Orbit prediction method and device based on correction of orbit data of ball satellite

Abstract

The application provides a satellite orbit prediction method and device based on orbit data of a spherical satellite. The method comprises determining a target atmospheric density model according to a target space environment condition of a satellite to be predicted, wherein the target atmospheric density model is obtained by correcting a preset atmospheric density model according to orbit data and a dynamic model of the spherical satellite in the target space environment condition; identifying an atmospheric drag coefficient of the satellite to be predicted based on the target atmospheric density model; and performing orbit prediction on the satellite to be predicted according to the target atmospheric density model and the atmospheric drag coefficient. According to the embodiment of the application, the spherical satellite maintains a stable and high-precision surface value ratio and atmospheric drag coefficient when operating in an orbit, the orbit data of the spherical satellite can be used to better achieve high-precision correction of the preset atmospheric density model, and the atmospheric drag coefficient of the satellite to be predicted can be more accurately identified based on the corrected atmospheric density model, thereby improving the orbit prediction accuracy of the satellite to be predicted.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of space technology, and particularly relates to an orbit prediction method and device for correcting orbit data based on a spherical satellite. BACKGROUND

[0002] The accuracy of low-orbit spacecraft orbit prediction is mainly determined by the calculation accuracy of atmospheric drag, so obtaining high-precision atmospheric drag is the key to ensuring the accuracy of low-orbit spacecraft orbit prediction, and the correction of atmospheric drag is usually the correction of atmospheric density and the identification of atmospheric drag coefficient. For orbit prediction under different space environment conditions, different model parameters have a great influence on the correction results of atmospheric density, and also affect the subsequent identification of atmospheric drag coefficient, thereby affecting the accuracy of orbit prediction. However, the model parameters in the existing atmospheric density model are usually single, resulting in low accuracy of orbit prediction. SUMMARY

[0003] The embodiments of the application provide an orbit prediction method and device for correcting orbit data based on a spherical satellite, to solve the technical problem of low accuracy of orbit prediction.

[0004] In a first aspect, the embodiments of the application provide an orbit prediction method for correcting orbit data based on a spherical satellite, and the method comprises:

[0005] According to the target space environment condition of the satellite to be predicted, a target atmospheric density model is determined, wherein the target atmospheric density model is obtained by correcting a preset atmospheric density model according to the orbit data and the dynamic model of the spherical satellite under the target space environment condition;

[0006] Based on the target atmospheric density model, the atmospheric drag coefficient of the satellite to be predicted is identified;

[0007] According to the target atmospheric density model and the atmospheric drag coefficient, the orbit of the satellite to be predicted is predicted.

[0008] In a second aspect, the embodiments of the application provide an orbit prediction device for correcting orbit data based on a spherical satellite, and the device comprises:

[0009] A determination module is configured to determine a target atmospheric density model according to a target space environment condition of a satellite to be predicted, wherein the target atmospheric density model is obtained by correcting a preset atmospheric density model according to the orbit data and the dynamic model of the spherical satellite under the target space environment condition;

[0010] An identification module is configured to identify the atmospheric drag coefficient of the satellite to be predicted based on the target atmospheric density model;

[0011] A prediction module is configured to perform orbit prediction on the satellite to be predicted according to the target atmospheric density model and the atmospheric drag coefficient.

[0012] In a third aspect, an electronic device is provided, and the device includes:

[0013] a processor and a memory storing programs or instructions;

[0014] The processor implements the above method when executing the programs or instructions.

[0015] In a fourth aspect, a readable storage medium is provided, and the readable storage medium stores programs or instructions, which are executed by a processor to implement the above method.

[0016] In a fifth aspect, a computer program product is provided, and instructions in the computer program product are executed by a processor of an electronic device to cause the electronic device to perform the above method.

[0017] The orbit prediction method and device based on the orbit data of the spherical satellite for correction according to the embodiments of the present application can determine a target atmospheric density model according to a target space environment condition of a satellite to be predicted, wherein the target atmospheric density model is obtained by correcting a preset atmospheric density model according to the orbit data of the spherical satellite in the target space environment condition and a dynamic model; identify an atmospheric drag coefficient of the satellite to be predicted based on the target atmospheric density model; and perform orbit prediction on the satellite to be predicted according to the target atmospheric density model and the atmospheric drag coefficient.

[0018] In this way, since the spherical satellite maintains a stable, high-precision surface value ratio and atmospheric drag coefficient when operating in an orbit, the orbit data of the spherical satellite can be used to better achieve high-precision correction of the preset atmospheric density model, and the atmospheric drag coefficient of the satellite to be predicted can be more accurately identified based on the corrected atmospheric density model, thereby effectively improving the orbit prediction accuracy of the satellite to be predicted. BRIEF DESCRIPTION OF DRAWINGS

[0019] To more clearly illustrate the technical solutions of the embodiments of the present application, the following will briefly introduce the drawings needed to be used in the embodiments of the present application. Those skilled in the art can obtain other drawings according to these drawings without any creative effort.

[0020] Figure 1 is a flowchart of an orbit prediction method provided by an embodiment of the present application;

[0021] Figure 2 is a scene flowchart of an orbit prediction method provided by an embodiment of the present application;

[0022] Figure 3 is a comparison chart before and after the atmospheric density correction in the orbit prediction method provided by the embodiment of the present application;

[0023] Figure 4a is one of the atmospheric density correction result schematic diagrams in the orbit prediction method provided by the embodiment of the present application;

[0024] Figure 4b is one of the relative error schematic diagrams of the atmospheric density correction result in the orbit prediction method provided by the embodiment of the present application;

[0025] Figure 5a is the second atmospheric density correction result schematic diagram in the orbit prediction method provided by the embodiment of the present application;

[0026] Figure 5b is the second relative error schematic diagram of the atmospheric density correction result in the orbit prediction method provided by the embodiment of the present application;

[0027] Figure 6a is the third atmospheric density correction result schematic diagram in the orbit prediction method provided by the embodiment of the present application;

[0028] Figure 6b is the third relative error schematic diagram of the atmospheric density correction result in the orbit prediction method provided by the embodiment of the present application;

[0029] Figure 7a is the fourth atmospheric density correction result schematic diagram in the orbit prediction method provided by the embodiment of the present application;

[0030] Figure 7b is the fourth relative error schematic diagram of the atmospheric density correction result in the orbit prediction method provided by the embodiment of the present application;

[0031] Figure 8 is a structure schematic diagram of the orbit prediction device provided by another embodiment of the present application;

[0032] Figure 9 is a structure schematic diagram of the electronic device provided by yet another embodiment of the present application. DETAILED DESCRIPTION

[0033] The features and exemplary embodiments of various aspects of the present application will be described in detail below, in order to make the purposes, technical solutions and advantages of the present application more clear and apparent, the present application will be further described in detail below in combination with the drawings and specific embodiments. It should be understood that the specific embodiments described herein are only intended to explain the present application, but not to limit the present application. The present application can be implemented without some of these specific details by those skilled in the art. The following description of the embodiments is only to provide a better understanding of the present application by showing examples of the present application.

[0034] It is to be noted that, in the present document, relational terms such as first and second and the like can be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Moreover, the terms "comprises", "comprising", or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but can include other elements not expressly listed or inherent to such process, method, article, or apparatus. An element proceeded by "comprises... a" does not, without more constraints, exclude the presence of additional identical elements in the process, method, article, or apparatus that comprises the element.

[0035] To solve the problems in the prior art, the application provides a satellite orbit prediction method based on corrected satellite orbit data.

[0036] Figure 1 A flowchart of the satellite orbit prediction method provided by an embodiment of the application is shown. As shown in Figure 1 The satellite orbit prediction method can include the following steps:

[0037] In step 101, a target atmosphere density model is determined according to a target space environment condition of a satellite to be predicted, wherein the target atmosphere density model is obtained by correcting a preset atmosphere density model according to satellite orbit data and a dynamics model of a spherical satellite in the target space environment condition.

[0038] In step 102, an atmosphere drag coefficient of the satellite to be predicted is identified based on the target atmosphere density model.

[0039] In step 103, the satellite to be predicted is orbit predicted according to the target atmosphere density model and the atmosphere drag coefficient.

[0040] The specific implementation of each step will be described in detail below.

[0041] In the embodiments of the application, the satellite orbit prediction method based on corrected satellite orbit data can determine a target atmosphere density model according to a target space environment condition of a satellite to be predicted, wherein the target atmosphere density model is obtained by correcting a preset atmosphere density model according to satellite orbit data and a dynamics model of a spherical satellite in the target space environment condition; identify an atmosphere drag coefficient of the satellite to be predicted based on the target atmosphere density model; and orbit predict the satellite to be predicted according to the target atmosphere density model and the atmosphere drag coefficient.

[0042] Thus, the orbit data of the spherical satellite can be used to better realize high-precision correction of the preset atmospheric density model, and the atmospheric drag coefficient of the satellite to be predicted can be more accurately identified based on the corrected atmospheric density model, thereby effectively improving the orbit prediction precision of the satellite to be predicted.

[0043] The specific implementation of each step is described below.

[0044] In step 101, the target space environment condition of the satellite to be predicted can be determined first, and then the orbit data of the spherical satellite under the same target space environment condition can be obtained. Since the spherical satellite can maintain a stable and high-precision area ratio and atmospheric drag coefficient when operating on the working orbit, the orbit data of the spherical satellite can be substituted into the kinematic model, and the model parameters of the preset atmospheric density model can be corrected by using the dynamic inversion method, thereby obtaining a high-precision target atmospheric density model after correction. The preset atmospheric density model can be J71-Roberts, NRLMSISE2000, or MISISE990 model.

[0045] In some examples, the J71-Roberts model can be used as the preset atmospheric density model. It can be understood that the atmospheric density model generally describes the atmospheric temperature variation through solar activity and geomagnetic activity, and then calculates the atmospheric composition and atmospheric density, so the atmospheric temperature is an important sensitive parameter of the atmospheric density model. In the J71-Roberts model, the atmospheric temperature at height h can be shown as formula (1):

[0046]

[0047] wherein T h is the atmospheric temperature at height h, T ∞ is the top layer temperature of the atmosphere, T x is the atmospheric temperature at 125 kilometers height, R a = 6356.766 kilometers, h is the current height of the satellite, and L is a coefficient.

[0048] As can be seen from formula (1), the coefficient L has a direct relationship with the atmospheric temperature at height h, and can be used as an important sensitive parameter of the atmospheric density model, so the coefficient L can be used as a model parameter to be corrected. The expression of the coefficient L can be shown as formula (2):

[0049]

[0050] wherein T ∞ is the top layer temperature of the atmosphere, and l iare the fitting sub-coefficients of the coefficient L. The five fitting sub-coefficients in the initial L are:

[0051] l1= 0.1031445 x 10 5 , l2= 0.2341230, l3= 0.1579202 x 10 -2 , l4= -0.1252487 x 10 -5 , l5= 0.2462708 x 10 -9

[0052] In combination with the formula (1) and the formula (2), the model parameters of the modified preset atmospheric density model can be the values of the five fitting sub-coefficients in the initial L.

[0053] In step 102, after obtaining the modified target atmospheric density model with high precision, the target atmospheric density model can be substituted into the dynamic model modification process of the satellite to be predicted, and then a more accurate atmospheric drag coefficient of the satellite to be predicted can be identified by using the dynamic inversion method.

[0054] In step 103, the orbit of the satellite to be predicted can be predicted according to the target atmospheric density model and the atmospheric drag coefficient. For example, based on the high-precision modified target atmospheric density model and the identified atmospheric drag coefficient of the satellite to be predicted, the dynamic model of the satellite to be predicted can be modified, and then the motion state of the satellite to be predicted can be calculated according to the modified dynamic model of the satellite to be predicted, so as to realize the orbit prediction of the satellite to be predicted.

[0055] The embodiments of the present application modify the atmospheric density model based on the precise orbit data of the spherical satellite, improve the J71-Roberts model, and realize the atmospheric density medium and short-term prediction error within 10%. Then, the drag coefficient of the satellite to be predicted can be identified according to the modified atmospheric density model, and the 24-hour orbit prediction error of the spherical satellite can be realized to be not more than 150 m.

[0056] In some embodiments, the above step 101 can include the following steps:

[0057] Obtaining the orbit data of the spherical satellite under N space environment conditions, N being a positive integer;

[0058] According to the orbit data of the spherical satellite under N space environment conditions and the dynamic model, the preset atmospheric density model is modified to obtain N first atmospheric density models corresponding to the N space environment conditions, wherein the first atmospheric density model corresponding to the first space environment condition is obtained based on the orbit data of the spherical satellite under the first space environment condition, and the first space environment condition is any one of the N space environment conditions.

[0059] Based on the target space environment conditions of the satellite to be predicted, determine the target atmospheric density model among N first atmospheric density models.

[0060] In this embodiment, orbital data of a spherical satellite under N space environment conditions can be obtained first. Based on the orbital data and dynamic model of the spherical satellite under N space environment conditions, a preset atmospheric density model is modified to obtain N first atmospheric density models corresponding one-to-one with the N space environment conditions. For example, as... Figure 2 As shown, based on the orbital data 1 and dynamic model of the spherical satellite under space environment condition 1, the preset atmospheric density model can be corrected using the dynamic inversion method to obtain the first atmospheric density model 1 corresponding to space environment condition 1; based on the orbital data 2 and dynamic model of the spherical satellite under space environment condition 2, the preset atmospheric density model can be corrected using the dynamic inversion method to obtain the first atmospheric density model 2 corresponding to space environment condition 2; based on the orbital data 3 and dynamic model of the spherical satellite under space environment condition 3, the preset atmospheric density model can be corrected using the dynamic inversion method to obtain the first atmospheric density model 3 corresponding to space environment condition 3...

[0061] In other words, based on the orbital data of spherical satellites under different space environment conditions, the model parameters in the preset atmospheric density model can be corrected to obtain the corrected first atmospheric density model under different space environment conditions.

[0062] In some examples, to make the results more accurate, the orbital data of the spherical satellite can include orbital data for multiple preset periods. For example, orbital data of spherical satellites for 5 to 7 days can be obtained to correct the preset atmospheric density model, thereby reducing the error of the correction.

[0063] After obtaining N first atmospheric density models that correspond one-to-one with N space environment conditions, the target atmospheric density model that matches the target space environment conditions can be determined from the N first atmospheric density models based on the target space environment conditions of the satellite to be predicted.

[0064] In this way, N first atmospheric density models can be pre-corrected. When orbit prediction of a satellite is required, the target atmospheric density model can be determined directly from the N first atmospheric density models based on the target space environment conditions of the satellite. This eliminates the need to re-acquire the orbit data of the spherical satellite under the target space environment conditions to correct the pre-set atmospheric density model before each orbit prediction, which can effectively improve the efficiency of orbit prediction.

[0065] like Figure 2As shown, after identifying the space environment condition of the satellite to be predicted, the target atmospheric density model is selected from the N first atmospheric density models, the target atmospheric density model is substituted into the dynamics model of the satellite to be predicted, and the atmospheric drag coefficient of the satellite to be predicted is identified by using the dynamics inversion method in combination with the orbit data of the satellite to be predicted, and then the dynamics model of the satellite to be predicted can be corrected according to the target atmospheric density model and the atmospheric drag coefficient, so as to realize more accurate orbit prediction of the satellite to be predicted.

[0066] In some embodiments, the above-mentioned step of correcting the preset atmospheric density model according to the orbit data and the dynamics model of the spherical satellite under N space environment conditions to obtain N first atmospheric density models corresponding to the N space environment conditions can include the following steps:

[0067] Based on the dynamics model, the orbit data of the spherical satellite under the first space environment condition is used to determine a state transition matrix, a sensitivity matrix and a motion state deviation, wherein the state transition matrix reflects the influence of the deviation of the initial motion state on the subsequent motion state, and the sensitivity matrix reflects the influence of the deviation of the model parameter on the subsequent motion state.

[0068] According to the state transition matrix, the sensitivity matrix and the motion state deviation, the preset atmospheric density model is corrected to obtain the first atmospheric density model corresponding to the first space environment condition.

[0069] In the embodiments of the present application, the dynamics model can be created according to the preset configuration information first, wherein the atmospheric drag parameter can be determined based on the atmospheric density model, the internationally common atmospheric density model includes J71-Roberts, NRLMSISE2000 and MISISE990 models, the earth ellipsoidal perturbation parameter can be determined based on the earth ellipsoidal perturbation model, the internationally common earth ellipsoidal perturbation model includes EGM2008, EGM96 and JGM3 models, and in addition, the solar radiation pressure, the lunar gravity and the tidal force parameters can also be determined based on the corresponding common model. In the embodiments of the present application, the atmospheric density model can adopt the J71-Roberts model, and the earth ellipsoidal perturbation model can adopt the EGM2008 model. The configuration information of the kinematic model can be as shown in Table 1:

[0070] Table 1

[0071]

[0072] The kinematic model can be created according to the configuration information of the above-mentioned kinematic model, and the dynamics model can be as shown in formula (3):

[0073]

[0074] Wherein X(t) = (rT (t),v T (t)) T The satellite's motion state vector is represented by r(t) = (x(t), y(t), z(t)). T The position vector of the satellite is represented by v(t) = (v x (t),v y (t),v z (t)) T Let a(t) represent the velocity vector of the satellite, and a(t) represent the acceleration experienced by the satellite. p = (C d (A / m,…) T The vector representing the characteristic parameters of the dynamic model is denoted by k. In the embodiments of this application, the J71-Robert model can be corrected using the dynamic inversion method. As mentioned above, the model parameters to be corrected can be the local temperature T. h Calculation coefficients The fitter coefficients l = [l1; ...; l5], therefore, p can refer to the fitter coefficients l = [l1; ...; l5].

[0075] After creating the kinematic model, the initial motion state and model parameters can be treated as independent variables, with X0 and p representing the exact values, respectively. and This represents an estimated value.

[0076] It is possible and Position of motion state vector Performing a first-order Taylor expansion yields formula (4):

[0077]

[0078] in, The state transition matrix can be represented by Φ(t,t0), which reflects the influence of the deviation of the initial motion state on the subsequent motion state. The sensitivity matrix, represented by S(t), reflects the impact of deviations in model parameters on subsequent motion states. ΔX(t) represents the difference between the actual and simulated motion states, ΔX0 represents the correction amount for the initial state, and Δp represents the correction amount for the model parameters.

[0079] According to formula (4), if the values ​​of the state transition matrix and sensitivity matrix at each time point are obtained, as well as the difference between the actual motion state in the orbital data of the spherical satellite at each time point and the simulated motion state obtained based on the integration of the kinematic model, the correction amount of the initial state and the correction amount of the model parameters can be obtained.

[0080] Therefore, based on the dynamic model, the state transition matrix, the sensitivity matrix and the motion state deviation can be determined according to the orbit data of the spherical satellite under the first space environment condition by using the existing kinematic calculation method, and then the preset atmospheric density model is corrected according to the state transition matrix, the sensitivity matrix and the motion state deviation, so as to obtain the first atmospheric density model corresponding to the first space environment condition.

[0081] In some embodiments, the above determining the state transition matrix, the sensitivity matrix and the motion state deviation based on the dynamic model and according to the orbit data of the spherical satellite under the first space environment condition can include the following steps:

[0082] Based on the dynamic model, a first differential equation of an initial motion state and a second differential equation of a model parameter are constructed.

[0083] According to the orbit data of the spherical satellite under the first space environment condition, the first differential equation is solved to obtain the state transition matrix.

[0084] According to the orbit data of the spherical satellite under the first space environment condition, the second differential equation is solved to obtain the sensitivity matrix.

[0085] According to the actual motion state and the simulated motion state in the orbit data of the spherical satellite under the first space environment condition, the motion state deviation is determined, wherein the simulated motion state is obtained based on the integration of the kinematic model.

[0086] In the embodiments of the present application, based on the dynamic model, a first differential equation of an initial motion state and a second differential equation of a model parameter can be constructed. Then, according to the orbit data of the spherical satellite under the first space environment condition, the first differential equation and the second differential equation can be solved to obtain the state transition matrix and the sensitivity matrix.

[0087] For example, the formula (3) can be partially differentiated with respect to the initial motion state X0to obtain the first differential equation, which can be shown as formula (5):

[0088]

[0089] Wherein, Φ(t, t0) can represent the state transition matrix, and Φ(t0, t0) = I 6×6 Solving formula (5) can obtain the state transition matrix, which can reflect the influence of the deviation of the initial motion state on the subsequent motion state.

[0090] The formula (3) can be partially differentiated with respect to the model parameter p to obtain the second differential equation, which can be shown as formula (6):

[0091]

[0092] Wherein, S(t) can represent a sensitivity matrix, since the motion state vector of the satellite at the initial moment is irrelevant to the model parameters, thus the initial condition of the sensitivity matrix can be S(t0)=0 。 Solving formula (6) can obtain the sensitivity matrix, which can reflect the influence of the bias of the model parameters on the subsequent motion state.

[0093] The motion state bias can be determined according to the actual motion state and the simulated motion state in the orbit data of the spherical satellite under the first space environment condition, wherein the simulated motion state is obtained based on the integration of the kinematic model. The calculation formula of the motion state bias can be as shown in formula (7):

[0094]

[0095] Wherein, X(t)=(r T (t),v T (t)) T represents the actual running state of the satellite at t moment, that is, the orbit data actually measured by the spherical satellite. represents the simulated running state of the satellite at t moment, which can be the motion state of the satellite obtained by integrating formula (3).

[0096] When solving the first differential equation and the second differential equation according to the orbit data of the spherical satellite, the position vector, the velocity vector and the acceleration of the spherical satellite can be substituted into formula (3), the state transition matrix, the sensitivity matrix and the motion state bias can be obtained based on the dynamic inversion method, and then the preset atmospheric density model can be corrected according to the state transition matrix, the sensitivity matrix and the motion state bias.

[0097] It can be understood that in the embodiments of the present application, the acceleration and the acceleration can include atmospheric drag perturbation acceleration, solar radiation pressure perturbation acceleration, lunar and solar gravity perturbation acceleration, earth center gravity acceleration and earth non-spherical perturbation acceleration. Wherein, the related partial derivative formula involved in the dynamic inversion method can be as follows:

[0098] The formula of each partial derivative term of the atmospheric drag perturbation acceleration can be as shown in formula (8):

[0099]

[0100] Wherein, represents the atmospheric drag acceleration, A is the windward area, m is the mass of the satellite, C d is the atmospheric drag coefficient, p is the atmospheric density, v r is the velocity vector of the satellite relative to the atmosphere (the black body is the velocity vector, and the italic is the module of the velocity vector), and I is the unit matrix.

[0101] The formula for the partial derivative of the solar radiation pressure perturbation acceleration can be shown in formula (9):

[0102]

[0103] Where asp is the solar radiation pressure perturbation acceleration, r and s represent the position vectors of the satellite and the sun in the geocentric coordinate system, respectively, and the radiation pressure coefficient C is... R P≈4.56·10 -6 Nm -2 AU represents solar radiation pressure, and light-year is a unit of light-year.

[0104] The formula for the partial derivative of the acceleration due to gravitational perturbation by the sun and moon can be shown in formula (10):

[0105]

[0106] Among them, a sm Let be the gravitational perturbation acceleration due to the Sun and Moon, r and s represent the position vectors of the satellite and the Sun in the geocentric coordinate system, respectively, and GM be the gravitational coefficient, which is the product of the Earth's mass and the gravitational constant, GM = 398600.4405 km. 3 s -2 .

[0107] The formula for the partial derivative of the gravitational acceleration at the Earth's center can be shown in formula (11):

[0108]

[0109] Among them, a c Let r be the gravitational acceleration at the Earth's center, and s be the position vectors of the satellite and the Sun in the geocentric coordinate system, respectively.

[0110] The formula for the partial derivative of the Earth's non-spherical perturbation acceleration can be shown in formula (12):

[0111]

[0112] Where anon is the non-spherical perturbation acceleration of the Earth, r and s represent the position vectors of the satellite and the Sun in the geocentric coordinate system, respectively, and a x,nm This represents the non-spherical perturbation acceleration in the x-direction, order nm.

[0113] In some embodiments, the above-mentioned process of correcting the preset atmospheric density model based on the state transition matrix, the sensitivity matrix, and the motion state deviation to obtain the first atmospheric density model corresponding to the first space environment conditions may include the following steps:

[0114] Based on the state transition matrix, sensitivity matrix, and motion state deviation, the initial motion state correction and model parameter correction are determined by the least squares method.

[0115] According to the initial motion state correction quantity and the model parameter correction quantity, the preset atmospheric density model is corrected to obtain a first atmospheric density model corresponding to the first space environment condition.

[0116] In the embodiments of the present application, the parameter correction equation of the preset atmospheric density model can be obtained by combining formula (5) and formula (6), and the parameter correction equation can be as shown in formula (13):

[0117]

[0118] Further, the first-order differential equation as shown in formula (14) can be obtained by combining formula (4):

[0119]

[0120] Wherein, Φ, S, ΔX can be a set of n data points, and the specific form is as shown in formula (15):

[0121]

[0122] As can be seen from formula (15), after the values of the motion state deviation at each time, the state transition matrix and the sensitivity matrix are obtained, the initial motion state correction quantity and the model parameter correction quantity can be obtained by using the least square method. Subsequently, according to the initial motion state correction quantity and the model parameter correction quantity, the preset atmospheric density model can be corrected to obtain a first atmospheric density model corresponding to the first space environment condition.

[0123] In some embodiments, the above-mentioned correction of the preset atmospheric density model according to the orbit data and the dynamics model of the spherical satellite under N space environment conditions to obtain N first atmospheric density models corresponding to the N space environment conditions can include the following steps:

[0124] According to the orbit data and the dynamics model of the spherical satellite under the first space environment condition, the preset atmospheric density model is corrected to obtain a second atmospheric density model corresponding to the first space environment condition;

[0125] Based on the second atmospheric density model, the simulated atmospheric density is obtained;

[0126] According to the actual atmospheric density and the simulated atmospheric density in the orbit data of the spherical satellite under the first space environment condition, the correction error of the second atmospheric density model is determined;

[0127] In the case that the correction error meets the preset error condition, the second atmospheric density model is determined as the first atmospheric density model.

[0128] In the embodiments of the present application, in order to further ensure the accuracy of the modified atmospheric density model, the correction error of the modified atmospheric density model can be detected. For example, first, the preset atmospheric density model can be modified according to the orbit data and the dynamic model of the spherical satellite under the first space environment condition, to obtain a second atmospheric density model corresponding to the first space environment condition. After obtaining the modified second atmospheric density model, the simulated atmospheric density of the spherical satellite can be obtained based on the second atmospheric density model. The correction result of the second atmospheric density model can be as shown in Figure 3 Figure 3 It can be seen that the modified atmospheric density is about half of the atmospheric density before modification.

[0129] The simulated atmospheric density can be compared with the actual atmospheric density in the orbit data of the spherical satellite, and then the correction error of the second atmospheric density model can be determined. If the correction error meets the preset error condition, for example, the correction error is less than or equal to the preset error threshold, it can be considered that the correction result of the second atmospheric density model is relatively accurate, and the second atmospheric density model can be determined as the first atmospheric density model, that is, it can be directly applied to the subsequent orbit prediction of the satellite to be predicted. If the correction error is greater than the preset error threshold, it can be considered that the correction result of the second atmospheric density model is inaccurate, and at this time, the second atmospheric density model cannot be applied to the subsequent orbit prediction of the satellite to be predicted, and the model parameters thereof still need to be continuously modified.

[0130] In this way, the modified preset atmospheric density model still needs to be verified for its correction accuracy, and when the correction error meets the preset error condition, it will be applied to the subsequent orbit prediction of the satellite to be predicted, thereby further improving the accuracy of the orbit prediction.

[0131] In some embodiments, based on the second atmospheric density model, the simulated atmospheric density can include the following steps:

[0132] Determine a first time period and a second time period under the first space environment condition, and the first time period and the second time period have a coincident period;

[0133] Based on the second atmospheric density model, a first simulated atmospheric density of the first time period and a second simulated atmospheric density of the second time period are obtained;

[0134] Determine a first atmospheric density corresponding to the coincident period in the first simulated atmospheric density, and a second atmospheric density corresponding to the coincident period in the second simulated atmospheric density;

[0135] The above determination of the correction error of the second atmospheric density model according to the actual atmospheric density and the simulated atmospheric density in the orbit data of the spherical satellite under the first space environment condition can include the following steps:

[0136] ​determine a target atmospheric density corresponding to the overlapping period in the orbit data of the spherical satellite under the first spatial environment condition;

[0137] determine a first relative error corresponding to the first time period according to the first atmospheric density and the target atmospheric density;

[0138] determine a second relative error corresponding to the second time period according to the second atmospheric density and the target atmospheric density;

[0139] determine a correction error of the second atmospheric density model according to the first relative error and the second relative error.

[0140] In the embodiments of the present application, the atmospheric density correction accuracy can be verified by using the overlapping arc segment method. For example, two consecutive time periods, i.e., a first time period and a second time period, can be determined first, wherein the first time period and the second time period have an overlapping period. As shown in Figure 4a and Figure 4b , the first time period can be from 00:00 on September 16 to 03:00 on September 17, and the second time period can be from 21:00 on September 16 to 24:00 on September 17. As can be seen, the overlapping period can be from 21:00 on September 16 to 03:00 on September 17.

[0141] The first simulated atmospheric density of the first time period and the second simulated atmospheric density of the second time period can be obtained based on the second atmospheric density model. For example, the correction length can be 27h, and the orbit data of the spherical satellite in the first time period and the orbit data of the spherical satellite in the second time period are corrected for 27h respectively to obtain the first simulated atmospheric density of the first time period and the second simulated atmospheric density of the second time period.

[0142] As shown in Figure 4a , the first atmospheric density corresponding to the overlapping period in the first simulated atmospheric density and the second atmospheric density corresponding to the overlapping period in the second simulated atmospheric density can be determined.

[0143] The target atmospheric density corresponding to the overlapping period in the orbit data of the spherical satellite can also be determined, and the target atmospheric density can be compared with the first atmospheric density and the second atmospheric density respectively, as shown in Figure 4b , the first relative error corresponding to the first time period and the second relative error corresponding to the second time period can be obtained.

[0144] The correction error of the second atmospheric density model can be determined according to the first relative error and the second relative error. For example, the maximum relative error in the first relative error and the second relative error can be determined as the correction error of the second atmospheric density model, and the average relative error of the first relative error and the second relative error can also be determined as the correction error of the second atmospheric density model.

[0145] In some examples, in order to further improve the verification accuracy of the correction accuracy of the second atmospheric density model, K sets of first and second time periods can be obtained, and the correction error of the second atmospheric density model corresponding to each of the K sets can be determined to obtain K correction errors. If all K correction errors meet the preset error conditions, the second atmospheric density model can be determined as the first atmospheric density model.

[0146] For example, such as Figures 4a to 7b As shown in the embodiment of this application, four consecutive time periods can be obtained. If the correction error of the second atmospheric density model corresponding to the four time periods is less than or equal to the preset error threshold, the correction result of the second atmospheric density model can be considered to be relatively accurate. The second atmospheric density model can be determined as the first atmospheric density model, which can be directly applied to the orbit prediction of subsequent satellites to be predicted.

[0147] In some embodiments, identifying the atmospheric drag coefficient of the satellite to be predicted based on the target atmospheric density model may include the following steps:

[0148] Based on the target atmospheric density model and dynamic model, theoretical orbit data corresponding to the preset atmospheric drag coefficient of the spherical satellite are generated, as well as M reference orbit data corresponding one-to-one with the M error atmospheric drag coefficients of the spherical satellite, where M is a positive integer;

[0149] Based on the theoretical orbit data and the first reference orbit data from M reference orbit data, the first error atmospheric drag coefficient for the i-th correction time unit is corrected to obtain the atmospheric drag coefficient correction results corresponding to the M i-th correction time units. Here, the orbital period of the spherical satellite is one correction time unit, the first reference orbit data is any reference orbit data from the M reference orbit data, the first error atmospheric drag coefficient is the error atmospheric drag coefficient corresponding to the first reference orbit data, and i is a positive integer.

[0150] Based on the atmospheric drag coefficient correction results corresponding to the Mth correction time units and the preset atmospheric drag coefficient, determine whether the correction accuracy of the ith correction time unit meets the preset correction accuracy condition.

[0151] If the correction accuracy of the i-th correction time unit meets the preset correction accuracy condition, the i-th correction time unit is determined as the target correction time unit.

[0152] Based on the target atmospheric density model and the target correction time unit, the atmospheric drag coefficient of the satellite to be predicted is identified.

[0153] It can be understood that, according to the basic principle of the dynamic inversion method, the correction effect of the model parameters and the initial motion state is closely related to the correction time length, and the better the correction effect of the model parameters and the initial motion state, the more accurate the atmospheric drag coefficient of the satellite to be predicted obtained by identification, so selecting a suitable correction time length is an important factor to obtain more accurate atmospheric drag coefficient.

[0154] In the embodiment of the application, the theoretical orbit data corresponding to the preset atmospheric drag coefficient of the spherical satellite and the M reference orbit data corresponding to the M error atmospheric drag coefficients of the spherical satellite can be generated based on the target atmospheric density model and the dynamic model.

[0155] For example, it can be assumed that the error of the kinematic model is only caused by the deviation of the atmospheric drag coefficient, the motion orbit of the spherical satellite is taken as the simulation object, the preset atmospheric drag coefficient of the spherical satellite can be Cd0, and the theoretical orbit data of 24h is generated. Then, the error atmospheric drag coefficient can be obtained by respectively superimposing 5%, 10%, 20%, 30%, 50%, and 100% errors on the preset atmospheric drag coefficient, and the 24h reference orbit data corresponding to the error atmospheric drag coefficient is generated.

[0156] The first error atmospheric drag coefficient of the i-th correction time length unit can be corrected according to the theoretical orbit data and the first reference orbit data in the M reference orbit data, to obtain M atmospheric drag coefficient correction results corresponding to the i-th correction time length unit. For example, the running period (for example, 1.5h) of the spherical satellite can be taken as the correction time length unit, and the correction results corresponding to the correction time length unit can be obtained by respectively correcting 1, 2, 4, 6, 8, 10, 12, 14, and 16 correction time length units.

[0157] Then, the atmospheric drag coefficient correction accuracy corresponding to different correction time length units can be calculated according to the M atmospheric drag coefficient correction results corresponding to the i-th correction time length unit and the preset atmospheric drag coefficient. For example, the i-th correction time length unit can be determined as the target correction time length unit when the correction accuracy of the i-th correction time length unit meets the preset correction accuracy condition.

[0158] For example, in the embodiment of the application, by calculating the atmospheric drag coefficient correction accuracy corresponding to 1, 2, 4, 6, 8, 10, 12, 14, and 16 correction time length units, it is determined that the atmospheric drag coefficient analysis result with higher accuracy can be obtained by using 4-12 correction time length units, so the 4-12 correction time length units can be determined as the target correction time length unit.

[0159] The atmospheric drag coefficient of the satellite to be predicted can be identified based on the target atmospheric density model and the target correction time unit. In this way, the atmospheric drag coefficient of the satellite to be predicted can be more accurately identified, and the orbit prediction accuracy of the satellite to be predicted is improved.

[0160] Based on the orbit prediction method for correcting the orbit data of the spherical satellite provided in the above embodiments, an embodiment of an orbit prediction device for correcting the orbit data of the spherical satellite is further provided.

[0161] Figure 8 A structural schematic diagram of an orbit prediction device provided by another embodiment of the present application is shown, and only parts related to the embodiments of the present application are shown for ease of illustration.

[0162] With reference to Figure 8 The orbit prediction device 800 can include:

[0163] A determination module 801 configured to determine a target atmospheric density model according to a target space environment condition of a satellite to be predicted, wherein the target atmospheric density model is obtained by correcting a preset atmospheric density model based on orbit data of a spherical satellite in the target space environment condition and a dynamics model;

[0164] An identification module 802 configured to identify an atmospheric drag coefficient of the satellite to be predicted based on the target atmospheric density model.

[0165] A prediction module 803 configured to perform orbit prediction on the satellite to be predicted according to the target atmospheric density model and the atmospheric drag coefficient.

[0166] In some embodiments, the determination module 801 can include:

[0167] An acquisition unit configured to acquire orbit data of a spherical satellite in N space environment conditions, N being a positive integer;

[0168] A correction unit configured to correct a preset atmospheric density model based on the orbit data of the spherical satellite in the N space environment conditions and a dynamics model, to obtain N first atmospheric density models corresponding to the N space environment conditions, wherein a first atmospheric density model corresponding to a first space environment condition is obtained based on orbit data of a spherical satellite in the first space environment condition, and the first space environment condition is any one of the N space environment conditions.

[0169] A determination unit configured to determine a target atmospheric density model in the N first atmospheric density models according to a target space environment condition of a satellite to be predicted.

[0170] In some embodiments, the correction unit can include:

[0171] The first determining subunit is configured to determine a state transition matrix, a sensitivity matrix and a motion state deviation based on the kinematic model and according to the orbit data of the spherical satellite under the first space environment condition, wherein the state transition matrix reflects the influence of the deviation of the initial motion state on the subsequent motion state, and the sensitivity matrix reflects the influence of the deviation of the model parameter on the subsequent motion state.

[0172] The first correcting subunit is configured to correct the preset atmospheric density model according to the state transition matrix, the sensitivity matrix and the motion state deviation, to obtain a first atmospheric density model corresponding to the first space environment condition.

[0173] In some embodiments, the first determining subunit described above can be further configured to:

[0174] construct a first differential equation of the initial motion state and a second differential equation of the model parameter based on the kinematic model;

[0175] obtain the state transition matrix by solving the first differential equation according to the orbit data of the spherical satellite under the first space environment condition;

[0176] obtain the sensitivity matrix by solving the second differential equation according to the orbit data of the spherical satellite under the first space environment condition;

[0177] determine the motion state deviation according to the actual motion state and the simulated motion state in the orbit data of the spherical satellite under the first space environment condition, wherein the simulated motion state is obtained based on the integration of the kinematic model.

[0178] In some embodiments, the first correcting subunit described above can be further configured to:

[0179] determine the initial motion state correction and the model parameter correction by the least square method according to the state transition matrix, the sensitivity matrix and the motion state deviation;

[0180] correct the preset atmospheric density model according to the initial motion state correction and the model parameter correction, to obtain the first atmospheric density model corresponding to the first space environment condition.

[0181] In some embodiments, the correcting unit described above can include:

[0182] The second correcting subunit is configured to correct the preset atmospheric density model according to the orbit data of the spherical satellite under the first space environment condition and the kinematic model, to obtain a second atmospheric density model corresponding to the first space environment condition;

[0183] The obtaining subunit is configured to obtain the simulated atmospheric density based on the second atmospheric density model.

[0184] The second determining sub-unit is configured to determine a correction error of the second atmospheric density model according to the actual atmospheric density and the simulated atmospheric density in the orbit data of the spherical satellite under the first space environment condition.

[0185] The third determining sub-unit is configured to determine the second atmospheric density model as the first atmospheric density model when the correction error meets a preset error condition.

[0186] In some embodiments, the obtaining sub-unit can be further configured to:

[0187] determine a first time period and a second time period under the first space environment condition, and the first time period and the second time period have a coincident period;

[0188] obtain a first simulated atmospheric density of the first time period and a second simulated atmospheric density of the second time period based on the second atmospheric density model;

[0189] determine a first atmospheric density corresponding to the coincident period in the first simulated atmospheric density, and a second atmospheric density corresponding to the coincident period in the second simulated atmospheric density;

[0190] The second determining sub-unit can be further configured to:

[0191] determine a target atmospheric density corresponding to the coincident period in the orbit data of the spherical satellite under the first space environment condition;

[0192] determine a first relative error corresponding to the first time period according to the first atmospheric density and the target atmospheric density;

[0193] determine a second relative error corresponding to the second time period according to the second atmospheric density and the target atmospheric density;

[0194] determine the correction error of the second atmospheric density model according to the first relative error and the second relative error.

[0195] In some embodiments, the recognition module 102 can be configured to:

[0196] generate theoretical orbit data corresponding to a preset atmospheric drag coefficient of the spherical satellite and M reference orbit data corresponding to M error atmospheric drag coefficients of the spherical satellite based on the target atmospheric density model and the dynamic model, M being a positive integer;

[0197] According to the theoretical orbit data and first reference orbit data in the M reference orbit data, a first error atmospheric drag coefficient of the i-th correction time unit is corrected to obtain M atmospheric drag coefficient correction results corresponding to the i-th correction time unit, wherein the running period of the spherical satellite is one correction time unit, the first reference orbit data is any reference orbit data in the M reference orbit data, the first error atmospheric drag coefficient is an error atmospheric drag coefficient corresponding to the first reference orbit data, and i is a positive integer;

[0198] According to the M atmospheric drag coefficient correction results corresponding to the i-th correction time unit and the preset atmospheric drag coefficient, it is determined whether the correction accuracy of the i-th correction time unit meets the preset correction accuracy condition;

[0199] In the case where the correction accuracy of the i-th correction time unit meets the preset correction accuracy condition, the i-th correction time unit is determined as the target correction time unit;

[0200] Based on the target atmospheric density model and the target correction time unit, the atmospheric drag coefficient of the satellite to be predicted is identified.

[0201] It should be noted that the information interaction, execution process and the like between the above devices / units are based on the same concept as the method embodiments of the present application, and are corresponding devices of the above orbit prediction method based on the orbit data of the spherical satellite. All implementation manners in the above method embodiments are applicable to the embodiments of the device, and the specific functions and technical effects brought by the device can be referred to the method embodiments part, which will not be described here.

[0202] Those skilled in the art can clearly understand that, for the convenience and brevity of description, only the division of the above functional units and modules is exemplified, and in actual application, the above functions can be completed by different functional units and modules according to needs, that is, the internal structure of the device is divided into different functional units or modules to complete all or part of the functions described above. The functional units and modules in the embodiments can be integrated in one processing unit, or each unit can exist physically, or two or more units can be integrated in one unit. The integrated unit can be realized in the form of hardware or software. In addition, the specific names of the functional units and modules are only for easy distinction, and do not limit the protection scope of the present application. The specific working process of the units and modules in the system can be referred to the corresponding process in the above method embodiments, which will not be described here.

[0203] Figure 9 A hardware structure schematic diagram of an electronic device provided by another embodiment of the present application is shown.

[0204] The device can include a processor 901 and a memory 902 storing programs or instructions.

[0205] The processor 901 implements the steps in any of the above method embodiments when executing the programs.

[0206] For example, the programs can be divided into one or more modules / units, one or more modules / units are stored in the memory 902 and executed by the processor 901 to complete the present application. One or more modules / units can be a series of program instruction segments capable of completing a specific function, which are used to describe the execution process of the program in the device.

[0207] Specifically, the above processor 901 can include a central processing unit (CPU), or a specific integrated circuit (ASIC), or can be configured to implement one or more integrated circuits of the embodiments of the present application.

[0208] The memory 902 can include a mass storage for data or instructions. For example, but not limited to, the memory 902 can include a hard disk drive (HDD), a floppy disk drive, a flash memory, an optical disc, a magneto-optical disc, a magnetic tape, or a universal serial bus (USB) drive, or a combination of two or more of these. Where appropriate, the memory 902 can include removable or non-removable (or fixed) media. Where appropriate, the memory 902 can be internal or external to the integrated gateway disaster recovery device. In a particular embodiment, the memory 902 is a non-volatile solid-state memory.

[0209] The memory can include read-only memory (ROM), random access memory (RAM), magnetic disk storage media devices, optical storage media devices, flash memory devices, electrical, optical, or other physical / tangible memory storage devices. Therefore, generally, the memory includes one or more tangible (non-transitory) readable storage media (e.g., memory devices) encoded with software including computer-executable instructions and, when the software is executed (e.g., by one or more processors), it is operable to perform operations described with reference to methods according to an aspect of the present disclosure.

[0210] The processor 901 implements any of the above embodiments by reading and executing the programs or instructions stored in the memory 902.

[0211] In one example, the electronic device can further include a communication interface 903 and a bus 910. Wherein the processor 901, the memory 902, the communication interface 903 are connected through the bus 910 and complete the communication between each other.

[0212] The communication interface 903 is mainly configured to implement communication between modules, devices, units and / or equipment in the embodiments of the present application.

[0213] The bus 910 includes hardware, software, or both, that couples components of the online data traffic billing device to each other in a known manner. Although the application is not limited in this regard, the bus can include an Accelerated Graphics Port (AGP) or other graphics bus, an Enhanced Industry Standard Architecture (EISA) bus, a Front Side Bus (FSB), a HyperTransport (HT) interconnect, an Industry Standard Architecture (ISA) bus, an InfiniBand (IB) interconnect, a Low Pin Count (LPC) bus, a memory bus, a Micro Channel Architecture (MCA) bus, a Peripheral Component Interconnect (PCI) bus, a PCI-Express (PCI-X) bus, a Serial Advanced Technology Attachment (SATA) bus, a Video Electronics Standards Association local (VLB) bus, or another suitable bus or a combination of two or more of these. Where appropriate, the bus 910 can include one or more buses. Although the application is not limited in this regard, the bus 910 can include one or more buses connecting the various circuits of the application, each of the one or more buses operating at one or more clock speeds. The bus 910 is used to transmit data between the various components of the online data traffic billing device.

[0214] In addition, in combination with the method in the above-mentioned embodiments, the embodiments of the present application can provide a readable storage medium to implement. The readable storage medium has a program or instructions stored thereon; the program or instructions are executed by a processor to implement any one of the methods in the above-mentioned embodiments. The readable storage medium can be read by a machine such as a computer.

[0215] The embodiments of the present application further provide a chip, which includes a processor and a communication interface, the communication interface is coupled with the processor, the processor is used to run a program or instructions, to implement various processes of the above-mentioned method embodiments and achieve the same technical effects. To avoid repetition, details are not described here.

[0216] It should be understood that the chip mentioned in the embodiments of the present application can also be referred to as a system-level chip, a system chip, a chip system or a system-on-chip chip, etc.

[0217] The embodiments of the present application provide a computer program product, which is stored in a readable storage medium, the program product is executed by at least one processor to implement various processes of the above-mentioned method embodiments and achieve the same technical effects. To avoid repetition, details are not described here.

[0218] It is to be understood that the application is not limited to particular configurations and processes described herein and shown in the drawings. The detailed description is not to be taken in a limiting sense, and the scope of the present application is defined by the appended claims. In the above embodiments, several specific steps are described and illustrated in order to provide a thorough disclosure of the application. However, it can be appreciated that the method process of the present application is not limited to the specifically enumerated steps, and that various changes, modifications and additions can be made thereto by those skilled in the art without departing from the scope of the present application. Further, the scope of the present application is not intended to be limited to particular configurations and process steps described herein and shown in the drawings.

[0219] The functional modules shown in the structural block diagram described above can be implemented as hardware, software, firmware or a combination thereof. When implemented in hardware, it can be, for example, an electronic circuit, an application specific integrated circuit (ASIC), appropriate firmware, a plug-in, a functional card, etc. When implemented in software, the elements of the present application are program or code segments that are used to perform the required tasks. The program or code segments can be stored in a machine-readable medium or transmitted through a data signal carried in a carrier wave over a transmission medium or communication link. The "machine-readable medium" can include any medium that can store or transfer information. Examples of the machine-readable medium include an electronic circuit, a semiconductor memory device, a ROM, a flash memory, an erasable ROM (EROM), a floppy diskette, a CD-ROM, an optical disk, a hard disk, a fiber optic medium, a radio frequency (RF) link, etc. The code segments can be downloaded via a computer network such as the Internet, an intranet, etc.

[0220] It is also to be understood that the example embodiments mentioned in the present application describe some methods or systems based on a series of steps or devices. However, the present application is not limited to the order of the above steps, that is, the steps can be performed in the order mentioned in the embodiments, or in an order different from the embodiments, or several steps can be performed simultaneously.

[0221] The computer program product can include a computer readable medium having stored thereon a computer program, which defines operations to be taken by a processor. The medium can include, but is not limited to, floppy diskettes, optical disks, CD-ROMs, and magneto-optical disks, ROMs, RAMs, erasable programmable

[0222] The above merely describes a specific implementation of the present application. Those skilled in the art can clearly understand the specific working processes of the system, modules and units described above for the convenience and brevity of description, and the corresponding processes in the foregoing method embodiments can be referred to, which will not be described herein again. It should be understood that the protection scope of the present application is not limited in this way, and any person skilled in the art can easily think of various equivalent modifications or replacements within the technical range disclosed in the present application, and these modifications or replacements should be covered in the protection scope of the present application.

Claims

1. A method for orbit prediction based on orbital data from spherical satellites, characterized in that, include: Based on the target space environment conditions of the satellite to be predicted, a target atmospheric density model is determined, wherein the target atmospheric density model is obtained by modifying a preset atmospheric density model based on the orbital data and dynamic model of the spherical satellite under the target space environment conditions; Based on the target atmospheric density model, the atmospheric drag coefficient of the satellite to be predicted is identified; Based on the target atmospheric density model and the atmospheric drag coefficient, the orbit of the satellite to be predicted is predicted. The process of determining the target atmospheric density model based on the target space environment conditions of the satellite to be predicted includes: Obtain orbital data for a spherical satellite under N space environment conditions, where N is a positive integer; Based on the orbital data and dynamic model of the spherical satellite under the N space environment conditions, the preset atmospheric density model is corrected to obtain N first atmospheric density models that correspond one-to-one with the N space environment conditions. The first atmospheric density model corresponding to the first space environment condition is obtained by correcting the orbital data of the spherical satellite under the first space environment condition. The first space environment condition is any one of the N space environment conditions. Based on the target space environment conditions of the satellite to be predicted, determine the target atmospheric density model among the N first atmospheric density models.

2. The method according to claim 1, characterized in that, The step involves modifying a preset atmospheric density model based on the orbital data and dynamic model of the spherical satellite under the N space environment conditions to obtain N first atmospheric density models corresponding one-to-one with the N space environment conditions, including: Based on the dynamic model, and according to the orbital data of the spherical satellite under the first space environment conditions, the state transition matrix, the sensitivity matrix, and the motion state deviation are determined. The state transition matrix reflects the influence of the initial motion state deviation on the subsequent motion state, and the sensitivity matrix reflects the influence of the model parameter deviation on the subsequent motion state. Based on the state transition matrix, the sensitivity matrix, and the motion state deviation, the preset atmospheric density model is corrected to obtain the first atmospheric density model corresponding to the first space environment conditions.

3. The method according to claim 2, characterized in that, Based on the dynamic model, and according to the orbital data of the spherical satellite under the first space environment conditions, the determination of the state transition matrix, sensitivity matrix, and motion state deviation includes: Based on the aforementioned dynamic model, the first differential equation for the initial motion state and the second differential equation for the model parameters are constructed. Based on the orbital data of the spherical satellite under the first space environment conditions, the first differential equation is solved to obtain the state transition matrix; Based on the orbital data of the spherical satellite under the first space environment conditions, the second differential equation is solved to obtain the sensitivity matrix; Based on the actual motion state and simulated motion state of the spherical satellite in the orbital data under the first space environment conditions, the motion state deviation is determined, wherein the simulated motion state is obtained by integrating the dynamic model.

4. The method according to claim 2, characterized in that, The step of correcting the preset atmospheric density model based on the state transition matrix, the sensitivity matrix, and the motion state deviation to obtain the first atmospheric density model corresponding to the first space environment conditions includes: Based on the state transition matrix, the sensitivity matrix, and the motion state deviation, the initial motion state correction and the model parameter correction are determined by the least squares method. Based on the initial motion state correction amount and the model parameter correction amount, the preset atmospheric density model is corrected to obtain the first atmospheric density model corresponding to the first space environment conditions.

5. The method according to claim 1, characterized in that, The step involves modifying a preset atmospheric density model based on the orbital data and dynamic model of the spherical satellite under the N space environment conditions to obtain N first atmospheric density models corresponding one-to-one with the N space environment conditions, including: Based on the orbital data and dynamic model of the spherical satellite under the first space environment conditions, the preset atmospheric density model is modified to obtain a second atmospheric density model corresponding to the first space environment conditions. Based on the second atmospheric density model, the simulated atmospheric density is obtained; Based on the actual atmospheric density in the orbital data of the spherical satellite under the first space environment condition and the simulated atmospheric density, the correction error of the second atmospheric density model is determined; If the error correction meets the preset error conditions, the second atmospheric density model is determined as the first atmospheric density model.

6. The method according to claim 5, characterized in that, The process of obtaining simulated atmospheric density based on the second atmospheric density model includes: Determine a first time period and a second time period under the first space environment conditions, wherein the first time period and the second time period have overlapping periods; Based on the second atmospheric density model, the first simulated atmospheric density for the first time period and the second simulated atmospheric density for the second time period are obtained; Determine the first atmospheric density corresponding to the overlapping time period in the first simulated atmospheric density, and the second atmospheric density corresponding to the overlapping time period in the second simulated atmospheric density; The step of determining the correction error of the second atmospheric density model based on the actual atmospheric density in the orbital data of the spherical satellite under the first space environment conditions and the simulated atmospheric density includes: Determine the target atmospheric density corresponding to the overlap period in the orbital data of the spherical satellite under the first space environment conditions; Based on the first atmospheric density and the target atmospheric density, determine the first relative error corresponding to the first time period; Based on the second atmospheric density and the target atmospheric density, determine the second relative error corresponding to the second time period; The correction error of the second atmospheric density model is determined based on the first relative error and the second relative error.

7. The method according to claim 1, characterized in that, The process of identifying the atmospheric drag coefficient of the satellite to be predicted based on the target atmospheric density model includes: Based on the target atmospheric density model and the dynamic model, theoretical orbit data corresponding to the preset atmospheric drag coefficient of the spherical satellite are generated, as well as M reference orbit data corresponding one-to-one with the M error atmospheric drag coefficients of the spherical satellite, where M is a positive integer; Based on the theoretical orbit data and the first reference orbit data among the M reference orbit data, the first error atmospheric drag coefficient for the i-th correction time unit is corrected to obtain the atmospheric drag coefficient correction results corresponding to the M i-th correction time units. Here, the orbital period of the spherical satellite is one correction time unit, the first reference orbit data is any reference orbit data among the M reference orbit data, the first error atmospheric drag coefficient is the error atmospheric drag coefficient corresponding to the first reference orbit data, and i is a positive integer. Based on the atmospheric drag coefficient correction results corresponding to the M i-th correction time units and the preset atmospheric drag coefficient, determine whether the correction accuracy of the i-th correction time unit meets the preset correction accuracy condition. If the correction accuracy of the i-th correction time unit meets the preset correction accuracy condition, the i-th correction time unit is determined as the target correction time unit. Based on the target atmospheric density model and the target correction time unit, the atmospheric drag coefficient of the satellite to be predicted is identified.

8. An orbit prediction device based on orbital data from a global satellite for correction, characterized in that, The device includes: The determination module is used to determine the target atmospheric density model based on the target space environment conditions of the satellite to be predicted, wherein the target atmospheric density model is obtained by modifying the preset atmospheric density model according to the orbital data and dynamic model of the spherical satellite under the target space environment conditions; The identification module is used to identify the atmospheric drag coefficient of the satellite to be predicted based on the target atmospheric density model. The forecasting module is used to predict the orbit of the satellite to be predicted based on the target atmospheric density model and the atmospheric drag coefficient. The determining module includes: The acquisition unit is used to acquire orbital data of a spherical satellite under N space environment conditions, where N is a positive integer; The correction unit is used to correct the preset atmospheric density model based on the orbital data and dynamic model of the spherical satellite under the N space environment conditions, so as to obtain N first atmospheric density models corresponding one-to-one with the N space environment conditions. The first atmospheric density model corresponding to the first space environment condition is obtained by correcting the orbital data of the spherical satellite under the first space environment condition. The first space environment condition is any one of the N space environment conditions. The determining unit is used to determine the target atmospheric density model among the N first atmospheric density models based on the target space environment conditions of the satellite to be predicted.

9. An electronic device, characterized in that, The device includes: a processor and a memory storing programs or instructions; When the processor executes the program or instructions, it implements the method as described in any one of claims 1-7.

10. A readable storage medium, characterized in that, The readable storage medium stores a program or instructions that, when executed by a processor, implement the method as described in any one of claims 1-7.

11. A computer program product, characterized in that, When the instructions in the computer program product are executed by the processor of the electronic device, the electronic device causes the electronic device to perform the method as described in any one of claims 1-7.

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