment of the present invention;

[0017] Figure 3 is a schematic diagram of an Earth-centered Earth-fixed coordinate system according to an embodiment of the present invention;

[0018] Figure 4 is a schematic diagram of the WGS-84 coordinate system of an embodiment of the present invention;

[0019] Figure 5 is a schematic diagram of a coordinate transformation matrix according to an embodiment of the present invention;

[0020] Figure 6 It is a schematic diagram of an aircraft in three-dimensional space according to an embodiment of the present invention. DETAILED DESCRIPTION

[0021] The impact of the space environment on spacecraft is the basic focus of the study of space environment effects. The main scientific issues involved are the basic laws of the interaction between the space environment and spacecraft and their engineering applications. The space environment effect is the macroscopic and microscopic manifestation of the interaction between the space environment and spacecraft, involving various physical, chemical and mechanical processes. The space environment effect has obvious dynamic change characteristics in time and space scales, and is directly restricted by the changes in the space environment and the characteristics of the spacecraft itself. In-depth research on the impact of the space environment on spacecraft is of great significance to improving the service life and reliability of spacecraft in orbit.

[0022] (1) Influence of the neutral atmospheric environment in space

[0023] The neutral atmosphere can have a variety of negative effects on low-Earth orbit spacecraft. In low-Earth orbits below about 800km, the residual atmosphere of the Earth constitutes a neutral atmosphere, which can produce aerodynamic drag on spacecraft. For large asymmetric spacecraft, the unevenness of the drag effect can generate torque, affecting the attitude of the spacecraft, which needs to be adjusted by the attitude control system. Aerodynamic drag can also cause the spacecraft orbit to drop, which needs to be regularly raised by the orbit control engine. Under low-Earth orbit conditions, atomic oxygen is a neutral atmospheric component that must be considered. Its average kinetic energy when it hits the front surface of the spacecraft can reach about 5eV, which can cause surface erosion of many polymer materials (such as Kapton, C / C composites) and Ag. There is an intrinsic gas environment around the spacecraft formed by the gas released by itself. Due to the effects of high vacuum and space radiation, it can cause outgassing of the surface materials of the spacecraft, becoming a source of contamination for optically sensitive surfaces. Neutral gas molecules generated by the plume of the orbit control / attitude control engine in the backflow area are also a common source of contamination. In low-Earth orbit conditions, the neutral gas environment is often the initiator of the ultraviolet-visible-infrared diffuse luminescence phenomenon on the surface of spacecraft. This complex luminescence phenomenon is the recovery effect of the catalytic and excitation process on the material surface, and is related to many factors such as orbital altitude, attitude, material properties, surface temperature, time on orbit, lighting conditions and spacecraft size. In recent years, the harmfulness of the atmosphere outside the spacecraft has become increasingly important. First, it may become a source of gas molecule contamination, and second, it is easy to trigger electrostatic discharge or form glow.

[0024] (2) Impact of space plasma environment

[0025] The main effect of the plasma environment on spacecraft is that it causes current to flow into the exposed surfaces of the spacecraft, resulting in a charge accumulation effect. The electric field generated by the high-voltage power system exposed to the space environment will have a significant effect on the flow of this current. The accumulated charge can generate a potential difference between different electrically insulating surfaces of the spacecraft, and even cause destructive arc discharges; or generate electromagnetic noise and ablate the surface by forming micro-arcs. This surface ablation effect will promote the formation of a gas and dust environment around the spacecraft. The low-Earth orbit plasma environment can cause arc discharges in high-voltage solar arrays (greater than 100V). Even at lower voltages, it is necessary to avoid micro-arc discharges in solar arrays and the electromagnetic interference caused by them as much as possible from the design. Generally, the operating voltage of the solar array should be lower than 200V (the empirical threshold of the arc starting voltage). This will significantly increase the weight of the spacecraft power distribution system. Under geosynchronous orbit conditions, the energy of the plasma is high, which will form a charging environment that is much more serious than that of the low-Earth orbit plasma, and can form a potential difference of several thousand volts between the spacecraft structure and the space plasma or between different surfaces. It has been found that the arc discharges generated can directly cause spacecraft failure. The charges accumulated on the spacecraft surface can also easily attract charged pollutant gas molecules to the sensitive surface, causing changes in the properties of the sensitive surface. For example, the surface conductivity can be reduced or its charging characteristics can be changed. This shows that under geosynchronous orbit conditions, environmental plasma and ionized gas molecules may produce a synergistic effect. On the surface of the solar array, the possibility of arc discharge may also increase through the ionization of the arriving neutral gas to provide electrons, that is, the secondary electron multiplication effect. Therefore, geosynchronous orbit spacecraft must take necessary measures in their design to prevent the charge and discharge effects caused by the plasma environment.

[0026] (3) Impact of space radiation environment

[0027] The damage effects of space charged particle irradiation on spacecraft involve radiation damage and deep dielectric charging and discharging. The latter is that high-energy electrons penetrate into the interior of the spacecraft, deposit charges in the electrical insulator and eventually lead to arc discharge. Radiation damage effects can be temporary or permanent. When the energy of the charged particles is high enough, a single particle passing through may cause the state of the electronic device to change, which is called a single particle event. The resulting impact is to flip the random storage unit, increase the noise of the CCD device, and induce various error signals. In severe cases, single particle events can cause the integration circuit to lock or burn out, becoming permanent damage. Common space charged particle radiation damage effects are caused by the accumulation of ionizing absorbed doses, which is called the total ionizing dose effect (TID). This is a gradual accumulation of damage, which is mainly manifested in the degradation of the performance of key materials and devices such as thermal control coatings, electronic devices and optical devices. For a long time, the research on space charged particle radiation damage effects and protection has been a topic of great concern in spacecraft design, and is also an important part of the study of the interaction between the space environment and spacecraft. Electromagnetic radiation in various bands of the sun can also have an adverse effect on spacecraft. Low-frequency radio frequency interference can affect electronic systems. Infrared radiation from the sun, the earth and other celestial bodies can affect the thermal balance of spacecraft in orbit. Weak signals or images may be generated when visible light is reflected from certain surfaces or dust particles near the sensor. Solar ultraviolet radiation can directly cause degradation of the performance of spacecraft surface materials and can affect the charging and discharging process of the spacecraft surface by inducing photoelectrons. Solar ultraviolet radiation may also promote the formation of contamination films on sensitive surfaces through photochemical bonding. X-rays and gamma rays (mainly from artificial pollution sources) can pass through the surface and produce charged particles in the spacecraft's protective layer, thereby affecting sensitive systems. Generally, the intensity of X-rays and gamma rays from solar electromagnetic radiation is weak and the impact is small. During solar flares, X-ray radiation may increase by orders of magnitude.

[0028] 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.

[0029] like Figure 1 As shown, an embodiment of the present invention provides a method for real-time quantitative characterization of a space comprehensive environment, comprising: setting simulation parameters, wherein the simulation parameters include a simulation start time, a simulation end time, and a simulation step time; from the simulation start time to the simulation end time, accumulating the simulation step time in sequence according to the simulation step time, and determining the space comprehensive environment of the aircraft at each simulation time one by one; selecting a corresponding quantitative characterization model according to the space comprehensive environment, so as to determine the real-time quantitative characterization data of the space comprehensive environment corresponding to different simulation times.

[0030] Specifically, the real-time quantitative characterization method of the space comprehensive environment is as follows: first, the simulation start time and the simulation end time are set to determine the calculation time range of the simulation. Then the simulation step time is determined, and the simulation step length is accumulated from the simulation start time according to the simulation step time, and the space comprehensive environment of the aircraft at each simulation time is calculated one by one to obtain real-time quantitative characterization data. Finally, for each moment, the orbital position of the next moment is calculated according to the initialized aircraft orbital parameters, and the IGRF13 earth magnetic field model is calculated in turn according to the simulation time corresponding to the orbital position and the position, and the NRLMSISE-00 earth atmosphere model is calculated in combination with environmental control parameters such as F107, F107A, and AP values, and the charged particle radiation model AE-8 electron model and AP-8 proton model are calculated in combination with model control parameters and energy level settings. Finally, the real-time quantitative characterization data of the space comprehensive environment that changes in real time during the on-orbit operation of the aircraft that changes in sequence according to the simulation time is obtained.

[0031] First, it is necessary to analyze the types of comprehensive space environments involved during the on-orbit operation of spacecraft, analyze the internal scientific principles of different types of environments, and establish quantitative characterization simulation calculation models based on previous detection data, analyze the interface structure and data types and characteristics of different space environment models, and establish a real-time quantitative characterization simulation technology architecture for the spacecraft's comprehensive environment, which can be used to simulate and calculate the real-time space position of the spacecraft to obtain the quantitative characterization data of the real-time space environment where the spacecraft is located. Ultimately, the problem of real-time quantitative characterization of the space comprehensive environment is solved.

[0032] Step 1: The aircraft is in a complex space environment during its on-orbit operation. First, the types and composition of the space comprehensive environment are analyzed. Since this embodiment is mainly aimed at the aircraft operating in space, the space comprehensive environment in which the aircraft is located during its on-orbit operation is characterized in real time and quantitatively during the operation of the aircraft through computer simulation. Artificial earth aircraft, also known as artificial earth satellites, refers to artificial aircraft that can fly around the earth for more than one week. The spatial distribution range of artificial earth satellites is also relatively wide, and the distribution height range ranges from hundreds of kilometers above sea level to tens of thousands of kilometers above sea level. The environment experienced by the aircraft during its operation may also change dramatically. It may be in the intersection of multiple environments at the same time, and may also experience the influence of several environments. Therefore, it is possible to realize the real-time quantitative characterization technology of the space comprehensive environment during the on-orbit operation of the aircraft, which is important for exploring the environmental changes of the aircraft during its operation and then exploring the influence of the environment on the spacecraft and the countermeasures. The quantitative characterization data can guide the reliability design of the aircraft in a quantitative manner, which is of great significance to the high-reliability operation of the aircraft on orbit.

[0033] The space environment can be roughly divided into the following categories according to the distribution range from near to far from the earth:

[0034] (1) The upper atmosphere of the Earth is an important environmental factor under low Earth orbit conditions. The Earth's atmosphere is divided into several characteristic regions according to temperature or composition profiles. The thermosphere, which is about 85km to 1000km, is mainly related to low Earth orbit. The characteristic of the thermosphere is that the temperature increases with increasing altitude. The actual structure of the thermosphere is closely related to the level of solar activity. In the thermosphere, the collisions of the gas molecules of each component are not enough to achieve full mixing, but are in a state of diffusion equilibrium. Above the thermosphere, the main gas components are hydrogen and helium, and have a fixed temperature, which is called the outer atmosphere.

[0035] The concentration of the thermosphere decreases roughly exponentially with altitude. This is the result of hydrostatic equilibrium. The main components of the thermosphere include Ar, O2, N2, O, He and H. Hydrostatic equilibrium makes H and He the main components of the atmosphere at the top of the thermosphere. Under normal low-Earth orbit and polar orbit conditions, the neutral gas is mainly atomic oxygen with a small amount of O2, N2 and H, and may also have less than 1% He, NO, N and Ar. The temperature of the thermosphere depends on factors such as the solar cycle, latitude and local time, and can increase from about 100K at an altitude of 100km to 500-1500K at 1000km, and can reach 2000K during strong geomagnetic activity. The flight speed of a low-Earth orbit spacecraft is about 7.8km / s, which can make the kinetic energy of the neutral atmosphere directly impacting the spacecraft reach about 5eV or more (from 4.6eV when N impacts to 10.25eV when O2 impacts). This will cause chemical reactions between the neutral atmosphere and spacecraft materials (such as atomic oxygen erosion, etc.). Since the directional motion speed of the neutral atmosphere relative to the spacecraft is significantly higher than the thermal motion speed, the interaction between the two is anisotropic.

[0036] Many factors affect the basic parameters of the neutral atmosphere (density, temperature and composition), including local time, latitude, altitude, solar activity and geomagnetic activity. Usually, the F10.7 index is used to characterize the changes in solar extreme ultraviolet radiation (EUV), and the number of sunspots reflects the influence of the sun on geomagnetic activity to a certain extent. Solar extreme ultraviolet radiation and geomagnetic gyrations are the main heating sources of the upper atmosphere. The density and temperature of the neutral atmosphere usually increase with the increase of the F10.7 index and the geomagnetic index Ap. For example, at an altitude of 400km, the average density of the neutral atmosphere in a high solar year (F10.7≈230) can be increased by about one order of magnitude compared to a low solar year (F10.7≈70). Correspondingly, in a high solar year, the temperature of the outer atmosphere can be increased from about 700K to about 1200K due to heating by solar extreme ultraviolet radiation. The relationship between the basic parameters of the neutral atmosphere and time shows diurnal and seasonal changes, and has a semi-annual variation pattern. At the middle altitude of the thermosphere (e.g. 500km), the maximum average density of the atmosphere is highest in October and November and lowest in April. At the same altitude, the daily average temperature is highest at 14:00 near the local time.

[0037] (2) Geomagnetic field environment. The geomagnetic field is the root of the geomagnetic layer formed by the interaction with the solar wind. Above 1000 km, the geomagnetic layer is a controlling geophysical environment; below 1000 km, the geomagnetic field mainly affects the dynamic process of the neutral atmosphere by controlling the ionospheric plasma. There are two sources of magnetic field in near-Earth space: one is the electric current in the earth, which can generate about 99% of the magnetic field on the earth's surface; the other is the geomagnetic current system. The latter plays a relatively large role beyond several earth radii because the former is inversely proportional to the cube of the distance from the center of the earth. In many cases, the earth's magnetic field can be regarded as an eccentric dipole, with the magnetic axis tilted 11.7° and deviating from the center of the earth by about 430 km in the direction of Southeast Asia (15.6°N, 150.9°E). Due to the 11.7° tilt of the geomagnetic axis, the geomagnetic latitude of eastern North America increases by 11.7°, while it decreases by 11.7° at the other end of the earth. The tilt and deviation of the geomagnetic dipole cause the Earth's surface to be higher in the geomagnetic field than other regions in the South Atlantic region off the coast of Brazil (with its center near 40°W, 30°S). This will lead to a decrease in the magnetic field intensity over the region (negative anomaly) and a decrease in the height of the inner radiation belt from the ground, which is an important reason for the formation of the South Atlantic Anomaly. Under the influence of the extremely low tilt and deviation of the geomagnetic dipole, the South Atlantic Anomaly slowly drifts westward.

[0038] Under low Earth orbit conditions, the geomagnetic internal source field plays a dominant role, and even during strong magnetic storms, it is about 99% of the geomagnetic intensity. This shows that during magnetic storms, the geomagnetic field at the low Earth orbit altitude produces less fluctuations. Unlike the internal source field, the external source field mainly comes from the ionospheric current and the magnetospheric current, and shows obvious short-term variation characteristics (ranging from a few minutes to a few days). The external source field can be divided into two parts: the quiet variation field Q and the fluctuation variation field D, which are measured by geomagnetic ground stations. The former mainly comes from the solar quiet day variation Sq field (obtained from the statistics of 5 magnetic quiet days per month, which comes from the ionospheric current induced by the solar electromagnetic radiation), which is at least 2 to 3 orders of magnitude lower than the internal source field; the latter comes from sudden changes in interplanetary space. Changes in interplanetary space are transmitted through solar wind plasma and its captured solar magnetic field. The fluctuation field D appears randomly and has no rules. The fluctuation field D contains two obviously different sources: geomagnetic storms and geomagnetic pulsation components. Magnetic storms are strong geomagnetic field fluctuations that last for a long time. In contrast, geomagnetic pulsations are a smaller, short-period variation in the Earth's magnetic field, which is related to a variety of factors, including changes in solar wind pressure, changes in the magnetosphere, and the movement of charged particles.

[0039] (3) Ionospheric plasma environment: The neutral atmosphere extends from the Earth's surface to an altitude of about 2500 km, and the corresponding atmospheric mass density drops to about 10-17 kg / m 3 . As the altitude continues to increase, the atmospheric density continues to decrease, and there is no strict outer boundary. The solar shortwave electromagnetic radiation can ionize the neutral atmosphere and produce plasma. In the altitude range of 50 to 1000km, the area where part of the neutral atmosphere undergoes photoionization is called the ionosphere. Below 1000km, the number density of plasma is lower than that of the neutral atmosphere. Above about 150km, plasma rarely collides with neutral gases and hardly interacts with each other. This makes the behavior of ionospheric plasma mainly controlled by electrostatic effects. Between about 50km and 150km, the neutral atmosphere and the ionosphere interact in a complex way. The ionosphere is generally electrically neutral, and the electron density is equal to the total positive ion density (the sum of various positive ion densities). The ionosphere has a high electron density (greater than 103-104cm -3 ) and low energy (equivalent temperature less than 3000K, average kinetic energy less than 0.3eV), and is often called cold and dense plasma.

[0040] (4) Charged particle radiation environment: Radiation belt particles surround the Earth and form a mid- and low-latitude annular belt, which is mainly composed of protons and electrons, and a small amount of heavy ions (such as O +The Earth's radiation belts are generally divided into two annular regions of different heights, called the inner belt and the outer belt. The inner belt extends from a few hundred km to about 6,000 km above the equator, and is mainly composed of high-energy protons (up to tens of MeV) and high-energy electrons (1-10MeV). The outer belt can reach an altitude of 60,000 km and is mainly composed of high-energy electrons. For low-Earth orbits, it is particularly important to note that the inner radiation belt extends to a lower altitude over the South Atlantic. The geomagnetic field intensity there is relatively low, forming the South Atlantic Anomaly. Although the location of the geosynchronous orbit is outside the center of the outer radiation belt, it still encounters a strong high-energy electron flow. It is generally believed that the protons and electrons in the inner radiation belt come from the galactic cosmic rays acting on the upper atmosphere to produce reflected neutrons and decay; the outer radiation belt is formed by the geomagnetic field capturing the solar wind plasma and then accelerating it. The motion state of the radiation belt particles is controlled by the geomagnetic field. The inner radiation belt is mainly controlled by the Earth's endogenous magnetic field and is relatively stable. When solar activity and atmospheric density change, the flux of particles in the inner radiation belt may change periodically to a certain extent. In contrast, the outer radiation belt is easily affected by large changes in the magnetic tail, and often undergoes short-term drastic changes. The flux of protons in the radiation belt is higher in solar low years than in solar high years, while the opposite is true for electrons, that is, the flux of electrons is higher in solar high years.

[0041] Step 2: In order to achieve real-time quantitative characterization of different environments, select the quantitative needle simulation model of the corresponding environment. The selected models are related to the real-time movement of the satellite and can be widely recognized and applied in related fields. They can more accurately reflect the quantitative characterization data of the corresponding environment and provide engineering designers with real and reliable quantitative simulation data.

[0042] (1) For the upper atmosphere environment. The US Standard Atmosphere 1976 model is a standard atmosphere model that is easy to use, internationally recognized and widely used. The so-called standard atmosphere assumes that under moderate solar activity conditions, the atmosphere obeys the ideal gas law and fluid statics equations. By establishing a hypothetical vertical distribution of atmospheric temperature, pressure and density, it characterizes the annual average state of the mid-latitude atmosphere within an altitude of 1000 km under moderate solar activity conditions. In the Earth Standard Atmosphere Model, the definition of the standard atmosphere, data source, basic assumptions, calculation formulas and data tables of the main atmospheric parameters changing with altitude are given. In the thermosphere above 100 km, the temperature begins to rise sharply with altitude, then rises slowly and finally reaches the temperature of the outer atmosphere. The outer atmosphere temperature of the US Standard Atmosphere 1976 model is 1000K. The average density and pressure of the atmosphere decrease exponentially with increasing altitude. Atmospheric components begin to diffuse and separate above about 100 km, and completely reach a diffuse and separated state above 120 km. Under conditions of moderate solar activity (F10.7=150) and quiet magnetic disturbance (AP=4), the number density of atomic oxygen is significantly higher than that of other atmospheric components in the altitude range of about 200km to 650km.

[0043] The difference between the MSIS reference atmosphere model and the standard atmosphere model is that the former takes into account the characteristics of the earth's atmosphere that change with latitude, season and solar activity, and can better describe the movement of the atmosphere. The MSIS reference atmosphere model is a semi-empirical model established based on the detection data of mass spectrometers on multiple satellites and ground-based incoherent scattering radars. MSIS is the abbreviation of Mass-Spectrometer-Incoherent-Scatter. The first few versions of this series of models focused on the upper atmosphere. Among them, the MSIS-86 version has been adopted by the Committee on Space Research (COSPAR) as the International Reference Atmosphere Model (CIRA), namely the CIRA-1986 model. Later, the MSIS model was expanded to the middle and lower atmospheres, forming the MSISE-90 version, which can give the atmospheric temperature, density and number density distribution of the main atmospheric components from the ground to the outer atmosphere. Above 72.5km, MSISE-90 is basically similar to MSIS-86, except that the former is appropriately corrected based on the flight data of the space shuttle and the detection results of relevant ground-based incoherent scattering radars. The MSIS reference atmosphere model takes into account the effects of solar extreme ultraviolet radiation and geomagnetic disturbances on the thermosphere. Solar activity has a significant impact on the distribution of thermospheric atmospheric components. In years with low solar activity, the diffusion separation rate accelerates, the heavy components intensify as the altitude decreases, and the light components quickly become the main components of the thermosphere; in years with high solar activity, the situation is the opposite. Geomagnetic disturbances can also cause changes in thermospheric atmospheric temperature and density. During magnetic storms, the injection of falling particles causes the atmosphere to heat up and the thermospheric atmospheric density to increase significantly.

[0044] The NRLMSISE-00 model reference atmosphere model used in the present invention is based on the existing MSIS reference atmosphere model, and further incorporates observation data such as atmospheric temperature, density and component concentration from various satellites, rockets and radars to become an extended MSIS model, namely, NRLMass Spectrometer-Incoherent-Scatter Radar Extended Model. This model can well describe the spatial distribution of the earth's atmospheric composition, temperature and total mass density from the ground to the outer layer.

[0045] The NRLMSISE-00 model used in the present invention can obtain the number density of atmospheric components N2, O, O2, He, Ar, H and N and anomalous atomic oxygen through simulation time and geodetic longitude, latitude and altitude, as well as model control parameters F107, F107A, and AP values, and can also obtain quantitative characterization data such as the total mass density of the atmosphere and the atmospheric temperature.

[0046] (2) For the geomagnetic field environment. The Earth's magnetic field is approximately a magnetic dipole at lower altitudes, but is severely deformed by the solar wind at higher altitudes. The geomagnetic field model is an indispensable condition for establishing the radiation belt and cosmic ray particle environment model. The distribution of particles in the Earth's radiation belt is often described based on the idealized spatial position of the geomagnetic dipole. For the solar energy proton and galactic cosmic ray environment, the magnetic shielding effect of the geomagnetic field needs to be considered. The geomagnetic field model is also used in the study of geomagnetospheric physics, such as describing the trajectory of charged particles passing through the magnetosphere.

[0047] When a spacecraft moves across the Earth's magnetic field, it will be affected by the induced dynamic electromagnetic field, that is, E = V·B (where E is the electric field vector, V is the velocity vector and B is the magnetic field vector). If a current loop is formed, a current will flow through the spacecraft and the surrounding plasma, resulting in a potential difference of several volts in the low-Earth orbit spacecraft. The interaction between the Earth's magnetic field and the spacecraft's on-orbit magnetic moment can cause a magnetic interference torque, which can change the spacecraft's attitude or can be used for attitude control.

[0048] The International Reference Geomagnetic Field Model IGRF is used in the present invention. The International Association of Geomagnetism and Aerophysics (IAGA) has established a calculation model describing the Earth's main magnetic field (internal source field) based on geomagnetic observatories and field measurements, spacecraft, space shuttles and satellites. The IGRF model is a general term and has different versions. Five years is a field period, and the Gaussian coefficients in the model are and When using the IGRF model, the version used should be indicated, such as IGRF-95 or IGRF-10. The IGRF-13 version used in the present invention can give the main parameters of the international reference geomagnetic field model for each period from 1900 to 2025. The dipole magnetic moment of the earth's magnetic field is slowly decreasing year by year. The magnetic potential of the earth's main magnetic field can be expressed by spherical harmonic series or spherical harmonic functions. The magnetic vector field is determined by the magnetic potential gradient, that is, The expression of geomagnetic potential is as follows:

[0049]

[0050] Where V is the potential of the magnetic field, r is the radial distance (distance from the center of the earth), θ is the geographic co-latitude (polar angle), λ is the geographic east longitude, and a is the reference earth radius (6371.2km); and It is the Schmidt coefficient or Gaussian coefficient, which is determined by the observation data of the Earth's main magnetic field. is the Schmidt normalized Legendre polynomial of order n, that is:

[0051]

[0052] The polynomial in the second square bracket is called the Legendre polynomial P nm (cosθ); ε m The values ​​are:

[0053]

[0054] In the spherical coordinate system (r,θ,λ), we can get The north, east and vertical downward components of the geomagnetic field are obtained as follows: and

[0055] Therefore, substituting the expression of geomagnetic potential into the corresponding calculation formula is as follows:

[0056]

[0057]

[0058]

[0059] Using the above expression and the coefficients of the corresponding period, the number of R above the ground can be determined EThe spatial distribution of the geomagnetic field in the Earth. Analysis shows that the term n=1 in the expression of the geomagnetic potential accounts for more than 90% of the magnetic potential V value, representing the dipole magnetic field at the center of the Earth. The remaining n>1 part is the non-dipole magnetic field. The terms n=2 and n=3 dominate the non-dipole magnetic field. In practical applications, a few terms of the Legendre series are often used to meet the requirements and simplify the calculation.

[0060] The IGRF-13 model is used in the present invention to obtain geomagnetic field parameters such as the total intensity of the geomagnetic field, the vertical component of the magnetic field intensity, the east component of the magnetic field intensity, the north component of the magnetic field intensity, the magnetic inclination, the magnetic declination, etc. by simulating the time and the parameters such as the longitude, latitude and altitude of the earth.

[0061] (3) For the ionospheric plasma environment. The present invention uses the International Reference Ionosphere Model, which is the most widely used, referred to as the IRI model (International Reference Ionosphere). It is a global ionosphere empirical model, and the commonly used versions are IRI-90, IRI-95 and IRI-2007. The IRI-95 model is applicable to latitudes below ±60°, and can calculate the characteristic parameters of ionospheric plasma at altitudes of 60km to 2000km under geomagnetic calm conditions, including the monthly average plasma density, composition and temperature. The input conditions include: date, altitude, latitude, longitude, local time, and the 12-month average number of sunspots or the corresponding F10.7. The output result is the electron number density, O + Number density, H + Number density, He + Number density, O2 + Number density, NO + Number density, N +Number density, ion cluster number density, neutral gas temperature, ion temperature and electron temperature. This mode has multiple options for calculation and can be used in different applications. Running the program will give recommended options. The error range of the model is 2 to 4 times below the F2 layer peak height; it can reach 1 order of magnitude above the F2 layer peak height. When running the IRI-2007 mode, you can choose geographic coordinates or geomagnetic coordinates. The input conditions include latitude, longitude, date, local time or universal time, altitude (start to end altitude and step size). Other input conditions such as RZ12 (12-month average sunspot number), F10.7 and ap can take the default values ​​of the program. In the program, the solar activity index can also use the IG12 index derived from the noon ionosphere observation data instead of the monthly average sunspot number as a new solar activity index. This model version calculates the ionospheric electron density with an accuracy of: 50-80% from 65km to 95km; 5-15% from 100km to 200km during the day; 15-30% from 100km to 200km at night; 15-25% from 200km to 1000km when the latitude is less than 60°; 50-80% from 200km to 1000km when the latitude is greater than 60°.

[0062] The present invention uses the latest IRI2016 model to calculate the electron density, electron temperature, ion density, ion temperature and various ion proportions of ionospheric plasma by bringing the simulation time and parameters such as geocentric longitude, latitude and altitude into the IRI2016 model, and obtains the electron density, electron temperature, ion density, ion temperature and various ion proportions of ionospheric plasma through the standard IRI2016 model.

[0063] (4) Charged particle radiation environment. The charged particle radiation environment around the earth analyzed in step 1 can be divided into two categories: one is the negatively charged electron radiation environment, usually called the electron radiation environment of the earth's radiation belt, and the other is the positively charged proton radiation environment, usually called the proton radiation environment of the earth's radiation belt.

[0064] The internationally common Earth radiation belt electron model is the AE-8 (NASA) model, which can give the static distribution of radiation belt electron fluxes. Through this model, the integral flux and differential flux of radiation belt electrons can be calculated respectively for the high and low solar activity years under different energies (E) and geomagnetic coordinates (L, B). The detection data relied on mainly come from more than twenty satellites from the 1960s to the mid-1970s, which can better cover the spatial region of the Earth radiation belt (L = 1.2 - 11RE) and have a relatively wide electron energy range (40 keV - 7 MeV). The Earth's electron radiation belt involves three parts: the inner belt (1.2 < L < 2.5), the transition region (2.5 < L < 3.0), and the outer belt (3.0 < L < 11), which is difficult to be expressed by a unified analytical model. The AE-8 model is established on the basis of model versions such as AE-4, AE-5, and AE-6, and further combines satellite detection data such as Azur, OV3-3, OV2-19, ATS-5, and ATS-6. The AE-8 (NASA) model is the model with the widest coverage in terms of space and energy range for the Earth's electron radiation belt so far.

[0065] The internationally common radiation belt proton model is the AP-8 model established by J.I. Vette et al. of the Goddard Space Flight Center of NASA, hereinafter simply referred to as the AP-8 (NASA) model. The detection data relied on mainly come from more than twenty satellites in the 1960s and early 1970s. This model can relatively fully cover the proton region of the Earth radiation belt and has a relatively wide proton energy range. Although quite a part of the data is obtained by extrapolation, the AP-8 (NASA) model is still the basic model used for engineering problems internationally. The AP-8 model is developed on the basis of the AP-1, AP-5, AP-6, and AP-7 models. The previous models expressed the proton energy spectrum of the Earth radiation belt in the form of power functions or exponential functions. In fact, simple functional relationships are difficult to fully fit the energy spectrum of radiation belt protons in the range of 0.1 MeV to 400 MeV.

[0066] In the present invention, the AE-8 radiation belt electron model is used to calculate and output the radiation differential flux and radiation integral flux of the corresponding energy level sequence of radiation belt electrons by combining parameters such as the simulation time, geodetic longitude, latitude, and altitude, the model control parameters of the solar maximum and minimum years, and the electron energy level setting sequence, and substituting the above parameters into the model.

[0067] In the present invention, the AP-8 radiation belt proton model is used to calculate and output the radiation differential flux and radiation integral flux of the corresponding energy level sequence of radiation belt protons by combining parameters such as the simulation time, geodetic longitude, latitude, and altitude, the model control parameters of the solar maximum and minimum years, and the proton energy level setting sequence, and substituting the above parameters into the model.

[0068] Step three: Construct a digital spatial model of the space area around the earth to achieve real-time quantitative characterization of the comprehensive space environment. The real-time quantitative characterization of the comprehensive space environment is mainly to quantify the complex space environment in which the on-orbit aircraft is located, according to the changes in the real-time time and spatial position of the aircraft, and to quantify different environments as much as possible through different space environment models. In order to solve the problem of the operating status of spacecraft flying near the earth, the present invention usually uses the following three-dimensional space rectangular Cartesian coordinate system definition method to analyze and describe the quantitative characterization of the on-orbit position, speed, and other states of the aircraft.

[0069] Because the models of various space environments are related to time and space position, the present invention adopts the definition of coordinated universal time (UTC) time definition method according to the definition of time calibration input into the space environment model and the calculation of the on-orbit motion state during the operation of the aircraft. The coordinated universal time is based on the international atomic time, and one second is defined as the duration of 9,192,631,770 cycles of transition radiation between two hyperfine energy levels of the ground state of the cesium-133 atom. The content is basically consistent with the world time of the mean solar time on the Greenwich meridian. Considering the non-uniformity of the world time, in order to ensure that the difference between the coordinated universal time and the world time (UT1) does not exceed 0.9 seconds, positive or negative leap seconds will be added to the coordinated universal time when necessary. The representation method of UTC in the present invention is the year, month, day, hour, minute, and second of the Gregorian calendar, which is convenient for users to set and use. In the internal calculation of the present invention, it is necessary to convert the time into a continuous integer, and calculate and judge in the software program of the present invention. In the present invention, the Julian day representation method is used to obtain a continuous integer form of time expression. Julian day is the number of days starting from 12h on January 1, 4573 BC. By converting the Gregorian year, month and day into Julian day, we can obtain the description of the difference between two Gregorian calendar moments under a unified standard, which is convenient for setting the simulation step size. Similarly, Julian day is also applicable to the calculation of the earth's rotation angle.

[0070] Calculate the Julian day from the Gregorian calendar:

[0071]

[0072] In the formula: INT()—round down.

[0073] In order to obtain the spatial position of the aircraft in orbit at the corresponding simulation time, we must first define a reasonable coordinate system to describe the position change of the aircraft in the coordinate system. Figure 2As shown, considering that the man-made aircraft moves in the inertial space around the earth, the present invention uses the J2000 geocentric coordinate system, the origin of the J2000 coordinate system coincides with the center of mass of the earth, the X-axis points to the mean equinox at J2000, the Z-axis points to the North Pole, and the Y-axis, the X-axis and the Z-axis form a right-handed rectangular coordinate system, which is an inertial coordinate system.

[0074] When a spacecraft is in orbit, the present invention solves the real-time spatial comprehensive environment of the spacecraft based on the spatial position and movement speed of the spacecraft. The spacecraft in orbit is initialized using Kepler orbital elements, which is convenient for users to set up and use the method of the present invention. 1) Semi-major axis, a, describes the size of the orbit. 2) Eccentricity, e, describes the shape of the orbit. 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) Perigee argument, ω, describes the position of the perigee relative to the ascending node. 6) True anomaly, f, describes the position of the satellite relative to the perigee. The method for calculating the position r0 and velocity v0 in the inertial system by orbital elements is as follows.

[0075] According to the two-body motion equation and Kepler's three laws, we can get the specific solution expressions of the six elements of the spacecraft orbit:

[0076]

[0077]

[0078]

[0079]

[0080]

[0081]

[0082] Where, μ = GM = 3.986005 × 10 14 m 3 / s 2 is the gravitational constant of the earth, G is the gravitational constant, and M is the mass of the earth. Assume that at time t0, in the inertial system, the velocity vector and position vector of the aircraft are:

[0083]

[0084]

[0085] Then the velocity and position are:

[0086]

[0087]

[0088] The angular momentum of the orbit is:

[0089]

[0090]

[0091] The calculated three-dimensional coordinate data of the satellite changing with time needs to be transformed into the geocentric coordinate system to obtain the longitude, latitude, and altitude data of the satellite in the coordinate system for use in the calculation of the space environment model.

[0092] First, establish the geocentric earth-fixed coordinate system and the geocentric geodetic coordinate system:

[0093] 1. Earth-centered Earth-fixed Coordinate System

[0094] In order to transform the epoch coordinate system of the latitude, longitude and altitude of the satellite as the fulcrum, the coordinates of the target point in the geocentric geodetic coordinate system must first be transformed into the geocentric earth-fixed coordinate system. The definition of the geocentric earth-fixed coordinate system is as follows:

[0095] Combination Figure 3 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.

[0096] 2. Geocentric Coordinate System

[0097] When using the space atomic oxygen environment model, the geodetic longitude and latitude are often used to represent it. This paper also performs subsequent calculations based on the WGS-84 coordinate system and its corresponding WGS-84 earth ellipsoid model. The coordinate system is defined as follows.

[0098] WGS-84 is a barycentric coordinate system, where the origin coincides with the Earth's center of mass. Figure 4 As shown, its Z axis points to the agreed pole 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 horizon with the equator, and the Y axis, X axis and Z axis form a right-hand rectangular coordinate.

[0099] The geodetic coordinates (lon, lat, alt) in the WGS-84 coordinate system are the latitude and longitude 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 line 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.

[0100] The WGS-84 coordinate system corresponds to the WGS-84 ellipsoid, and the parameters are shown in Table 1 below.

[0101] Among them, a represents the major radius, b represents the minor radius, c represents the polar radius, all in units of m, f represents the flattening, e 2 represents the first eccentricity square, e ’2 represents the square of the second eccentricity, and J2 represents the second-order spherical harmonic coefficient of the Earth's gravity field.

[0102] Table 1 WGS-84 ellipsoid parameters

[0103]

[0104] First, the changes of J2000 inertial system and Earth-centered Earth-fixed coordinate system are carried out.

[0105] From the J2000 coordinate system to the Earth-centered Earth-fixed coordinate system, the effects of precession, nutation, Earth rotation, and polar motion need to be taken into account. The Earth rotation can be expressed in Greenwich sidereal hour angle. The conversion relationship is as follows: Figure 5 As shown in Figure 1. PR, NR, ER, and EP are the precession matrix, nutation matrix, earth rotation matrix, and polar motion matrix, respectively.

[0106] HG is the overall change matrix from the J2000 coordinate system to the Earth-centered Earth-fixed coordinate system:

[0107] HG=(PR)(NR)(ER)(EP)

[0108] (1) Precession matrix

[0109] Precession is the phenomenon that the Earth's rotation axis moves westward along the ecliptic due to the long-term precession of the Earth's rotation axis under the gravitational force of the sun, moon and other planets, causing the vernal equinox to move westward along the ecliptic, making the tropical year shorter than the sidereal year. The precession matrix is ​​as follows:

[0110] PR=R z (-z A )R z (-θ A )R z (-ζ A )

[0111] Where: z A ,θ A ,ζ A —The precession angle can be calculated by the following formula:

[0112]

[0113] (2) Nutation matrix

[0114] Nutation is the short-term swing of the Earth's rotation axis caused by external forces. The transformation matrix is ​​as follows:

[0115] NR=R X (-ε A )Rz (-ψ)R X (-ε A +Δε)

[0116] Where: ε A — obliquity of the mean ecliptic in the epoch;

[0117] Δψ—ecliptic longitude oscillation;

[0118] Δε—Nutation of the obliquity of the ecliptic.

[0119] These items can be obtained through the DE405 ephemeris file by interpolating the following formula:

[0120] ε A =84381”.448-46.8150T-0.0059T 2 +0.001813T 3

[0121]

[0122] σ i =a 1j l+a 2j l'+a 3j F+a 4j D+a 5j Ω

[0123] Where: l—moon's mean anomaly angle;

[0124] l'—sun's mean anomaly;

[0125] F—the moon’s angular distance from the mean ascending node;

[0126] D—the angular distance between the sun and the moon;

[0127] Ω—Moon's ecliptic longitude.

[0128] It can be obtained by the following formula:

[0129]

[0130] (3) Earth rotation matrix

[0131] The main difference between the J2000 coordinate system and the Earth-fixed coordinate system is that the Earth-fixed coordinate system takes into account the rotation of the Earth, so an accurate Earth rotation matrix is ​​particularly important. The matrix is ​​as follows:

[0132] ER=R z (θ G )

[0133] In the formula, θ G Greenwich sidereal time.

[0134]

[0135] (4) Pole shift matrix

[0136] The position of the Earth's rotation axis relative to the Earth changes over time, which will change the position of the observer's sky spike on the celestial sphere, which is called polar shift. The polar shift matrix is ​​as follows:

[0137] EP=R Y (-x p )R X (-y p )

[0138] Where: x p ,y p —Polar coordinates.

[0139] Then, the geocentric coordinate system and the earth-fixed rectangular coordinate system are transformed to convert the three-dimensional coordinates in the earth-fixed coordinate system into the longitude, latitude and altitude data of the geocentric coordinate system for use in environmental calculations.

[0140] Assume that the coordinates of the target in the geocentric geodetic coordinate system are (lon, lat, alt), then the coordinates in the geocentric earth-fixed coordinate system are:

[0141]

[0142] Where: e 2 =(a 2 -b 2 ) / a 2 , see the WGS-84 ellipsoid definition.

[0143] N—normal length,

[0144] Similarly, the longitude, latitude and altitude can be inverted using the coordinates in the Earth-centered, Earth-fixed coordinate system.

[0145]

[0146] A specific simulation example is provided below.

[0147] Select the initialization spacecraft attitude and orbit parameters. The six numbers of the initial orbit of the spacecraft are: major axis 42166.3km, eccentricity 0 degree, inclination 0 degree, ascending node right ascension 0 degree, perigee argument 0 degree, perigee angle 0 degree.

[0148] The task started at 12:0:00 on January 1, 2017. The simulation step length was 20 seconds.

[0149] like Figure 6 The figure shows the real-time position change of the aircraft in space, a schematic diagram in three-dimensional space.

[0150] The real-time comprehensive environment quantitative data of the aircraft is obtained, including:

[0151] (1) Real-time quantitative representation of data from the atmospheric environment NRLMSISE-00 model. Specific environmental output types include:

[0152] Helium atomic number density, oxygen atomic number density, nitrogen molecular number density, oxygen molecular number density, argon atomic number density, total mass density, hydrogen atomic number density, nitrogen atomic number density, abnormal oxygen (oxygen-17, oxygen-18) number density, exoatmospheric temperature, temperature at ALT;

[0153] (2) Real-time quantitative characterization data of the Earth's magnetic field environment IGRF13 model. Specific environmental output types include: magnetic declination, magnetic inclination, horizontal intensity, north intensity, east intensity, vertical intensity, and total intensity;

[0154] (3) Real-time quantitative characterization data of the electron AE8 model and proton AP8 model of the Earth's radiation belt environment. Specific environmental output types include:

[0155] The integrated flux of electrons in the Earth's radiation belt outputs the corresponding flux value according to the user's energy level settings.

[0156] The electron differential flux of the Earth's radiation belt outputs the corresponding flux value according to the user's energy level setting.

[0157] The integrated proton flux of the Earth's radiation belt outputs the corresponding flux value according to the user's energy level settings.

[0158] The differential flux of protons in the Earth's radiation belt outputs the corresponding flux value according to the user's energy level settings.

[0159] In this embodiment, by determining the spatial comprehensive environment of the aircraft at each simulation moment, and then selecting the corresponding quantitative representation model according to the spatial comprehensive environment to determine the real-time quantitative representation data of the spatial comprehensive environment corresponding to different simulation moments, the problem of real-time quantitative representation of the spatial comprehensive environment can be solved to ensure flight safety.

[0160] Optionally, the comprehensive space environment includes an upper atmosphere environment, a geomagnetic field environment, an ionospheric plasma environment and a charged particle radiation environment.

[0161] Optionally, the quantitative characterization model corresponding to the high-altitude atmospheric environment includes the NRLMSISE-00 model, and the environmental output types of the NRLMSISE-00 model include the number density of helium atoms, the number density of oxygen atoms, the number density of nitrogen molecules, the number density of oxygen molecules, the number density of argon atoms, the total mass density, the number density of hydrogen atoms, the number density of nitrogen atoms, the abnormal number density of oxygen, the temperature of the outer atmosphere and the temperature at the target altitude.

[0162] Optionally, the quantitative characterization model corresponding to the geomagnetic field environment includes the International Reference Geomagnetic Field Model IGRF, and the environmental output types of the International Reference Geomagnetic Field Model IGRF include magnetic declination, magnetic inclination, horizontal intensity, north intensity, east intensity, vertical intensity and total intensity.

[0163] Optionally, the quantitative characterization model corresponding to the ionospheric plasma environment includes an international reference ionosphere model, and the environmental output types of the international reference ionosphere model include electron density, electron temperature, ion density, ion temperature and ion ratio of ionospheric plasma.

[0164] Optionally, the charged particle radiation environment includes an earth radiation belt electron radiation environment and an earth radiation belt proton radiation environment.

[0165] Optionally, the quantitative characterization model corresponding to the electron radiation environment of the Earth radiation belt includes the AE-8 electron model, and the environmental output types of the AE-8 electron model include the Earth radiation belt electron integral flux and the Earth radiation belt electron differential flux; the quantitative characterization model corresponding to the Earth radiation belt proton radiation environment includes the AP-8 proton model, and the environmental output types of the AP-8 proton model include the Earth radiation belt proton integral flux and the Earth radiation belt proton differential flux.

[0166] Another embodiment of the present invention provides a real-time quantitative characterization device for a space comprehensive environment, comprising: a parameter module, used to set simulation parameters, wherein the simulation parameters include a simulation start time, a simulation end time and a simulation step time; an environment module, used to determine the space comprehensive environment of the aircraft at each simulation time one by one by accumulating the simulation step time from the simulation start time to the simulation end time; and a quantitative characterization module, used to select a corresponding quantitative characterization model according to the space comprehensive environment to determine the real-time quantitative characterization data of the space comprehensive environment corresponding to different simulation times.

[0167] Another embodiment of the present invention provides a real-time quantitative characterization system for a spatial comprehensive environment, 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 above-mentioned real-time quantitative characterization method for a spatial comprehensive environment is implemented.

[0168] Another embodiment of the present invention provides a computer-readable storage medium, wherein the computer-readable storage medium stores a computer program, and when the computer program is read and executed by a processor, the above-mentioned method for real-time quantitative characterization of a spatial comprehensive environment is implemented.

[0169] 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 real-time quantitative characterization method for a spatial comprehensive environment, characterized in that: include: Setting simulation parameters, wherein the simulation parameters include simulation start time, simulation end time and simulation step time; From the simulation start time to the simulation end time, the simulation step lengths are accumulated in sequence according to the simulation step lengths, and the spatial comprehensive environment of the aircraft at each simulation time is determined one by one; Selecting a corresponding quantitative representation model according to the spatial comprehensive environment to determine real-time quantitative representation data of the spatial comprehensive environment corresponding to different simulation moments; The space comprehensive environment includes the upper atmosphere environment, the geomagnetic field environment, the ionospheric plasma environment and the charged particle radiation environment; The quantitative characterization model corresponding to the high-altitude atmospheric environment includes the NRLMSISE-00 model, and the environmental output types of the NRLMSISE-00 model include the number density of helium atoms, the number density of oxygen atoms, the number density of nitrogen molecules, the number density of oxygen molecules, the number density of argon atoms, the total mass density, the number density of hydrogen atoms, the number density of nitrogen atoms, the abnormal number density of oxygen, the temperature of the outer atmosphere and the temperature at the target altitude.

2. The method for real-time quantitative characterization of spatial comprehensive environment according to claim 1, characterized in that: The quantitative characterization model corresponding to the geomagnetic field environment includes the International Reference Geomagnetic Field Model IGRF, and the environmental output types of the International Reference Geomagnetic Field Model IGRF include magnetic declination, magnetic inclination, horizontal intensity, north intensity, east intensity, vertical intensity and total intensity.

3. The method for real-time quantitative characterization of spatial comprehensive environment according to claim 1, characterized in that: The quantitative characterization model corresponding to the ionospheric plasma environment includes an international reference ionosphere model, and the environmental output types of the international reference ionosphere model include the electron density, electron temperature, ion density, ion temperature and ion ratio of the ionospheric plasma.

4. The method for real-time quantitative characterization of spatial comprehensive environment according to claim 1, characterized in that: The charged particle radiation environment includes the earth radiation belt electron radiation environment and the earth radiation belt proton radiation environment.

5. The method for real-time quantitative characterization of spatial comprehensive environment according to claim 4, characterized in that: The quantitative characterization model corresponding to the electron radiation environment of the Earth's radiation belt includes the AE-8 electron model, and the environmental output types of the AE-8 electron model include the Earth's radiation belt electron integral flux and the Earth's radiation belt electron differential flux. The quantitative characterization model corresponding to the Earth's radiation belt proton radiation environment includes the AP-8 proton model, and the environmental output types of the AP-8 proton model include the Earth's radiation belt proton integral flux and the Earth's radiation belt proton differential flux.

6. A device for real-time quantitative characterization of a spatial comprehensive environment, characterized in that: include: A parameter module, used to set simulation parameters, wherein the simulation parameters include simulation start time, simulation end time and simulation step time; An environment module, used to successively accumulate simulation steps according to the simulation step time from the simulation start time to the simulation end time, and determine the spatial comprehensive environment of the aircraft at each simulation time one by one; A quantitative characterization module, used for selecting a corresponding quantitative characterization model according to the spatial comprehensive environment, so as to determine real-time quantitative characterization data of the spatial comprehensive environment corresponding to different simulation moments; The space comprehensive environment includes the upper atmosphere environment, the geomagnetic field environment, the ionospheric plasma environment and the charged particle radiation environment; The quantitative characterization model corresponding to the high-altitude atmospheric environment includes the NRLMSISE-00 model, and the environmental output types of the NRLMSISE-00 model include the number density of helium atoms, the number density of oxygen atoms, the number density of nitrogen molecules, the number density of oxygen molecules, the number density of argon atoms, the total mass density, the number density of hydrogen atoms, the number density of nitrogen atoms, the abnormal number density of oxygen, the temperature of the outer atmosphere and the temperature at the target altitude.

7. A real-time quantitative characterization system for spatial comprehensive environment, characterized in that: It comprises a computer-readable storage medium storing a computer program and a processor, and when the computer program is read and executed by the processor, the real-time quantitative characterization method of the spatial comprehensive environment as claimed 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 real-time quantitative characterization of a spatial comprehensive environment as claimed in any one of claims 1 to 5 is implemented.

Images