Processing method, device and electronic equipment for high-orbit satellite orbit determination

Abstract

The present invention provides a processing method, device and electronic equipment for high-orbit satellite orbit determination, which relate to the field of satellite remote sensing technology. The processing method comprises: parsing onboard receiver data to obtain arc segment time; performing at least one of the following operations to obtain high-orbit satellite orbit determination data: delaying a predetermined time after the arc segment time, starting a post-precision orbit determination processing flow to produce post-precision orbit determination data and a first orbit description file; in response to the completion of downloading required real-time precision ephemeris data, starting a real-time precision orbit determination processing flow to complete the production of real-time precision orbit determination data within the arc segment time and a second orbit description file; after the real-time precision orbit determination processing flow is completed, starting a predicted precision orbit processing flow to predict and obtain predicted precision orbit determination data within a preset time period after the arc segment time and a third orbit description file.

Description

Technical Field

[0001] The present invention relates to the field of satellite remote sensing technology, and in particular to a processing method, device and electronic equipment for high-orbit satellite orbit determination. Background Art

[0002] Most satellites in remote sensing satellite processing use the traditional orbit determination method, that is, obtaining single-point observation values ​​such as pseudorange and carrier phase based on the onboard GPS receiver, combined with the dynamic model, and using filtering to obtain the satellite's orbit determination information. In actual satellite flight, the initial state of the satellite is unknown. Affected by multiple factors such as the earth's gravity field and atmospheric resistance, the physical constants in its differential equation of motion and the model itself will have errors, which makes its dynamic model not only complex but also highly nonlinear. The achievable orbit determination accuracy is low, and there is a deviation between the calculated orbit and the satellite's true orbit, which cannot meet the current high-resolution satellite's orbit determination capability requirements. Therefore, in order to obtain orbit data as close to the real orbit as possible, it is necessary to track and observe the satellite, and estimate the satellite's initial state and related physical parameters by combining the geometric information of satellite tracking and the dynamic information of satellite motion. Therefore, with the development of technology, in order to obtain higher quality product image data, more and more satellite processing systems are currently adding precise orbit determination processing.

[0003] Since the satellite orbit is high above the ground, it may be interfered by the natural environment (such as space radiation, electromagnetic environment, etc.) during operation, which places relatively high requirements on the reception of the onboard GPS receiver. During the actual satellite processing system test, the images of the onboard GPS-related data processing have blurred and defocused problems, and there are many data quality problems, which has caused great troubles in the subsequent use of images. Therefore, precise orbit determination data is used for subsequent data processing. Summary of the invention

[0004] In view of this, the present invention provides a processing method, device and electronic equipment for high-orbit satellite orbit determination, which are used to at least partially solve the above-mentioned technical problems.

[0005] One aspect of the present invention provides a processing method for high-orbit satellite orbit determination, including: parsing onboard receiver data to obtain arc segment time; performing at least one of the following operations to obtain high-orbit satellite orbit determination data: delaying a predetermined time after the arc segment time, starting a post-precision orbit determination processing flow to produce post-precision orbit determination data and a first orbit description file; in response to the completion of downloading required real-time precision ephemeris data, starting a real-time precision orbit determination processing flow to complete the production of real-time precision orbit determination data and a second orbit description file within the arc segment time; after the real-time precision orbit determination processing flow is completed, starting a predicted precision orbit processing flow to predict and obtain predicted precision orbit determination data and a third orbit description file within a preset time period after the arc segment time.

[0006] According to an embodiment of the present invention, obtaining high-orbit satellite orbit determination data also includes: obtaining the perturbation force exerted on the high-orbit satellite in an inertial system, the perturbation force including conservative force, non-conservative force and empirical force, the empirical force being used to represent the error between the perturbation force model and the corresponding real perturbation force or the unmodeled perturbation force; determining the high-orbit satellite orbit determination data based on the conservative force, non-conservative force and empirical force.

[0007] According to an embodiment of the present invention, the method further includes: setting a priority of the orbit determination processing flow; and obtaining high-orbit satellite orbit determination data based on the priority.

[0008] According to an embodiment of the present invention, when the priority is the first priority, obtaining the high-orbit satellite orbit determination data includes: first starting the post-precision orbit determination processing flow to produce the post-precision orbit determination data and the first orbit description file, then starting the real-time precision orbit determination processing flow to complete the production of the real-time precision orbit determination data and the second orbit description file within the arc time, and finally starting the predicted precision orbit processing flow to predict and obtain the predicted precision orbit determination data and the third orbit description file within a preset time period after the arc time.

[0009] According to an embodiment of the present invention, when the priority is the second priority, obtaining high-orbit satellite orbit determination data includes: starting a post-precision orbit determination processing flow to generate post-precision orbit determination data and a first orbit description file.

[0010] According to an embodiment of the present invention, when the priority is the third priority, obtaining high-orbit satellite orbit determination data includes: starting a real-time precise orbit determination processing flow to complete the production of real-time precise orbit determination data and a second orbit description file within an arc segment time.

[0011] According to an embodiment of the present invention, when the priority is the fourth priority, obtaining high-orbit satellite orbit determination data includes: starting the predicted precise orbit processing flow to predict the predicted precise orbit determination data and the third orbit description file within a preset time period after the arc time.

[0012] According to an embodiment of the present invention, it also includes: configuring an operation interface, the operation interface is used for an interactive interface with a user, so that the user can edit, modify, import and select priorities.

[0013] Another aspect of the present invention provides a processing device for high-orbit satellite orbit determination, including: a parsing module, used to parse onboard receiver data to obtain arc segment time; a setting module, used to set the priority of the orbit determination processing flow; an execution module, used to perform at least one of the following operations based on the priority to obtain high-orbit satellite orbit determination data: delay a predetermined time after the arc segment time, start the post-precision orbit determination processing flow to produce post-precision orbit determination data and a first orbit description file; in response to the required real-time precision ephemeris data download completion, start the real-time precision orbit determination processing flow to complete the production of real-time precision orbit determination data and a second orbit description file within the arc segment time; after the real-time precision orbit determination processing flow ends, start the predicted precision orbit processing flow to predict and obtain the predicted precision orbit determination data and a third orbit description file within a preset time period after the arc segment time.

[0014] Another aspect of the present invention provides an electronic device, comprising: at least one processor; and a memory communicatively connected to the at least one processor; wherein the memory stores instructions executable by the at least one processor, and the instructions are executed by the at least one processor to enable the at least one processor to execute the above method.

[0015] The processing method, device and electronic device for high-orbit satellite orbit determination according to the embodiments of the present invention have at least the following beneficial effects:

[0016] By configuring three precise orbit determination processing tasks, it is possible to process the precise orbit determination data for the receiver platform data period and future periods, solving the problem of missing precise orbit determination data for some platform data due to quality issues, and has high fault tolerance. After completing the platform data analysis, the various types of precise ephemeris downloaded are scanned to complete the processing of the precise orbit determination tasks for the corresponding data, which has high timeliness. The three precise orbit determination processing tasks are all automatically retrieved by the system, and the processing tasks are automatically initiated, which reduces manual intervention and improves processing efficiency. The method and device complete multiple processes such as platform data source acquisition and analysis, automatic matching of precise ephemeris products, and automatic processing of multiple precise orbit determination, improving the modularization, automation, and standardization of the system's precise orbit determination processing tasks for high-orbit satellites.

[0017] When performing product tasks, different precise orbit determination data are intelligently matched according to the configured matching priority. The priority can be adjusted as needed, and different matching priorities are adopted for different levels of products. The priority follows the principle of optimal accuracy. According to the different timeliness requirements in the product processing process, the most accurate precise orbit determination data is selected to obtain the best high-precision image data. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] The above and other objects, features and advantages of the present invention will become more apparent through the following description of the embodiments of the present invention with reference to the accompanying drawings, in which:

[0019] Figure 1 A flowchart of a processing method for high-orbit satellite orbit determination according to an embodiment of the present invention is schematically shown;

[0020] Figure 2 A flowchart schematically shows the intelligent matching priority of precise orbit determination data of different products according to an embodiment of the present invention;

[0021] Figure 3 A diagram schematically showing an intelligent matching interface configuration diagram according to an embodiment of the present invention;

[0022] Figure 4 A structural block diagram of a processing system for high-orbit satellite orbit determination according to an embodiment of the present invention is schematically shown;

[0023] Figure 5 A structural block diagram of a processing device for high-orbit satellite orbit determination according to an embodiment of the present invention is schematically shown;

[0024] Figure 6 A block diagram of an electronic device suitable for implementing the method described above according to an embodiment of the present invention is schematically shown. DETAILED DESCRIPTION

[0025] Below, embodiments of the present invention will be described with reference to the accompanying drawings. However, it should be understood that these descriptions are exemplary only and are not intended to limit the scope of the present invention. In the following detailed description, for ease of explanation, many specific details are set forth to provide a comprehensive understanding of embodiments of the present invention. However, it is apparent that one or more embodiments may also be implemented without these specific details. In addition, in the following description, descriptions of known structures and technologies are omitted to avoid unnecessary confusion of concepts of the present invention.

[0026] The terms used herein are only for describing specific embodiments and are not intended to limit the present invention. The terms "comprise", "include", etc. used herein indicate the existence of the features, steps, operations and / or components, but do not exclude the existence or addition of one or more other features, steps, operations or components.

[0027] All terms (including technical and scientific terms) used herein have the meanings commonly understood by those skilled in the art unless otherwise defined. It should be noted that the terms used herein should be interpreted as having a meaning consistent with the context of this specification and should not be interpreted in an idealized or overly rigid manner.

[0028] When using expressions such as "at least one of A, B, and C, etc.", they should generally be interpreted according to the meaning of the expression commonly understood by those skilled in the art (for example, "a system having at least one of A, B, and C" should include but is not limited to a system having A alone, B alone, C alone, A and B, A and C, B and C, and / or A, B, C, etc.).

[0029] In the process of realizing the present invention, the applicant found that: in the related technology, during the processing of precise orbit determination data, the natural environment has a large interference on the onboard GNSS receiver, especially during the period of more active solar activity. Affected by the relevant radiation, the data quality is poor and some data cannot complete precise orbit determination, resulting in missing data in the data arc segment, and the image in the data arc segment cannot be processed with high precision. There is an urgent need to improve the fault tolerance of precise orbit determination; in order to cope with the high requirements for data timeliness in disaster prevention and mitigation work, it is required to provide high-precision image data at the hour level after the data is landed, and there is an urgent need to improve the processing efficiency of precise orbit determination; the traditional method of realizing high-orbit satellite precise orbit determination data processing has a complex processing process and is prone to introduce other new problems. There is an urgent need to improve the degree of automation of precise orbit determination data processing.

[0030] In view of this, an embodiment of the present invention provides a processing method for high-orbit satellite orbit determination. The processing method may include: parsing the satellite receiver data to obtain the arc segment time. Setting the priority of the orbit determination processing flow, and based on the priority, performing at least one of the following operations to obtain high-orbit satellite orbit determination data:

[0031] After the arc time, the predetermined time is delayed and the post-precision orbit determination processing flow is started to generate post-precision orbit determination data and the first orbit description file.

[0032] In response to the required real-time precise ephemeris data being downloaded, a real-time precise orbit determination processing flow is initiated to complete the production of the real-time precise orbit determination data and the second orbit description file during the arc segment time.

[0033] After the real-time precise orbit determination processing flow is completed, the predicted precise orbit determination processing flow is started to predict the predicted precise orbit determination data and the third orbit description file within a preset time period after the arc segment time.

[0034] This method performs real-time, post-event and predictive precise orbit determination processing on satellite platform data to ensure that the precise orbit determination data covers the entire product period, meets different image mission modes, completes high-precision and rapid data processing, improves processing efficiency, and ensures data timeliness.

[0035] The following is a detailed description with reference to specific embodiments.

[0036] Figure 1The flowchart of the processing method for high-orbit satellite orbit determination according to an embodiment of the present invention is schematically shown.

[0037] like Figure 1 As shown, in this embodiment, the precise ephemeris products can be divided into ultra-fast products, fast products and final products, with different timeliness and accuracy. The ultra-fast precise ephemeris product can be delayed by 2 hours, for example, with high timeliness; the fast precise ephemeris product can be delayed by 1-2 days, with slightly poor timeliness and good accuracy; the final precise ephemeris product can be delayed by 3-7 days, with poor timeliness but higher accuracy.

[0038] Since precise ephemeris can be divided into products with different timeliness, three processing procedures are set up in the precise orbit determination process: real-time (ROD), prediction (PRE), and post-event (POD) precise orbit determination to ensure all-weather coverage of precise orbit data, realize automated processing of precise orbit determination data, and ensure normal production of product data.

[0039] Real-time (ROD) precise orbit determination processing flow: Applicable to the real-time processing of digital raw data. After completing the platform data analysis, the real-time precise orbit determination processing is performed after retrieving the available ultra-fast precise ephemeris. The real-time precise orbit determination data accuracy can reach 5m-6m, with high timeliness, and is carried out simultaneously with the raw data processing.

[0040] Predictive (PRE) orbit determination process: After the real-time orbit determination process, the predicted orbit determination is performed, which has a lower accuracy (20m-50m), but is still much better than the on-board orbit data, has high timeliness, and is almost synchronized with the original data processing.

[0041] Post-OD precise orbit determination processing flow: Since the rapid and final precise ephemeris products can be delayed by 1-7 days, it is difficult to adapt to the real-time data processing requirements. Therefore, after a fixed period of platform data analysis, the available rapid or final precise ephemeris is retrieved for post-OD precise orbit determination. The precision of post-OD precise orbit determination can reach up to 3m-4m, which is better than real-time precise orbit determination, but has poor timeliness and cannot be synchronized with the original data processing.

[0042] In a possible implementation of this embodiment, during the data processing of the onboard GNSS receiver, after the data is parsed, the main information parameters such as the orbit number, mission number, platform data path, and arc time are obtained and saved in the platform information database table. Next, the real-time precise ephemeris data required for the arc time is scanned and matched through a scan matching program. If the required real-time precise ephemeris data has been downloaded, a real-time precise orbit determination process (ROD) is initiated to complete the production of real-time precise orbit determination data and orbit description files within the time arc (for example, 30 hours), and the orbit number, orbit determination time, orbit determination type and other information are stored in the precise orbit determination library table. The processing flag in the platform information database table is modified to avoid repeated processing.

[0043] In a possible implementation of this embodiment, the predicted precise orbit determination is a predicted precise orbit processing process (PRE) initiated after the real-time precise orbit determination is completed, which predicts the data of a preset time period (for example, 3 days) after the current time arc, generates predicted precise orbit determination data and orbit description files, and completes the storage management of the predicted precise orbit determination data.

[0044] In a possible implementation of this embodiment, the post-precision orbit determination is delayed because the final precise ephemeris product has a delay. Therefore, after a certain delay (determined by the production time of the final precise ephemeris), the final precise ephemeris data required for the time segment is scanned and matched. If the relevant data has been downloaded from the network, the post-precision orbit determination processing flow (POD) of the corresponding time segment (for example, 30 hours) is initiated. After the post-precision orbit determination data and orbit description file are produced, the data information is stored and managed.

[0045] Through the method of this embodiment, by configuring three precise orbit determination processing tasks, it is possible to process and obtain precise orbit determination data for the receiver platform data period and future period, solving the problem of missing precise orbit determination data for this period due to quality problems of some platform data, and having high fault tolerance. After completing the platform data analysis, the various types of precise ephemeris downloaded are scanned to complete the processing of the corresponding data precise orbit determination tasks, which has high timeliness. The three precise orbit determination processing tasks are all automatically retrieved by the system, and the processing tasks are automatically initiated, which reduces manual intervention and improves processing efficiency.

[0046] Based on the above embodiment, obtaining high-orbit satellite orbit determination data further includes:

[0047] The perturbation force on the high-orbit satellite in the inertial system is obtained. The perturbation force includes conservative force, non-conservative force and empirical force. The empirical force is used to represent the error between the perturbation force model and the corresponding real perturbation force or the perturbation force that has not been modeled.

[0048] The orbit determination data of high-orbit satellites are determined based on conservative force, non-conservative force and empirical force.

[0049] In this embodiment, during the precise orbit determination process, the satellite's motion equation can be used, that is, the satellite with a mass of m is affected by various perturbations in the inertial system. These perturbations include the conservative force , non-conservative force , Experience There are three types, among which the empirical force is used to represent the error between the perturbation force model and the corresponding real perturbation force or the perturbation force that is not modeled. Therefore, the instantaneous acceleration of the satellite at time t can be expressed as:

[0050]

[0051] Acceleration It is with time , satellite position vector , velocity vector and the model parameter vector By solving the first-order equation of its acceleration, the position and velocity vectors can be calculated. On this basis, the various forces such as the non-spherical perturbation force of the earth, N-body gravity, earth tides, general relativity effect, solar radiation pressure, earth reflected radiation pressure, atmospheric drag, satellite thrust, and empirical force can be introduced to accurately describe the model, and finally the precise orbit determination result can be calculated.

[0052] Through the processing method of the embodiment of the present invention, conservative force, non-conservative force and empirical force are introduced to accurately describe the model, so that more accurate high-orbit satellite orbit determination data can be obtained.

[0053] On the basis of the above embodiment, the processing method may further include, for example: setting the priority of the orbit determination processing flow and obtaining the high-orbit satellite orbit determination data based on the priority.

[0054] In this embodiment, since different products have different timeliness, usage rules can be formulated for the precise orbit determination data processing of different precise ephemeris products, that is, the priorities of different functions can be configured.

[0055] Figure 2 A flowchart of intelligent matching priorities of precise orbit determination data of different products according to an embodiment of the present invention is schematically shown.

[0056] like Figure 2As shown in the figure, the matching priority can be set according to the task types at each level. The matching priority can include the first priority (BEST), the second priority (POD), the third priority (ROD) and the fourth priority (PRE). When selecting and using the real-time (ROD), post-event (POD) and predicted (PRE) precise orbit determination data, it is configured according to the actual processing requirements of the satellite. The current system can adopt different registration priorities according to the timeliness requirements of different product levels, all of which follow the BEST precision optimization principle (preferentially select the post-event precise orbit determination data POD with the highest accuracy, select the real-time precise orbit determination data ROD if there is no post-event precise orbit determination data, and finally select the predicted precise orbit determination data PRE).

[0057] In some embodiments, when the priority is the first priority, obtaining high-orbit satellite orbit determination data includes:

[0058] First, the post-precision orbit determination processing flow is started to produce the post-precision orbit determination data and the first orbit description file, then the real-time precision orbit determination processing flow is started to complete the production of the real-time precision orbit determination data and the second orbit description file within the arc time, and finally the predicted precision orbit processing flow is started to predict the predicted precision orbit determination data and the third orbit description file within the preset time period after the arc time.

[0059] In some other embodiments, when the priority is the second priority, obtaining high-orbit satellite orbit determination data includes:

[0060] Start the post-precision orbit determination process to produce post-precision orbit determination data and the first orbit description file.

[0061] In some other embodiments, when the priority is the third priority, obtaining high-orbit satellite orbit determination data includes:

[0062] Start the real-time precise orbit determination processing flow to complete the production of real-time precise orbit determination data and the second orbit description file during the arc segment time.

[0063] In some other embodiments, when the priority is the fourth priority, obtaining high-orbit satellite orbit determination data includes:

[0064] The predicted precise orbit processing flow is started to predict the predicted precise orbit determination data and the third orbit description file within the preset time period after the arc segment time.

[0065] According to an embodiment of the present invention, real-time product processing is real-time processing of digital transmission data, and has high requirements for data timeliness. At this time, there is no post-precision high-precision orbit determination data, so real-time precise orbit determination data is preferentially matched and used. If there is no real-time precise orbit data, predicted precise orbit data is used to ensure that the data image is produced normally without blurring and defocusing problems. Post-product processing is a product task performed when the requirements for data timeliness are not high. At this time, post-precision orbit determination data is preferentially used. If there is no post-precision orbit data, real-time precise orbit data is used, and finally predicted orbit data is selected.

[0066] Based on the above embodiment, the processing method may further include:

[0067] The configuration operation interface is used for interaction with users so that they can edit, modify, import and select priorities.

[0068] Figure 3 The figure schematically shows a configuration diagram of an intelligent matching interface according to an embodiment of the present invention.

[0069] like Figure 3 As shown, the satellite list, satellite mode, matching parameters, mission type, matching priority and other parameters can be designed through the interface configuration method. The configuration interface is as shown below. The satellite list parameter represents the required satellite list for matching. The matching parameters are set to precise orbit determination data. The mission types include L0, L1, and L2 product production. The matching priorities include BEST, POD, ROD, and PRE. At the same time, the module supports the matching rule import function, which can be imported with one click through the configuration xml. The matching rules are determined by various parameters, and the back-end automatically parses and generates an automated matching program, which automatically matches data during data processing.

[0070] Based on the processing method for high-orbit satellite orbit determination in the above embodiment, an embodiment of the present invention further provides a processing system for high-orbit satellite orbit determination.

[0071] Figure 4 The structure block diagram of the processing system for high-orbit satellite orbit determination according to an embodiment of the present invention is schematically shown.

[0072] like Figure 4 As shown, the processing system for high-orbit satellite orbit determination includes a data monitoring subsystem, a management and scheduling subsystem, a data processing subsystem and a data management subsystem.

[0073] The data monitoring subsystem is responsible for data monitoring functions. It can also scan data and initiate related tasks. It can perform precise orbit determination tasks and product task orders through scanning data, and provide a visual data monitoring and task management interface. The data monitoring subsystem scans and monitors satellite platforms and precise ephemeris data.

[0074] The management and scheduling subsystem is used to parse the task order, perform automatic matching of multi-satellite data, trigger the corresponding task flow according to the matching results, and transfer the pre-processing job execution file to the management and scheduling subsystem.

[0075] The data processing subsystem is used to receive the preprocessing job execution file, initiate the corresponding task flow according to the preprocessing file and resource conditions, and monitor the task status for reporting. After the task is completed, the result data is pushed to the data management subsystem. The data processing subsystem calls the corresponding processing program according to the resource configuration to complete the precise orbit determination processing.

[0076] The data management subsystem is responsible for storing the data generated by management and scheduling, and supports interaction with the human-computer interface for query retrieval, space management and other operations.

[0077] In order to address the problems of poor quality of some data from high-orbit satellite onboard receivers due to other factors and different acquisition times of different precise ephemeris products, the system has designed a highly fault-tolerant, time-efficient and automated precise orbit determination processing system, which completes multiple processes including platform data source acquisition and analysis, automatic matching of precise ephemeris products, and automated processing of multiple precise orbit determination products, thus improving the modularization, automation and standardization of the system's precise orbit determination processing tasks for high-orbit satellites.

[0078] It should be noted that the specific implementation details of the high-orbit satellite orbit determination data processing provided by the embodiment of the present invention and the technical effects brought about are the same or similar to the above-mentioned high-orbit satellite orbit determination data processing method, and will not be repeated here.

[0079] Based on the above processing method for high-orbit satellite orbit determination, the present invention also provides a processing device for high-orbit satellite orbit determination. Figure 5 The device is described in detail.

[0080] Figure 5 The structure block diagram of a processing device for high-orbit satellite orbit determination according to an embodiment of the present invention is schematically shown.

[0081] like Figure 5 As shown, the processing device 500 for high-orbit satellite orbit determination in this embodiment includes a parsing module 510 , a setting module 520 and an execution module 530 .

[0082] The analysis module 510 is used to analyze the satellite receiver data to obtain the arc time.

[0083] The setting module 520 is used to set the priority of the orbit determination process.

[0084] The execution module 530 is configured to perform at least one of the following operations based on the priority to obtain high-orbit satellite orbit determination data:

[0085] After the arc time, a predetermined time is delayed, and a post-precision orbit determination processing flow is started to generate post-precision orbit determination data and a first orbit description file;

[0086] In response to the required real-time precise ephemeris data being downloaded, a real-time precise orbit determination processing flow is initiated to complete the production of the real-time precise orbit determination data and the second orbit description file during the arc segment time;

[0087] After the real-time precise orbit determination processing flow is completed, the predicted precise orbit determination processing flow is started to predict the predicted precise orbit determination data and the third orbit description file within a preset time period after the arc segment time.

[0088] According to the embodiments of the present invention, any one or more of the modules, submodules, units, and subunits, or at least part of the functions of any one of them can be implemented in one module. According to the embodiments of the present invention, any one or more of the modules, submodules, units, and subunits can be split into multiple modules for implementation. According to the embodiments of the present invention, any one or more of the modules, submodules, units, and subunits can be at least partially implemented as hardware circuits, such as field programmable gate arrays (FPGAs), programmable logic arrays (PLAs), systems on chips, systems on substrates, systems on packages, application specific integrated circuits (ASICs), or can be implemented by hardware or firmware in any other reasonable way of integrating or packaging the circuit, or by any one of the three implementation methods of software, hardware, and firmware, or by a proper combination of any of them. Alternatively, according to the embodiments of the present invention, one or more of the modules, submodules, units, and subunits can be at least partially implemented as computer program modules, and when the computer program modules are run, the corresponding functions can be executed.

[0089] For example, any multiple of the parsing module 510, the setting module 520, and the execution module 530 can be combined in one module / unit / sub-unit for implementation, or any one of the modules / units / sub-units can be split into multiple modules / units / sub-units. Alternatively, at least part of the functions of one or more of these modules / units / sub-units can be combined with at least part of the functions of other modules / units / sub-units and implemented in one module / unit / sub-unit. According to an embodiment of the present invention, at least one of the parsing module 510, the setting module 520, and the execution module 530 can be at least partially implemented as a hardware circuit, such as a field programmable gate array (FPGA), a programmable logic array (PLA), a system on a chip, a system on a substrate, a system on a package, an application specific integrated circuit (ASIC), or can be implemented by hardware or firmware such as any other reasonable way of integrating or packaging the circuit, or implemented in any one of the three implementation methods of software, hardware, and firmware, or in any appropriate combination of any of them. Alternatively, at least one of the parsing module 510 , the setting module 520 , and the execution module 530 may be at least partially implemented as a computer program module, and when the computer program module is executed, a corresponding function may be executed.

[0090] It should be noted that the processing device part for high-orbit satellite orbit determination in the embodiment of the present invention corresponds to the processing method part for high-orbit satellite orbit determination in the embodiment of the present invention, and their specific implementation details are also the same, which will not be repeated here.

[0091] Figure 6 A block diagram of an electronic device suitable for implementing the method described above according to an embodiment of the present invention is schematically shown. Figure 6 The electronic device shown is only an example and should not bring any limitation to the functions and scope of use of the embodiments of the present invention.

[0092] like Figure 6 As shown, the electronic device 600 according to an embodiment of the present invention includes a processor 601, which can perform various appropriate actions and processes according to a program stored in a read-only memory (ROM) 602 or a program loaded from a storage part 608 to a random access memory (RAM) 603. The processor 601 may include, for example, a general-purpose microprocessor (e.g., a CPU), an instruction set processor and / or a related chipset and / or a special-purpose microprocessor (e.g., an application-specific integrated circuit (ASIC)), etc. The processor 601 may also include an onboard memory configured for cache purposes. The processor 601 may include a single processing unit or multiple processing units configured to perform different actions of the method flow according to an embodiment of the present invention.

[0093] In RAM 603, various programs and data required for the operation of electronic device 600 are stored. Processor 601, ROM 602 and RAM 603 are connected to each other via bus 604. Processor 601 performs various operations of the method flow according to the embodiment of the present invention by executing the program in ROM 602 and / or RAM 603. It should be noted that the program can also be stored in one or more memories other than ROM 602 and RAM 603. Processor 601 can also perform various operations of the method flow according to the embodiment of the present invention by executing the program stored in the one or more memories.

[0094] According to an embodiment of the present invention, the electronic device 600 may further include an input / output (I / O) interface 605, which is also connected to the bus 604. The electronic device 600 may further include one or more of the following components connected to the input / output (I / O) interface 605: an input portion 606 including a keyboard, a mouse, etc.; an output portion 607 including a cathode ray tube (CRT), a liquid crystal display (LCD), etc., and a speaker, etc.; a storage portion 608 including a hard disk, etc.; and a communication portion 609 including a network interface card such as a LAN card, a modem, etc. The communication portion 609 performs communication processing via a network such as the Internet. A drive 610 is also connected to the input / output (I / O) interface 605 as needed. A removable medium 611, such as a magnetic disk, an optical disk, a magneto-optical disk, a semiconductor memory, etc., is installed on the drive 610 as needed, so that a computer program read therefrom is installed into the storage portion 608 as needed.

[0095] According to an embodiment of the present invention, the method flow according to an embodiment of the present invention can be implemented as a computer software program. For example, an embodiment of the present invention includes a computer program product, which includes a computer program carried on a computer-readable storage medium, and the computer program contains a program code configured to execute the method shown in the flowchart. In such an embodiment, the computer program can be downloaded and installed from the network through the communication part 609, and / or installed from the removable medium 611. When the computer program is executed by the processor 601, the above-mentioned functions defined in the system of the embodiment of the present invention are executed. According to an embodiment of the present invention, the system, equipment, device, module, unit, etc. described above can be implemented by a computer program module.

[0096] The present invention also provides a computer-readable storage medium, which may be included in the device / apparatus / system described in the above embodiment; or may exist independently without being assembled into the device / apparatus / system. The above computer-readable storage medium carries one or more programs, and when the above one or more programs are executed, the method according to the embodiment of the present invention is implemented.

[0097] According to an embodiment of the present invention, the computer-readable storage medium may be a non-volatile computer-readable storage medium. For example, it may include, but is not limited to: a portable computer disk, a hard disk, a random access memory (RAM), a read-only memory (ROM), an erasable programmable read-only memory (EPROM or flash memory), a portable compact disk read-only memory (CD-ROM), an optical storage device, a magnetic storage device, or any suitable combination thereof. In the present invention, the computer-readable storage medium may be any tangible medium containing or storing a program, which may be used by or in combination with an instruction execution system, apparatus, or device.

[0098] For example, according to an embodiment of the present invention, the computer-readable storage medium may include the ROM 602 and / or the RAM 603 described above and / or one or more memories other than the ROM 602 and the RAM 603 .

[0099] An embodiment of the present invention also includes a computer program product, which includes a computer program, which contains program code configured to execute the method provided by the embodiment of the present invention. When the computer program product runs on an electronic device, the program code is configured to enable the electronic device to implement the processing method for high-orbit satellite orbit determination provided by the embodiment of the present invention.

[0100] When the computer program is executed by the processor 601, the above functions defined in the system / device of the embodiment of the present invention are executed. According to the embodiment of the present invention, the system, device, module, unit, etc. described above can be implemented by a computer program module.

[0101] In one embodiment, the computer program may rely on tangible storage media such as optical storage devices, magnetic storage devices, etc. In another embodiment, the computer program may also be transmitted and distributed in the form of signals on a network medium, and downloaded and installed through the communication part 609, and / or installed from a removable medium 611. The program code contained in the computer program may be transmitted using any appropriate network medium, including but not limited to: wireless, wired, etc., or any suitable combination of the above.

[0102] According to an embodiment of the present invention, the program code configured to execute the computer program provided by the embodiment of the present invention can be written in any combination of one or more programming languages. Specifically, these computing programs can be implemented using high-level process and / or object-oriented programming languages, and / or assembly / machine languages. Programming languages ​​include, but are not limited to, Java, C++, python, "C" language or similar programming languages. The program code can be executed entirely on the user computing device, partially on the user device, partially on the remote computing device, or entirely on the remote computing device or server. In the case of a remote computing device, the remote computing device can be connected to the user computing device through any type of network, including a local area network (LAN) or a wide area network (WAN), or can be connected to an external computing device (e.g., using an Internet service provider to connect through the Internet).

[0103] The flowcharts and block diagrams in the accompanying drawings illustrate the possible implementation architecture, functions and operations of the systems, methods and computer program products according to various embodiments of the present invention. In this regard, each box in the flowchart or block diagram may represent a module, a program segment, or a part of a code, and the above-mentioned module, program segment, or a part of the code contains one or more executable instructions configured to implement the specified logical function. It should also be noted that in some alternative implementations, the functions marked in the box may also occur in an order different from that marked in the accompanying drawings. For example, two boxes represented in succession can actually be executed substantially in parallel, and they can sometimes be executed in the opposite order, depending on the functions involved. It should also be noted that each box in the block diagram or flowchart, and the combination of boxes in the block diagram or flowchart, can be implemented with a dedicated hardware-based system that performs a specified function or operation, or can be implemented with a combination of dedicated hardware and computer instructions. It will be understood by those skilled in the art that the features recorded in the various embodiments of the present invention can be combined and / or combined in various ways, even if such a combination or combination is not explicitly recorded in the present invention. In particular, without departing from the spirit and teachings of the present invention, the features recorded in the various embodiments of the present invention can be combined and / or combined in various ways. All these combinations and / or combinations fall within the scope of the present invention.

[0104] The embodiments of the present invention are described above. However, these embodiments are only for the purpose of illustration, and are not intended to limit the scope of the present invention. Although each embodiment is described above, it does not mean that the measures in each embodiment cannot be used in combination advantageously. Without departing from the scope of the present invention, those skilled in the art may make various substitutions and modifications, which should all fall within the scope of the present invention.

Claims

1. A processing method for high-orbit satellite orbit determination, characterized in that: include: Analyze the satellite receiver data to obtain the arc time; Set the priority of the orbit determination process; In the case where the priority is the first priority, obtaining high-orbit satellite orbit determination data includes: first starting a post-precision orbit determination processing flow to produce post-precision orbit determination data and a first orbit description file, then starting a real-time precision orbit determination processing flow to complete the production of real-time precision orbit determination data and a second orbit description file within the arc segment time, and finally starting a predicted precision orbit processing flow to predict and obtain predicted precision orbit determination data and a third orbit description file within a preset time period after the arc segment time; In the case where the priority is the second priority, obtaining the high-orbit satellite orbit determination data includes: starting a post-precision orbit determination processing flow to produce post-precision orbit determination data and a first orbit description file; When the priority is the third priority, obtaining the high-orbit satellite orbit determination data includes: starting a real-time precise orbit determination processing flow to complete the production of the real-time precise orbit determination data and the second orbit description file within the arc time; When the priority is the fourth priority, obtaining high-orbit satellite orbit determination data includes: starting a predicted precise orbit processing flow to predict and obtain predicted precise orbit determination data and a third orbit description file within a preset time period after the arc time.

2. The processing method according to claim 1, characterized in that: Obtaining high-orbit satellite orbit determination data also includes: Obtaining the perturbation force on the high-orbit satellite in an inertial system, wherein the perturbation force includes a conservative force, a non-conservative force, and an empirical force, wherein the empirical force is used to represent an error between a perturbation force model and a corresponding real perturbation force or a perturbation force that is not modeled; The high-orbit satellite orbit determination data is determined based on the conservative force, the non-conservative force and the empirical force.

3. The processing method according to claim 1 or 2, characterized in that: Also includes: An operation interface is configured, which is used for interaction with users so that users can edit, modify, import and select priorities.

4. A processing device for high-orbit satellite orbit determination, characterized in that: include: The analysis module is used to analyze the satellite receiver data to obtain the arc time; The setting module is used to set the priority of the orbit determination process; An execution module is used to perform at least one of the following operations based on the priority to obtain high-orbit satellite orbit determination data, including: In the case where the priority is the first priority, obtaining high-orbit satellite orbit determination data includes: first starting a post-precision orbit determination processing flow to produce post-precision orbit determination data and a first orbit description file, then starting a real-time precision orbit determination processing flow to complete the production of real-time precision orbit determination data and a second orbit description file within the arc segment time, and finally starting a predicted precision orbit processing flow to predict and obtain predicted precision orbit determination data and a third orbit description file within a preset time period after the arc segment time; In the case where the priority is the second priority, obtaining the high-orbit satellite orbit determination data includes: starting a post-precision orbit determination processing flow to produce post-precision orbit determination data and a first orbit description file; When the priority is the third priority, obtaining the high-orbit satellite orbit determination data includes: starting a real-time precise orbit determination processing flow to complete the production of the real-time precise orbit determination data and the second orbit description file within the arc time; When the priority is the fourth priority, obtaining high-orbit satellite orbit determination data includes: starting a predicted precise orbit processing flow to predict and obtain predicted precise orbit determination data and a third orbit description file within a preset time period after the arc time.

5. An electronic device comprising: at least one processor; as well as a memory communicatively connected to the at least one processor; wherein, The memory stores instructions that can be executed by the at least one processor, and the instructions are executed by the at least one processor to enable the at least one processor to perform the method according to any one of claims 1 to 3.

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