Space atomic oxygen environment characterization methods, devices, computer equipment and storage media

Abstract

The present invention provides a method, device, computer equipment and storage medium for characterizing a space atomic oxygen environment, which belongs to the field of aerospace technology. The method includes obtaining the spatial position coordinates, running speed, running attitude and time parameters of the satellite at the current moment, and then obtaining the atomic oxygen number density data, wind speed data and complex structure data of the spacecraft itself at the real-time on-orbit position during the spacecraft mission according to the running position, speed and attitude, combined with the atomic oxygen environment model and the horizontal wind environment model, and realizing the real-time characterization of the space atomic oxygen environment according to these data, and solving the problem of atomic oxygen effect considering the structure shape of the spacecraft.

Description

Technical Field

[0001] The present invention relates to the field of aerospace technology, and in particular to a method, device, computer equipment and storage medium for characterizing a space atomic oxygen environment. Background Art

[0002] As an important component of the Earth's upper atmosphere, atomic oxygen poses a serious threat to spacecraft in low Earth orbit, including: elastic specular reflection or diffuse scattering may occur when atomic oxygen hits the surface of the spacecraft, atomic oxygen may react with substances attached to the surface of the spacecraft, such as atomic oxygen and NO2 will form excited nitrogen oxides (NO3+) when they collide with each other at high speed. 2 * ), when NO 2 * NO is desorbed from the spacecraft surface and restored to its ground state 2 When the spacecraft is in orbit, the atomic oxygen environment will have a serious impact on the spacecraft in orbit, not only affecting the reliability and life of the spacecraft during the orbital operation, but also affecting the normal operation of various subsystems on the spacecraft, including the payload. Therefore, it is necessary to study the role of atomic oxygen during the orbital operation of the spacecraft.

[0003] There are currently two main research methods. The first is satellite in-orbit testing. This method has the disadvantages of high cost, limited number of onboard tests and difficulty in testing all materials due to the satellite being launched by a rocket. In addition, it is difficult to test the results of the atomic oxygen effect under satellite orbit in all areas of space due to the satellite's attitude and orbit mission.

[0004] The second is a ground-based physical test, in which the satellite studies the impact of atomic oxygen on the satellite in a ground laboratory environment. However, it cannot achieve the complex atomic oxygen environment of a space satellite during its in-orbit operation, nor can it consider the impact of changes in the spacecraft's orbital attitude on the atomic oxygen effect. It cannot consider the impact of changes in the relative positions of the satellite, the earth, and the sun on the satellite's atomic oxygen effect. Summary of the invention

[0005] The technical problem to be solved by the present invention is how to characterize the atomic oxygen environment in space so as to study the effect of atomic oxygen on the spacecraft during its on-orbit operation.

[0006] In order to solve the above problems, the present invention provides a method for characterizing a space atomic oxygen environment, comprising:

[0007] Obtain the satellite's current spatial position coordinates, time parameters, operating speed, operating attitude, control parameters of the atomic oxygen environment model, and control parameters of the horizontal wind environment model;

[0008] Obtaining the atomic oxygen density at which the satellite is currently located according to the spatial position coordinates of the satellite at a current moment, the time parameters, and the control parameters of the atomic oxygen environment model;

[0009] Obtaining the current longitudinal wind speed and latitudinal wind speed of the satellite according to the spatial position coordinates of the satellite at the current moment, the time parameters and the control parameters of the horizontal wind environment model;

[0010] Obtaining a current structural model of the satellite according to the spatial position coordinates, the running speed and the running attitude of the satellite at a current moment;

[0011] The space atomic oxygen environment is characterized according to the atomic oxygen density, the meridional wind speed, the latitudinal wind speed, and the current structural model of the satellite.

[0012] Preferably, obtaining the spatial position coordinates and the running speed includes:

[0013] Get the six Kepler orbit numbers of the satellite at the current moment;

[0014] The spatial position coordinates and the running speed of the satellite at the current moment are obtained according to the six Kepler orbit numbers, wherein the six Kepler orbit numbers include the major semi-axis, eccentricity, inclination, right ascension of ascending node, argument of perigee, and perigee angle, and the orbital dynamics model includes the SGP4S orbit extrapolation model.

[0015] Preferably, obtaining the running posture includes:

[0016] The attitude quaternion of the satellite at the current moment is obtained, and the attitude quaternion is used to characterize the running attitude of the satellite, wherein the attitude quaternion q of the satellite is:

[0017]

[0018] Among them, q 1 ,q 2 ,q 3 is the vector component, q 0 is a scalar component, and q 1 2 +q 2 2 +q 3 2 +q 0 2 =1, α is the angle required for the orbital coordinate system to rotate around the spatial rotation axis e to coincide with the satellite body coordinate system, wherein the direction vector of the spatial rotation axis e in the orbital coordinate system is e=(C x ,C y ,Cz ), (C x ,C y ,C z ) represents direction cosines.

[0019] Preferably, the time parameter is expressed in Julian day, and the Julian day is calculated according to a fourth formula, and the fourth formula includes:

[0020]

[0021] Among them, JD represents Julian day, INT represents rounding, Year represents year in the Gregorian calendar, Month represents month, Day represents day, Hour represents hour, Minute represents minute, and Second represents second.

[0022] Preferably, obtaining the atomic oxygen density of the satellite at present according to the spatial position coordinates of the satellite at the current moment, the time parameter and the control parameter of the atomic oxygen environment model comprises:

[0023] Get the input parameters of the atmospheric model,

[0024] According to the input parameters of the atmospheric model, the spatial position coordinates of the satellite at the current moment and the time parameter, the output parameters of the atmospheric model are obtained,

[0025] Describe the atomic oxygen density of the satellite according to the output parameters of the atmospheric model.

[0026] The input parameters of the atmospheric model include: the number of days from January 1st of the current year to the current day, the number of seconds from 00:00:00 of the current day to the solution time, the geographic longitude, the geographic latitude, the altitude, the solar 10.7cm radiation flux of the previous day, the average solar 10.7cm radiation flux of 81 days, and the 8-bit array obtained according to the average geomagnetic index of the current day and the 20 3-hour average geomagnetic indices before the solution time.

[0027] The output parameters of the atmospheric model include: 2 , O 2 , He, Ar, N, H, O and ionospheric positive oxygen ions O + number density, neutral atmospheric temperature, and overall atmospheric density.

[0028] Preferably, obtaining the meridional wind speed and the zonal wind speed of the satellite at the current moment according to the spatial position coordinates of the satellite at the current moment, the time parameters and the control parameters of the horizontal wind environment model comprises:

[0029] Get the input parameters of the horizontal wind environment model,

[0030] According to the input parameters of the horizontal wind environment model, the spatial position coordinates of the satellite at the current moment and the time parameter, the output parameters of the horizontal wind environment model are obtained,

[0031] Describing the current meridional wind speed and zonal wind speed of the satellite according to the output parameters of the horizontal wind environment model,

[0032] The input parameters of the horizontal wind environment model include: the number of days from January 1st of the current year to the current day, the number of seconds from 00:00:00 of the current day to the solution time, the geographical longitude, the geographical latitude, the altitude, the solar 10.7cm radiation flux of the previous day, the average solar 10.7cm radiation flux of 81 days, and the 8-bit array obtained according to the average geomagnetic index of the current day and the 20 3-hour average geomagnetic indices before the solution time.

[0033] The output parameters of the horizontal wind environment model include the longitudinal wind speed and the latitudinal wind speed.

[0034] Preferably, the spatial position coordinates are the three-dimensional coordinates of the satellite in the geocentric J2000 coordinate system, and the geographic longitude and the geographic latitude are the longitude and latitude coordinates of the satellite in the WGS-84 coordinate system obtained based on the three-dimensional coordinates and coordinate system transformation.

[0035] The present invention also provides a space atomic oxygen environment characterization device, comprising:

[0036] The acquisition unit is used to obtain the satellite's current spatial position coordinates, time parameters, running speed, running attitude, control parameters of the atomic oxygen environment model and control parameters of the horizontal wind environment model.

[0037] The atomic oxygen environment generating unit of the satellite is used to obtain the atomic oxygen density of the satellite according to the spatial position coordinates of the satellite at the current moment, the time parameters and the control parameters of the atomic oxygen environment model,

[0038] The satellite wind speed environment generating unit is used to obtain the current longitudinal wind speed and latitudinal wind speed of the satellite according to the spatial position coordinates of the satellite at the current moment, the time parameters and the control parameters of the horizontal wind environment model,

[0039] A satellite structure model generating unit, used for obtaining a current structure model of the satellite according to the spatial position coordinates, the running speed and the running attitude of the satellite at a current moment;

[0040] The characterization processing unit characterizes the space atomic oxygen environment according to the atomic oxygen density, the meridional wind speed, the latitudinal wind speed, and the current structural model of the satellite.

[0041] The present invention also provides a computer device, comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the steps of the method are implemented when the processor executes the computer program.

[0042] The present invention also provides a computer-readable storage medium on which a computer program is stored. When the computer program is executed by a processor, the steps of the method described are implemented.

[0043] The beneficial effects of the space atomic oxygen environment characterization method of the present invention compared with the prior art are:

[0044] The present invention obtains the spatial position coordinates, running speed and running attitude of the satellite at each simulation moment, and obtains the atomic oxygen number density data, wind speed data and the spacecraft's own structure data of the environment where the spacecraft is located according to the running position, speed and attitude, combined with the atomic oxygen environment model and the horizontal wind environment model. The space atomic oxygen environment can be described according to the atomic oxygen number density data, wind speed data and spacecraft structure data. The present invention comprehensively considers the structure of the spacecraft itself and can more realistically characterize the atomic oxygen environment in real time. BRIEF DESCRIPTION OF THE DRAWINGS

[0045] Figure 1 This is an application environment diagram of the space atomic oxygen environment characterization method in an embodiment of the present invention;

[0046] Figure 2 This is a flow chart of a method for characterizing a space atomic oxygen environment in an embodiment of the present invention;

[0047] Figure 3 Schematic diagram of Euler angle posture change in an embodiment of the present invention;

[0048] Figure 4 Schematic diagram of quaternion posture change in an embodiment of the present invention;

[0049] Figure 5 Schematic diagram of the J2000 inertial coordinate system and the satellite body coordinate system in an embodiment of the present invention;

[0050] Figure 6 A schematic diagram of modeling a cube in three-dimensional feature modeling in an embodiment of the present invention;

[0051] Figure 7 A schematic diagram of modeling a cylinder in three-dimensional feature modeling in an embodiment of the present invention;

[0052] Figure 8 It is a schematic diagram of modeling a frustum in three-dimensional feature modeling in an embodiment of the present invention;

[0053] Fig. 9 A schematic diagram of modeling a sphere in three-dimensional feature modeling in an embodiment of the present invention;

[0054] Fig.10 It is a technical roadmap of the method for characterizing the space atomic oxygen environment in the embodiment of the present invention;

[0055] Fig.11 The three-dimensional space trajectory of the satellite in orbit in the embodiment of the present invention;

[0056] Fig.12 is a two-dimensional sub-satellite point trajectory of a satellite in an embodiment of the present invention;

[0057] Fig.13 The satellite attitude display in the embodiment of the present invention;

[0058] Fig.14 The satellite attitude quaternion change display in the embodiment of the present invention;

[0059] Fig.15 This is a graph showing the change in characterization data of atomic oxygen in a spacecraft in an embodiment of the present invention;

[0060] Fig.16 Schematic diagram of a space atomic oxygen environment characterization device in an embodiment of the present invention. DETAILED DESCRIPTION

[0061] 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.

[0062] Figure 1 This is an application environment diagram of the space atomic oxygen environment characterization method in an embodiment of the present invention. Figure 1 The space atomic oxygen environment characterization method is applied to a space atomic oxygen environment characterization system. The space atomic oxygen environment characterization system includes a terminal 110 and a server 120. The terminal 110 and the server 120 are connected via a network. The terminal 110 can be a desktop terminal or a mobile terminal, and the mobile terminal can be at least one of a mobile phone, a tablet computer, a laptop computer, etc. The server 120 can be implemented as an independent server or a server cluster consisting of multiple servers.

[0063] Computer simulation can be used to study the effects of atomic oxygen on spacecraft during its on-orbit operation, that is, the influence of the space atomic oxygen environment effect on satellites can be achieved through computer simulation modeling. This requires characterization of the complex space atomic oxygen environment data to which the spacecraft is subjected during its on-orbit operation. Since the structural shape of the spacecraft will have a certain influence on the space atomic oxygen environment effect, for example, for a spacecraft with a complex structure, its structure and its projection in each direction are different. Therefore, when characterizing its atomic oxygen environment, it is necessary to fully consider the effects of occlusion and reflection between structures caused by the complex structure of the spacecraft. Therefore, the present invention mainly solves the influence of the space atomic oxygen environment effect on the spacecraft during its on-orbit operation during the computer simulation process. In order to solve the atomic oxygen real-time characterization technology that can consider the complex spacecraft structure, the complex motion state data simulation problem of the spacecraft on-orbit operation must be provided, as well as the characterization problem of the space atomic oxygen environment data of the spacecraft that changes in real time with the real-time motion of the spacecraft during its on-orbit operation.

[0064] In order to solve the atomic oxygen effect problem considering the spacecraft structure shape, the atomic oxygen environment real-time characterization technology considering the spacecraft structure environment must first be carried out. The present invention mainly solves the problem of the spacecraft operating state, external environment and real-time conversion output required for the atomic oxygen effect calculation in the computer simulation process. Figure 2 As shown, a method for characterizing a space atomic oxygen environment according to an embodiment of the present invention includes:

[0065] Step 210, obtaining the satellite's current spatial position coordinates, time parameters, operating speed, operating attitude, control parameters of the atomic oxygen environment model, and control parameters of the horizontal wind environment model,

[0066] Step 221, obtaining the atomic oxygen density of the satellite at present according to the spatial position coordinates of the satellite at the current moment, the time parameter and the control parameter of the atomic oxygen environment model,

[0067] Step 222, obtaining the current longitudinal wind speed and latitudinal wind speed of the satellite according to the spatial position coordinates of the satellite at the current moment, the time parameters and the control parameters of the horizontal wind environment model,

[0068] Step 223, obtaining a current structural model of the satellite according to the spatial position coordinates, the running speed and the running attitude of the satellite at the current moment;

[0069] Step 230 , characterizing the space atomic oxygen environment according to the atomic oxygen density, the meridional wind speed, the latitudinal wind speed, and the current structural model of the satellite.

[0070] For spacecraft with complex structures, their structures and their projections in each direction are different. Therefore, when describing the atomic oxygen environment, it is necessary to fully consider the occlusion and reflection between structures caused by the complex structure of the spacecraft. Therefore, the on-orbit simulation problem of the atomic oxygen environment of a spacecraft with complex structure is a multi-factor coupling problem that considers the spacecraft's operating position, speed, direction, attitude, atomic oxygen density, wind speed, etc.

[0071] The embodiment of the present invention first obtains the spatial position coordinates, running speed and running attitude of the satellite at each simulation time from the start time of the simulation to the end time of the simulation, that is, the orbital flight altitude and the longitude and latitude of the sub-satellite point during the spacecraft mission, and the description of the on-orbit attitude during the spacecraft mission. Then, based on the running position, speed and attitude, combined with the atomic oxygen environment model and the horizontal wind environment model, the atomic oxygen number density data, wind speed data, and complex structure data of the spacecraft itself at the real-time on-orbit position during the spacecraft mission are obtained, and the structural data of the spacecraft is compared with the initial structural model data to obtain the structural deformation change of the spacecraft. According to the atomic oxygen number density data, wind speed data, and spacecraft structure data, the space atomic oxygen environment can be described, the space atomic oxygen environment can be understood, and the real-time characterization of the atomic oxygen environment can be achieved. The above description takes into account the structural shape of the complex spacecraft when performing real-time characterization and description of the space atomic oxygen environment, thereby improving the accuracy of the simulation output results of the space atomic oxygen environment during the on-orbit operation of the spacecraft.

[0072] Therefore, the embodiment of the present invention obtains the spatial position coordinates, running speed and running attitude of the satellite at the current moment, and obtains the atomic oxygen number density data, wind speed data and the spacecraft's own structural data of the environment in which the spacecraft is located based on the running position, speed and attitude and in combination with the atomic oxygen environment model and the horizontal wind environment model. These data are used to characterize the spatial atomic oxygen environment and wind speed environment in which the satellite is located, and the structural characteristics of the spacecraft itself are taken into consideration, so that the atomic oxygen environment can be more realistically characterized in real time.

[0073] In order to calculate the quantitative characterization data of the space atomic oxygen environment made by the spacecraft during its on-orbit operation, it is necessary to provide the real-time operating space position of the spacecraft. The present invention realizes the simulation calculation of the quantitative characterization data of the real-time motion state of the spacecraft through the following method.

[0074] In some implementations, it is necessary to establish a continuous time representation model. The embodiment of the present invention considers the calculation of the satellite's space motion state, uses the Julian day model to express time, and converts the Gregorian year, month, day, hour, minute, and second into continuously changing real numbers. The Gregorian year, month, day, hour, minute, and second are used as engineering applications to define UTC time for use by users such as engineering designers. For internal simulation calculations, the Julian day is used to convert time into a continuous linear real number through the Julian day, which is convenient for calculation and simulation solutions.

[0075] Among them, UTC time is Coordinated Universal Time, also known as the world's same time, based on the length of the atomic second. Julian day is the number of days starting at 12h on January 1, 4573 BC. By converting the Gregorian calendar year, month, and day into Julian day, the description of the difference between two Gregorian calendar moments can be obtained under a unified specification, which is convenient for setting the simulation step size.

[0076] The method of calculating the Julian day from the Gregorian calendar is to use the fourth formula to calculate the Julian day. The fourth formula is:

[0077]

[0078] In the fourth formula, JD represents Julian day, INT() represents rounding, Year represents year in the Gregorian calendar, Month represents month, Day represents day, Hour represents hour, Minute represents minute, and Second represents second.

[0079] In some implementations, a unified coordinate system is required to be established in the simulation data for calculating the space motion state of the aircraft. The geocentric inertial coordinate system is used as a reference in the present invention. The geocentric inertial coordinate system in the present invention uses the celestial equator and the equinox at J2000 (12:00 on January 1, 2000) to define the celestial reference coordinate system. Figure 5 As shown, 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, X-axis and Z-axis form a right-handed rectangular coordinate system, which is an inertial coordinate system.

[0080] In some of the implementation methods, obtaining the spatial position coordinates and running speed of the satellite at the current moment includes: obtaining the six Kepler orbit numbers of the satellite at the current moment, and obtaining the spatial position coordinates and running speed of the satellite at each moment based on the six Kepler orbit numbers.

[0081] Among them, the orbit is described by Kepler's six numbers. The six numbers of Kepler's orbit are physical quantities used to describe the size, shape, and spatial position of the orbit. They are composed of six elements, namely: 1) semi-major axis, represented by a, used to describe the size of the orbit; 2) eccentricity, represented by e, used to describe the shape of the orbit; 3) inclination, represented by i, used to describe the inclination angle of the orbital plane relative to the equatorial plane; 4) right ascension of the ascending node, represented by Ω, used to describe the position of the ascending node relative to the vernal equinox; 5) argument of perigee, represented by ω, used to describe the position of the perigee relative to the ascending node; 6) true anomaly, represented by f, used to describe the position of the satellite relative to the perigee.

[0082] The obtaining of the spatial position coordinates and running speed of the satellite at each moment according to the six Kepler orbit numbers includes:

[0083] Obtain a satellite orbital dynamics model, calculate the position and velocity of the satellite according to the six Kepler orbital numbers and the satellite orbital dynamics model, preferably use the SGP4 orbital extrapolation model to perform orbital dynamics extrapolation calculations, and calculate the motion position coordinates and motion velocity of the spacecraft mass center in the J2000 geocentric inertial coordinate system in real time. The real-time changes in the spacecraft motion state obtained by the SGP4 orbital model calculation and the corresponding three-dimensional coordinates of the spatial position not only describe the on-orbit operation state of the spacecraft, but can also be used in the calculation of the atomic oxygen environment model of the spacecraft.

[0084] In some of the implementation methods, because the embodiments of the present invention take into account the complex structure and shape of the spacecraft, different flight attitudes will cause different changes in the direction of the aircraft surface, causing different windward surfaces to be corroded by atomic oxygen. Therefore, in order to analyze the impact of atomic oxygen, it is necessary to first obtain the change data of the aircraft attitude. In order to achieve real-time characterization of atomic oxygen taking into account the complex structure of the spacecraft, the present invention outputs the motion state and environment of the satellite at every moment in real time to meet the calculation requirements of the atomic oxygen effect of the aircraft. It is also necessary to analyze and simulate the in-orbit attitude of the spacecraft. In this embodiment, the satellite attitude is defined as the relative position rotation relationship of the satellite body coordinate system relative to the J2000 inertial coordinate system, and is expressed using the inertial system quaternion. First, define the satellite body coordinate system. The satellite body coordinate system is defined as follows: See Figure 5 As shown in the figure, the origin of the coordinates is located at the satellite's mass center, and the Xs axis, Ys axis, and Zs axis are the three principal inertia axes of the satellite body. In the absence of attitude deviation, the three coordinate axes (Xs axis, Ys axis, and Zs axis) of the satellite body coordinate system coincide with the satellite orbit coordinate system. At this time, the satellite's Zs axis points to the center of the earth, the Xs axis direction coincides with the satellite's motion direction, and the Ys axis points to the negative normal direction of the satellite's orbital plane, forming a right-handed rectangular coordinate system with the Xs axis and the Zs axis. Among them, α represents the orbital inclination, β represents the longitude of the ascending node, and δ represents the pericentric angular distance.

[0085] The satellite orbit attitude definition in the embodiment of the present invention uses the quaternion method. The embodiment of the present invention can customize the attitude reference coordinate system and attitude description coordinate system of the aircraft, can use the commonly used four-element method, Euler angle method and YPR description method to describe the attitude, can input the attitude of various aircraft in the form of files, and can perform attitude parameter conversion and attitude parameter prediction based on multiple rotation sequences and multiple attitude working modes.

[0086] Euler angles refer to the fact that any two coordinate systems in space can be rotated several times to make the three coordinate axes of the two coordinate systems coincide with each other. During the rotation process, the angle of each rotation is called the Euler angle. In the attitude description of an on-orbit spacecraft, any attitude transformation can be achieved by rotating the corresponding Euler angles around the three coordinate axes in sequence. The description of the aircraft attitude in the aviation field is referred to to make the satellite Euler angle transformation have a specific physical meaning, that is, the yaw angle Yaw is represented by the symbol φ, the pitch angle Pitch is represented by the symbol θ, and the roll angle Roll is represented by the symbol Indicates, see Figure 3 shown.

[0087] In the description of satellite attitude, the reference coordinate system is assumed to be the orbital coordinate system O O X O Y O Z O , satellite body coordinate system O b X b Y b Z b In attitude transformation, the orbital coordinate system is rotated to obtain the satellite body coordinate system, which is usually rotated in the order of ZXY. To define the satellite's Euler angle. φ is the yaw angle, and X is the satellite's rolling axis. b The projection of the satellite velocity on the local horizontal plane is the same as the orbit X O The angle of the axis, is the roll angle, is the satellite pitch axis Y b The angle between the projection of the satellite on the local horizontal plane and the elevation angle is θ, which is the satellite rolling axis X. b The angle between it and its projection on the local horizontal plane. From this, we can get the attitude transformation matrix as shown in the first formula, which is:

[0088]

[0089] In the first formula, for simplicity of representation, c represents cosine and s represents sin.

[0090] Although the Euler angle representation of attitude is simple, direct and easy to observe, it has a singularity problem, that is, there is a certain attitude that can be represented by two sets of Euler angle values, which loses uniqueness. To solve this problem, quaternions are introduced to describe the attitude problem. In some embodiments of the present invention, the quaternion attitude description method is used to calculate the output of the attitude change of the spacecraft in space.

[0091] The quaternion q consists of two parts: a scalar and a vector. The form is shown in the second formula. The second formula is:

[0092] q=q 0 +q 1 i+q2 j+q 3 k=[q s ,q v ];

[0093] In the second formula, q s Represents the scalar part, the unit is 1; q v Represents the vector part, i, j, k are the imaginary units, and i, j, k are unit vectors that are orthogonal to each other.

[0094] The geometric description of quaternion is defined as O 0 X 0 Y 0 Z 0 , the direction vector of the rotation axis e in the orbital coordinate system is e=(C x ,C y ,C z ), where (C x ,C y ,C z ) represents the direction cosine, and the orbital coordinate system rotates around the rotation axis e by an angle α to obtain the satellite body coordinate system O b X b Y b Z b , see Figure 4 As shown, the satellite attitude quaternion is as shown in the third formula, which is:

[0095]

[0096] In the third formula, q 1 ,q 2 ,q 3 is the vector component, q 0 is a scalar component, and q 1 2 +q 2 2 +q 3 2 +q 0 2 =1.

[0097] In some of the embodiments, the atomic oxygen environment in space during the spacecraft's on-orbit operation is analyzed. For geosynchronous orbit and medium Earth orbit, the density of the neutral atmosphere is low and becomes unimportant. The Earth's atmosphere is divided into several characteristic regions according to temperature or composition profiles. The thermosphere, which is approximately from 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 exosphere.

[0098] The concentration of the thermosphere decreases roughly exponentially with altitude, which is the result of hydrostatic equilibrium. The main components of the thermosphere include Ar, O 2 、N 2 , 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 O 2 、N 2 and H, and possibly <1% He, NO, N and Ar. The temperature of the thermosphere is related to 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 a neutral atmosphere head-on impact with a spacecraft reach about 5eV (from 4.6eV when N hits to 5eV when O hits). 2 10.25eV at impact). This will cause chemical reactions between the neutral atmosphere and the spacecraft materials (such as atomic oxygen stripping, 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.

[0099] Many factors affect the basic parameters of the neutral atmosphere (density, temperature, and composition), including local time, latitude, altitude, solar activity, and geomagnetic activity. 10.7 The index characterizes the changes in solar extreme ultraviolet radiation (EUV), and reflects the influence of the sun on geomagnetic activity to a certain extent through the number of sunspots. Solar extreme ultraviolet radiation and geomagnetic fluctuations are the main sources of heating in the upper atmosphere. The density and temperature of the neutral atmosphere usually vary with F. 10.7 The index increases with the increase of the geomagnetic index Ap. For example, at an altitude of 400 km, the neutral atmosphere is higher in the solar high year (F 10.7 ≈230) is comparable to the average density of the Sun (F 10.7≈70). Correspondingly, in a high solar year, the temperature of the outer atmosphere can be raised from about 700K to about 1200K due to the heating of the 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 (such as 500km), the highest average density of the atmosphere reaches its highest in October to November and is lowest in April. At the same altitude, the daily average temperature is highest at 14:00 when approaching the local time.

[0100] To sum up, in order to realize the real-time characterization technology of atomic oxygen that can take into account the structural morphology of the spacecraft, it is necessary to calculate the real-time changing atomic oxygen environment of the spacecraft according to the different real-time positions of the spacecraft in orbit.

[0101] The obtaining of the atomic oxygen density of the satellite at present according to the spatial position coordinates of the satellite at the current moment, the time parameter and the control parameter of the atomic oxygen environment model comprises:

[0102] Get the input parameters of the atmospheric model,

[0103] According to the input parameters of the atmospheric model, the spatial position coordinates of the satellite at the current moment and the time parameter, the output parameters of the atmospheric model are obtained,

[0104] The atomic oxygen density at which the satellite is currently located is described according to the output parameters of the atmospheric model.

[0105] In the embodiment of the present invention, it is necessary to use the simulation calculation model of the composition of the upper atmosphere of the earth, and the present embodiment uses the MSIS reference atmosphere model. The MSIS reference atmosphere model is a semi-empirical model established based on the detection data of mass spectrometers and ground-based incoherent scattering radars on multiple satellites. Among them, MSIS is the abbreviation of Mass-Spectrometer-Incoherent-Scatter. The first few versions of this series of models focus on the upper atmosphere. Among them, the MSIS-86 version has been adopted by the Space Research Committee (COSPAR) as the International Reference Atmosphere Model (CIRA), i.e., the CIRA-1986 model. Later, the MSIS model was extended to the middle and lower atmospheres to form the MSISE-90 version, which can give the number density distribution of atmospheric temperature, density and main atmospheric components from the ground to the height of the outer atmosphere. Above 72.5km, MSISE-90 is basically similar to the MSIS-86 version, except that the former is appropriately corrected based on the flight data of the space shuttle and the detection results of the ground-based incoherent scattering radar. The MSIS reference atmosphere model better considers the influence of solar extreme ultraviolet radiation and geomagnetic disturbances on the thermosphere. Solar activity has a significant impact on the composition distribution of the thermosphere. In years with low solar activity, the diffusion separation speed is accelerated, the heavy components increase with decreasing altitude, 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 the temperature and density of the thermosphere. During magnetic storms, the injection of falling particles causes the atmosphere to heat up and the density of the thermosphere to increase significantly.

[0106] The atmospheric model used in this embodiment can be the NRLMSISE-00 atmospheric model, or other types of atmospheric models that can achieve the same or similar purposes, which will not be described in detail here. Among them, the NRLMSISE-00 atmospheric model is based on the existing MSIS reference atmospheric 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 the NRL Mass Spectrometer-Incoherent-ScatterRadar 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.

[0107] In the embodiment of the present invention, the NRLMSISE00 model needs to be controlled by time, space three-dimensional coordinates and model control parameters F107, F107A, AP value. The output parameters of the NRLMSISE-00 atmospheric model include N 2 , O 2 , He, Ar, N, H, O and ionospheric positive oxygen ions O +The number density, neutral atmospheric temperature and overall atmospheric density, that is, the atmospheric mass density, the fractional density of each atmospheric component and the atmospheric temperature and other quantitative characterization data of the spatial atmospheric environment. The atmospheric components specifically include the number density of helium atoms (per cubic centimeter), the number density of oxygen atoms (per cubic centimeter), the number density of nitrogen molecules (per cubic centimeter), the number density of oxygen molecules (per cubic centimeter), the number density of argon atoms (per cubic centimeter), the number density of hydrogen atoms (per cubic centimeter), the number density of nitrogen atoms (per cubic centimeter), and the number density of atomic oxygen (per cubic centimeter). The atmospheric temperature includes the temperature of the exosphere and the temperature of the atmosphere.

[0108] The NRLMSISE-00 atmospheric model has a total of 8 input parameters, including: the number of days from January 1st of the current year to the current day, the number of seconds from 00:00:00 of the current day to the solution time, the geographic longitude, latitude, altitude, the solar radiation flux of 10.7 cm on the previous day (F 10.7 ), 81 days (3 solar rotation cycles, with the day as the midpoint) average F 10.7 , based on the average geomagnetic index of the day (A p ) and the 20 3-hour average A before the solution time p The calculated 8-bit array.

[0109] In addition to being related to the wind speed in the upper atmosphere where the spacecraft is located, the atomic oxygen environment of the satellite needs to take into account the wind speed and the satellite's movement speed, and then calculate the relative speed between the atomic oxygen and the spacecraft body to calculate the destructive effect of atomic oxygen on flight.

[0110] In some of the implementation modes, obtaining the current longitudinal wind speed and latitudinal wind speed of the satellite according to the spatial position coordinates of the satellite at the current moment, the time parameters and the control parameters of the horizontal wind environment model includes:

[0111] Get the input parameters of the horizontal wind environment model,

[0112] According to the input parameters of the horizontal wind environment model, the spatial position coordinates of the satellite at the current moment and the time parameter, the output parameters of the horizontal wind environment model are obtained,

[0113] The output parameters of the horizontal wind environment model describe the meridional wind speed and the zonal wind speed at which the satellite is currently located.

[0114] In the embodiment of the present invention, the horizontal wind environment model may be a HWM-93 model, or other types of models that can achieve the same or similar purpose, which will not be described in detail herein.

[0115] The present invention has relevant understanding of the wind pattern of the earth's atmosphere in the upper atmosphere where the satellite is located, mainly based on the test data of satellites such as AE-E and DE-2. At a lower altitude, ground-based incoherent scattering radar data and atmospheric observation data are mainly used. The existing wind model is mainly limited to predicting the longitudinal component Vx (positive to the north) and the latitudinal component Vy (positive to the east) of horizontal motion. The average wind speed Vz in the vertical direction is usually less than 1cm / s and can be ignored. Horizontal wind is the flow caused by the local pressure gradient in the upper atmosphere under the influence of compound centripetal acceleration.

[0116] The HWM model (Horizontal Wind Model) is a commonly used upper atmosphere horizontal wind model. It is an empirical model based on satellite and ground detection data and expressed in the form of vector spherical harmonic polynomials. The first version was published in 1987 (HWM-87 model), which is applicable to altitudes above 220km. The current commonly used version is HWM-93, which can be extended to the ground.

[0117] The input items of the HWM-93 model are: the number of days from January 1st of the current year to the current day, the number of seconds from 00:00:00 of the current day to the solution time, the geographical longitude, latitude, altitude, the solar radiation flux of 10.7 cm on the previous day (F 10.7 ), 81 days (3 solar rotation cycles, with the day as the midpoint) average F 10.7 , based on the average geomagnetic index of the day (A p ) and the 20 3-hour average A before the solution time p The calculated 8-bit array.

[0118] The output items of the HWM-93 model include meridional wind speed and zonal wind speed.

[0119] Among them, the input parameters of geographic longitude and geographic latitude in the NRLMSISE-00 atmospheric model and the HWM-93 model are the longitude and latitude coordinates of the satellite in the WGS-84 coordinate system obtained according to the three-dimensional coordinates and coordinate system transformation.

[0120] In an embodiment of the present invention, before obtaining the spatial position coordinates, time parameters, operating speed, operating attitude, control parameters of the atomic oxygen environment model and control parameters of the horizontal wind environment model of the satellite at the current moment, the method also includes: modeling, including the construction of an initial structural model of the satellite, and also including the construction of an atomic oxygen environment model and a horizontal wind environment model.

[0121] In order to digitally represent and record the morphological features of complex structure spacecraft in the form of points, lines and surfaces in a computer file. In this embodiment, the initial structural model of the satellite can be obtained according to the input three-dimensional feature parameters. Among them, three-dimensional feature modeling is three-dimensional modeling according to the form of input three-dimensional feature parameters, which can quickly realize the creation of simple three-dimensional models. The three-dimensional feature modeling currently realized by the software mainly includes: cube, cylinder, truncated cone, sphere, and points, straight lines and planes in space.

[0122] In one embodiment of the present invention, the following functions can be achieved:

[0123] Create point: Receive the parameters for creating a point through the "Create point" button on the toolbar. The parameters for creating a point can be 3D coordinates, offsets, etc. You can create a point by specifying 3D coordinates, or you can create a point by offsetting the original position by a corresponding distance through an offset.

[0124] Editable points: You can edit points by modifying the parameters of the created points.

[0125] Create a line: Receive the parameters for creating a line through the "Create Line" button on the toolbar. The parameters for creating a line include at least two 3D coordinates. A line can be created through two specified 3D coordinates; or, the parameters for creating a line include 3D coordinates, length, and direction parameters. A line is created by extending a specified length in a specified direction based on the specified 3D coordinates.

[0126] Editable Line: You can edit a straight line by modifying the parameters of the created line.

[0127] Create plane: Receive the parameters for creating a plane through the "Create plane" button on the toolbar. The parameters for creating a plane are existing straight lines. A plane can be created by specifying a closed wireframe composed of straight lines.

[0128] Create a cube: Receive the parameters for creating a cube through the "Create Cube" button on the toolbar. The parameters for creating a cube can be the base point coordinates and length, width and height parameters. The base point can be selected at the minimum value of the XYZ coordinates of the cube to be created or the coordinates of the existing points on the graph. The length, width and height parameters correspond to the offset of XYZ respectively. The cube is created by offsetting the corresponding distance in the three directions of XYZ based on the base point coordinates through the length, width and height parameters.

[0129] Editable cube: Figure 6 As shown, the cube can be edited by modifying the parameters of the created cube.

[0130] Create a cylinder: Receive the parameters for creating a cylinder through the "Create Cylinder" button on the toolbar. The parameters for creating a cylinder can be the coordinates of the center position of the cylinder bottom surface, the geometric dimensions of the cylinder, and the axis direction. The cylinder is created by extending the specified geometric dimensions in the axis direction based on the coordinates of the center position of the cylinder bottom surface.

[0131] Editable Cylinder: Figure 7 As shown, you can edit the cylinder by modifying the parameters of the created cylinder.

[0132] Create a frustum or cone: Receive the parameters for creating a frustum through "Create Frustum" on the toolbar. The parameters for creating a frustum are similar to those for a cylinder, including the coordinates of the center of the bottom surface of the frustum, the geometric parameters of the frustum, and the direction of the axis. "Radius 1" refers to the bottom radius, that is, the radius of the plane where the center of the bottom surface of the frustum is located, and "Radius 2" is the top radius. The two radii are different. When one of the radii is 0, a cone can be created.

[0133] Editable frustum: Figure 8 As shown in the figure, the frustum can be edited by modifying the parameters of the created frustum.

[0134] Create a sphere: Receive the parameters for creating a sphere through the "Create Sphere" button on the toolbar. The parameters for creating a sphere include the center position coordinates and radius. The creation method is the same as other bodies. The center position coordinates can be the received input coordinates or the received coordinates of an existing point.

[0135] Editable sphere: Fig. 9 As shown, you can edit the sphere by modifying the parameters on the created sphere.

[0136] In an embodiment of the present invention, the initial structural model of the satellite needs to be initialized during operation, that is, the initial simulation start time and the simulation end time are obtained, and it also includes initializing the six satellite orbit initialization numbers required for real-time characterization, initializing the attitude quaternion, initializing the atomic oxygen model control parameters, and initializing the lateral wind model control parameters to obtain the satellite's initial attitude, initial orbit, initial atomic oxygen environment model parameters, initial horizontal wind environment model parameters, and initial structural model.

[0137] like Fig.10As shown, after initializing various parameters, the embodiment of the present invention starts calculation from the start time of the simulation, and then calculates the position, velocity, and attitude of the satellite at the next moment according to the simulation step size. The satellite position and velocity are calculated according to the satellite orbital dynamics model to obtain the inertial system position and velocity, and the attitude is calculated according to the satellite attitude dynamics model to obtain the inertial system quaternion output. The satellite atomic oxygen environment, combined with the satellite's current position and time and the model control parameters, is used to calculate the satellite atomic oxygen density to obtain the atomic oxygen density of the satellite. The wind speed environment at the satellite, combined with the satellite's current position and time and the model control parameters, is used to calculate the satellite wind speed to obtain the longitudinal wind speed and latitudinal wind speed of the satellite. The satellite structure obtains changes in the satellite structure based on the satellite's position, velocity, and attitude and the tasks to be performed.

[0138] In the embodiment of the present invention, the initialization spacecraft attitude and orbit parameters are selected. The six numbers of the initial orbit of the spacecraft are: the major axis is 42166.3km, the eccentricity is 0 degrees, the inclination is 0 degrees, the right ascension of the ascending node is 0 degrees, the argument of perigee is 0 degrees, and the perigee angle is 0 degrees, that is, the initial orbit parameters after initialization. The mission start time is 12:0:00 on January 1, 2017, that is, the simulation start time after initialization. The initial attitude orbit quaternion of the spacecraft is described as (1,0,0,0), that is, the initial attitude parameters after initialization.

[0139] The initial posture parameters may be empirical values, or may be calculated based on other parameters, or may be detected values, or may be a mixture of empirical values, calculated values ​​or detected values, which will not be elaborated here.

[0140] Satellite in-orbit status Fig.11 As shown, Fig.11 The three-dimensional space trajectory of the satellite is displayed. Using the coordinate system transformation method, the satellite position in the inertial system is transformed into the longitude and latitude coordinates under WGS-84 to obtain the two-dimensional coordinates of the spacecraft. The sub-satellite point trajectory of the spacecraft can be obtained by connecting the two-dimensional coordinates of the spacecraft in chronological order. Fig.12 is the two-dimensional sub-satellite point trajectory of the satellite. Fig.13 The satellite attitude display. The satellite attitude quaternion changes as follows Fig.14 Display. Since quaternions are dimensionless numbers, they have no units but only numerical values. Fig.14 Quaternion 1 represents the scalar component value in the quaternion, and quaternion 2, quaternion 3, and quaternion 4 correspond to the x, y, and z values ​​of the vector components in the quaternion, respectively.

[0141] The atomic oxygen environment of the satellite is obtained according to the space atmosphere model NRLMSISE-00, and the model control parameters are set to F107 as 150, F107A as 150, and Ap as 4, that is, the control parameters of the initialized atomic oxygen environment model, and the atomic oxygen number density at the real-time position of the aircraft.

[0142] The wind speed environment of the satellite is obtained according to the spatial lateral wind model HWM93, and the model control parameters are set to F107 as 150, F107A as 150, and Ap as 4, that is, the control parameters of the initialized horizontal wind environment model, the longitudinal wind speed and latitudinal wind speed of the real-time position of the aircraft.

[0143] Real-time characterization data of spacecraft atomic oxygen such as Fig.15 As shown, it includes satellite longitude, latitude, altitude, atomic oxygen density, abnormal oxygen density, total atomic oxygen density, meridional wind speed, latitudinal wind speed, and real-time change characterization output.

[0144] Corresponding to the above-mentioned space atomic oxygen environment characterization method, the embodiment of the present invention also provides a space atomic oxygen environment characterization device, such as Fig.16 As shown, the device comprises:

[0145] The acquisition unit 1100 is used to acquire the spatial position coordinates, time parameters, running speed, running attitude, control parameters of the atomic oxygen environment model and control parameters of the horizontal wind environment model of the satellite at the current moment.

[0146] The satellite atomic oxygen environment generating unit 1200 is used to obtain the atomic oxygen density of the satellite at present according to the spatial position coordinates of the satellite at the current moment, the time parameters and the control parameters of the atomic oxygen environment model,

[0147] The satellite wind speed environment generating unit 1300 is used to obtain the current longitudinal wind speed and latitudinal wind speed of the satellite according to the spatial position coordinates of the satellite at the current moment, the time parameters and the control parameters of the horizontal wind environment model,

[0148] The satellite structure model generating unit 1400 is used to obtain the current structure model of the satellite according to the spatial position coordinates, the running speed and the running attitude of the satellite at the current moment;

[0149] The characterization processing unit 1500 is used to characterize the space atomic oxygen environment according to the atomic oxygen density, the meridional wind speed, the latitudinal wind speed, and the current structural model of the satellite.

[0150] In a specific embodiment of the present invention, the acquisition unit is further used to acquire six Kepler orbit numbers of the satellite at the current moment, the six Kepler orbit numbers including the semi-major axis, eccentricity, inclination, right ascension of ascending node, argument of perigee, and perigee angle, and the orbital dynamics model includes the SGP4S orbit extrapolation model;

[0151] The device also includes a position and speed generating unit, which is used to obtain the spatial position coordinates and the running speed of the satellite at the current moment according to the six elements of the Kepler orbit, wherein the spatial position coordinates are the three-dimensional coordinates of the satellite in the geocentric J2000 coordinate system.

[0152] In a specific embodiment of the present invention, the acquisition unit is used to obtain the attitude quaternion of the satellite at the current moment, and the attitude quaternion q of the satellite is:

[0153]

[0154] Among them, q 1 ,q 2 ,q 3 is the vector component, q 0 is a scalar component, and q 1 2 +q 2 2 +q 3 2 +q 0 2 =1, α is the angle required for the orbital coordinate system to rotate around the spatial rotation axis e to coincide with the satellite body coordinate system, wherein the direction vector of the spatial rotation axis e in the orbital coordinate system is e=(C x ,C y ,C z ), (C x ,C y ,C z ) represents direction cosines.

[0155] In a specific embodiment of the present invention, the time parameter obtained by the acquisition unit is expressed in Julian day, and the Julian day is calculated according to a fourth formula, and the fourth formula includes:

[0156]

[0157] Among them, JD represents Julian day, INT represents rounding, Year represents year in the Gregorian calendar, Month represents month, Day represents day, Hour represents hour, Minute represents minute, and Second represents second.

[0158] In a specific embodiment of the present invention, the acquisition unit is further used to acquire input parameters of the atmospheric model;

[0159] The satellite atomic oxygen environment generating unit 1200 is used to obtain the output parameters of the atmospheric model according to the input parameters of the atmospheric model, the spatial position coordinates of the satellite at the current moment and the time parameters.

[0160] The atomic oxygen density at which the satellite is currently located is described according to the output parameters of the atmospheric model.

[0161] The input parameters of the atmospheric model include: the number of days from January 1st of the current year to the current day, the number of seconds from 00:00:00 of the current day to the solution time, the geographic longitude, the geographic latitude, the altitude, the solar 10.7cm radiation flux of the previous day, the average solar 10.7cm radiation flux of 81 days, and the 8-bit array obtained according to the average geomagnetic index of the current day and the 20 3-hour average geomagnetic indices before the solution time.

[0162] The output parameters of the atmospheric model include: 2 , O 2 , He, Ar, N, H, O and ionospheric positive oxygen ions O + number density, neutral atmospheric temperature, and overall atmospheric density.

[0163] The acquisition unit is also used to acquire input parameters of the horizontal wind environment model;

[0164] The satellite wind speed environment generating unit 1300 is used to obtain the output parameters of the horizontal wind environment model according to the input parameters of the horizontal wind environment model, the spatial position coordinates of the satellite at the current moment and the time parameter.

[0165] The output parameters of the horizontal wind environment model describe the meridional wind speed and the zonal wind speed at which the satellite is currently located.

[0166] The input parameters of the horizontal wind environment model include: the number of days from January 1st of the current year to the current day, the number of seconds from 00:00:00 of the current day to the solution time, the geographical longitude, the geographical latitude, the altitude, the solar 10.7cm radiation flux of the previous day, the average solar 10.7cm radiation flux of 81 days, and the 8-bit array obtained according to the average geomagnetic index of the current day and the 20 3-hour average geomagnetic indices before the solution time.

[0167] The output parameters of the horizontal wind environment model include the longitudinal wind speed and the latitudinal wind speed.

[0168] The geographic longitude and the geographic latitude are the longitude and latitude coordinates of the satellite in the WGS-84 coordinate system obtained according to the three-dimensional coordinates and coordinate system transformation.

[0169] In one embodiment, a computer device is provided, comprising a memory, a processor, and a computer program stored in the memory and executable on the processor. When the processor executes the computer program, the following steps are implemented: obtaining the spatial position coordinates, time parameters, running speed, running attitude, control parameters of an atomic oxygen environment model, and control parameters of a horizontal wind environment model of a satellite at a current moment; obtaining the atomic oxygen density of the satellite at a current moment according to the spatial position coordinates, time parameters, and control parameters of the atomic oxygen environment model of the satellite at a current moment; obtaining the meridional wind speed and latitudinal wind speed of the satellite at a current moment according to the spatial position coordinates, time parameters, and control parameters of the horizontal wind environment model of the satellite at a current moment; obtaining the current structural model of the satellite according to the spatial position coordinates, running speed, and running attitude of the satellite at a current moment; and characterizing the spatial atomic oxygen environment according to the atomic oxygen density, the meridional wind speed, the latitudinal wind speed, and the current structural model of the satellite.

[0170] In one embodiment, when the processor executes the computer program, the steps of the above-mentioned spatial atomic oxygen environment characterization method are also implemented.

[0171] In one embodiment, a computer-readable storage medium is provided, on which a computer program is stored. When the computer program is executed by a processor, the following steps are implemented: obtaining the spatial position coordinates, time parameters, running speed, running attitude, control parameters of the atomic oxygen environment model and control parameters of the horizontal wind environment model of the satellite at the current moment; obtaining the atomic oxygen density of the satellite at the current moment according to the spatial position coordinates, time parameters and control parameters of the atomic oxygen environment model of the satellite at the current moment; obtaining the meridional wind speed and latitudinal wind speed of the satellite at the current moment according to the spatial position coordinates, time parameters and control parameters of the horizontal wind environment model of the satellite at the current moment; obtaining the current structural model of the satellite according to the spatial position coordinates, running speed and running attitude of the satellite at the current moment; and characterizing the space atomic oxygen environment according to the atomic oxygen density, the meridional wind speed and the latitudinal wind speed and the current structural model of the satellite.

[0172] In one embodiment, when the computer program is executed by a processor, the steps of the above-mentioned spatial atomic oxygen environment characterization method are also implemented.

[0173] Those skilled in the art can understand that all or part of the processes in the above-mentioned embodiments can be completed by instructing the relevant hardware through a computer program, and the program can be stored in a non-volatile computer-readable storage medium. When the program is executed, it can include the processes of the embodiments of the above-mentioned methods. Among them, any reference to memory, storage, database or other media used in the embodiments provided by the present invention can include non-volatile and / or volatile memory. Non-volatile memory can include read-only memory (ROM), programmable ROM (PROM), electrically programmable ROM (EPROM), electrically erasable programmable ROM (EEPROM) or flash memory. Volatile memory can include random access memory (RAM) or external cache memory. As an illustration and not limitation, RAM is available in many forms, such as static RAM (SRAM), dynamic RAM (DRAM), synchronous DRAM (SDRAM), double data rate SDRAM (DDRSDRAM), enhanced SDRAM (ESDRAM), synchronous link (Synchlink) DRAM (SLDRAM), memory bus (Rambus) direct RAM (RDRAM), direct memory bus dynamic RAM (DRDRAM), and memory bus dynamic RAM (RDRAM).

[0174] Although the disclosure is disclosed as above, the protection scope of the disclosure is not limited thereto. Those skilled in the art may make various changes and modifications without departing from the spirit and scope of the disclosure, and these changes and modifications will fall within the protection scope of the present invention.

Claims

1. A method for characterizing a space atomic oxygen environment, characterized in that: include: Obtain the satellite's current spatial position coordinates, time parameters, operating speed, operating attitude, control parameters of the atomic oxygen environment model, and control parameters of the horizontal wind environment model; Obtaining the atomic oxygen density at which the satellite is currently located according to the spatial position coordinates of the satellite at a current moment, the time parameters, and the control parameters of the atomic oxygen environment model; Obtaining the meridional wind speed and the zonal wind speed of the satellite at present according to the spatial position coordinates of the satellite at present time, the time parameters and the control parameters of the horizontal wind environment model; Obtaining a current structural model of the satellite according to the spatial position coordinates, the running speed and the running attitude of the satellite at a current moment; The space atomic oxygen environment is characterized according to the atomic oxygen density, the meridional wind speed, the latitudinal wind speed, and the current structural model of the satellite.

2. The method for characterizing a space atomic oxygen environment according to claim 1, characterized in that: The obtaining of the spatial position coordinates and the running speed includes: Get the six Kepler orbit numbers of the satellite at the current moment; The spatial position coordinates and the running speed of the satellite at the current moment are obtained according to the six Kepler orbit numbers, wherein the six Kepler orbit numbers include the major semi-axis, eccentricity, inclination, right ascension of ascending node, argument of perigee, and perigee angle, and the orbital dynamics model includes the SGP4S orbit extrapolation model.

3. The method for characterizing a space atomic oxygen environment according to claim 1, characterized in that: The obtaining of the running posture comprises: The attitude quaternion of the satellite at the current moment is obtained, and the attitude quaternion is used to characterize the running attitude of the satellite, wherein the attitude quaternion q of the satellite is: Among them, q1, q2, q3 are vector components, q0 is a scalar component, and q1 2 +q2 2 +q3 2 +q0 2 =1, α is the angle required for the orbital coordinate system to rotate around the spatial rotation axis e to coincide with the satellite body coordinate system, wherein the direction vector of the spatial rotation axis e in the orbital coordinate system is e=(C x , C y , C z ), (C x , C y , C z ) represents direction cosines.

4. The method for characterizing a space atomic oxygen environment according to claim 1, characterized in that: The time parameter is expressed in Julian days, and the Julian days are calculated according to a fourth formula, wherein the fourth formula includes: Among them, JD represents Julian day, INT represents rounding, Year represents year in the Gregorian calendar, Month represents month, Day represents day, Hour represents hour, Minute represents minute, and Second represents second.

5. The method for characterizing a space atomic oxygen environment according to claim 1, characterized in that: The obtaining of the atomic oxygen density of the satellite at present according to the spatial position coordinates of the satellite at the current moment, the time parameter and the control parameter of the atomic oxygen environment model comprises: Get the input parameters of the atmospheric model, According to the input parameters of the atmospheric model, the spatial position coordinates of the satellite at the current moment and the time parameter, the output parameters of the atmospheric model are obtained, Describe the atomic oxygen density of the satellite according to the output parameters of the atmospheric model. The input parameters of the atmospheric model include: the number of days from January 1st of the current year to the current day, the number of seconds from 00:00:00 of the current day to the solution time, the geographical longitude, the geographical latitude, the altitude, the solar 10.7cm radiation flux of the previous day, the average solar 10.7cm radiation flux of 81 days, and the 8-bit array obtained according to the average geomagnetic index of the current day and the 20 3-hour average geomagnetic indices before the solution time. The output parameters of the atmospheric model include: N2, O2, He, Ar, N, H, O and ionospheric positive oxygen ions O + number density, neutral atmospheric temperature, and overall atmospheric density.

6. The method for characterizing a space atomic oxygen environment according to claim 1, characterized in that: The step of obtaining the current longitudinal wind speed and latitudinal wind speed of the satellite according to the spatial position coordinates of the satellite at the current moment, the time parameters, and the control parameters of the horizontal wind environment model comprises: Get the input parameters of the horizontal wind environment model, According to the input parameters of the horizontal wind environment model, the spatial position coordinates of the satellite at the current moment and the time parameter, the output parameters of the horizontal wind environment model are obtained, Describing the current meridional wind speed and zonal wind speed of the satellite according to the output parameters of the horizontal wind environment model, The input parameters of the horizontal wind environment model include: the number of days from January 1st of the current year to the current day, the number of seconds from 00:00:00 of the current day to the solution time, the geographical longitude, the geographical latitude, the altitude, the solar 10.7cm radiation flux of the previous day, the average solar 10.7cm radiation flux of 81 days, and the 8-bit array obtained according to the average geomagnetic index of the current day and the 20 3-hour average geomagnetic indices before the solution time. The output parameters of the horizontal wind environment model include the longitudinal wind speed and the latitudinal wind speed.

7. The method for characterizing a space atomic oxygen environment according to claim 5 or 6, characterized in that: The spatial position coordinates are the three-dimensional coordinates of the satellite in the geocentric J2000 coordinate system, and the geographic longitude and the geographic latitude are the longitude and latitude coordinates of the satellite in the WGS-84 coordinate system obtained based on the three-dimensional coordinates and coordinate system transformation.

8. A space atomic oxygen environment characterization device, characterized in that: include: The acquisition unit is used to obtain the satellite's current spatial position coordinates, time parameters, running speed, running attitude, control parameters of the atomic oxygen environment model and control parameters of the horizontal wind environment model. The atomic oxygen environment generating unit of the satellite is used to obtain the atomic oxygen density of the satellite according to the spatial position coordinates of the satellite at the current moment, the time parameters and the control parameters of the atomic oxygen environment model, The satellite wind speed environment generating unit is used to obtain the current longitudinal wind speed and latitudinal wind speed of the satellite according to the spatial position coordinates of the satellite at the current moment, the time parameters and the control parameters of the horizontal wind environment model, A satellite structure model generating unit, configured to obtain a current structure model of the satellite according to the spatial position coordinates, the running speed and the running attitude of the satellite at a current moment; The characterization processing unit characterizes the space atomic oxygen environment according to the atomic oxygen density, the meridional wind speed, the latitudinal wind speed, and the current structural model of the satellite.

9. A computer device comprising a memory, a processor and a computer program stored in the memory and executable on the processor, characterized in that: When the processor executes the computer program, the steps of the method according to any one of claims 1 to 7 are implemented.

10. A computer-readable storage medium having a computer program stored thereon, characterized in that: When the computer program is executed by a processor, the steps of the method according to any one of claims 1 to 7 are implemented.

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