Earth satellite orbit fast calculation method and system based on matching point iteration

Abstract

The application discloses a kind of based on point iteration earth satellite orbit fast calculation method and system, belong to aerospace technology field, selected single time calculation interval step and the point number in each calculation interval;According to the initial position and velocity of earth satellite, set the position and velocity estimation value of each point time of earth satellite in calculation interval;Local point feedback iteration method is used to carry out iterative correction to the position and velocity estimation value of earth satellite at each point time;It is judged whether the position and velocity state of earth satellite in all running time have been completely calculated, repeat the preceding steps, until the end time of calculation interval reaches target calculation time length stops.The application estimates and corrects the position and velocity information of earth satellite using feedback iteration method, uses point method to avoid integral symbol operation to reduce calculation amount, uses CGL point to improve the calculation precision of earth satellite velocity and position at the end of each interval, provides a kind of high-efficiency high-precision calculation method for earth satellite orbit prediction.

Description

Technical Field

[0001] The present invention relates to the field of aerospace technology, and in particular to a method and system for quickly calculating an earth satellite orbit based on point allocation iteration. Background Art

[0002] The problem of fast computation of orbital dynamics is a fundamental issue in aerospace engineering, widely encountered in missions such as orbital design, space capture, and deep space exploration. The development of new and efficient computational methods for this problem is of great significance. Many Earth orbital dynamics problems are formally expressed as initial value problems of ordinary differential equations. These problems, given the initial position and velocity state of an Earth satellite, are recursively deduced from the satellite's orbital dynamics equations. Finite difference methods are the classic numerical solutions to initial value problems in orbital dynamics, with representative ones including the Euler method and the Runge-Kutta method.

[0003] However, the computational accuracy of the finite difference classification method is heavily dependent on small step sizes, and the method's performance is limited. In tasks such as spacecraft pursuit and escape games and rapid on-orbit repair of failed spacecraft, it will be difficult to meet the real-time requirements of the mission's Earth satellite orbit and the requirements of high efficiency and high precision in the long-term solution process. Summary of the Invention

[0004] In view of the problems existing in the prior art, the present invention provides a method for fast calculation of earth satellite orbits based on point allocation iteration to improve the calculation accuracy and efficiency of earth satellite orbits.

[0005] The present invention is achieved through the following technical solutions:

[0006] A method for quickly calculating an Earth satellite orbit based on point-matching iteration comprises the following steps:

[0007] Step S1, constructing a Chebyshev basis function according to the calculation interval step size of the target trajectory and the number of collocation points within each calculation interval step size;

[0008] Step S2, determining estimated values ​​of the Earth satellite position and velocity at each distribution point within the calculation interval step length based on the Earth satellite initial position and velocity;

[0009] Step S3, iteratively correcting the estimated values ​​of the earth satellite's position and velocity at each distribution point time according to the Bischoff basis function combined with an iterative method, to obtain the corrected estimated values ​​of the earth satellite's position and velocity at each distribution point time;

[0010] Step S4: Use the estimated values ​​of the position and velocity of the Earth satellite at the last corrected point moment within the current calculation interval step as the initial position and initial velocity of the Earth satellite in the next calculation interval step, repeat steps S2-S4 until the end moment of the calculation interval step is equal to the operating time length of the target Earth satellite, and obtain the orbital parameters of the target satellite.

[0011] Preferably, in step 1, the number of collocation points M within the calculation interval step is set, M CGL nodes are selected within the calculation interval step according to the number of collocation points M, a collocation time vector is constructed according to the M CGL nodes, and a Chebyshev basis function is constructed according to the collocation time vector.

[0012] Preferably, the Chebyshev basis function includes a Chebyshev basis function value matrix, a Chebyshev basis function differential value matrix and a Chebyshev basis function integral value matrix.

[0013] Preferably, in step 2, the state values ​​of the position and velocity within the interval step length are calculated to be equal to the initial position vector and velocity vector of the Earth satellite.

[0014] Preferably, the iterative method described in step 3 is a local point matching feedback iterative method.

[0015] Preferably, the method for obtaining the estimated values ​​of the position and velocity of the Earth satellite at each distribution point after correction in step 3 is as follows:

[0016] S3.1. Iteratively correct the estimated position and velocity of the Earth satellite at each distribution point using the Bischoff basis function;

[0017] S3.2. Calculate the binary norm of the difference vector between the estimated position and velocity of the Earth satellite at each distribution point after the k+1th iteration and the kth iteration;

[0018] S3.3. If the second norm is greater than the termination iteration precision error limit, let k = k+1, and repeat step S3.1 until the second norm is less than or equal to the termination iteration precision error limit, and obtain the estimated value of the position and velocity of the earth satellite at each distribution point after the k+1th iteration correction within the previous calculation interval step.

[0019] Preferably, the iterative correction formula in step S3.1 is as follows:

[0020] x k+1 =x k -P(Dx k -g(x k ))

[0021] Among them, x k =[x1 k (τ); x2 k (τ); x3k (τ); x4 k (τ); x5 k (τ); x6 k (τ);], is the estimated value of the six state variables representing the position and velocity of the earth satellite at each distribution point after the kth iteration correction, x k+1 are the estimated values ​​of the six state variables representing the position and velocity of the Earth satellite at each distribution point after the k+1th iteration correction, P is the square matrix of the integral values ​​of the Chebyshev basis functions corresponding to the M CGL nodes, D is the square matrix of the differential values ​​of the Chebyshev basis functions corresponding to the M CGL nodes, and g is the right-hand side function value vector of the first-order form of the orbital dynamics system corresponding to the M CGL nodes after time scaling.

[0022] Preferably, the expression of the second norm e in step S3.2 is as follows:

[0023] e=||x k+1 -x k ||2

[0024] A system for fast calculation of earth satellite orbit based on point-matching iteration, comprising:

[0025] The Chebyshev basis function module is used to construct the Chebyshev basis function according to the calculation interval step of the target orbit and the number of collocation points within each calculation interval step;

[0026] An estimation module, for determining an estimated value of the position and velocity of the earth satellite at each distribution point within a calculation interval step according to the initial position and velocity of the earth satellite;

[0027] An estimation correction module is used to iteratively correct the estimated value of the earth satellite position and velocity at each distribution point time according to the Bischoff basis function combined with the iterative method, so as to obtain the estimated value of the earth satellite position and velocity at each distribution point time after correction;

[0028] The orbit calculation module is used to use the estimated values ​​of the position and velocity of the earth satellite at the last point moment corrected within the current calculation interval step as the initial position and initial velocity of the earth satellite in the next calculation interval step, and repeatedly calculate the estimated values ​​of the earth satellite position and velocity at each point moment within the interval step and perform iterative correction until the end time of the calculation interval step is equal to the operating time length of the target earth satellite, thereby obtaining the orbit parameters of the target satellite.

[0029] Compared with the prior art, the present invention has the following beneficial technical effects:

[0030] The present invention discloses a method for rapidly calculating the orbit of an Earth satellite based on point-matching iteration. The method comprises the following steps: selecting the interval step size for a single calculation and the number of points in each calculation interval; setting the estimated position and velocity of the Earth satellite at each point-matching moment in the calculation interval based on the initial position and velocity of the Earth satellite; iteratively correcting the estimated position and velocity of the Earth satellite at each point-matching moment using a local point-matching feedback iteration method; determining whether the position and velocity states of the Earth satellite throughout its entire operating time have been fully calculated, and repeating the aforementioned steps until the target calculation time length is reached at the end of the calculation interval. The present invention uses a feedback iteration method to estimate and correct the position and velocity information of the Earth satellite, uses a point-matching method to avoid integral sign operations to reduce the amount of calculation, and uses CGL point-matching to improve the calculation accuracy of the Earth satellite velocity and position at the end of each interval, thereby providing a highly efficient and accurate calculation method for predicting the orbit of an Earth satellite. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] Figure 1 This is a schematic diagram of a method for rapidly calculating an Earth satellite orbit based on point-matching iteration according to the present invention;

[0032] Figure 2 Flowchart of the implementation of the method for fast calculation of earth satellite orbit based on point allocation iteration of the present invention

[0033] Figure 3 This is a schematic diagram of the results of the method for quickly calculating the Earth satellite orbit based on point-matching iteration according to the present invention; DETAILED DESCRIPTION

[0034] The present invention will be further described in detail below with reference to the accompanying drawings, which are intended to explain rather than limit the present invention.

[0035] like Figure 1 and Figure 2 As shown in FIG, a method for quickly calculating the orbit of an earth satellite based on point-matching iteration includes the following steps:

[0036] Step S1: Construct a Chebyshev basis function based on the target trajectory calculation interval step size and the number of collocation points within each calculation interval step size. The specific method is as follows:

[0037] S1.1. Set the calculation interval step length Δt, and determine the end time t of the calculation interval step according to the calculation interval step length Δt and the initial time t0 of the calculation interval step length. f ;

[0038] t f =t0+Δt

[0039] S1.2. Set the number of points M within the calculation interval step, and select M CGL nodes within the calculation interval step [-1, 1] based on the number of points M.

[0040] The method for selecting M CGL nodes is as follows:

[0041]

[0042] S1.3, construct the point allocation time vector τ=[τ1,τ2,…,τ M ];

[0043] S1.4. Construct a Chebyshev basis function, wherein the Chebyshev basis function includes a Chebyshev basis function value matrix C, a Chebyshev basis function differential value matrix D, and a Chebyshev basis function integral value matrix P.

[0044] According to the point-matching time vector, the Chebyshev basis function value matrix C corresponding to the M CGL nodes is constructed. The construction rule is:

[0045] C=[cos(0arccos(τ T )),cos(1arccos(τ T )),…,cos((M-1)arccos(τ T ))];

[0046] According to the collocation time vector and the Chebyshev basis function value matrix C, the Chebyshev basis function differential value matrix D corresponding to the M CGL nodes is constructed. The construction rule is:

[0047]

[0048] in, D1=[D1 1 ,D1 2 ,…,D1 M ],

[0049] Among them, (D1 k ) 1,1 =(-1) k (k-1) 2 ,(D1 k ) M,1 =(k-1) 2 ,k=1,…,M;

[0050] in,

[0051] According to the Chebyshev basis function value matrix C of the collocation time vector, the Chebyshev basis function integral value matrix P corresponding to M CGL nodes is constructed. The construction rule is:

[0052]

[0053] Where P = P1C-1 , P1=[P1 1 ,P1 2 ,…,P1 M ],

[0054] Among them, P1 1 =1+τ T ,

[0055] in,

[0056] in,

[0057] in,

[0058] Step S2: Determine the estimated value of the Earth satellite position and velocity at each point within the calculation interval step length based on the initial position and velocity of the Earth satellite, as follows:

[0059] The state values ​​of position and velocity within the calculation interval step are always equal to the initial position vector r0 and velocity vector v0 of the earth satellite;

[0060] The iteration count variable k=0.

[0061] Step S3: Iteratively correcting the estimated values ​​of the Earth satellite's position and velocity at each collocation time according to the Bischoff basis function combined with the local collocation feedback iteration method to obtain the corrected estimated values ​​of the Earth satellite's position and velocity at each collocation time, specifically comprising the following steps:

[0062] S3.1. Iteratively correct the estimated position and velocity of the Earth satellite at each distribution point using the Bischoff basis function. The iterative correction formula is as follows:

[0063] x k+1 =x k -P(Dx k -g(x k ))

[0064] Among them, x k =[x1 k (τ); x2 k (τ); x3 k (τ); x4 k (τ); x5 k (τ); x6 k (τ);], is the estimated value of the six state variables representing the position and velocity of the earth satellite at each distribution point after the kth iteration correction, x k+1is the estimated value of the six state variables representing the position and velocity of the Earth satellite at each collocation point after the k+1th iteration correction, P is the square matrix of the integral value of the Chebyshev basis function corresponding to the M CGL nodes, D is the square matrix of the differential value of the Chebyshev basis function corresponding to the M CGL nodes, g is the right-hand function value vector of the first-order form of the orbital dynamics system corresponding to the M CGL nodes after time scaling, and each element of the g vector is the first-order derivative value of the corresponding element in the x vector at the corresponding collocation point time;

[0065] S3.2. Calculate the bimodal value e of the difference vector between the estimated position and velocity of the Earth satellite at each distribution point after the k+1th iteration and the kth iteration, using the following formula:

[0066] e=||x k+1 -x k ||2

[0067] S3.3. Determine whether the two-norm of the difference vector between the estimated position and velocity of each satellite at each distribution point after the k+1th iteration and the kth iteration is less than or equal to the termination iteration accuracy error limit, thereby obtaining a first determination result.

[0068] If the first judgment result indicates no, that is, the second norm is greater than the termination iteration precision error limit, set k = k + 1, and return to step S3.1 to iteratively correct the position and velocity estimates of the Earth satellite at each point in time;

[0069] If the first judgment result indicates yes, that is, the second norm is less than or equal to the termination iteration accuracy error limit, the position and velocity estimation values ​​of the earth satellite at each distribution point after the k+1th iteration correction within the current calculation interval step are recorded.

[0070] According to the calculation interval step and the time vector of the distribution point, the actual time t corresponding to the mth CGL node in the interval step [-1,1] is determined. m , and record the real time corresponding to each calculation result, the actual time t m The calculation method is as follows:

[0071]

[0072] Step S4: The estimated values ​​of the position and velocity of the Earth satellite at the last point of the iterative correction in the current calculation interval step are used as the initial position and initial velocity of the Earth satellite in the next calculation interval step, and steps S2-S4 are repeated until the end time t of the previous calculation interval step. f =Equal to the target Earth satellite's operating time length, the orbital parameters of the target satellite are obtained. The specific method is as follows:

[0073] Determine the current calculation interval step [t0,t f ] the end time tf whether it is equal to the target earth satellite operation time length that needs to be estimated, obtaining a second judgment result;

[0074] If the second judgment result indicates yes, output all interval calculation results and terminate the calculation;

[0075] If the second judgment result indicates no, the last point distribution moment in the current calculation interval is used as the initial moment of the next calculation interval, and the position and velocity of the earth satellite at the last point distribution moment obtained by iterative correction in the current calculation interval are used as the initial position and initial velocity of the earth satellite in the next calculation interval, and steps S2-S4 are repeated.

[0076] The embodiments of the present invention will be described below with reference to the accompanying drawings.

[0077] The present invention aims to solve the problem of calculating the orbit of the earth satellite and proposes a local point allocation feedback iteration method, which specifically includes the following steps:

[0078] Step 1: For the orbit prediction problem of near-Earth satellites, select the single-step calculation subinterval step size, the number of collocation points M within the single-step calculation step size, and the single-step calculation termination iteration accuracy error limit according to project needs; determine the collocation time based on the selected number of collocation points within the single-step calculation step size, and construct the collocation time vector τ, the Chebyshev basis function differential value matrix D corresponding to the selected number of collocation points, and the Chebyshev basis function integral value matrix P.

[0079] Step 2: Set the iteratively corrected state quantity to a 6M-dimensional column vector x, where the 1st to Mth elements of the vector correspond to the state estimation values ​​of the x-axis coordinates of the Earth satellite at each distribution point, the M+1th to 2Mth elements of the vector correspond to the state estimation values ​​of the y-axis coordinates of the Earth satellite at each distribution point, the 2M+1th to 3Mth elements of the vector correspond to the state estimation values ​​of the z-axis coordinates of the Earth satellite at each distribution point, the 3M+1th to 4Mth elements of the vector correspond to the state estimation values ​​of the x-axis velocity components of the Earth satellite at each distribution point, the 4M+1th to 5Mth elements of the vector correspond to the state estimation values ​​of the y-axis velocity components of the Earth satellite at each distribution point, and the 5M+1th to 6Mth elements of the vector correspond to the state estimation values ​​of the z-axis velocity components of the Earth satellite at each distribution point; set the estimated values ​​of the position and velocity state values ​​at all distribution points before the first iteration equal to the initial values ​​of the position and velocity of the Earth satellite.

[0080] Step 3: Substitute the iteratively corrected state into equation x k+1 =x k -P(Dx k -g(x k)) performs iterative calculations. After each iteration, the binary norm e of the difference vector between the previous and next iteration state vector estimates is calculated, and a check is made to see whether the binary norm e is less than or equal to the termination iteration precision error limit. If the binary norm e is less than or equal to the termination iteration precision error limit, the iteration result is recorded. If the binary norm e is greater than the termination iteration precision error limit, the process jumps to the third step and iterates again to update the state vector estimate.

[0081] Step 4: Determine whether the satellite's states for the entire operating time have been fully calculated. If the satellite's states for the entire operating time have not been fully calculated, use the last point-matching time of the current subinterval as the initial time of the next subinterval. Use the satellite's position and velocity states at the last point-matching time of the current subinterval as the initial values ​​for the satellite's position and velocity for the next subinterval. Enter the next interval and jump to step 2 for iterative calculation. If the satellite's states for the entire operating time have been fully calculated, output the calculation results and terminate the calculation.

[0082] Example 1: The dynamic equation of the near-Earth satellite orbit recursion problem is:

[0083]

[0084] Where r = [x, y, z] T is the position vector of the near-Earth satellite, μ=3986004.418×10 8 m 3 / s 2 , represents the earth's gravitational constant, r=||r||, represents the distance between the center of the earth and the center of mass of the near-Earth satellite, t0 is the initial time of orbit recursion, a J is a perturbation term, and in this embodiment, the J2 perturbation term is considered.

[0085] The first-order form of the near-Earth satellite orbit recursion problem equation used in the iteration is as follows:

[0086]

[0087] This embodiment uses the initial calculation conditions as shown in Table 1 and the calculation parameters as shown in Table 2. The calculated 24-hour orbit of the near-Earth satellite is as follows: Figure 3 shown.

[0088] Table 1 Initial calculation conditions used in Example 1

[0089] Parameter Value <![CDATA[初始位置坐标r0(m)]]> <![CDATA[[-0.3889×10 6 ,7.7388×10 6 ,0.6736×10 6 ] T ]]> <![CDATA[初始速度向量v0(m / s)]]> <![CDATA[[-4.2953×10 3 ,0,7.4396×10 3 ] T ]]>

[0090] Table 2 Calculation parameters used in Example 1

[0091] Parameter Value Satellite running time / day 1 Number of points / each 10 Sub-interval step / s 60 Iteration accuracy error limit / m <![CDATA[10 -5 ]]>

[0092] The present invention discloses a method for calculating an earth satellite orbit. The method comprises the following steps: selecting an interval step size for a single calculation and the number of collocation points within each calculation interval; setting an estimated value of the earth satellite's position and velocity at each collocation point within the calculation interval based on the earth satellite's initial position and velocity; iteratively correcting the estimated value of the earth satellite's position and velocity at each collocation point using a local collocation point feedback iteration method; and determining whether the position and velocity states of the earth satellite during the entire operating time have been completely calculated, and repeating the aforementioned steps until the target calculation time length is reached at the end time of the calculation interval.

[0093] The present invention also provides a system for a method for quickly calculating an earth satellite orbit based on point-matching iteration, which comprises a Chebyshev basis function module, an estimation module, an estimation correction module and an orbit calculation module.

[0094] The Chebyshev basis function module is used to construct the Chebyshev basis function according to the calculation interval step of the target orbit and the number of collocation points within each calculation interval step;

[0095] An estimation module, for determining an estimated value of the position and velocity of the earth satellite at each distribution point within a calculation interval step according to the initial position and velocity of the earth satellite;

[0096] An estimation correction module is used to iteratively correct the estimated value of the earth satellite position and velocity at each distribution point time according to the Bischoff basis function combined with the iterative method, so as to obtain the estimated value of the earth satellite position and velocity at each distribution point time after correction;

[0097] The orbit calculation module is used to use the estimated values ​​of the position and velocity of the earth satellite at the last point moment corrected within the current calculation interval step as the initial position and initial velocity of the earth satellite in the next calculation interval step, and repeatedly calculate the estimated values ​​of the earth satellite position and velocity at each point moment within the interval step and perform iterative correction until the end time of the calculation interval step is equal to the operating time length of the target earth satellite, thereby obtaining the orbit parameters of the target satellite.

[0098] The present invention adopts a feedback iteration method to estimate and correct the position and velocity information of the earth satellite, adopts a point matching method to avoid integral symbol operation to reduce the amount of calculation, and adopts CGL point matching to improve the calculation accuracy of the earth satellite velocity and position at the end of each interval, providing a high-efficiency and high-precision calculation method for the prediction of the earth satellite orbit.

[0099] The above content is only for explaining the technical idea of ​​the present invention and cannot be used to limit the protection scope of the present invention. Any changes made on the basis of the technical solution in accordance with the technical idea proposed by the present invention shall fall within the protection scope of the claims of the present invention.

Claims

1. A method for fast calculation of earth satellite orbits based on point-matching iteration, characterized in that: The steps include: Step S1, constructing a Chebyshev basis function according to the calculation interval step size of the target trajectory and the number of collocation points within each calculation interval step size; Step S2, determining estimated values ​​of the Earth satellite position and velocity at each distribution point within the calculation interval step length based on the Earth satellite initial position and velocity; Step S3, iteratively correcting the estimated values ​​of the earth satellite's position and velocity at each distribution point time according to a Chebyshev basis function combined with an iterative method, to obtain corrected estimated values ​​of the earth satellite's position and velocity at each distribution point time; The method for obtaining the estimated values ​​of the position and velocity of the Earth satellite at each point after correction is as follows: S3.

1. Iteratively correct the estimated position and velocity of the Earth satellite at each distribution point based on the Chebyshev basis function; S3.

2. Calculate the binary norm of the difference vector between the estimated position and velocity of the Earth satellite at each distribution point after the k+1th iteration and the kth iteration; S3.

3. If the second norm is greater than the terminating iteration precision error limit, set k = k + 1 and repeat step S3.1 until the second norm is less than or equal to the terminating iteration precision error limit, obtaining the estimated values ​​of the Earth satellite position and velocity at each distribution point after the k + 1th iteration correction within the previous calculation interval step size; Step S4: Use the estimated values ​​of the position and velocity of the Earth satellite at the last corrected point moment within the current calculation interval step as the initial position and initial velocity of the Earth satellite in the next calculation interval step, repeat steps S2-S4 until the end moment of the calculation interval step is equal to the operating time length of the target Earth satellite, and obtain the orbital parameters of the target satellite.

2. The method for fast calculation of earth satellite orbits based on point-matching iteration according to claim 1, characterized in that: In step 1, the number of collocation points M within the calculation interval step is set, and M CGL nodes are selected within the calculation interval step according to the number of collocation points M. The collocation time vector is constructed according to the M CGL nodes, and the Chebyshev basis function is constructed according to the collocation time vector.

3. The method for fast calculation of earth satellite orbits based on point-matching iteration according to claim 1, characterized in that: The Chebyshev basis function includes a Chebyshev basis function value matrix, a Chebyshev basis function differential value matrix and a Chebyshev basis function integral value matrix.

4. The method for fast calculation of earth satellite orbits based on point-matching iteration according to claim 1, characterized in that: The state values ​​of the position and velocity within the interval step calculated in step 2 are always equal to the initial position vector and velocity vector of the Earth satellite.

5. The method for fast calculation of earth satellite orbits based on point-matching iteration according to claim 1, characterized in that: The iterative method described in step 3 is a local collocation feedback iterative method.

6. The method for fast calculation of earth satellite orbits based on point-matching iteration according to claim 1, characterized in that: The iterative correction formula described in step S3.1 is as follows: x k+1 =x k -P(Dx k -g(x k )) Among them, x k =[x1 k (τ); x2 k (τ); x3 k (τ); x4 k (τ); x5 k (τ); x6 k (τ);], is the estimated value of the six state variables representing the position and velocity of the earth satellite at each distribution point after the kth iteration correction, x k+1 are the estimated values ​​of the six state variables representing the position and velocity of the Earth satellite at each distribution point after the k+1th iteration correction, P is the square matrix of the integral values ​​of the Chebyshev basis functions corresponding to the M CGL nodes, D is the square matrix of the differential values ​​of the Chebyshev basis functions corresponding to the M CGL nodes, and g is the right-hand side function value vector of the first-order form of the orbital dynamics system corresponding to the M CGL nodes after time scaling.

7. The method for fast calculation of earth satellite orbits based on point-matching iteration according to claim 6, characterized in that: The expression of the second norm e in step S3.2 is as follows: e=||x k+1 -x k ||2。 8. A system for executing the method for fast calculation of earth satellite orbits based on point allocation iteration according to any one of claims 1 to 7, characterized in that: include, The Chebyshev basis function module is used to construct the Chebyshev basis function according to the calculation interval step of the target orbit and the number of collocation points within each calculation interval step; An estimation module, for determining an estimated value of the position and velocity of the earth satellite at each distribution point within a calculation interval step according to the initial position and velocity of the earth satellite; An estimation correction module is used to iteratively correct the estimated value of the earth satellite's position and velocity at each distribution point time according to the Chebyshev basis function combined with the iterative method, so as to obtain the estimated value of the earth satellite's position and velocity at each distribution point time after correction; The orbit calculation module is used to use the estimated values ​​of the position and velocity of the earth satellite at the last point moment corrected within the current calculation interval step as the initial position and initial velocity of the earth satellite in the next calculation interval step, and repeatedly calculate the estimated values ​​of the earth satellite position and velocity at each point moment within the interval step and perform iterative correction until the end time of the calculation interval step is equal to the operating time length of the target earth satellite, thereby obtaining the orbit parameters of the target satellite.

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