A verification method for satellite orbit determination

Abstract

The present disclosure provides a verification method for satellite orbit determination, including: dividing each on-orbit satellite into different categories according to the orbit altitude of each on-orbit satellite, and determining the orbit determination result of each on-orbit satellite; the orbit determination result contains multiple parameters; automatically verifying the multiple parameters in the orbit determination result with a preset adjustable threshold through machine learning to determine whether the orbit determination result meets the orbit determination accuracy requirements; if the orbit determination result meets the orbit determination accuracy requirements, directly publish the orbit determination result; if the orbit determination result does not meet the orbit determination accuracy requirements, continue with the orbit determination optimization strategy, repeat the satellite orbit determination and automatic verification process until the orbit determination result meets the orbit determination accuracy requirements, and continue to complete the orbit determination result publishing process; or transfer to manual processing after the orbit determination optimization strategy can no longer solve the problem. The present disclosure shortens the time for large-scale satellite orbit determination and product release, improves the operation efficiency of the satellite orbit system; and reduces the workload of operators.

Description

Technical Field

[0001] The present disclosure relates to the technical field of on-orbit spacecraft TT&C technology, and particularly to a verification method for satellite orbit determination. Background Art

[0002] Satellite orbit determination generally includes orbit calculation, verification of the orbit calculation results, optimization, and release of orbit products. In the process of determining the existing satellite orbits, the verification of the satellite orbit determination results mainly relies on the experience of operators. When the number of satellites is small, the problems and errors in this working mode are not obvious. However, with the sharp increase in the number of on-orbit satellites, the manual processing method will consume a large amount of manpower and time. Moreover, with the multiple increase in the workload, the timeliness, correctness, and reliability of manual operations cannot be guaranteed, and this method cannot meet the current requirements for the orbit determination accuracy of a large number of satellites. Therefore, it is necessary to improve one or more problems existing in the above related technical solutions to improve the operation efficiency of the satellite orbit system.

[0003] It should be noted that the information disclosed in the above background art is only used to enhance the understanding of the background of the present disclosure, and therefore may include information that does not constitute the prior art known to those of ordinary skill in the art. Summary of the Invention

[0004] The purpose of the embodiments of the present disclosure is to provide a verification method for satellite orbit determination. This verification method can intelligently determine and optimize the orbits of a large number of satellites, shorten the time for orbit determination and product release, and improve the operation efficiency of the satellite orbit system.

[0005] The embodiments of the present disclosure provide a verification method for satellite orbit determination, and the method includes the following steps:

[0006] Divide each of the on-orbit satellites into different categories according to the orbit altitude of each on-orbit satellite, and determine the orbit determination results of each on-orbit satellite; multiple parameters are included in the orbit determination results;

[0007] Automatically verify multiple parameters in the orbit determination results with a preset adjustable threshold through machine learning, and determine whether the orbit determination results meet the orbit determination accuracy requirements;

[0008] If the orbit determination results meet the orbit determination accuracy requirements, directly release the orbit determination results;

[0009] If the orbit determination results do not meet the orbit determination accuracy requirements, continue with the orbit determination optimization strategy, repeat the satellite orbit determination and automatic verification process until the orbit determination results meet the orbit determination accuracy requirements, and then continue to complete the orbit determination result release process; or transfer to manual processing after the orbit determination optimization strategy can no longer solve the problem.

[0010] In an exemplary embodiment of the present disclosure, in the step of dividing each of the on-orbit satellites into different categories according to the orbital altitude of each on-orbit satellite and determining the orbit determination result of each on-orbit satellite, where the orbit determination result includes multiple parameters, the different categories of the on-orbit satellites include:

[0011] For type A satellites, the orbital altitude is: h ≤ 700 km;

[0012] For type B satellites, the orbital altitude is: 700 km < h ≤ 5000 km;

[0013] For type C satellites, the orbital altitude is: 5000 km < h ≤ 30000 km;

[0014] For type D satellites, the orbital altitude is: h > 30000 km.

[0015] In an exemplary embodiment of the present disclosure, in the step of dividing each of the on-orbit satellites into different categories according to the orbital altitude of each on-orbit satellite and determining the orbit determination result of each on-orbit satellite, where the orbit determination result includes multiple parameters, the setting of the multiple parameters and the preset adjustable threshold is determined according to the experience of orbital engineers and experts. The multiple parameters and the preset adjustable threshold include: data arc segment, initial orbit improvement amount, total orbit determination data utilization rate, total orbit determination data residual, latest orbit data utilization rate, latest orbit data residual, satellite navigation data, and orbit epoch.

[0016] In an exemplary embodiment of the present disclosure, for type A satellites:

[0017] In the data arc segment, when performing post-control orbit determination, it is greater than 1 day, and the atmospheric drag coefficient CD is not solved during post-control orbit determination; during normal operation, it is greater than 2 days; during normal operation, the atmospheric drag coefficient 7.0 > CD > 0.0;

[0018] In the initial orbit improvement amount, the absolute value of the difference between the semi-major axis of the orbit determination result of the on-orbit satellite and the initial orbit used for orbit determination is: |Δa| < 20 m; the absolute value of the difference between the spatial position of the orbit determination result of the on-orbit satellite and the initial orbit used for orbit determination is: |ΔP| < 300 m;

[0019] In the total orbit determination data utilization rate, both ranging and velocity measurement are greater than 75%;

[0020] In the total orbit determination data residual, the root mean square RMS of the ranging data in the orbit determination result of the on-orbit satellite R is less than 30, and the root mean square RMS of the velocity measurement data in the orbit determination result of the on-orbit satellite V is less than 30;

[0021] In the latest circle data utilization rate, both the ranging and velocity measurement are greater than 75%;

[0022] In the latest circle data residuals, the root mean square (RMS) of the ranging data in the orbit determination result of the on-orbit satellite R is less than 30, and the root mean square (RMS) of the velocity measurement data in the orbit determination result of the on-orbit satellite V is less than 30;

[0023] In the satellite navigation data, the GNSS data utilization rate is greater than 80%, and the root mean square (RMS) of the satellite navigation data in the orbit determination result of the on-orbit satellite G is less than 25;

[0024] The orbital epoch is consistent with that sent the previous day.

[0025] In an exemplary embodiment of the present disclosure, for type B satellites:

[0026] In the data arc segment, when performing post-control orbit determination, it is greater than 1 day, and the atmospheric drag coefficient CD is not solved during post-control orbit determination; when operating normally, it is greater than 2 days, and during normal operation, 7.0 > CD > 0.0;

[0027] In the initial orbit improvement amount, the absolute value of the difference between the semi-major axis of the orbit determination result of the on-orbit satellite and the initial orbit used for orbit determination is: |Δa| < 10 m; the absolute value of the difference between the spatial position of the orbit determination result of the on-orbit satellite and the initial orbit used for orbit determination is: |ΔP| < 200 m;

[0028] In the total orbit determination data utilization rate, both the ranging and velocity measurement are greater than 80%;

[0029] In the total orbit determination data residuals, the root mean square (RMS) of the ranging data in the orbit determination result of the on-orbit satellite R is less than 25, and the root mean square (RMS) of the velocity measurement data in the orbit determination result of the on-orbit satellite V is less than 25;

[0030] In the latest circle data utilization rate, both the ranging and velocity measurement are greater than 80;

[0031] In the latest circle data residuals, the root mean square (RMS) of the ranging data in the orbit determination result of the on-orbit satellite R is less than 25, and the root mean square (RMS) of the velocity measurement data in the orbit determination result of the on-orbit satellite V is less than 25;

[0032] In the satellite navigation data, the GNSS data utilization rate is greater than 80%, and the root mean square (RMS) of the satellite navigation data in the orbit determination result of the on-orbit satellite G is less than 25;

[0033] The orbital epoch is consistent with that sent the previous day.

[0034] In an exemplary embodiment of the present disclosure, for Class C satellites:

[0035] In the data arc segment, during post-control orbit determination, it is greater than 1 day, and the atmospheric drag coefficient CD is not solved during post-control orbit determination; during normal operation, it is greater than 2.5 days, and the atmospheric drag coefficient CD is not solved during normal operation;

[0036] In the initial orbit improvement amount, the absolute value of the difference between the semi-major axis of the orbit of the orbit determination result of the on-orbit satellite and the initial orbit used for orbit determination is: |Δa| < 10 m; the absolute value of the difference between the spatial position of the orbit determination result of the on-orbit satellite and the initial orbit used for orbit determination is: |ΔP| < 200 m;

[0037] In the total orbit determination data utilization rate, both ranging and velocity measurement are greater than 80%;

[0038] In the total orbit determination data residual, the root mean square RMS of the ranging data in the orbit determination result of the on-orbit satellite R is less than 10, and the root mean square RMS of the velocity measurement data in the orbit determination result of the on-orbit satellite V is less than 10;

[0039] In the latest circle data utilization rate, both ranging and velocity measurement are greater than 90%;

[0040] In the latest circle data residual, the root mean square RMS of the ranging data in the orbit determination result of the on-orbit satellite R is less than 10, and the root mean square RMS of the velocity measurement data in the orbit determination result of the on-orbit satellite V is less than 10;

[0041] In the satellite navigation data, the GNSS data utilization rate is greater than 80%, and the root mean square RMS of the navigation data in the orbit determination result of the on-orbit satellite G is less than 25;

[0042] The orbital epoch is consistent with that sent the previous day.

[0043] In an exemplary embodiment of the present disclosure, for Class D satellites:

[0044] In the data arc segment, during post-control orbit determination, it is greater than 1 day, and the atmospheric drag coefficient CD is not solved during post-control orbit determination; during normal operation, it is greater than 1 day, and the atmospheric drag coefficient CD is not solved during normal operation;

[0045] Among the initial orbit improvement amounts, the absolute value of the difference between the orbital semi-major axis of the orbit determination result of the on-orbit satellite and the initial orbit used for orbit determination is: |Δa| < 10 m; the absolute value of the difference between the spatial position of the orbit determination result of the on-orbit satellite and the initial orbit used for orbit determination is: |ΔP| < 1000 m;

[0046] Among the total orbit determination data usage rates, both the ranging and velocity measurement are greater than 90%;

[0047] Among the total orbit determination data residuals, the root mean square RMS of the ranging data in the orbit determination result of the on-orbit satellite R is less than 10, and the root mean square RMS of the velocity measurement data in the orbit determination result of the on-orbit satellite V is less than 10;

[0048] Among the latest orbit data usage rates, both the ranging and velocity measurement are greater than 90%;

[0049] Among the latest orbit data residuals, the root mean square RMS of the ranging data in the orbit determination result of the on-orbit satellite R is less than 10, and the root mean square RMS of the velocity measurement data in the orbit determination result of the on-orbit satellite V is less than 10;

[0050] Among the satellite navigation data, the GNSS data usage rate is greater than 80%, and the root mean square RMS of the satellite navigation data in the orbit determination result of the on-orbit satellite G is less than 25;

[0051] The orbit epoch is consistent with that sent the previous day.

[0052] In an exemplary embodiment of the present disclosure, in the step of dividing each of the on-orbit satellites into different categories according to the orbital altitude of each on-orbit satellite and determining the orbit determination result of each on-orbit satellite, the orbital altitude h of each on-orbit satellite is the difference between the semi-major axis of the on-orbit satellite and the equatorial radius of the earth.

[0053] In an exemplary embodiment of the present disclosure, if the orbit determination result does not meet the orbit determination accuracy requirements, the orbit determination optimization strategy is continued, and the orbit determination and automatic verification process of the satellite is repeated until the orbit determination result meets the orbit determination accuracy requirements, and then the orbit determination result release process is continued; or in the step of transferring to manual processing after the orbit determination optimization strategy can no longer solve the problem, the abnormal situations where the satellite orbit determination result does not meet the orbit determination accuracy requirements include:

[0054] Situation 1: The latest orbit data usage rate is low or the residual exceeds the limit;

[0055] Situation 2: The total residuals of the ranging data or velocity measurement data in the satellite orbit determination result are too large or the percentage of rejected data is too high;

[0056] Case 3: The atmospheric damping coefficient exceeds the limit;

[0057] Case 4: The change amount of the satellite orbit improvement result compared to the initial orbit value exceeds the limit;

[0058] Case 5: All satellite orbit determination is excluded.

[0059] In an exemplary embodiment of the present disclosure, if the orbit determination result does not meet the orbit determination accuracy requirements, the orbit determination optimization strategy is continued, and the satellite orbit determination and automatic verification process are repeated until the orbit determination result meets the orbit determination accuracy requirements, and then the orbit determination result release process is completed; or in the step of transferring to manual processing after the orbit determination optimization strategy can no longer solve the problem,

[0060] If it is Case 1, the orbit determination optimization strategy includes re-performing preprocessing, warehousing, and downloading data of the external measurement data submission, and starting orbit calculation;

[0061] If it is Case 2, the orbit determination optimization strategy includes viewing the first orbit improvement process, comparing and performing systematic difference calculation on the measurement station data with large initial orbit residuals, and starting orbit calculation;

[0062] If it is Case 3, the orbit determination optimization strategy includes setting the atmospheric damping coefficient as not to be solved or a fixed value in the menu, and starting orbit calculation;

[0063] If it is Case 4, the orbit determination optimization strategy includes performing systematic difference calculation on the measurement station data with large residuals in the zero-th iteration or appropriately shortening the length of the orbit determination arc segment, and starting orbit calculation;

[0064] If it is Case 5, the orbit determination optimization strategy includes resetting the data arc segment length and starting orbit calculation.

[0065] The technical solution provided by the present disclosure may include the following beneficial effects:

[0066] In the embodiment of the present disclosure, a verification method for satellite orbit determination is proposed. This verification method can intelligently determine and optimize the orbits of a large number of on-orbit satellites, shorten the time for orbit determination and product release, and improve the operation efficiency of the satellite orbit system; at the same time, by intelligently optimizing the satellite orbit determination strategy when the orbit determination result of the on-orbit satellite does not meet the orbit determination accuracy, the success rate of automatic verification of the satellite orbit determination result is further increased, and the workload of operators is greatly reduced. Description of the Drawings

[0067] The accompanying drawings herein are incorporated into and constitute a part of this specification, showing embodiments consistent with the present disclosure, and are used together with the specification to explain the principles of the present disclosure. Obviously, the accompanying drawings in the following description are only some embodiments of the present disclosure, and those of ordinary skill in the art can obtain other drawings based on these drawings without creative efforts.

[0068] Figure 1 Schematic diagram showing the steps of a verification method for satellite orbit determination in an exemplary embodiment of the present disclosure;

[0069] Figure 2 Schematic diagram showing the general process of verifying the satellite orbit determination result in an exemplary embodiment of the present disclosure;

[0070] Figure 3 Schematic diagram showing the satellite orbit determination optimization strategy in an exemplary embodiment of the present disclosure;

[0071] Figure 4 Schematic diagram showing the relationship between the verification of satellite orbit determination and the satellite orbit determination optimization strategy in an exemplary embodiment of the present disclosure. Detailed implementation manners

[0072] Example embodiments will now be described more fully with reference to the accompanying drawings. However, the example embodiments can be implemented in various forms and should not be construed as limited to the examples set forth herein; rather, these embodiments are provided so that this disclosure will be more thorough and complete, and will fully convey the concept of the example embodiments to those skilled in the art. The features, structures, or characteristics described can be combined in any suitable manner in one or more embodiments.

[0073] In addition, the accompanying drawings are only schematic illustrations of the present disclosure and are not necessarily drawn to scale. The same reference numerals in the drawings denote the same or similar parts, and thus their repeated description will be omitted. Some of the block diagrams shown in the drawings are functional entities and do not necessarily correspond to physically or logically independent entities. These functional entities can be implemented in software form, or in one or more hardware modules or integrated circuits, or in different networks and / or processor devices and / or microcontroller devices.

[0074] In this example embodiment, a verification method for satellite orbit determination is provided. Referring to Figure 1 as shown, the verification method may include the following steps:

[0075] Step S101: Divide each on-orbit satellite into different categories according to the orbital altitude of each on-orbit satellite, and determine the orbit determination result of each on-orbit satellite; the orbit determination result includes multiple parameters;

[0076] Step S102: Automatically check multiple parameters in the orbit determination result against preset adjustable thresholds through machine learning to determine whether the orbit determination result meets the orbit determination accuracy requirements;

[0077] Step S103: If the orbit determination result meets the orbit determination accuracy requirements, directly release the orbit determination result;

[0078] Step S104: If the orbit determination result does not meet the orbit determination accuracy requirements, continue with the orbit determination optimization strategy, repeat the satellite orbit determination and automatic check process until the orbit determination result meets the orbit determination accuracy requirements, and then continue with the orbit determination result release process; or transfer to manual processing after the orbit determination optimization strategy can no longer solve the problem.

[0079] A check method for satellite orbit determination proposed in this embodiment can intelligently determine and optimize the orbits of a large number of on-orbit satellites, shorten the time for orbit determination and product release, and improve the operation efficiency of the satellite orbit system; at the same time, through intelligent optimization of the satellite orbit determination strategy when the orbit determination result of the on-orbit satellite does not meet the orbit determination accuracy, the success rate of passing the automatic check of the satellite orbit determination result is further increased, greatly reducing the workload of operators.

[0080] Next, each step of the check method in this exemplary embodiment will be described in more detail.

[0081] This disclosure sorts out each link of manually checking the satellite orbit determination result, extracts the key check parameters in the check process, and automatically checks each parameter through machine learning using adjustable thresholds. For the case where the orbit determination result meets the satellite orbit determination accuracy, directly release the orbit determination result of the satellite; if the orbit determination result does not meet the satellite orbit determination accuracy requirements, continue with the orbit determination optimization strategy, repeat the satellite orbit determination and automatic check process until the orbit determination result meets the orbit determination accuracy requirements or the orbit determination optimization strategy can no longer solve the problem, and then continue with the orbit determination result release process.

[0082] In step S101,

[0083] For medium and low Earth orbit satellites, in addition to the action of the Earth's gravity, atmospheric drag is the most important influencing factor. The degree of influence of atmospheric drag is closely related to the satellite orbit height. Satellites at different orbit heights have different characteristics in terms of the influence of atmospheric drag, the daily orbit decay situation, and the fitting situation of measurement data. Therefore, in one embodiment, each on-orbit satellite is classified according to the orbit height of each on-orbit satellite, and the orbit determination result and release standard of each on-orbit satellite are determined.

[0084] Generally, based on past experience, low Earth orbit satellites in orbit are divided into two categories with a 700 km orbital altitude as the boundary. Low orbit satellites below 700 km are one category, and high orbit satellites above 700 km are another category. Different strategies are used for judgment respectively. Finally, the classification results according to orbital altitude are obtained: that is

[0085] The orbital altitude of type A satellites is: h ≤ 700 km;

[0086] The orbital altitude of type B satellites is: 700 km < h ≤ 5000 km;

[0087] The orbital altitude of type C satellites is: 5000 km < h ≤ 30000 km;

[0088] The orbital altitude of type D satellites is: h > 30000 km.

[0089] It should be noted that the satellite orbit determination (i.e., orbit determination) results include multiple parameters, such as data arc segment, initial orbit improvement amount, total orbit determination data utilization rate, total orbit determination data residual, latest circle data utilization rate, latest circle data residual, satellite navigation data, and orbit epoch, etc. The setting of these parameters and preset adjustable thresholds is determined based on the years of experience of orbit engineers and experts. And, according to the experience of orbit engineers and experts, in special cases, some specific satellites can also be processed with a recalculation strategy. For example: when the orbit determination result of a geostationary satellite is poor, the radiation pressure coefficient can be solved; by comparing the orbit determination results over a certain period of time, when large residuals continuously appear, the influence of the space environment such as intense solar activity should also be considered, and an orbit determination strategy of appropriately shortening the orbit determination arc segment should be adopted for orbit improvement.

[0090] The orbital altitude h of the satellite is the difference between the semi-major axis of the satellite and the equatorial radius of the Earth.

[0091] After obtaining the orbit determination result of the satellite in orbit, step S102 is entered. Through machine learning, multiple parameters in the orbit determination result are automatically checked against the preset adjustable thresholds to determine whether the orbit determination result meets the orbit determination accuracy requirements. As shown in Table 1 below:

[0092] Table 1: Checking basis for orbit determination results of different levels of satellites

[0093]

[0094]

[0095] As can be seen from Table 1, for type A satellites,

[0096] In the data arc segment, during post-control orbit determination, it is greater than 1 day, and the atmospheric drag coefficient CD is not solved during post-control orbit determination; during normal operation, it is greater than 2 days; during normal operation, the atmospheric drag coefficient 7.0 > CD > 0.0;

[0097] In the initial orbit improvement amount, the absolute value of the difference between the semi-major axis of the orbit determination result of the on-orbit satellite and the initial orbit used for orbit determination is: |Δa| < 20 m; the absolute value of the difference between the spatial position of the orbit determination result of the on-orbit satellite and the initial orbit used for orbit determination is: |ΔP| < 300 m;

[0098] In the total orbit determination data utilization rate, both ranging and velocity measurement are greater than 75%;

[0099] In the total orbit determination data residuals, the root mean square RMS of the ranging data in the orbit determination result of the on-orbit satellite R is less than 30, and the root mean square RMS of the velocity measurement data in the orbit determination result of the on-orbit satellite V is less than 30;

[0100] In the latest orbit data utilization rate, both ranging and velocity measurement are greater than 75%;

[0101] In the latest orbit data residuals, the root mean square RMS of the ranging data in the orbit determination result of the on-orbit satellite R is less than 30, and the root mean square RMS of the velocity measurement data in the orbit determination result of the on-orbit satellite V is less than 30;

[0102] In the satellite navigation data, the GNSS data utilization rate is greater than 80%, and the root mean square RMS of the satellite navigation data in the orbit determination result of the on-orbit satellite G is less than 25;

[0103] The orbit epoch is consistent with that sent the previous day.

[0104] For type B satellites,

[0105] In the data arc segment, during post-control orbit determination, it is greater than 1 day, and the atmospheric drag coefficient CD is not solved during post-control orbit determination; during normal operation, it is greater than 2 days, during normal operation, the atmospheric drag coefficient 7.0 > CD > 0.0;

[0106] In the initial orbit improvement amount, the absolute value of the difference between the semi-major axis of the orbit determination result of the on-orbit satellite and the initial orbit used for orbit determination is: |Δa| < 10 m; the absolute value of the difference between the spatial position of the orbit determination result of the on-orbit satellite and the initial orbit used for orbit determination is: |ΔP| < 200 m;

[0107] In the total orbit determination data utilization rate, both ranging and velocity measurement are greater than 80%;

[0108] Among the total orbit determination data residuals, the root mean square (RMS) of the ranging data in the orbit determination result of the on-orbit satellite R is less than 25, and the root mean square (RMS) of the velocity measurement data in the orbit determination result of the on-orbit satellite V is less than 25;

[0109] In the latest circle data utilization rate, both ranging and velocity measurement are greater than 80%;

[0110] Among the latest circle data residuals, the root mean square (RMS) of the ranging data in the orbit determination result of the on-orbit satellite R is less than 25, and the root mean square (RMS) of the velocity measurement data in the orbit determination result of the on-orbit satellite V is less than 25;

[0111] In the satellite navigation data, the GNSS data utilization rate is greater than 80%, and the root mean square (RMS) of the satellite navigation data in the orbit determination result of the on-orbit satellite G is less than 25;

[0112] The orbit epoch is consistent with that sent the previous day.

[0113] For type C satellites,

[0114] In the data arc segment, when performing post-control orbit determination, it is greater than 1 day, and the atmospheric drag coefficient CD is not solved during post-control orbit determination; when operating normally, it is greater than 2.5 days, and the atmospheric drag coefficient CD is not solved during normal operation;

[0115] In the initial orbit improvement amount, the absolute value of the difference between the semi-major axis of the orbit determination result of the on-orbit satellite and the initial orbit used for orbit determination is: |Δa| < 10 m; the absolute value of the difference between the spatial position of the orbit determination result of the on-orbit satellite and the initial orbit used for orbit determination is: |ΔP| < 200 m;

[0116] In the total orbit determination data utilization rate, both ranging and velocity measurement are greater than 80%;

[0117] Among the total orbit determination data residuals, the root mean square (RMS) of the ranging data in the orbit determination result of the on-orbit satellite R is less than 10, and the root mean square (RMS) of the velocity measurement data in the orbit determination result of the on-orbit satellite V is less than 10;

[0118] In the latest circle data utilization rate, both ranging and velocity measurement are greater than 90%;

[0119] Among the latest circle data residuals, the root mean square (RMS) of the ranging data in the orbit determination result of the on-orbit satellite R is less than 10, and the root mean square (RMS) of the velocity measurement data in the orbit determination result of the on-orbit satellite V is less than 10;

[0120] In satellite navigation data, the usage rate of GNSS data is greater than 80%, and the root mean square (RMS) of satellite navigation data in the orbit determination results of on-orbit satellites G is less than 25;

[0121] The orbital epoch is consistent with that sent the previous day.

[0122] For D-class satellites,

[0123] In the data arc segment, during post-control orbit determination, it is greater than 1 day, and the atmospheric drag coefficient CD is not solved during post-control orbit determination; during normal operation, it is greater than 1 day, and the atmospheric drag coefficient CD is not solved during normal operation;

[0124] In the initial orbit improvement, the absolute value of the difference between the semi-major axis of the orbit determination result of the on-orbit satellite and the initial orbit used for orbit determination is: |Δa| < 10 m; the absolute value of the difference between the spatial position of the orbit determination result of the on-orbit satellite and the initial orbit used for orbit determination is: |ΔP| < 1000 m;

[0125] In the total orbit determination data usage rate, both ranging and velocity measurement are greater than 90%;

[0126] In the total orbit determination data residuals, the root mean square (RMS) of the ranging data in the orbit determination result of the on-orbit satellite R is less than 10, and the root mean square (RMS) of the velocity measurement data in the orbit determination result of the on-orbit satellite V is less than 10;

[0127] In the latest orbit data usage rate, both ranging and velocity measurement are greater than 90%;

[0128] In the latest orbit data residuals, the root mean square (RMS) of the ranging data in the orbit determination result of the on-orbit satellite R is less than 10, and the root mean square (RMS) of the velocity measurement data in the orbit determination result of the on-orbit satellite V is less than 10;

[0129] In satellite navigation data, the usage rate of GNSS data is greater than 80%, and the root mean square (RMS) of satellite navigation data in the orbit determination results of on-orbit satellites G is less than 25;

[0130] The orbital epoch is consistent with that sent the previous day.

[0131] According to the criteria set for intelligent verification of the satellite orbit determination results described above, in this embodiment, taking a certain A-class satellite as an example for illustration, the semi-major axis of this satellite is 7,005,650 meters, and the corresponding satellite altitude is 634,646 meters. Therefore, the corresponding satellite level is A-class satellite. As shown in Table 2 below,

[0132] Table 2: Results of checking a set of orbit determination results of A-class satellites

[0133]

[0134] As can be seen from Table 2, by automatically checking multiple parameters in the orbit determination result with preset adjustable thresholds through machine learning, it can be seen that the orbit determination result of this type-A satellite meets the orbit determination accuracy requirements. Then, proceed to step S103 and directly release the orbit determination result.

[0135] If the orbit determination result does not meet the orbit determination accuracy requirements, see Table 3 below:

[0136] Table 3: Verification results of another set of orbit determination results of this type-A satellite

[0137]

[0138] As can be seen from Table 3, if the orbit determination result fails to automatically check multiple parameters in the orbit determination result with preset adjustable thresholds through machine learning, then select abnormal stations for systematic error calculation of station observation data.

[0139] If the orbit determination result does not meet the orbit determination accuracy requirements, then proceed to step S104, and continue with the orbit determination optimization strategy, repeating the satellite orbit determination and automatic verification process until the orbit determination result meets the orbit determination accuracy requirements, and then continue to complete the release process of the orbit determination result; or transfer to manual handling after the orbit determination optimization strategy can no longer solve the problem.

[0140] In this embodiment, by solving the systematic error of the station observation data, it is found that there is a systematic error of about 130 meters in the ranging data of this station. After processing the original ranging data of the station, the orbit determination result of this satellite is reduced again. Through the orbit determination optimization strategy, see Table 4 below:

[0141] Table 4: Verification results of this type-A satellite through the orbit determination optimization strategy

[0142]

[0143]

[0144] As can be seen from Table 4, through the optimization of the orbit determination strategy, the newly obtained orbit determination result meets the requirements of the preset adjustable threshold, and then the satellite orbit determination result can be directly released externally; or transfer to manual processing after the orbit determination optimization strategy can no longer solve the problem.

[0145] It should be noted here that the abnormal situations where the satellite orbit determination result does not meet the orbit determination accuracy requirements include:

[0146] Case 1: The utilization rate of the latest loop data is low or the residual exceeds the limit. The reason for Case 1 is generally that the quality of the loop measurement data is poor. In this case, it is necessary to re - perform the pre - processing, warehousing, data downloading of the external measurement data, and start the orbit calculation.

[0147] Case 2: The total residual of the ranging data or the velocity - measuring data in the satellite orbit determination result is too large or the percentage of the rejected data is too high. When Case 2 appears alone, the reason is generally that the quality of the external measurement data of some measurement stations or the satellite navigation data is poor, there are systematic errors or time - system errors, resulting in a large final total data residual and a large number of other valid measurement data being rejected. In this case, it is necessary to check the first - order orbit improvement process, compare and solve the systematic errors of the measurement station data with large initial - orbit residuals, and start the orbit calculation.

[0148] Case 3: The atmospheric damping coefficient exceeds the limit. The reason for Case 3 is generally that during the solution of the atmospheric damping coefficient, part of the perturbation modeling deviation is absorbed or the orbit change caused by the satellite's own actions makes the damping coefficient exceed the normal value range. In this case, it is necessary to set the atmospheric damping coefficient as not to be solved or a fixed value in the menu and start the orbit calculation.

[0149] Case 4: The change amount of the satellite orbit improvement result compared with the orbit initial value exceeds the limit. Case 4 generally appears simultaneously with Case 2. In addition to the reasons analyzed in Case 2, it may also be due to the use of an overly long orbit - determination arc segment, and the data before and after fitting cannot be described by a unified dynamic model; or events such as satellite orbit control or air leakage occur, and the satellite orbit has actually changed. For this case, it is necessary to solve the systematic errors of the measurement station data with large residuals in the zero - order iteration or appropriately shorten the length of the orbit - determination arc segment and start the orbit calculation.

[0150] Case 5: All satellite orbit determinations are rejected. The reason for Case 5 is that for some satellites with fewer arranged measurement and control loops and a single observation measurement station, in the case of only external measurement data, due to the small amount of data within the orbit - determination arc segment, the constraints for solving the satellite orbit are insufficient, which will lead to the failure of iteration to converge and ultimately all data being rejected. For this case, it is necessary to reset the length of the data - usage arc segment and start the orbit calculation.

[0151] Figure 2 The general process for checking the satellite orbit determination result is shown. It can be seen that in the general process, for the orbit determination of a large number of satellites, since it is necessary to operate manually one by one, the operation process is very cumbersome. And the present disclosure uses machine learning to automatically check multiple parameters in the orbit - determination result with preset adjustable thresholds, and finally draws a conclusion on whether the result meets the requirements.

[0152] Figure 3Shown is a loop process for machine learning to determine the orbit determination result. If the result meets the accuracy requirements, the orbit product can be released externally; if the result does not meet the accuracy requirements, it needs to be transferred to the recalculation link to optimize the orbit determination strategy and perform the orbit determination operation again, which is the optimization process of the strategy. As Figure 3 shown, when the orbit determination result does not meet the orbit determination accuracy requirements, according to the abnormal type of the satellite orbit determination result not meeting the orbit determination accuracy requirements, the orbit determination strategy will continue to be optimized, and the orbit determination and automatic verification processes of the satellite will be repeated until the orbit determination result meets the orbit determination accuracy requirements, and then continue to complete the release process of the orbit determination result; or transfer to manual processing after the orbit optimization strategy can no longer solve the problem.

[0153] And Figure 4 shows a schematic diagram of the overall operation process of satellite orbit determination verification and orbit determination optimization strategy. This diagram reflects the full-process operation starting from the orbit determination result review, including both the final release of the orbit determination result after meeting each review threshold determination and the handling method after an abnormality in a specific review threshold, that is, the process of re-determining the orbit by optimizing the strategy and re-verifying, which is a key link of the present disclosure.

[0154] The present disclosure effectively compresses the orbit determination and product release duration and greatly improves the operation efficiency of the orbit system by constructing an intelligent orbit determination and optimization strategy process for a large number of satellites; effectively avoids the misjudgment risk that may be caused by personnel during a large number of repeated operations and ensures the correctness of the orbit determination result verification by summarizing the verification knowledge of orbit engineers and experts and using it for the automatic verification of orbit determination results; further increases the success rate of passing the automatic verification of orbit determination results by performing an orbit determination optimization strategy for the situation where the orbit determination result fails, and greatly reduces the workload of operators.

[0155] It should be noted that although the steps of the method in the present disclosure are described in a specific order in the drawings, this does not require or imply that these steps must be executed in this specific order, or that all the shown steps must be executed to achieve the desired result. Additionally or alternatively, some steps can be omitted, multiple steps can be combined into one step for execution, and / or one step can be decomposed into multiple steps for execution, etc. Also, it is easy to understand that these steps can be executed synchronously or asynchronously, for example, in multiple modules / processes / threads.

[0156] It should be noted that although several units of the system for action execution are mentioned in the above detailed description, such division is not mandatory. In fact, according to the embodiments of the present disclosure, the features and functions of two or more of the above-described units may be embodied in one unit. Conversely, the features and functions of one unit described above may be further divided and embodied by multiple units. Some or all of the units may be selected according to actual needs to achieve the purpose of the solution of the present disclosure. A person of ordinary skill in the art can understand and implement it without creative work.

[0157] Other embodiments of the present disclosure will be readily apparent to those skilled in the art after considering the specification and practicing the invention disclosed herein. This application is intended to cover any variations, uses, or adaptations of the present disclosure that follow the general principles of the present disclosure and include known common general knowledge or conventional technical means in the technical field not disclosed in the present disclosure. The specification and examples are only to be considered as exemplary, and the true scope and spirit of the present disclosure are pointed out by the appended claims.

Claims

1. A verification method for satellite orbit determination, characterized in that, It includes the following steps: Each of the on-orbit satellites is divided into different categories according to the orbital altitude of each on-orbit satellite, and the orbit determination result of each on-orbit satellite is determined; the orbit determination result contains multiple parameters; Through machine learning, multiple parameters in the orbit determination result are automatically checked against a preset adjustable threshold to determine whether the orbit determination result meets the orbit determination accuracy requirements; If the orbit determination result meets the orbit determination accuracy requirements, the orbit determination result is directly released; If the orbit determination result does not meet the orbit determination accuracy requirements, the orbit determination optimization strategy is continued, and the orbit determination and automatic check process of the satellite are repeated until the orbit determination result meets the orbit determination accuracy requirements, and then the release process of the orbit determination result is continued; or when the orbit determination optimization strategy can no longer solve the problem, it is transferred to manual processing.

2. The verification method for satellite orbit determination according to claim 1, characterized in that, In the step of dividing each of the on-orbit satellites into different categories according to the orbital altitude of each on-orbit satellite and determining the orbit determination result of each on-orbit satellite, where the orbit determination result contains multiple parameters, the different categories of the on-orbit satellites include: For class A satellites, the orbital altitude is: h ≤ 700 km; For class B satellites, the orbital altitude is: 700 km < h ≤ 5000 km; For class C satellites, the orbital altitude is: 5000 km < h ≤ 30000 km; For class D satellites, the orbital altitude is: h > 30000 km.

3. The verification method for satellite orbit determination according to claim 2, characterized in that, In the step of dividing each of the on-orbit satellites into different categories according to the orbital altitude of each on-orbit satellite and determining the orbit determination result of each on-orbit satellite, where the orbit determination result contains multiple parameters, the setting of multiple parameters and the preset adjustable threshold are determined according to the experience of orbit engineers and experts. The multiple parameters and the preset adjustable threshold include: data arc segment, initial orbit improvement amount, total orbit determination data utilization rate, total orbit determination data residual, latest orbit data utilization rate, latest orbit data residual, satellite navigation data, and orbit epoch.

4. The verification method for satellite orbit determination according to claim 3, characterized in that, For class A satellites: In the data arc segment, when performing post-control orbit determination, it is greater than 1 day, and the atmospheric drag coefficient CD is not solved during post-control orbit determination; during normal operation, it is greater than 2 days; during normal operation, the atmospheric drag coefficient 7.0 > CD > 0.0; In the initial orbit improvement amount, the absolute value of the difference between the semi-major axis of the orbit determination result of the on-orbit satellite and the initial orbit used for orbit determination is: |Δa| < 20 m; the absolute value of the difference between the spatial position of the orbit determination result of the on-orbit satellite and the initial orbit used for orbit determination is: |ΔP| < 300 m; In the total orbit determination data utilization rate, both ranging and velocity measurement are greater than 75%; Among the total orbit determination data residuals, the root mean square RMS of the ranging data in the orbit determination result of the on-orbit satellite R is less than 30, and the root mean square RMS of the velocity measurement data in the orbit determination result of the on-orbit satellite V is less than 30; In the latest orbit data utilization rate, both ranging and velocity measurement are greater than 75%; Among the residuals of the latest circle data, the root mean square (RMS) of the ranging data in the orbit determination result of the on-orbit satellite R is less than 30, and the root mean square (RMS) of the velocity measurement data in the orbit determination result of the on-orbit satellite V is less than 30; In the satellite navigation data, the usage rate of GNSS data is greater than 80%, and the root mean square (RMS) of the satellite navigation data in the orbit determination result of the on-orbit satellite G is less than 25; The orbit epoch is consistent with that sent the previous day.

5. The verification method for satellite orbit determination according to claim 3, characterized in that, For class B satellites: In the data arc segment, when performing post-control orbit determination, it is greater than 1 day, and the atmospheric drag coefficient CD is not solved during post-control orbit determination; during normal operation, it is greater than 2 days, and during normal operation, the atmospheric drag coefficient 7.0 > CD > 0.0; In the initial orbit improvement amount, the absolute value of the difference between the orbital semi-major axis of the orbit determination result of the on-orbit satellite and the initial orbit used for orbit determination is: |Δa| < 10 m; the absolute value of the difference between the spatial position of the orbit determination result of the on-orbit satellite and the initial orbit used for orbit determination is: |ΔP| < 200 m; In the total orbit determination data utilization rate, both the ranging and velocity measurement are greater than 80%; Among the total orbit determination data residuals, the root mean square (RMS) of the ranging data in the orbit determination result of the on-orbit satellite R is less than 25, and the root mean square (RMS) of the velocity measurement data in the orbit determination result of the on-orbit satellite V is less than 25; In the utilization rate of the latest circle data, both the ranging and velocity measurement are greater than 80%; Among the latest loop data residuals, the root mean square (RMS) of the ranging data in the orbit determination result of the on-orbit satellite R is less than 25, and the root mean square (RMS) of the velocity measurement data in the orbit determination result of the on-orbit satellite V is less than 25; Among the satellite navigation data, the usage rate of GNSS data is greater than 80%, and the root mean square (RMS) of the satellite navigation data in the orbit determination result of the on-orbit satellite G is less than 25; The orbit epoch is consistent with that sent the previous day.

6. The verification method for satellite orbit determination according to claim 3, characterized in that, For type C satellites: In the data arc segment, when performing post-control orbit determination, it is greater than 1 day, and the atmospheric drag coefficient CD is not solved during post-control orbit determination; during normal operation, it is greater than 2.5 days, and the atmospheric drag coefficient CD is not solved during normal operation; In the initial orbit improvement amount, the absolute value of the difference between the orbital semi-major axis of the orbit determination result of the on-orbit satellite and the initial orbit used for orbit determination is: |Δa| < 10 m; the absolute value of the difference between the spatial position of the orbit determination result of the on-orbit satellite and the initial orbit used for orbit determination is: |ΔP| < 200 m; In the total orbit determination data utilization rate, both the ranging and velocity measurement are greater than 80%; Among the total orbit determination data residuals, the root mean square RMS of the ranging data in the orbit determination result of the on-orbit satellite R is less than 10, and the root mean square RMS of the velocity measurement data in the orbit determination result of the on-orbit satellite V is less than 10; In the utilization rate of the latest circle data, both the ranging and velocity measurement are greater than 90%; Among the residuals of the latest circle data, the root mean square RMS of the ranging data in the orbit determination result of the on-orbit satellite R is less than 10, and the root mean square RMS of the velocity measurement data in the orbit determination result of the on-orbit satellite V is less than 10; Among the satellite navigation data, the usage rate of GNSS data is greater than 80%, and the root mean square (RMS) of the satellite navigation data in the orbit determination result of the on-orbit satellite G is less than 25; The orbit epoch is consistent with that sent the previous day.

7. The verification method for satellite orbit determination according to claim 3, wherein, For type D satellites: In the data arc segment, when performing post-control orbit determination, it is greater than 1 day, and the atmospheric drag coefficient CD is not solved during post-control orbit determination; during normal operation, it is greater than 1 day, and the atmospheric drag coefficient CD is not solved during normal operation; In the initial orbit improvement amount, the absolute value of the difference between the orbital semi-major axis of the orbit determination result of the on-orbit satellite and the initial orbit used for orbit determination is: |Δa| < 10 m; the absolute value of the difference between the spatial position of the orbit determination result of the on-orbit satellite and the initial orbit used for orbit determination is: |ΔP| < 1000 m; In the total orbit determination data utilization rate, both the ranging and velocity measurement are greater than 90%; Among the total orbit determination data residuals, the root mean square RMS of the ranging data in the orbit determination result of the on-orbit satellite R is less than 10, and the root mean square RMS of the velocity measurement data in the orbit determination result of the on-orbit satellite V is less than 10; In the utilization rate of the latest circle data, both the ranging and velocity measurement are greater than 90%; Among the residuals of the latest circle data, the root mean square RMS of the ranging data in the orbit determination result of the on-orbit satellite R is less than 10, and the root mean square RMS of the velocity measurement data in the orbit determination result of the on-orbit satellite V is less than 10; Among the satellite navigation data, the usage rate of GNSS data is greater than 80%, and the root mean square (RMS) of the satellite navigation data in the orbit determination result of the on-orbit satellite G is less than 25; The orbit epoch is consistent with that sent the previous day.

8. The verification method for satellite orbit determination according to claim 1, wherein, In the step of dividing each of the on-orbit satellites into different categories according to the orbital altitude of each on-orbit satellite and determining the orbit determination result of each on-orbit satellite, the orbital altitude h of each on-orbit satellite is the difference between the semi-major axis of the on-orbit satellite and the equatorial radius of the Earth.

9. The verification method for satellite orbit determination according to claim 1, wherein, If the orbit determination result does not meet the orbit determination accuracy requirements, continue with the orbit determination optimization strategy, repeat the process of satellite orbit determination and automatic verification until the orbit determination result meets the orbit determination accuracy requirements, and then continue to complete the release process of the orbit determination result; Or in the step of transferring to manual processing after the orbit determination optimization strategy can no longer solve the problem, the abnormal situations where the satellite orbit determination result does not meet the orbit determination accuracy requirements include: Situation 1: The utilization rate of the latest circle data is low or the residuals exceed the limit; Situation 2: The total residuals of the ranging data or velocity measurement data in the satellite orbit determination result are too large or the percentage of rejected data is too high; Situation 3: The atmospheric damping coefficient exceeds the limit; Situation 4: The change amount of the satellite orbit improvement result compared to the orbit initial value exceeds the limit; Situation 5: All satellite orbit determinations are rejected.

10. The verification method for satellite orbit determination according to claim 9, wherein, If the orbit determination result does not meet the orbit determination accuracy requirements, continue with the orbit determination optimization strategy, repeat the satellite orbit determination and automatic verification process until the orbit determination result meets the orbit determination accuracy requirements, and then continue with the orbit determination result release process; or in the step of transferring to manual processing after the orbit determination optimization strategy can no longer solve the problem, If it is Case 1, the orbit determination optimization strategy includes re-performing preprocessing of external measurement data submission, warehousing, downloading data, and starting orbit calculation; If it is Case 2, the orbit determination optimization strategy includes viewing the first orbit improvement process, comparing and performing systematic error resolution on the measurement station data with large initial orbit residuals, and starting orbit calculation; If it is Case 3, the orbit determination optimization strategy includes setting the atmospheric damping coefficient as not to be resolved or a fixed value in the menu and starting orbit calculation; If it is Case 4, the orbit determination optimization strategy includes performing systematic error resolution on the measurement station data with large residuals in the zero-th iteration or appropriately shortening the length of the orbit determination arc segment, and starting orbit calculation; If it is Case 5, the orbit determination optimization strategy includes resetting the data arc segment length and starting orbit calculation.

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