Method, device and equipment for fast simulation of high-precision orbit of giant constellation and medium

Abstract

The application relates to a mega-constellation high-precision orbit rapid simulation method, device, equipment and medium. First, initial orbit information of a mega-constellation is acquired, rapid high-precision orbit simulation calculation is carried out through a preprocessing module, and orbit proxy model parameters are obtained; the orbit proxy model parameters are sent to a real-time calculation module for mega-constellation orbit simulation; when the real-time calculation module receives a new satellite control instruction, a calculation task of the new satellite control instruction is sent to a calculation pool module for simulation calculation, new orbit proxy model parameters are obtained; and the new orbit proxy model parameters are sent to the real-time calculation module for re-mega-constellation orbit simulation. Under the premise of ensuring high precision, the application realizes rapid simulation of tens of thousands of satellite orbits, can respond to constellation satellite orbit maneuvering control instructions in real time, and can rapidly adjust and calculate the satellite orbit.

Description

Technical Field

[0001] This application relates to the field of satellite technology, and in particular to a method, apparatus, equipment and medium for rapid simulation of high-precision orbits of giant constellations. Background Technology

[0002] With the booming development of commercial spaceflight, mega-constellation networks have made rapid progress in construction, networking, and service in recent years. Currently, several mega-constellation schemes have been announced both domestically and internationally, including domestic constellations such as Hongyan, Hongyun, and Galaxy Aerospace, and international systems such as Starlink, OneWeb, LeoSat, TeleSat, Kepler, Samsung, and Boeing. Taking Starlink as an example, as of April 21, 2022, SpaceX had launched a total of 2,388 Starlink satellites, deployed in orbits between 328km and 580km. According to the plan, the final number of Starlink satellites will reach approximately 42,000. To quickly design and analyze mega-constellations, dynamic and efficient high-precision orbit simulation is crucial. Its computational efficiency directly affects the efficiency of constellation design and analysis. Traditional constellation orbit simulation methods use real-time orbit simulation, which becomes very slow as the number of satellites increases. For mega-constellations with tens of thousands of satellites, the computational speed becomes unbearable. Currently, there is no method in China that can quickly and accurately simulate the orbits of giant constellations. Summary of the Invention

[0003] Therefore, it is necessary to provide a method, device, equipment, and medium for rapid simulation of high-precision orbits of giant constellations to address the aforementioned technical problems. This method can achieve rapid simulation of the orbits of tens of thousands of satellites while ensuring high precision, and can respond in real time to control commands such as orbital maneuvers of constellation satellites to quickly adjust and calculate satellite orbits.

[0004] A rapid simulation method for high-precision orbits of giant constellations includes:

[0005] The initial orbital information of the giant constellation is obtained, and the orbital surrogate model parameters are obtained by performing rapid and high-precision orbital simulation calculations through the preprocessing module.

[0006] The orbital proxy model parameters are sent to the real-time computing module for giant constellation orbit simulation; wherein, the real-time computing module uses a proxy model for fast giant constellation orbit simulation.

[0007] When the real-time computing module receives a new satellite control command, it sends the calculation task of the new satellite control command to the computing pool module for simulation calculation to obtain the parameters of the new orbit proxy model.

[0008] The parameters of the newly added orbital proxy model are sent to the real-time calculation module to re-perform the giant constellation orbit simulation.

[0009] In one embodiment, the preprocessing module includes a data loading unit, a task scheduling unit, a preprocessing calculation unit, and a result processing unit;

[0010] The initial orbital information of the giant constellation is stored in the data loading unit. During simulation calculations, the data loading unit determines the parameter information and sends the parameters to the task scheduling unit.

[0011] After obtaining the parameter information, the task scheduling unit performs multi-process division of the computation task according to the number of satellites in the giant constellation, thus obtaining multi-process computation tasks.

[0012] The multi-process computing task is assigned to the preprocessing computing unit. The preprocessing computing unit further subdivides the computing task into multiple parts according to the process and assigns them to multiple threads in the preprocessing computing unit for parallel computing to obtain the orbital proxy model parameters.

[0013] The orbital proxy model parameters are sent to the result processing unit, which sorts and organizes the parameters and stores them in a file or database according to rules.

[0014] In one embodiment, the data loading unit verifies the file format and data being loaded. If there are errors in the file format and data, the calculation process is interrupted, and an error message is given to guide the user to modify the data file.

[0015] In one embodiment, the real-time computing module includes a real-time loading unit, a real-time control unit, a proxy model computing unit, and a result output unit;

[0016] After the preprocessing module completes the simulation calculation, the real-time calculation module is started; the real-time loading unit retrieves the parameters of the orbital proxy model from the files and database of the result processing unit, and sends the retrieved orbital proxy model parameters to the real-time control unit;

[0017] After receiving the parameters sent by the real-time loading unit, the real-time control unit starts to call the proxy model calculation unit to perform the giant constellation orbit simulation, and controls the simulation process and simulation speed in the proxy model calculation unit.

[0018] Under the scheduling of the real-time control unit, the proxy model calculation unit calls the proxy model to perform rapid giant constellation orbit simulation according to the orbit proxy model parameters loaded by the real-time loading unit, and sends the simulation data to the result output unit.

[0019] The results output unit processes the simulation data, performing real-time data processing and time-lapse data processing.

[0020] In one embodiment, the real-time computing module further includes an instruction receiving unit and an instruction processing unit;

[0021] When the instruction receiving unit receives a new satellite control instruction, it sends the new satellite control instruction to the instruction processing unit for processing;

[0022] The instruction processing unit injects the received new satellite control instructions into the satellite to form new mega-constellation orbit information. Based on the new mega-constellation orbit information, it determines the number of new computing tasks and sends the new computing tasks to the computing pool module for simulation calculation.

[0023] In one embodiment, the computing pool module includes a computing task receiving unit, a computing task management unit, a computing resource management unit, and a computing resource unit;

[0024] The computing task receiving unit receives new computing tasks by function calls and records the function pointers and dependency data of the new computing tasks. At the same time, it sends the new computing tasks to the computing task management unit, which stores the new computing tasks by a task linked list.

[0025] The computing resource management unit manages all computing resource units in a unified manner. When a new computing task arrives, the computing resource management unit wakes up the computing resource unit to start computing.

[0026] The computing resource unit obtains the parameters of the new computing task from the task chain list of the computing task management unit, and starts the calculation according to the function pointer and dependency data to obtain the parameters of the new track proxy model.

[0027] In one embodiment, the computing resource unit employs a multi-threaded parallel strategy to compute newly added computing tasks.

[0028] A high-precision rapid simulation device for the orbits of giant constellations, the device comprising:

[0029] The preprocessing module is used to perform rapid and high-precision orbit simulation calculations based on the initial orbit information of the giant constellation, and obtain orbit surrogate model parameters.

[0030] A real-time computing module is used to send the orbital proxy model parameters to the real-time computing module for giant constellation orbit simulation; wherein, the real-time computing module uses a proxy model to perform rapid giant constellation orbit simulation.

[0031] The computing pool module is used to send the computing task of the new satellite control command to the computing pool module for simulation calculation when the real-time computing module receives the new satellite control command, so as to obtain the new orbit proxy model parameters; and send the new orbit proxy model parameters to the real-time computing module to re-perform the giant constellation orbit simulation.

[0032] A computer device includes a memory and a processor, the memory storing a computing program, and the processor executing the computer program to implement the steps of the above-described method.

[0033] A computer-readable storage medium having a computer program stored thereon, which, when executed by a processor, implements the steps of the above-described method.

[0034] The aforementioned method, apparatus, equipment, and medium for rapid high-precision orbit simulation of mega-constellations first acquire the initial orbit information of the mega-constellation. A preprocessing module then performs rapid, high-precision orbit simulation calculations to obtain orbit proxy model parameters. These parameters are then sent to a real-time calculation module for mega-constellation orbit simulation. The real-time calculation module uses a proxy model for rapid mega-constellation orbit simulation. When the real-time calculation module receives new satellite control commands, it sends the calculation task for these commands to a calculation pool module for simulation calculations, obtaining new orbit proxy model parameters. These new parameters are then sent back to the real-time calculation module to re-perform the mega-constellation orbit simulation. This invention ensures high-precision orbit simulation calculations through a preprocessing module. The proxy model in the real-time calculation module enables rapid simulation of the orbits of tens of thousands of satellites. Furthermore, the real-time calculation module can respond in real-time to new control commands such as orbital maneuvers of constellation satellites, recalculating the new orbit proxy model parameters through the calculation pool module and sending them back to the real-time calculation module for re-perform the mega-constellation orbit simulation. This allows for rapid adjustment calculations of satellite orbits, providing a foundation for mega-constellation orbit simulation, coverage analysis, configuration design, and network analysis. Attached Figure Description

[0035] Figure 1 Flowchart of a rapid simulation method for high-precision orbits of giant constellations;

[0036] Figure 2 A schematic diagram of a high-precision rapid simulation of the orbits of a giant constellation;

[0037] Figure 3 Working principle diagram of the computing pool module;

[0038] Figure 4 This is a block diagram of a high-precision rapid orbit simulation device for a giant constellation in one embodiment;

[0039] Figure 5This is an internal structural diagram of a computer device in one embodiment. Detailed Implementation

[0040] To make the objectives, technical solutions, and advantages of this application clearer, the following detailed description is provided in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative and not intended to limit the scope of this application.

[0041] The purpose of this invention is to propose a high-precision rapid orbit simulation method suitable for mega-constellations. Under the premise of ensuring high precision, it can rapidly simulate tens of thousands of satellites and respond in real time to control commands such as orbital maneuvers of constellation satellites. Then, by using methods such as computing pools, it can quickly adjust and calculate satellite orbits, providing a foundation for mega-constellation orbit simulation, coverage analysis, configuration design, and network analysis.

[0042] In one embodiment, such as Figure 1 and 2 As shown, the method for rapid simulation of high-precision orbits of giant constellations provided by this invention includes the following steps:

[0043] Step 102: Obtain the initial orbit information of the giant constellation, and perform fast and high-precision orbit simulation calculations through the preprocessing module to obtain the orbit proxy model parameters.

[0044] Specifically, the preprocessing module includes a data loading unit, a task scheduling unit, a preprocessing calculation unit, and a result processing unit.

[0045] The data loading unit is responsible for loading the initial orbital information of the mega-constellation into a file and storing it on the hard drive. When the task begins, the data loading unit opens the data file, reads the data, and then determines geometric parameters such as the number of satellites, orbital configuration, satellite mass, and windward area, as well as initial orbital parameters such as satellite position and velocity, based on the data. This information is then sent to the mission scheduling unit. Simultaneously, the data loading unit verifies the file format and data. If errors are found, the calculation process is interrupted, an error message is displayed, and the user is guided to modify the data file.

[0046] The task scheduling unit is responsible for the overall scheduling of satellite preprocessing computation tasks. The task scheduling unit reads the parameter information sent by the data loading unit, then divides the computation tasks into multiple processes based on the number of mega-satellites. The resulting computation tasks are then assigned to the preprocessing computation units for specific computations. It is worth noting that, to improve computation speed, the preprocessing module employs a parallel computing strategy combining multiple processes and multiple threads. The task scheduling unit is responsible for managing the parallel processing of these processes, including starting, monitoring, and checking the termination of the preprocessing computation units, ensuring their smooth execution.

[0047] The preprocessing calculation unit is primarily responsible for the specific calculation of the parameters of the giant constellation orbital proxy model. Based on the calculation tasks assigned by the task scheduling unit, it specifically executes the calculation and generation of the giant constellation orbital proxy model parameters. The preprocessing calculation unit is responsible for the classification and management of multi-threaded tasks. It further subdivides the calculation tasks into multiple parts according to the progress and distributes them to multiple threads for parallel computation. During the calculation, a high-precision orbital model considering perturbations such as Earth's non-spherical perturbation, atmospheric perturbation, lunar three-body perturbation, and solar three-body perturbation is used. A variable step size method is employed to accelerate the calculation speed, and the calculation results are sent to the results processing unit for further processing.

[0048] This invention uses a high-precision orbital model to generate surrogate model parameters. When considering other perturbation factors, in addition to the gravity of the central gravitational body, other perturbation accelerations must also be added, namely:

[0049] ;

[0050] in, For spacecraft mass, For the spacecraft's position vector, The gravitational pull of Earth on the spacecraft, The spacecraft is perturbed by the gravitational pull of the Sun and Moon. Perturbations caused by atmospheric drag on the spacecraft The solar radiation pressure perturbation experienced by the spacecraft Tidal perturbations experienced by spacecraft Due to Earth's spherical gravity, This is due to the gravitational perturbation caused by Earth's non-spherical shape.

[0051] The variable step size method can employ various algorithms; this invention uses the RKF7(8) formula.

[0052] ;

[0053] ;

[0054] No. The truncation error of the step is:

[0055] ;

[0056] in, To calculate the satellite's position and velocity at step n, The satellite's position and velocity at step n+1. , , , The integral coefficient is... To calculate the step size, For function values, This represents the truncation error.

[0057] The results processing unit is responsible for collecting, summarizing, and storing all calculation results. Results generated by multiple processes are collected, sorted and organized according to the configuration of the megacons, and stored in files or a database according to rules for use by the real-time computing module. If the calculation results are stored in a folder, a subdirectory is created under the Satellite directory according to the current computer time, and the file is stored as a Satellite.bin binary file, stored in order of satellite ID. If stored in a database, binary data is stored using Satellite as the key. The data to be stored includes geometric parameters such as the number of megaconstellation satellites, satellite orbital configuration, satellite mass and windward area, initial orbital parameters such as satellite position and velocity, and the parameters of the megaconstellation orbital surrogate model calculated by the preprocessing module.

[0058] Step 104: Send the orbit proxy model parameters to the real-time calculation module for giant constellation orbit simulation; wherein, the real-time calculation module uses a proxy model to perform fast giant constellation orbit simulation.

[0059] Specifically, the real-time computing module includes a real-time loading unit, a real-time control unit, a proxy model computing unit, an instruction receiving unit, an instruction processing unit, and a result output unit.

[0060] The real-time loading unit is responsible for loading the data generated by the preprocessing module. After the preprocessing module completes its simulation calculations, the real-time calculation module is started. The real-time loading unit retrieves files or databases from the result processing unit to obtain geometric parameters such as the number of giant constellation satellites, satellite orbital configuration, satellite mass, and windward area, as well as initial orbital parameters such as satellite position and velocity. It also obtains orbital surrogate model parameters and sends these parameters to the real-time control unit. Simultaneously, the real-time loading unit needs to verify the loaded parameters. If incomplete or incorrect data is found, the calculation process is terminated, and an error message is displayed to the user.

[0061] The real-time control unit (RTU) is responsible for the rapid simulation control of the high-precision orbits of the mega-constellation. After receiving parameters from the real-time loading unit, the RTU begins invoking the proxy model calculation unit to perform the mega-constellation orbit simulation. The RTU primarily controls the simulation process and speed within the proxy model calculation unit. The simulation process includes simulation start, pause, stop, acceleration, and deceleration signals, and the RTU intervenes in the simulation process based on these signals. Simulation speed control includes internal clock speed control and external clock synchronization. Internal clock speed control utilizes the relationship between the computer's high-precision clock and the computation time to maintain the computation speed at a specified speedup ratio. External clock synchronization periodically receives external clock signals and controls the internal simulation clock to synchronize with the external clock, ensuring that the internal computation speedup ratio matches the speedup ratio of the external system.

[0062] The proxy model calculation unit is responsible for calculating the high-precision orbit proxy model for the mega-constellation. Under the scheduling of the real-time control unit, the proxy model calculation unit calls the proxy model to perform mega-constellation orbit simulation based on the orbit proxy model parameters loaded by the real-time loading unit. The proxy model takes the orbit proxy model parameters as input, uses the Lagrange interpolation method, and outputs the satellite orbit information corresponding to the real-time simulation time. The proxy model calculation speed is 1-2 orders of magnitude faster than directly using high-precision orbit calculation. Because the proxy model has a faster calculation speed than the high-precision orbit model, a very fast calculation speed can be achieved, greatly improving the speed of mega-constellation orbit simulation.

[0063] The command receiving unit is primarily responsible for receiving new satellite control commands, such as orbital maneuvers, from external input. During rapid simulation of giant constellation orbits, orbital maneuvers may be required. In such cases, an external system needs to calculate the orbital maneuver quantities and then send them to the device of this invention as new satellite control commands for execution. The command receiving unit is the unit in this invention that receives these new satellite control commands. It creates a Socket, binds to a receiving port, and triggers a receiving processing function when an external system sends a command, beginning the command reception process. New satellite control commands include the satellite ID, command injection epoch, command execution epoch, and maneuver quantities. The command receiving unit then sends the new satellite control commands to the command processing unit for further processing.

[0064] The instruction processing unit is responsible for processing the satellite maneuvering and other control instructions received by the instruction receiving unit. Upon receiving a new satellite control instruction, the instruction processing unit injects the instruction into the satellite according to the instruction injection epoch. Since the results generated by the preprocessing module are only applicable to satellite orbit calculations without instruction input, when instructions are injected, the satellite needs to recalculate the high-precision orbit surrogate model parameters. This calculation requires the assistance of the computation pool module. The orbit calculation for each satellite containing the injected instruction constitutes a new computation task. The instruction processing unit sends the new computation tasks requiring recalculation of surrogate model parameters to the computation pool module and checks the completion of the computation task at each simulation step. The completion time of the computation task must be earlier than the simulation speed time of the real-time computation module; otherwise, the instruction processing unit needs to wait until the computation task is completed. When this waiting situation occurs, the instruction processing unit needs to subdivide the new computation task into several new sub-tasks before sending them to the computation pool module. Let the initial orbit extrapolation time of the computation task be t; then the extrapolation time of the new sub-tasks is changed to t / 2 to reduce computation time and ensure the overall simulation speed.

[0065] The results output unit is responsible for outputting all calculation results from the real-time calculation module. Real-time calculation results include giant constellation configuration parameters, position and velocity, orbital elements, geometric relationships, etc., and the results output unit processes this data. The results output unit includes two categories: real-time data processing and post-processing data processing. Real-time data processing sends all parameters of the giant constellation to external systems in real time. First, a socket is created, a sending port is bound, and then the result data is sent as a byte stream. The external system receives the real-time data using the socket for display or use. Post-processing saves all parameters of the giant constellation, either as a data file or in a database, for analysis and evaluation purposes. Saving can be achieved using multi-threaded file reading and writing, or by storing the data in memory during simulation and then saving it to disk after simulation.

[0066] Step 106: When the real-time calculation module receives a new satellite control command, it sends the calculation task of the new satellite control command to the calculation pool module for simulation calculation to obtain the parameters of the new orbital proxy model.

[0067] Specifically, such as Figure 3 The diagram shown illustrates the working principle of the computing pool module provided by this invention. The computing pool module includes a computing task receiving unit, a computing task management unit, a computing resource management unit, and a computing resource unit.

[0068] The computation task receiving unit is responsible for receiving new computation tasks sent by the instruction processing unit in the real-time computing module. The unit receives new computation tasks via function calls, records the function pointer and dependent data of each task, and returns the task ID to the instruction processing unit. The instruction processing unit can use the task ID to cancel unexecuted computation tasks in the computation pool module, and can also use it to identify the data corresponding to the ID from multiple new computation tasks.

[0069] The computation task management unit is responsible for the unified management of all received computation tasks. When the computation task receiving unit sends a new computation task to the computation task management unit, the computation task management unit stores the new computation task using a task linked list. The stored new computation task can be submitted to the computation resource management unit for computation, or it can be cancelled by the real-time computing module as needed. It is worth noting that tasks in the computation task management unit adopt a first-in, first-out (FIFO) management strategy; tasks submitted to the computation task management unit first are sent to the computation resource unit for computation first. When a computation task is cancelled, the FIFO principle is not applied; the new computation task is searched for by ID and then deleted from the task linked list.

[0070] The Computing Resource Management Unit (CRMU) is responsible for the unified management of all computing resource units. It's worth noting that the CRMU employs a multi-threaded parallel strategy to compute new tasks; therefore, computing resources are represented by individual threads. During initialization, the CRMU creates multiple threads and keeps them in a dormant state, awaiting new computing tasks. When a new task arrives, the CRMU wakes up the dormant threads, thus activating the computing resource unit to begin computation. At the end of the process, the CRMU also cancels all unexecuted tasks, checks whether all computations within the computing resource unit have been completed, and destroys the threads after computation is finished. The CRMU monitors the idle status of each computing resource unit to ensure efficient task processing and prevent backlog. If too many new computing tasks are added, it may lead to a backlog. In such cases, the CRMU should promptly warn the real-time computing module so that the module can take measures such as reducing computation speed or subdividing computational tasks.

[0071] The computing resource unit (CRU) is the computational unit that executes computational tasks using threads. Initially, the CRU is also in a dormant state. When the computing resource management unit sends a wake-up message, the CRU checks the task list in the computing task management unit, retrieves the parameters for the new computational task, and then begins computation based on the function pointer, input data, and other parameters to obtain the parameters for the new orbital proxy model. It is worth noting that after completing a computational task, the CRU checks the task list again. If there are still computational tasks, it continues computation; otherwise, it enters a dormant state, waiting for a new wake-up message from the computing resource management unit.

[0072] Step 108: Send the parameters of the newly added orbital proxy model to the real-time calculation module to re-perform the giant constellation orbit simulation.

[0073] The aforementioned method, apparatus, equipment, and medium for rapid high-precision orbit simulation of mega-constellations first acquire the initial orbit information of the mega-constellation. A preprocessing module then performs rapid, high-precision orbit simulation calculations to obtain orbit proxy model parameters. These parameters are then sent to a real-time calculation module for mega-constellation orbit simulation. The real-time calculation module uses a proxy model for rapid mega-constellation orbit simulation. When the real-time calculation module receives new satellite control commands, it sends the calculation task for these commands to a calculation pool module for simulation calculations, obtaining new orbit proxy model parameters. These new parameters are then sent back to the real-time calculation module to re-perform the mega-constellation orbit simulation. This invention ensures high-precision orbit simulation calculations through a preprocessing module. The proxy model in the real-time calculation module enables rapid simulation of the orbits of tens of thousands of satellites. Furthermore, the real-time calculation module can respond in real-time to new control commands such as orbital maneuvers of constellation satellites, recalculating the new orbit proxy model parameters through the calculation pool module and sending them back to the real-time calculation module for re-perform the mega-constellation orbit simulation. This allows for rapid adjustment calculations of satellite orbits, providing a foundation for mega-constellation orbit simulation, coverage analysis, configuration design, and network analysis.

[0074] In one embodiment, a simple example is selected for illustration based on the technical solution of the present invention, and detailed implementation methods and operation processes are given.

[0075] Taking the Starlink mega-constellation as an example, as of April 21, 2022, SpaceX had launched a total of 2,388 Starlink satellites, including one batch of 2 test satellites, one batch of 60 Starlink 0.9 satellites, 28 batches of 1,678 Starlink 1.0 satellites (including 2 batches of polar orbit satellites), and 13 batches of 651 Starlink 1.5 satellites (including 3 prototype 1.5 satellites). If the planned 30,000 satellites are included, the mega-constellation used in this launch will have approximately 32,000 satellites. These satellites are deployed in orbits ranging from 328 km to 580 km, with orbital inclinations of 53°, 70°, 74°, and 81°.

[0076] The requirement is to conduct a two-day simulation of the Starlink mega-constellation, and at the 10th hour after the simulation begins, perform an orbital maneuver for 100 satellites. Initial data for the mega-constellation should be stored in files for system loading, and simulation data should also be saved to files.

[0077] The data loading unit in the preprocessing module reads the Starlink configuration and orbital parameters from the initial data file of the mega-constellation and then sends them to the mission scheduling unit. The mission scheduling unit divides the 32,000 satellites into five groups based on the number of satellites and initiates five independent preprocessing computation unit processes. The preprocessing computation units calculate the mega-constellation orbits and save the generated surrogate model parameters to files. The data from the five preprocessing computation unit processes is saved as five files in the same directory. After the calculations are complete, a message is sent to initiate real-time computation.

[0078] The real-time loading unit in the real-time computing module reads five files generated by the preprocessing module and sends them to the real-time control unit. The real-time control unit then calls the proxy model calculation unit to start the simulation. The proxy model calculation unit uses the proxy model parameters in the five files to quickly calculate the orbits of the giant constellation. During the simulation, the command receiving unit prepares to receive control commands for newly added satellites. After the simulation starts, an external system sends orbital maneuver commands for 100 satellites. Upon receiving these commands, the command receiving unit sends them to the command processing unit. The command processing unit divides the subsequent calculation tasks for these 100 satellites into multiple proxy model calculation tasks and sends them to the computing pool module for solving. After the computing pool module completes the calculation, it sends a feedback message to the command processing unit. After all calculations are completed, the result output unit saves all calculation results to a file.

[0079] The computing pool module establishes a thread pool upon startup, awaiting computing tasks. The computing task receiving unit within the computing pool module receives subsequent computing tasks from 100 satellites and sends them to the computing task management unit. The computing task management unit creates a task list and submits it to the computing resource management unit for computation. The computing resource management unit wakes up dormant threads. After being woken up, the computing resource unit checks the task list, retrieves new computing tasks, and begins computation. After computation is completed, it continues to check the task list and perform computations until all tasks are completed.

[0080] It should be understood that, although Figure 1 The steps in the flowchart are shown sequentially as indicated by the arrows, but these steps are not necessarily executed in the order indicated by the arrows. Unless otherwise specified herein, there is no strict order in which these steps are executed, and they can be performed in other orders. Figure 1 At least some of the steps in the process may include multiple sub-steps or multiple stages. These sub-steps or stages are not necessarily completed at the same time, but can be executed at different times. The execution order of these sub-steps or stages is not necessarily sequential, but can be executed in turn or alternately with other steps or at least some of the sub-steps or stages of other steps.

[0081] In one embodiment, such as Figure 4 As shown, this invention provides a high-precision rapid simulation device for the orbits of giant constellations, comprising:

[0082] The preprocessing module is used to perform rapid and high-precision orbit simulation calculations based on the initial orbit information of the giant constellation, and obtain orbit surrogate model parameters.

[0083] The real-time calculation module is used to send the orbital proxy model parameters to the real-time calculation module for giant constellation orbit simulation; the real-time calculation module uses the proxy model to perform rapid giant constellation orbit simulation.

[0084] The computing pool module is used to send the calculation task of the new satellite control command to the computing pool module for simulation calculation when the real-time computing module receives the new satellite control command, so as to obtain the parameters of the new orbit proxy model; and then send the parameters of the new orbit proxy model to the real-time computing module to re-perform the giant constellation orbit simulation.

[0085] Specific limitations regarding the rapid simulation device for high-precision orbits of giant constellations can be found in the limitations of the rapid simulation method for high-precision orbits of giant constellations mentioned above, and will not be repeated here. Each module in the aforementioned rapid simulation device for high-precision orbits of giant constellations can be implemented entirely or partially through software, hardware, or a combination thereof. These modules can be embedded in or independent of the processor in a computer device in hardware form, or stored in the memory of a computer device in software form, so that the processor can call and execute the operations corresponding to each module.

[0086] In one embodiment, a computer device is provided, which may be a server, and its internal structure diagram may be as follows: Figure 5 As shown, the computer device includes a processor, memory, network interface, and database connected via a system bus. The processor provides computational and control capabilities. The memory includes non-volatile storage media and internal memory. The non-volatile storage media stores the operating system, computer programs, and database. The internal memory provides an environment for the operation of the operating system and computer programs stored in the non-volatile storage media. The database stores high-precision orbital rapid simulation data for giant constellations. The network interface communicates with external terminals via a network connection. When the computer program is executed by the processor, it implements a method for high-precision orbital rapid simulation of giant constellations.

[0087] Those skilled in the art will understand that Figure 5 The structure shown is merely a block diagram of a portion of the structure related to the present application and does not constitute a limitation on the computer device to which the present application is applied. Specific computer devices may include more or fewer components than those shown in the figure, or combine certain components, or have different component arrangements.

[0088] In one embodiment, a computer device is provided, including a memory and a processor, the memory storing a computer program, the processor executing the computer program to perform the following steps:

[0089] Step 102: Obtain the initial orbit information of the giant constellation, and perform fast and high-precision orbit simulation calculations through the preprocessing module to obtain the orbit proxy model parameters.

[0090] Step 104: Send the orbital proxy model parameters to the real-time calculation module for giant constellation orbit simulation; wherein, the real-time calculation module uses the proxy model to perform fast giant constellation orbit simulation.

[0091] Step 106: When the real-time calculation module receives a new satellite control command, it sends the calculation task of the new satellite control command to the calculation pool module for simulation calculation to obtain the parameters of the new orbital proxy model.

[0092] Step 108: Send the parameters of the newly added orbital proxy model to the real-time calculation module to re-perform the giant constellation orbit simulation.

[0093] In one embodiment, a computer-readable storage medium is provided having a computer program stored thereon, the computer program performing the following steps when executed by a processor:

[0094] Step 102: Obtain the initial orbit information of the giant constellation, and perform rapid and high-precision orbit simulation calculations through the preprocessing module to obtain the orbit proxy model parameters.

[0095] Step 104: Send the orbital proxy model parameters to the real-time calculation module for giant constellation orbit simulation; wherein, the real-time calculation module uses the proxy model to perform fast giant constellation orbit simulation.

[0096] Step 106: When the real-time calculation module receives a new satellite control command, it sends the calculation task of the new satellite control command to the calculation pool module for simulation calculation to obtain the parameters of the new orbital proxy model.

[0097] Step 108: Send the parameters of the newly added orbital proxy model to the real-time calculation module to re-perform the giant constellation orbit simulation.

[0098] Those skilled in the art will understand that all or part of the processes in the above embodiments can be implemented by a computer program instructing related hardware. The computer program can be stored in a non-volatile computer-readable storage medium. When executed, the computer program can include the processes of the embodiments of the above methods. Any references to memory, storage, databases, or other media used in the embodiments provided in this application can include non-volatile and / or volatile memory. Non-volatile memory may include read-only memory (ROM), programmable ROM (PROM), electrically programmable ROM (EPROM), electrically erasable programmable ROM (EEPROM), or flash memory. Volatile memory may include random access memory (RAM) or external cache memory. By way of illustration and not limitation, RAM is available in a variety of forms, such as static RAM (SRAM), dynamic RAM (DRAM), synchronous DRAM (SDRAM), dual data rate SDRAM (DDRSDRAM), enhanced SDRAM (ESDRAM), synchronous link DRAM (SLDRAM), RAMbus direct RAM (RDRAM), direct memory bus dynamic RAM (DRDRAM), and memory bus dynamic RAM (RDRAM), etc.

[0099] The technical features of the above embodiments can be combined in any way. For the sake of brevity, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0100] The embodiments described above are merely illustrative of several implementation methods of this application, and while the descriptions are relatively specific and detailed, they should not be construed as limiting the scope of the invention patent. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of this application, and these all fall within the protection scope of this application. Therefore, the protection scope of this patent application should be determined by the appended claims.

Claims

1. A method for rapid simulation of high-precision orbits of giant constellations, characterized in that, The method includes: The initial orbital information of the giant constellation is obtained, and the orbital surrogate model parameters are obtained by performing rapid and high-precision orbital simulation calculations through the preprocessing module. The orbital proxy model parameters are sent to the real-time computing module for giant constellation orbit simulation; wherein, the real-time computing module uses a proxy model for fast giant constellation orbit simulation. When the real-time computing module receives a new satellite control command, it sends the calculation task of the new satellite control command to the computing pool module for simulation calculation to obtain the parameters of the new orbit proxy model. The parameters of the newly added orbit proxy model are sent to the real-time calculation module to re-perform the giant constellation orbit simulation. The real-time computing module includes a real-time loading unit, a real-time control unit, a proxy model computing unit, and a result output unit; After the preprocessing module completes the simulation calculation, the real-time calculation module is started; the real-time loading unit retrieves the parameters of the orbital proxy model from the files and database of the result processing unit, and sends the retrieved orbital proxy model parameters to the real-time control unit; After receiving the parameters sent by the real-time loading unit, the real-time control unit starts to call the proxy model calculation unit to perform the giant constellation orbit simulation, and controls the simulation process and simulation speed in the proxy model calculation unit. Under the scheduling of the real-time control unit, the proxy model calculation unit calls the proxy model to perform rapid giant constellation orbit simulation according to the orbit proxy model parameters loaded by the real-time loading unit, and sends the simulation data to the result output unit. The results output unit processes the simulation data, performing real-time data processing and time-of-flight data processing. The real-time computing module also includes an instruction receiving unit and an instruction processing unit; When the instruction receiving unit receives a new satellite control instruction, it sends the new satellite control instruction to the instruction processing unit for processing; The instruction processing unit injects the received new satellite control instructions into the satellite to form new mega-constellation orbit information. Based on the new mega-constellation orbit information, it determines the number of new computing tasks and sends the new computing tasks to the computing pool module for simulation calculation.

2. The method for rapid simulation of high-precision orbits of giant constellations according to claim 1, characterized in that, The preprocessing module includes a data loading unit, a task scheduling unit, a preprocessing calculation unit, and a result processing unit. The initial orbital information of the giant constellation is stored in the data loading unit. During simulation calculations, the data loading unit determines the parameter information and sends the parameters to the task scheduling unit. After obtaining the parameter information, the task scheduling unit performs multi-process division of the computation task according to the number of satellites in the giant constellation, thus obtaining multi-process computation tasks. The multi-process computing task is assigned to the preprocessing computing unit. The preprocessing computing unit further subdivides the computing task into multiple parts according to the process and assigns them to multiple threads in the preprocessing computing unit for parallel computing to obtain the orbital proxy model parameters. The orbital proxy model parameters are sent to the result processing unit, which sorts and organizes the parameters and stores them in a file or database according to rules.

3. The method for rapid simulation of high-precision orbits of giant constellations according to claim 2, characterized in that, The data loading unit verifies the file format and data of the loaded file. If there are errors in the file format and data, the calculation process is interrupted and an error message is given to guide the user to modify the data file.

4. The method for rapid simulation of high-precision orbits of giant constellations according to any one of claims 1 to 3, characterized in that, The computing pool module includes a computing task receiving unit, a computing task management unit, a computing resource management unit, and a computing resource unit; The computing task receiving unit receives new computing tasks by function calls and records the function pointers and dependency data of the new computing tasks. At the same time, it sends the new computing tasks to the computing task management unit, which stores the new computing tasks by a task linked list. The computing resource management unit manages all computing resource units in a unified manner. When a new computing task arrives, the computing resource management unit wakes up the computing resource unit to start computing. The computing resource unit obtains the parameters of the new computing task from the task chain list of the computing task management unit, and starts the calculation according to the function pointer and dependency data to obtain the parameters of the new track proxy model.

5. The method for rapid simulation of high-precision orbits of giant constellations according to claim 4, characterized in that, The computing resource unit employs a multi-threaded parallel strategy to perform calculations on newly added computing tasks.

6. A high-precision rapid simulation device for the orbit of a giant constellation, characterized in that, The apparatus employing the high-precision rapid simulation method for the orbits of giant constellations according to any one of claims 1 to 5 comprises: The preprocessing module is used to perform rapid and high-precision orbit simulation calculations based on the initial orbit information of the giant constellation, and obtain orbit surrogate model parameters. A real-time computing module is used to send the orbital proxy model parameters to the real-time computing module for giant constellation orbit simulation; wherein, the real-time computing module uses a proxy model to perform rapid giant constellation orbit simulation. The computing pool module is used to send the computing task of the new satellite control command to the computing pool module for simulation calculation when the real-time computing module receives the new satellite control command, so as to obtain the new orbit proxy model parameters; and send the new orbit proxy model parameters to the real-time computing module to re-perform the giant constellation orbit simulation.

7. A computer device comprising a memory and a processor, wherein the memory stores a calculation program, characterized in that, When the processor executes the computer program, it implements the steps of the method according to any one of claims 1 to 5.

8. A computer-readable storage medium having a computer program stored thereon, characterized in that, When the computer program is executed by a processor, it implements the steps of the method according to any one of claims 1 to 5.

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