A method and device for optimizing the high-orbit satellite orbit change detection process

Abstract

The present invention discloses a method and device for optimizing the high-orbit satellite orbit change detection process. By optimizing the detection process, a batch of satellites with orbital anomalies in observation data can be quickly screened out, reducing the time and labor costs of analysis and judgment, improving the timeliness of the entire discovery process, and facilitating timely and rapid discovery of orbital anomalies of high-orbit satellites.

Description

Technical Field

[0001] The present invention relates to the field of data technology, and in particular to a method and device for optimizing a high-orbit satellite orbit change detection process. Background Art

[0002] At present, the geosynchronous orbit is valued by all countries as an important strategic resource. Due to the characteristics of this orbit, it has unique advantages in agriculture, meteorology, communications, science and national defense, which greatly improves human productivity. However, synchronous orbit satellites are often affected by external factors during operation, causing changes in satellite orbits. In order to timely detect changes in satellite orbits, it is necessary to image the satellite through ground-based photoelectric detection and other means, and process the captured image data. At present, the observation data analysis process is cumbersome, and the discovery and analysis of abnormal behaviors are mostly based on manual processing, which is slow and inefficient. A large amount of observation data is accumulated in the storage space, and it is extremely inefficient to analyze and process them one by one to determine the orbit change situation. Therefore, a method and device for optimizing the high-orbit satellite orbit change detection process is provided, which is conducive to timely and rapid discovery of orbital anomalies of high-orbit satellites. Summary of the invention

[0003] The technical problem to be solved by the present invention is to provide a method and device for optimizing the high-orbit satellite orbit change detection process, which is conducive to timely and rapid detection of orbital anomalies of high-orbit satellites.

[0004] In order to solve the above technical problems, the first aspect of the embodiment of the present invention discloses a method for optimizing a high-orbit satellite orbit change detection process, the method comprising:

[0005] S1, obtaining first orbital data information, orbit determination threshold, first position, and second position of the satellite to be processed; the first orbital data information includes N orbital data information; N is a positive integer; the N orbital data information are arranged in order according to time, and each orbital data information corresponds to a time point;

[0006] S2, performing fusion processing on the first orbit data information to obtain orbit determination variance information;

[0007] S3, determining whether the orbit determination variance information is greater than the orbit determination threshold, and obtaining a determination result;

[0008] When the judgment result is no, execute S4;

[0009] When the judgment result is yes, execute S5;

[0010] S4, performing untracked fusion processing on the first track data information to obtain untracked data information, storing the untracked data information in the first position, and ending the process;

[0011] S5, performing orbit change fusion processing on the first orbit data information to obtain orbit change data information, and storing the orbit change data information into the second position.

[0012] As an optional implementation manner, in the first aspect of the embodiment of the present invention, the fusing process of the first orbit data information to obtain orbit determination variance information includes:

[0013] S21, preprocessing the first track data information to obtain preprocessed track data information;

[0014] S22, performing orbit determination data processing on the pre-processed orbit data information to obtain orbit determination information;

[0015] S23, analyzing and calculating the orbit determination information to obtain orbit determination variance information.

[0016] As an optional implementation manner, in the first aspect of the embodiment of the present invention, performing untracked fusion processing on the first track data information to obtain untracked data information, and storing the untracked data information in the first position includes:

[0017] S41, performing graphic element processing on the first track data information to obtain data information without track change;

[0018] S42, storing the unchanged track data information into the first position.

[0019] As an optional implementation manner, in the first aspect of the embodiment of the present invention, performing track change fusion processing on the first track data information to obtain track change data information, and storing the track change data information in the second position includes:

[0020] S51, determining a first time point and a second time point based on the first track data information;

[0021] S52, using the first time point and the second time point, performing fusion processing on the first track data information to obtain second track data information and third track data information;

[0022] S53, determining track change data information based on the first track data information, the second track data information and the third track data information;

[0023] S54, storing the track change data information into the second location.

[0024] As an optional implementation manner, in the first aspect of the embodiment of the present invention, determining the first time point and the second time point based on the first track data information includes:

[0025] S511, performing calculation processing on the first orbit data information to obtain first orbit determination data information;

[0026] S512, performing calculation processing on the first orbit determination data information to obtain second orbit determination data information;

[0027] S513: Determine a first time point and a second time point based on the second orbit determination data information.

[0028] As an optional implementation manner, in the first aspect of the embodiment of the present invention, the using the first time point and the second time point to fuse the first orbital data information to obtain the second orbital data information and the third orbital data information includes:

[0029] S521, calculating and processing the orbital data information corresponding to the first time point and the orbital data information corresponding to the second time point to obtain a first orbital data value and a second orbital data value;

[0030] S522, determining whether the first track data value is greater than 0, and obtaining a first determination result;

[0031] When the first judgment result is yes, determining that the track data information corresponding to the time point before the first time point is the termination track data information;

[0032] When the first judgment result is no, determining that the track data information corresponding to the first time point is the termination track data information;

[0033] S523, determining whether the second track data value is greater than 0, and obtaining a second determination result;

[0034] When the second judgment result is yes, determining that the orbit data information corresponding to the second time point is the starting orbit data information;

[0035] When the second judgment result is no, determining that the orbit data information corresponding to the time point after the second time point is the starting orbit data information;

[0036] S524, determining second track data information based on the first track data information and the termination track data information;

[0037] S525: Determine third track data information based on the first track data information and the start track data information.

[0038] As an optional implementation manner, in the first aspect of the embodiment of the present invention, determining the track change data information based on the first track data information, the second track data information and the third track data information includes:

[0039] S531, processing the first track data information, the second track data information and the third track data information to obtain fourth track data information;

[0040] S532, performing graphic element processing on the fourth track data information to obtain track change data information.

[0041] A second aspect of an embodiment of the present invention discloses a high-orbit satellite orbit change detection process optimization device, characterized in that the device comprises:

[0042] An acquisition module, used to acquire first orbit data information, orbit determination threshold, first position, and second position of the satellite to be processed;

[0043] The first orbital data information includes N orbital data information; N is a positive integer; the N orbital data information are arranged in order according to time, and each orbital data information corresponds to a time point;

[0044] A first calculation module is used to perform fusion processing on the first orbit data information to obtain orbit determination variance information;

[0045] A judgment module, used to judge whether the orbit determination variance information is greater than the orbit determination threshold, and obtain a judgment result;

[0046] When the judgment result is no, executing the second calculation module;

[0047] When the judgment result is yes, executing the third calculation module;

[0048] A second calculation module is used to perform un-track-changed fusion processing on the first track data information to obtain un-track-changed data information, store the un-track-changed data information in the first position, and end the process;

[0049] The third calculation module is used to perform orbit change fusion processing on the first orbit data information to obtain orbit change data information, and store the orbit change data information into the second position.

[0050] A third aspect of an embodiment of the present invention discloses another device for optimizing a high-orbit satellite orbit change detection process, wherein the device comprises:

[0051] processor;

[0052] a memory coupled to the processor and storing executable program code;

[0053] The processor calls the executable program code stored in the memory to execute part or all of the steps of the high-orbit satellite orbit change detection process optimization method disclosed in the first aspect of an embodiment of the present invention.

[0054] Compared with the prior art, the embodiments of the present invention have the following beneficial effects:

[0055] This application is conducive to timely and rapid discovery of orbital anomalies of high-orbit satellites, and realizes the automatic detection of satellite orbit changes by optimizing the orbit change detection process:

[0056] 1. The calculation process is greatly simplified, and the computer can automatically detect satellite orbit changes. Compared with manual work, the calculation efficiency and the timeliness of abnormal judgment are significantly improved;

[0057] 2. By optimizing the detection process, we can quickly filter out abnormal data and solve the problem of a large amount of observation data to be analyzed accumulating in the storage space;

[0058] 3. Through the design process, avoid the situation where all data are judged one by one to change the track time.

[0059] In an embodiment, first orbital data information, an orbit determination threshold, a first position, and a second position of a to-be-processed satellite are obtained; the first orbital data information includes N orbital data information; N is a positive integer; the N orbital data information are arranged in order according to time, and each orbital data information corresponds to a time point; the first orbital data information is fused to obtain orbit determination variance information; it is determined whether the orbit determination variance information is greater than the orbit determination threshold to obtain a determination result; when the determination result is no, the first orbital data information is fused without orbit change to obtain data information without orbit change, and the data information without orbit change is stored in the first position; when the determination result is yes, the first orbital data information is fused with orbit change to obtain data information with orbit change, and the data information with orbit change is stored in the second position. BRIEF DESCRIPTION OF THE DRAWINGS

[0060] In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the following briefly introduces the drawings required for use in the description of the embodiments. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0061] Figure 1 A schematic diagram of a process flow of a high-orbit satellite orbit change detection process optimization method disclosed in an embodiment of the present invention;

[0062] Figure 2A schematic diagram of the structure of a high-orbit satellite orbit change detection process optimization device disclosed in an embodiment of the present invention;

[0063] Figure 3 A schematic diagram of the structure of another high-orbit satellite orbit change detection process optimization device disclosed in an embodiment of the present invention. DETAILED DESCRIPTION

[0064] In order to enable those skilled in the art to better understand the scheme of the present invention, the technical scheme in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0065] The terms "first", "second", etc. in the specification and claims of the present invention and the above-mentioned drawings are used to distinguish different objects, rather than to describe a specific order. In addition, the terms "including" and "having" and any variations thereof are intended to cover non-exclusive inclusions. For example, a process, method, device, product or equipment that includes a series of steps or units is not limited to the listed steps or units, but may optionally include steps or units that are not listed, or may optionally include other steps or units that are inherent to these processes, methods, products or equipment.

[0066] Reference to "embodiments" herein means that a particular feature, structure, or characteristic described in conjunction with the embodiments may be included in at least one embodiment of the present invention. The appearance of the phrase in various places in the specification does not necessarily refer to the same embodiment, nor is it an independent or alternative embodiment that is mutually exclusive with other embodiments. It is explicitly and implicitly understood by those skilled in the art that the embodiments described herein may be combined with other embodiments.

[0067] The present invention discloses a method and device for optimizing the high-orbit satellite orbit change detection process, which is conducive to timely and rapid discovery of orbital abnormality information of high-orbit satellites. Detailed descriptions are given below.

[0068] Embodiment 1

[0069] See also Figure 1 , Figure 1 1 is a flow chart of a method for optimizing a high-orbit satellite orbit change detection process disclosed in an embodiment of the present invention. Figure 1 The described high-orbit satellite orbit change detection process optimization method is applied to a high-orbit satellite orbit change detection process optimization device, such as a local server or cloud server for high-orbit satellite orbit change detection process optimization management, and the embodiments of the present invention are not limited. Figure 1As shown, the high-orbit satellite orbit change detection process optimization method may include the following operations:

[0070] S1, obtaining first orbital data information, orbit determination threshold, first position, and second position of the satellite to be processed; the first orbital data information includes N orbital data information; N is a positive integer; the N orbital data information are arranged in order according to time, and each orbital data information corresponds to a time point;

[0071] S2, performing fusion processing on the first orbit data information to obtain orbit determination variance information;

[0072] S3, determining whether the orbit determination variance information is greater than the orbit determination threshold, and obtaining a determination result;

[0073] When the judgment result is no, execute S4;

[0074] When the judgment result is yes, execute S5;

[0075] S4, performing untracked fusion processing on the first track data information to obtain untracked data information, storing the untracked data information in the first position, and ending the process;

[0076] S5, performing orbit change fusion processing on the first orbit data information to obtain orbit change data information, and storing the orbit change data information into the second position.

[0077] It should be noted that the first orbital data information is obtained through a photoelectric detection device, and the station information of the photoelectric detection device includes a station number, a device number, a station name, geodetic longitude, geodetic latitude and altitude.

[0078] It should be noted that the first position represents a computer storage position for storing the non-track change data information;

[0079] It should be noted that the second position represents a computer storage position, which is used to store the track change data information.

[0080] It should be noted that the first position and the second position may be set by a user or determined based on historical experience, and the embodiment of the present invention does not specifically limit this.

[0081] Implementing the high-orbit satellite orbit change detection process optimization method described in the embodiment of the present invention is conducive to timely and rapid discovery of orbital anomaly information of high-orbit satellites.

[0082] In an optional embodiment, the step of fusing the first orbit data information to obtain orbit determination variance information includes:

[0083] S21, preprocessing the first track data information to obtain preprocessed track data information;

[0084] S22, performing orbit determination data processing on the pre-processed orbit data information to obtain orbit determination information;

[0085] S23, analyzing and calculating the orbit determination information to obtain orbit determination variance information.

[0086] It should be noted that the preprocessing of the first orbital data information to obtain the preprocessed orbital data information includes unifying the data format of the first orbital data, detecting and correcting observation value interruptions caused by signal loss or other reasons;

[0087] It should be noted that the orbit determination information is obtained by performing orbit determination data processing on the pre-processed orbit data information, and a dynamic model of the satellite is established through factors such as the earth's gravitational field, the gravity of the sun and the moon, the solar radiation pressure, and the atmospheric resistance, and the orbit determination information is obtained by calculating the mathematical model, which is not limited in detail in the embodiment of the present invention;

[0088] It should be noted that the orbit determination information is analyzed and calculated to obtain the orbit determination variance information, which is obtained by comparing the predicted orbit data with the actual observation data, analyzing the orbit determination error, and obtaining the orbit determination variance.

[0089] It should be noted that the above S21-S23 are all obtained using existing technologies.

[0090] Implementing the high-orbit satellite orbit change detection process optimization method described in the embodiment of the present invention is conducive to timely and rapid discovery of orbital anomaly information of high-orbit satellites.

[0091] In another optional embodiment, performing untracked fusion processing on the first track data information to obtain untracked data information, and storing the untracked data information in the first position includes:

[0092] S41, performing graphic element processing on the first track data information to obtain data information without track change;

[0093] S42, storing the unchanged track data information into the first position.

[0094] It should be noted that the first track data information is processed into a graphic element to obtain the data information without track change, which is to convert the first track data information into data in CSV, JSON or other formats, and use a graphic element software tool such as GIS to draw the converted data information, and set the color, width, transparency and other styles of the data elements in the drawing according to the user's needs. Finally, according to the visualization results, necessary adjustments are made to ensure that the trajectory is clear and correct, and finally the data after the first track data information is processed into a graphic element, that is, the data information without track change, is obtained. If the first track data information is converted into a visual scatter plot, each scatter point represents one of the track data information in the first track data information, and its position in the coordinate system reflects its value on these variables.

[0095] Implementing the high-orbit satellite orbit change detection process optimization method described in the embodiment of the present invention is conducive to timely and rapid discovery of orbital anomaly information of high-orbit satellites.

[0096] In yet another optional embodiment, performing track change fusion processing on the first track data information to obtain track change data information, and storing the track change data information in the second position includes:

[0097] S51, determining a first time point and a second time point based on the first track data information;

[0098] S52, using the first time point and the second time point, performing fusion processing on the first track data information to obtain second track data information and third track data information;

[0099] S53, determining track change data information based on the first track data information, the second track data information and the third track data information;

[0100] S54, storing the track change data information into the second location.

[0101] Implementing the high-orbit satellite orbit change detection process optimization method described in the embodiment of the present invention is conducive to timely and rapid discovery of orbital anomaly information of high-orbit satellites.

[0102] In an optional embodiment, determining the first time point and the second time point based on the first track data information includes:

[0103] S511, performing calculation processing on the first orbit data information to obtain first orbit determination data information;

[0104] It should be noted that the first orbit data information is calculated and processed to obtain the first orbit determination data information, which can be obtained by processing using an orbit data information processing method set by a user, or by calculating and processing using a first orbit determination model, and the embodiment of the present invention does not make any specific limitation.

[0105] Wherein, the first orbit determination model is:

[0106]

[0107] Where, d i is the first orbit determination information corresponding to the i-th time point in the first orbit determination data information, n is the sliding window, a j is the jth weight coefficient, b i+j is the track data information corresponding to the i+jth time point in the first track data information, b i is the orbital data information corresponding to the i-th time point in the first orbital data information;

[0108] It should be noted that the sliding window, the j and the a j It can be set by the user or calculated based on historical data, and this embodiment does not make any specific limitation.

[0109] S512, performing calculation processing on the first orbit determination data information to obtain second orbit determination data information;

[0110] It should be noted that the first orbit determination data information is calculated and processed to obtain the second orbit determination data information, which can be obtained by processing using an orbit data information processing method set by a user, or by calculating and processing using a second orbit determination model, and the embodiment of the present invention does not make any specific limitation.

[0111] Wherein, the second orbit determination model is:

[0112]

[0113] In the formula, e k is the second orbit determination information corresponding to the kth time point in the second orbit determination data information, d k is the first orbit determination information corresponding to the kth time point in the first orbit determination data information, N is the total number of the first orbit determination information in the first orbit determination data information, δ1 and δ2 are respectively a first weight factor and a second weight factor;

[0114] It should be noted that the first weight factor and the second weight factor may be set by a user or obtained based on historical data, and this embodiment does not make any specific limitation thereto.

[0115] S513: Determine a first time point and a second time point based on the second orbit determination data information.

[0116] Implementing the high-orbit satellite orbit change detection process optimization method described in the embodiment of the present invention is conducive to timely and rapid discovery of orbital anomaly information of high-orbit satellites.

[0117] In another optional embodiment, determining the first time point and the second time point based on the second orbit determination data information includes:

[0118] S5131, using a fifth orbit determination model, calculating and processing the second orbit determination data information to obtain first threshold information;

[0119] Among them, the fifth orbit determination model is:

[0120]

[0121] In the formula, p q is the threshold information corresponding to the qth time point in the first threshold information, e q and e q-1 is the second orbit determination information corresponding to the qth and q-1th time points in the second orbit determination data information, T q and T q-1 are the qth and q-1th time points, w1 and w2 are the third weighting factor and the fourth weighting factor;

[0122] It should be noted that the third weight factor and the fourth weight factor may be set by a user or obtained based on historical data, and this embodiment does not specifically limit this.

[0123] S5132, obtaining a second threshold;

[0124] S5133, determining whether the threshold information corresponding to any time point in the first threshold information is greater than the second threshold, and obtaining a third determination result;

[0125] When the third judgment result is yes, adding the threshold information corresponding to the time point in the first threshold information to the first track change data set;

[0126] S5134, sorting the threshold information in the track change data set according to the time point to obtain a second track change data set;

[0127] S5135, determining that the time point corresponding to the first threshold information in the second track change data set is the first time point;

[0128] S5136: Determine that the time point corresponding to the last threshold information in the second track change data set is the second time point.

[0129] Implementing the high-orbit satellite orbit change detection process optimization method described in the embodiment of the present invention is conducive to timely and rapid discovery of orbital anomaly information of high-orbit satellites.

[0130] In an optional embodiment, the using the first time point and the second time point to fuse the first orbit data information to obtain the second orbit data information and the third orbit data information includes:

[0131] S521, calculating and processing the orbital data information corresponding to the first time point and the orbital data information corresponding to the second time point to obtain a first orbital data value and a second orbital data value;

[0132] It should be noted that the orbital data information corresponding to the first time point and the orbital data information corresponding to the second time point are calculated and processed to obtain the first orbital data value and the second orbital data value. This may be obtained by processing using an orbital data information processing method set by a user, or by calculating and processing using a third orbit determination model, and this embodiment of the present invention does not make any specific limitation.

[0133] Wherein, the third orbit determination model is:

[0134] f1=|g1-g 11 |-|g1-g 12 |;

[0135] f2=|g2-g 21 |-|g2-g 22 |;

[0136] Wherein, f1 and f2 are the first orbital data value and the second orbital data value, g1 and g2 are the orbital data information corresponding to the first time point and the orbital data information corresponding to the second time point, and g 11 and g 12 are the track data information corresponding to the time point before and after the first time point, respectively, 21 and g 22 are the track data information corresponding to the time point before and after the second time point, respectively, and || represents an absolute value;

[0137] S522, determining whether the first track data value is greater than 0, and obtaining a first determination result;

[0138] When the first judgment result is yes, determining that the track data information corresponding to the time point before the first time point is the termination track data information;

[0139] When the first judgment result is no, determining that the track data information corresponding to the first time point is the termination track data information;

[0140] S523, determining whether the second track data value is greater than 0, and obtaining a second determination result;

[0141] When the second judgment result is yes, determining that the orbit data information at the second time point is the starting orbit data information;

[0142] When the second judgment result is no, determining that the orbit data information corresponding to the time point after the second time point is the starting orbit data information;

[0143] S524, determining second track data information based on the first track data information and the termination track data information;

[0144] S525: Determine third track data information based on the first track data information and the start track data information.

[0145] It should be noted that, based on the first orbital data information and the termination orbital data information, the second orbital data information is determined, and all data from the first orbital data information to the termination orbital data information of the first orbital data information are extracted to obtain the second orbital data information. For example, the first orbital data information is {α1, α2, α3, α4, α5, α6, α7, α8}, and the termination orbital data information is α5, then the second orbital data information is {α1, α2, α3, α4, α5}.

[0146] It should be noted that, based on the first orbital data information and the starting orbital data information, the third orbital data information is determined by extracting the orbital data information from the starting orbital data information to the last one of the first orbital data information to obtain the third orbital data information. For example, the first orbital data information is {α1, α2, α3, α4, α5, α6, α7, α8}, and the starting orbital data information is α7, then the third orbital data information is {α7, α8}.

[0147] Implementing the high-orbit satellite orbit change detection process optimization method described in the embodiment of the present invention is conducive to timely and rapid discovery of orbital anomaly information of high-orbit satellites.

[0148] In an optional embodiment, determining the track change data information based on the first track data information, the second track data information, and the third track data information includes:

[0149] S531, processing the first track data information, the second track data information and the third track data information to obtain fourth track data information;

[0150] It should be noted that the first orbital data information, the second orbital data information and the third orbital data information are processed to obtain the fourth orbital data information, which can be obtained by processing using an orbital data information processing method set by a user or by calculating and processing using a fourth orbit determination model, and the embodiment of the present invention does not make any specific limitation.

[0151] Wherein, the fourth orbit determination model is:

[0152] S = X - (Y ∪ Z);

[0153] Wherein, S is the fourth track data information, X, Y, and Z are the first track data information, the second track data information, and the third track data information, respectively;

[0154] S532, performing graphic element processing on the fourth track data information to obtain track change data information.

[0155] It should be noted that the fourth track data information is processed into a graphic element to obtain the data information without track change, which is to convert the fourth track data information into data in CSV, JSON or other formats, and use a graphic element software tool such as GIS to draw the converted data information, and set the color, width, transparency and other styles of the data elements in the drawing according to the needs of the user. Finally, according to the visualization results, necessary adjustments are made to ensure that the trajectory is clear and correct, and finally the data after the fourth track data information is processed into a graphic element, that is, the data information without track change is obtained. If the fourth track data information is converted into a visual scatter plot, each scatter point represents one of the track data information in the fourth track data information, and its position in the coordinate system reflects its value on these variables.

[0156] Implementing the high-orbit satellite orbit change detection process optimization method described in the embodiment of the present invention is conducive to timely and rapid discovery of orbital anomaly information of high-orbit satellites.

[0157] Embodiment 2

[0158] See also Figure 2 , Figure 2 1 is a schematic diagram of the structure of a high-orbit satellite orbit change detection process optimization device disclosed in an embodiment of the present invention. Figure 2The described high-orbit satellite orbit change detection process optimization device is applied to a high-orbit satellite orbit change detection process optimization system, such as a local server or cloud server for high-orbit satellite orbit change detection process optimization, and the embodiments of the present invention are not limited thereto. Figure 2 As shown, the high-orbit satellite orbit change detection process optimization device includes:

[0159] An acquisition module 201 is used to acquire first orbit data information, orbit determination threshold, first position, and second position of a satellite to be processed;

[0160] The first orbital data information includes N orbital data information; N is a positive integer; the N orbital data information are arranged in order according to time, and each orbital data information corresponds to a time point;

[0161] A first calculation module 202 is used to perform fusion processing on the first orbit data information to obtain orbit determination variance information;

[0162] A judgment module 203 is used to judge whether the orbit determination variance information is greater than the orbit determination threshold, and obtain a judgment result;

[0163] When the judgment result is no, executing the second calculation module 204;

[0164] When the judgment result is yes, executing the third calculation module 205;

[0165] A second calculation module 204 is used to perform un-track-changed fusion processing on the first track data information to obtain un-track-changed data information, store the un-track-changed data information in the first position, and end the process;

[0166] The third calculation module 205 is used to perform orbit change fusion processing on the first orbit data information to obtain orbit change data information, and store the orbit change data information into the second position.

[0167] Implementing the high-orbit satellite orbit change detection process optimization device described in the embodiment of the present invention is conducive to timely and rapid discovery of orbital anomaly information of high-orbit satellites.

[0168] Embodiment 3

[0169] See also Figure 3 , Figure 3 1 is a schematic diagram of another high-orbit satellite orbit change detection process optimization device disclosed in an embodiment of the present invention. Figure 3 The described high-orbit satellite orbit change detection process optimization device is applied to a high-orbit satellite orbit change detection process optimization system, such as a local server or cloud server for high-orbit satellite orbit change detection process optimization, and the embodiments of the present invention are not limited thereto. Figure 3As shown, the high-orbit satellite orbit change detection process optimization device includes:

[0170] Processor 301;

[0171] A memory 302 coupled to the processor 301 and storing executable program codes;

[0172] The processor 301 calls the executable program code stored in the memory 302 to execute some or all of the steps in the high-orbit satellite orbit change detection process optimization method described in Example 1.

[0173] Implementing the high-orbit satellite orbit change detection process optimization device described in the embodiment of the present invention is conducive to timely and rapid discovery of orbital anomaly information of high-orbit satellites.

[0174] Embodiment 4

[0175] An embodiment of the present invention discloses a computer program product, which includes a non-transitory computer-readable storage medium storing a computer program, and the computer program is operable to enable a computer to execute part or all of the steps in the high-orbit satellite orbit change detection process optimization method described in Example 1.

[0176] The system embodiments described above are only illustrative, wherein the modules described as separate components may or may not be physically separated, and the components displayed as modules may or may not be physical modules, i.e., they may be located in one place, or they may be distributed on multiple network modules. Some or all of the modules may be selected according to actual needs to achieve the purpose of the scheme of this embodiment. Those of ordinary skill in the art may understand and implement it without creative labor.

[0177] Through the specific description of the above embodiments, those skilled in the art can clearly understand that each implementation method can be implemented by means of software plus a necessary general hardware platform, and of course, it can also be implemented by hardware. Based on such an understanding, the above technical solution can be essentially or partly contributed to the prior art in the form of a software product, and the computer software product can be stored in a computer-readable storage medium, and the storage medium includes a read-only memory (ROM), a random access memory (RAM), a programmable read-only memory (PROM), an erasable programmable read-only memory (EPROM), a one-time programmable read-only memory (OTPROM), an electronically erasable rewritable read-only memory (EEPROM), a compact disc (CD-ROM) or other optical disc storage, magnetic disk storage, magnetic tape storage, or any other computer-readable medium that can be used to carry or store data.

[0178] Finally, it should be noted that the method and device for optimizing the high-orbit satellite orbit change detection process disclosed in the embodiment of the present invention only discloses the preferred embodiments of the present invention, which are only used to illustrate the technical scheme of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that the technical schemes described in the aforementioned embodiments can still be modified, or some of the technical features therein can be replaced by equivalents. However, these modifications or replacements do not deviate the essence of the corresponding technical schemes from the spirit and scope of the technical schemes of the various embodiments of the present invention.

Claims

1. A method for optimizing the high-orbit satellite orbit change detection process, characterized in that: The method comprises: S1, obtaining first orbital data information, orbit determination threshold, first position, and second position of the satellite to be processed; the first orbital data information includes N orbital data information; N is a positive integer; the N orbital data information are arranged in order according to time, and each orbital data information corresponds to a time point; S2, performing fusion processing on the first orbit data information to obtain orbit determination variance information; S3, determining whether the orbit determination variance information is greater than the orbit determination threshold, and obtaining a determination result; When the judgment result is no, execute S4; When the judgment result is yes, execute S5; S4, performing untracked fusion processing on the first track data information to obtain untracked data information, storing the untracked data information in the first position, and ending the process; S5, performing orbit change fusion processing on the first orbit data information to obtain orbit change data information, and storing the orbit change data information in the second position; The performing track change fusion processing on the first track data information to obtain track change data information, and storing the track change data information in the second position includes: S51, determining a first time point and a second time point based on the first track data information; S52, using the first time point and the second time point, performing fusion processing on the first track data information to obtain second track data information and third track data information; S53, determining track change data information based on the first track data information, the second track data information and the third track data information; S54, storing the track change data information into the second location; The determining the first time point and the second time point based on the first track data information includes: S511, performing calculation processing on the first orbit data information to obtain first orbit determination data information; S512, performing calculation processing on the first orbit determination data information to obtain second orbit determination data information; S513, determining a first time point and a second time point based on the second orbit determination data information; The calculating and processing the first orbit data information to obtain first orbit determination data information includes: Using a first orbit determination model, calculating and processing the first orbit data information to obtain first orbit determination data information; Wherein, the first orbit determination model is: Where, d i is the first orbit determination information corresponding to the i-th time point in the first orbit determination data information, n is the sliding window, a j is the jth weight coefficient, b i+j is the track data information corresponding to the i+jth time point in the first track data information, b i is the orbital data information corresponding to the i-th time point in the first orbital data information; The calculating and processing the first orbit determination data information to obtain second orbit determination data information includes: Using a second orbit determination model, calculating and processing the first orbit determination data information to obtain second orbit determination data information; Wherein, the second orbit determination model is: In the formula, e k is the second orbit determination information corresponding to the kth time point in the second orbit determination data information, d k is the first orbit determination information corresponding to the kth time point in the first orbit determination data information, N is the total number of the first orbit determination information in the first orbit determination data information, and δ1 and δ2 are the first weight factor and the second weight factor respectively.

2. The high-orbit satellite orbit change detection process optimization method according to claim 1 is characterized in that: The fusing the first orbit data information to obtain orbit determination variance information includes: S21, preprocessing the first track data information to obtain preprocessed track data information; S22, performing orbit determination data processing on the pre-processed orbit data information to obtain orbit determination information; S23, analyzing and calculating the orbit determination information to obtain orbit determination variance information.

3. The high-orbit satellite orbit change detection process optimization method according to claim 1 is characterized in that: The performing non-track-change fusion processing on the first track data information to obtain non-track-change data information, and storing the non-track-change data information in the first position includes: S41, performing graphic element processing on the first track data information to obtain data information without track change; S42, storing the unchanged track data information into the first position.

4. The high-orbit satellite orbit change detection process optimization method according to claim 1 is characterized in that: The step of fusing the first track data information using the first time point and the second time point to obtain second track data information and third track data information includes: S521, calculating and processing the orbital data information corresponding to the first time point and the orbital data information corresponding to the second time point to obtain a first orbital data value and a second orbital data value; S522, determining whether the first track data value is greater than 0, and obtaining a first determination result; When the first judgment result is yes, determining that the track data information corresponding to the time point before the first time point is the termination track data information; When the first judgment result is no, determining that the track data information corresponding to the first time point is the termination track data information; S523, determining whether the second track data value is greater than 0, and obtaining a second determination result; When the second judgment result is yes, determining that the orbit data information corresponding to the second time point is the starting orbit data information; When the second judgment result is no, determining that the orbit data information corresponding to the time point after the second time point is the starting orbit data information; S524, determining second track data information based on the first track data information and the termination track data information; S525: Determine third track data information based on the first track data information and the start track data information.

5. The high-orbit satellite orbit change detection process optimization method according to claim 1 is characterized in that: The determining the track change data information based on the first track data information, the second track data information and the third track data information includes: S531, processing the first track data information, the second track data information and the third track data information to obtain fourth track data information; S532, performing graphic element processing on the fourth track data information to obtain track change data information.

6. A high-orbit satellite orbit change detection process optimization device, characterized in that: The device comprises: processor; a memory coupled to the processor and storing executable program code; The processor calls the executable program code stored in the memory to execute the high-orbit satellite orbit change detection process optimization method as described in any one of claims 1-5.

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