Using method of digital SOMT architecture for aerospace target simulation

Abstract

The invention discloses a method for using a digital SOMT architecture for aerospace target simulation. The method comprises the following steps: constructing a distributed space target orbit dynamics algorithm service, defining an aerospace simulation model template (SOMT), pre-calculating and caching the position, speed and attitude data of a space target, and responding to a time message and a discrete event message; based on a basic engine, through a micro-service cloud architecture and a message driving technology, a space target simulation service is provided, and a standardized simulation result is output. Through distributed orbit dynamics algorithm servitization packaging and micro-service architecture and in combination with pre-calculation and caching mechanisms, the simulation efficiency in a multi-target aerospace scene is remarkably improved, ephemeris data of a space target is pre-generated and cached, the real-time calculation frequency is reduced, simulation deduction of a larger-scale target and a higher speed can be supported, and the simulation efficiency of the multi-target aerospace scene is improved. And the method has efficient simulation deduction capability.

Description

Technical Field

[0001] The present invention relates to the technical field of digital model template design for aerospace mission space and air target simulation tasks, and particularly to a method for using a digital SOMT architecture for space and air target simulation. Background Art

[0002] In the process of designing and implementing current aerospace missions, aerospace mission simulation technology runs through the entire life cycle of aerospace missions and has become a key technology essential for the execution of aerospace missions.

[0003] In the conceptual design stage of spacecraft, digital modeling and simulation can help engineers quickly evaluate the feasibility and performance of different design schemes and shorten the design cycle. In the detailed design stage, accurate digital models can be used to simulate various performance indicators, platform payload states, and dynamic characteristics of spacecraft. Digital models can be used to analyze the orbits of spacecraft, predict and optimize their orbit parameters to ensure the achievement of mission objectives. Before mission execution, rehearsals through simulation can help identify potential problems and formulate countermeasures to improve mission success rates. Simulation modeling designs simulation scenarios, predicts possible platform failures and their impacts, and provides a basis for formulating emergency plans. In the implementation and operation stage, safety assessments are carried out through simulation to ensure the safety of spacecraft under various extreme conditions.

[0004] At the present stage, the commonly used simulation modeling methods for space and air missions generally inherit the traditional digital modeling and model-driven methods. For example, in the method of establishing models in HLA (High-Level Architecture, HLA), the Federation Object Model (FOM) defines the standards for shared data and interactions in the federation, including the definitions of objects, attributes, interactions, and parameters. Federation members advance time at fixed time steps. This mode is suitable for simulation applications that require continuous updating of random states over time. For the simulation of continuous systems, in addition to continuous-time driving, there is also a mode of discrete event-driven (Event-Driven) federation members, which advances according to the occurrence time of events to achieve discrete event simulation.

[0005] Time synchronization of model states generally has two modes: Conservative Synchronization and Optimistic Synchronization. Conservative synchronization ensures that events are processed strictly in the order of timestamps, avoiding time reversal. Usually, the "Time Advance Request (TAR)" mechanism is used. Optimistic synchronization allows events to be processed in the predicted order of time and rollback when time reversal occurs. Typical mechanisms are "Time Window" and "State Saving and Restoration".

[0006] The state update of existing simulation models relies on real-time time driving. Each time the time advances, the computational model of the model needs to be called. For large-scale multi-objective aerospace simulation scenarios, the efficiency of simulation deduction will be greatly reduced. Therefore, there is a need for an aerospace simulation model that conforms to the laws of motion of aerospace dynamics, optimizes the model driving method, and improves the simulation deduction efficiency of more targets and greater multiples.

[0007] For example, the invention application with the application number 202411013332.3 discloses a digital satellite simulation system and a simulation method. The simulation system includes a ground simulation module, a network management module, a data management module, and a satellite integrated electronics module. Its solution simulates various states of the satellite through a digital model, making the ground simulation test process more efficient and reliable. However, its solution has the problem of reducing the efficiency of simulation deduction for large-scale multi-objective aerospace simulation scenarios. Summary of the Invention

[0008] Aiming at the above problems, the purpose of the present invention is to provide a method for using a digital SOMT architecture for aerospace target simulation, which optimizes the model driving method and improves the simulation deduction efficiency of simulation targets.

[0009] An embodiment of the present invention provides a method for using a digital SOMT architecture for aerospace target simulation, including the steps of: S1. Construct a distributed space target orbital dynamics algorithm service, classify the orbital dynamics algorithms according to the algorithms, and realize the service-oriented encapsulation and call of the algorithms; S2. Define an aerospace simulation model template (SOMT), pre-compute and cache the position, velocity, and attitude data of space targets, and respond to time messages and discrete event messages; S3. Based on the orbital dynamics algorithm service and the aerospace simulation model template (SOMT), relying on the basic engine, through the microservice cloud architecture and message-driven technology, provide space target simulation services and output standardized simulation results; Among them, the space simulation model template (SOMT) application services include: satellite model simulation, ground station model simulation, rocket model simulation, surface target model simulation, sensor model simulation, and communication payload model simulation.

[0010] Furthermore, the orbital dynamics algorithms are classified by algorithm type as follows: Orbital dynamics calculation algorithms: including numerical integrators, numerical extrapolation algorithms, analytical extrapolation algorithms, numerical least squares algorithms for orbit determination, and analytical orbit determination estimation algorithms; Coordinate system algorithms: various coordinate system algorithms and conversion algorithms between coordinate systems; Planet body algorithms: including ellipsoid algorithms for the Earth, the Moon, and other planets in the solar system; Spacecraft attitude algorithms: defining the attitude of the spacecraft, including algorithms for pointing to the Earth, pointing to the Sun, attitude biases in the orbital coordinate system, and inertial pointing attitudes; Orbital dynamics perturbation algorithms: atmosphere algorithms, gravity field algorithms, thrust control algorithms, radiation pressure algorithms, solid tide algorithms, ocean tide algorithms; Orbit algorithms: including Keplerian elements, Cartesian orbit elements, and nearly circular orbit algorithms; Time algorithms: including time definition and time conversion.

[0011] Furthermore, the algorithm service encapsulation types include: orbit prediction, orbit determination, visible analysis of ground point targets, visible analysis of satellite payload ground areas, perigee and apogee prediction, terminator prediction, tracking prediction of ground stations, prediction of earth and lunar shadows, prediction of crossing meridians, prediction of crossing parallels, spacecraft attitude prediction and analysis, generation of orbit change strategies, inter-satellite visibility analysis, coordinate conversion, time conversion, and collision warning.

[0012] Furthermore, the standardized simulation result types include: satellite position and velocity, visible arc time window, three-point tracking prediction of ground stations, collision warning analysis results, RAE measurement data for equipment tracking, and various element predictions.

[0013] Furthermore, the space simulation model template (SOMT) format includes general fields and personalized fields.

[0014] Furthermore, the creation method of the space simulation model template (SOMT) includes: S21. Instantiate the model according to the type of space target object and preset the initial state of the model; S22. Initialize the object, input the orbital parameters and the time period of the simulation scenario into the model, calculate the relevant simulation data of the object, maintain the object MAP table, and store it in the data cache unit.

[0015] Further, the Space-Air Simulation Model Template (SOMT) is applied to satellite model simulation services, including the steps: S31. Trigger the satellite model initialization process, receive the input orbital parameters and extrapolation model type, parse the input satellite orbital parameters and the input orbital extrapolation model; S32. Determine whether the satellite orbital parameters are HPOP parameters; S33. If yes, enter S34; otherwise, directly execute S35; S34. Parse the perturbation parameters; S35. Extrapolate and calculate the satellite ephemeris data, cache the satellite ephemeris data, maintain the satellite object MAP table, insert a new object, and send a message indicating that the satellite object creation is completed.

[0016] Further, the steps for responding to the time message include: S41. Receive and parse the time synchronization message; S42. Retrieve the object list, obtain the ephemeris time window of the object, and check the end time point of the ephemeris time window of the object; S43. Determine whether the time window needs to be updated. If yes, enter S44; otherwise, directly execute S45; S44. Update the time window of the object and send a new object ephemeris message; S45. Determine whether it is the last object. If yes, end the response; otherwise, continue to execute S42.

[0017] Further, the discrete event includes an orbit change event. Responding to the orbit change event message includes the steps: S51. Receive and parse the orbit change event message in the message; S52. Generate an orbit change strategy queue and read the orbit change strategy queue; S53. Generate the ephemeris to the next orbit change time according to the acceleration component of the orbit change, and retrieve the orbital elements according to the orbit change time point; S54. Determine whether it is the last orbit change. Otherwise, read the next queue and execute S53. If yes, execute S55; S55. Generate the ephemeris to the end of the simulation according to the acceleration component of the orbit change, update the ephemeris data in the object cache, and end the response.

[0018] Advantages of the present invention: 1. Through the service encapsulation of the distributed orbital dynamics algorithm and the microservice architecture, combined with the pre-computation and caching mechanism, the present invention significantly improves the simulation efficiency in the multi-target space-air scenario. The ephemeris data of space targets is pre-generated and cached, reducing the real-time calculation frequency, and can support larger-scale targets and higher-speed simulation deductions, having efficient simulation deduction capabilities.

[0019] 2. The present invention uses message-driven technology to achieve efficient processing of time synchronization and discrete events (such as orbit transfer). Through the event queue management and the dynamic update mechanism of the ephemeris time window, while ensuring the timing accuracy, it avoids the computational redundancy of traditional conservative synchronization modes, improves the response speed to emergencies, and realizes the optimization of the response to dynamic events.

[0020] 3. The present invention classifies and serves the orbit dynamics algorithms according to functions (such as perturbation calculation, coordinate transformation, etc.) to form standardized algorithm service modules. Combining the separation design of the general and individual fields of the SOMT template, it supports the rapid expansion of heterogeneous models such as satellites, ground stations, and sensors, and improves the system reusability. The modular and extensible architecture caches pre-computed data through an in-memory database, and combines the object MAP table maintenance mechanism to reduce repeated calculations, realizes the display of measured data, improves the target carrying capacity under the same hardware conditions, reduces the consumption of computing resources, and effectively improves the resource utilization efficiency.

[0021] 4. The standardized output of the present invention includes structured data such as orbit element prediction and collision warning, covering the full-cycle requirements of spacecraft design, on-orbit operation, emergency deduction, etc. It supports multi-level simulations (from single-satellite refinement to constellation-level macroscopic deduction) to meet the verification requirements of different mission phases.

[0022] 5. The present invention can achieve seamless integration with traditional simulation architectures such as HLA by defining a unified message interface (such as the time synchronization message format) and data access APIs, is compatible with the existing aerospace simulation ecosystem, and enhances cross-platform compatibility. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 It is a schematic flow chart of the usage method of the digital SOMT architecture for aerospace target simulation of the present invention; Figure 2 It is a schematic structural diagram of the digital SOMT architecture for aerospace target simulation of the present invention; Figure 3 It is a schematic diagram of the SOMT general field code of the present invention; Figure 4 It is a schematic flow chart of the SOMT applied to satellite model simulation services of the present invention; Figure 5 It is a schematic flow chart of the SOMT responding to time messages of the present invention; Figure 6 It is a schematic flow chart of the SOMT responding to orbit transfer event messages of the present invention; Figure 7 It is a schematic diagram of the SOMT application example of the active section flight simulation of a rocket reflection of the present invention; Figure 8 It is a schematic structural diagram of the electronic device of the present invention. Detailed implementation manners

[0024] The embodiments of the present invention will be described in detail below. Examples of the embodiments are shown in the accompanying drawings, where the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below by referring to the accompanying drawings are exemplary and are only used to explain the present invention and should not be construed as a limitation to the present invention.

[0025] The state update of the existing simulation model relies on real-time time driving. Each time the time advances, the calculation model of the model needs to be called. For large-scale multi-target aerospace simulation scenarios, the efficiency of simulation deduction will be greatly reduced.

[0026] In view of the above problems, the present invention provides a method for using a digital aerospace simulation model template (SpaceObject Model Template SOMT) architecture for aerospace target simulation.

[0027] Figure 1 FIG. is a schematic structural diagram of the aerospace simulation model template (SOMT) architecture provided by the embodiment of the present invention. The architecture includes: a basic engine unit, an orbital dynamics calculation service unit, an aerospace target simulation model template unit, etc.

[0028] Among them, the services provided by the basic engine unit include: a service registration center, a message publishing and subscribing center, an in-memory database, an engine management service, a situation display component, etc.

[0029] The simulation services provided by the aerospace target simulation model template (SOMT) unit include: a satellite model, a ground station model, a rocket model, a surface target model, a sensor model, a communication payload model, etc.

[0030] Based on the above SOMT architecture, as Figure 1 shown, the present invention discloses a method for using a digital SOMT architecture for aerospace target simulation, including the steps of: S1. Construct a distributed space target orbital dynamics algorithm service, classify the orbital dynamics algorithms according to the algorithm type, and realize the service-oriented encapsulation and call of the algorithms.

[0031] The orbital dynamics calculation service (Xtalg Service) unit provides various algorithm services, classifies the mathematical models involved in various designed spacecraft orbital dynamics algorithms, and realizes the service-oriented call. In this way, the efficiency of orbital dynamics calculation can be optimized through distributed computing service nodes.

[0032] The orbital dynamics algorithms are classified according to the algorithm including but not limited to the following classifications: Orbit dynamics calculation algorithms: including numerical integrators, numerical extrapolation algorithms, analytical extrapolation algorithms, numerical orbit determination least squares algorithms, and analytical orbit determination estimation algorithms; Coordinate system algorithms: various coordinate system algorithms and conversion algorithms between coordinate systems; Planet body algorithms: including ellipsoid algorithms for the Earth, the Moon, and other planets in the solar system; Spacecraft attitude algorithms: defining the attitudes of spacecraft, including attitude algorithms such as earth-pointing, sun-pointing, attitude biases in the orbital coordinate system, inertial-pointing attitudes, etc.; Orbit dynamics perturbation algorithms: atmosphere algorithms, gravity field algorithms, thrust control algorithms, radiation pressure algorithms, solid tide algorithms, ocean tide algorithms; Orbit algorithms: including typical orbit algorithms such as Keplerian elements, Cartesian orbit elements, and near-circular orbits.

[0033] Time algorithms: including time definition and time conversion.

[0034] The Orbit Dynamics Calculation Service (Xtalg Service) unit provides services for the basic algorithms of aerospace target objects. According to the application requirements of aerospace target objects, various algorithms can be encapsulated into services to form service calls at the application level after encapsulation.

[0035] The types of algorithm service encapsulation include: orbit prediction, orbit determination, visible analysis of ground point targets, visible analysis of satellite payload ground areas, perigee and apogee prediction, terminator prediction, tracking prediction of ground stations, earth shadow and moon shadow prediction, longitude crossing prediction, latitude crossing prediction, spacecraft attitude prediction analysis, orbit transfer strategy generation, inter-satellite visibility analysis, coordinate conversion, time conversion, and collision warning, etc.

[0036] S2. Define the Space Object Model Template (SOMT), pre-compute and cache the position, velocity, and attitude data of space targets, and respond to time messages and discrete event messages.

[0037] The Space Object Model Template SOMT (Space Object Model Template) is designed in combination with the characteristics of aerospace target mission simulations to achieve pre-set caching of space position and attitude data, update the time window of simulation data, and can also implement the call of main interfaces.

[0038] Specifically, the format of the Space Object Model Template (SOMT) includes general fields and personalized fields, which are the definition codes for the general fields of the Space Object Model Template (SOMT). All models inherit this general field template and rewrite the common parts according to the actual behaviors of each simulation object. When the model service is initialized and started, it is registered in the service registry for the engine management service to call.

[0039] As shown Figure 3 It shows the general field to define the basic information of the model, the unique mark of the model object, the model name, to judge whether it is a parent model, to define the ID of the sub-model, the model parameters, and the scenario ID; to implement functions such as model object creation, model object deletion, model parameter modification, time synchronization message consumption response, and discrete event message response, and to maintain data retrieval and status retrieval.

[0040] By configuring the model parameters and object parameters through the general fields, time-driven can be achieved to ensure the system timing, which can improve the system response speed, standardize the unified interface, and improve the architecture expansion performance and code maintainability.

[0041] Each simulation model service not only manages all objects of this type of model, but also interacts with the simulation engine through message-driven and remote service calls to realize the deduction of the entire simulation process. Taking the parameter structure of the satellite object as an example of the personalized field, the specific code is as follows: Abstract structure MoldeParamater / / Model basic information { Int Id; / / Unique identifier of the model object string modlename / / Model name bool parent / / Whether it is a parent model Int parentId / / Sub-model ID Object initparamater / / Model parameters SenceId / / Scenario ID } class SatelliteParamater External MoldeParamater { OrbitBulletin orbit / / Satellite orbit parameters ForceModle forcemodel / / Orbit perturbation Propagator propagator / / Extrapolator model } Based on inheriting the general fields, the above-mentioned personalized fields realize the setting of the personalized parameter structure of the satellite orbit parameters, orbit perturbation, and extrapolator model of the satellite object.

[0042] Furthermore, the creation method of the space simulation model template (SOMT) includes: S21. Instantiate the model according to the type of space target object and preset the initial state of the model; S22. Initialize the object, input the orbital parameters and the time period of the simulation scenario into the model, calculate the relevant simulation data of the object, maintain the object MAP table, and store it in the data cache unit.

[0043] According to the initialization parameters of different models, instantiate the model object, preset the initial state of the model, and manage the object MAP table. As Figure 2 shown, the common objects in space mission simulation include satellites, ground targets, rockets, ground moving targets (non-real-time maneuver), sensor payloads, communication payloads, radar payloads, optical payloads, and infrared payloads, etc. Payloads are generally attached to satellite or ground station objects, so a parent object should be defined for such objects. When initializing space targets, based on the input orbital parameters, calculate the position, velocity, and attitude data of the aerospace target object according to the time period of the simulation scenario, and store it in the data cache of the simulation object.

[0044] For aerospace service simulation applications, the position, velocity, and attitude data of space targets updated over time are the basic inputs for many simulation calculations, including visibility calculations (TT&C plan, observation plan, data transmission plan), simulation observation data (external measurement, optical measurement data), and are also the basic inputs for payload data simulation (remote sensing, infrared, communication link, and interference, etc.). By presetting and calculating the ephemeris of space targets, the simulation efficiency can be effectively improved.

[0045] The method for creating the aerospace simulation model template (SOMT) is mainly to instantiate the model object according to the parameters, calculate the relevant simulation data of the object through the set initialization parameters, maintain the object map table, add the model object, and send a message indicating that the object creation is completed to the relevant services.

[0046] Taking the satellite platform as an example below, as Figure 4 shown, the process of creating a satellite model object is described, including the steps: S31. Trigger the satellite model initialization process, receive the input orbital parameters and the type of extrapolation model, and parse the input satellite orbital parameters and the input orbital extrapolation model; S32. Determine whether the satellite orbital parameters are HPOP parameters; S33. If yes, go to S34; otherwise, directly execute S35; S34. Parse the perturbation parameters; S35. Extrapolate and calculate the satellite ephemeris data, cache the satellite ephemeris data, maintain the satellite object MAP table, insert a new object, and send a message indicating that the satellite object creation is completed.

[0047] For the response processing of time synchronization messages, the system architecture subscribes to time messages and updates the status of model objects according to the time, including publishing the time window of the latest simulation data or publishing real-time simulation data, and updating the object status by time point. Taking the satellite platform model as an example, as Figure 5 shown, the satellite platform model responds to time messages, and the steps include: S41. Receive and parse the time synchronization message; S42. Retrieve the object list, obtain the ephemeris time window of the object, and check the end time point of the ephemeris time window of the object; S43. Judge whether the time window needs to be updated. If so, go to S44; otherwise, directly execute S45; S44. Update the time window of the object and send a new message of the object ephemeris; S45. Judge whether it is the last object. If so, end the response; otherwise, continue to execute S42.

[0048] It can be known from the above solution that the response processing of the satellite platform model time synchronization message mainly completes two tasks: One is to calculate the start and end times of the current and next orbits of the satellite object according to the time point, and publish a message to notify other model objects and application services that need to update the orbit data to retrieve the orbit data of the current object from the cache database. For example, the front-end situation promotes the satellite movement and updates the orbit data in a timely manner. The other is to retrieve the event timeline queue of the satellite object, whether an event start or end is triggered, and make a response. For example, when a satellite orbit change start event is triggered, a message will be sent, and the satellite situation display will make corresponding effects.

[0049] For the response processing of discrete event messages, subscribe to the discrete event messages for this type of model and make a response. Different models update corresponding data or status for different events. And manage the event timeline table of the object (insert the events into the list according to the timeline of the events), including the simulation data of the object. The status update is subscribed by the front-end state component and the situation status is updated. Taking the satellite platform orbit change event as an example, as Figure 6 shown, the response to the orbit change event message includes the steps: S51. Receive and parse the message of the orbit change event in the message; S52. Generate an orbit change strategy queue and read the orbit change strategy queue; S53. Generate the ephemeris to the next orbit change time according to the acceleration component of the orbit change, and retrieve the orbital elements according to the orbit change time point; S54. Judge whether it is the last orbit change. Otherwise, read the next queue and execute S53. If so, execute S55; S55. Generate the ephemeris until the end time of the simulation based on the acceleration components of the orbit change, update the ephemeris data in the object cache, and end the response.

[0050] It can be learned from the above solution that the discrete events of the satellite platform model mainly include events such as satellite orbit change and satellite disintegration. Taking the satellite orbit change event response as an example, when receiving the event message of satellite orbit change, the sequence of orbit change time points and the sequence of acceleration components in the event message are used as parameters to extrapolate the orbit data to the next orbit change point, and so on until the orbit change is completed. Then extrapolate the ephemeris of the satellite object until the end of the simulation and update the ephemeris in the cache. At the same time, save the time line of the orbit change time into the event queue. The event can be a preset event during scenario design or a random guidance event temporarily added during the simulation process.

[0051] At the same time, the system can use the simulation data access interface to remotely provide the retrieval and query of object data. Use the management interface of the model object to realize the addition, deletion and parameter update of the object, and make corresponding updates to the object data according to the operation.

[0052] S3. Based on the orbit dynamics algorithm service and the space - air simulation model template (SOMT), relying on the basic engine, through the microservice cloud architecture and message - driven technology, provide space target simulation services and output standardized simulation results.

[0053] According to the simulation call of the space - air target object, after the corresponding space - air simulation digital model template design and planning calculation service, the calculation output result data in standard format can be output. The standardized simulation result data types include: satellite position and velocity, visible arc time window, three - point prediction of station tracking, collision warning analysis structure, equipment tracking RAE measurement data, and various root number predictions, etc.

[0054] Application case of the space - air simulation model template SOMT: such as Figure 7 shown in the schematic diagram of the active - section flight simulation of rocket launch.

[0055] The model template of the present invention has been successfully applied in the Insight space analysis software of Star Map Measurement and Control and various simulation projects, and achieved good results.

[0056] The present invention defines an implementation model template SOMT (Space Object Model Template) for an aerospace service simulation model and its usage method. Different from the implementation and driving standards of traditional simulation models, aerospace service simulation has its own characteristics. In particular, the motion characteristics of space objects (satellites, spacecraft, rockets, space debris) always follow specific space dynamics physical laws. According to the initial orbital parameters and different requirements, corresponding mathematical models (two-body, J2, J4, SGP4, HPOP, etc.) can be used to calculate considering different perturbations. Therefore, under the condition that the initial simulation conditions are determined, data such as the position, velocity, and attitude of the object can be pre-calculated, and there is no need to frequently call the algorithm model during the simulation process, which can improve the efficiency of simulation deduction. Combining the message publishing and subscribing mechanism to achieve continuous-time driving and discrete-event driving of the model, it is applicable to the implementation of aerospace simulation services and can more efficiently implement aerospace service simulation deduction.

[0057] The present invention also provides an electronic device. Figure 8 As shown in the structural schematic diagram of the electronic device provided by the embodiment of the present invention, Figure 8 the electronic device may include: a processor, a communication interface, a memory, and a communication bus. Among them, the processor, the communication interface, and the memory complete communication with each other through the communication bus. The processor can call the logical instructions in the memory, for example, to execute the following methods: S1. Construct a distributed space object orbital dynamics algorithm service, classify the orbital dynamics algorithms according to the algorithms, and implement service-oriented encapsulation and invocation of the algorithms; S2. Define an aerospace simulation model template (SOMT), pre-calculate and cache the position, velocity, and attitude data of space objects, and respond to time messages and discrete event messages; S3. Based on the orbital dynamics algorithm service and the aerospace simulation model template (SOMT), relying on the basic engine, through the microservice cloud architecture and message-driven technology, provide space object simulation services and output standardized simulation results.

[0058] In addition, when the logical instructions in the above-mentioned memory are implemented in the form of software functional units and sold or used as independent products, they can be stored in a computer-readable storage medium. Based on such an understanding, the technical solution of the present invention, in essence, or the part that contributes to the prior art, or a part of the technical solution, can be embodied in the form of a software product. This computer software product is stored in a storage medium and includes several instructions for causing a computer device (which may be a personal computer, a server, or a network device, etc.) to execute all or part of the steps of the methods described in various embodiments of the present invention. The foregoing storage medium includes: various media such as USB flash drives, mobile hard disks, read-only memories (ROM, Read-Only Memory), random access memories (RAM, Random Access Memory), magnetic disks, or optical discs that can store program codes.

[0059] Embodiments of the present invention also provide a non-transitory computer-readable storage medium, on which a computer program is stored. When the computer program is executed by a processor, it is configured to execute the methods provided in the above-mentioned various embodiments, for example, including: S1. Construct a distributed space target orbit dynamics algorithm service, classify the orbit dynamics algorithms according to the algorithm types, and realize the service-oriented encapsulation and invocation of the algorithms; S2. Define a space-air simulation model template (SOMT), pre-calculate and cache the position, velocity, and attitude data of space targets, and respond to time messages and discrete event messages; S3. Based on the orbit dynamics algorithm service and the space-air simulation model template (SOMT), relying on the basic engine, through the microservice cloud architecture and message-driven technology, provide space target simulation services and output standardized simulation results.

[0060] The device embodiments described above are merely illustrative. The units described as separate components may or may not be physically separated, and the components shown as units may or may not be physical units, that is, they may be located in one place or distributed to multiple network units. Some or all of the modules can be selected according to actual needs to achieve the purpose of the solution of this embodiment. Those of ordinary skill in the art can understand and implement it without creative efforts.

[0061] Through the description of the above embodiments, those skilled in the art can clearly understand that each embodiment can be implemented by means of software plus a necessary general hardware platform, and of course, it can also be implemented by hardware. Based on such an understanding, the essence of the above technical solution, or the part that contributes to the prior art, can be embodied in the form of a software product. This computer software product can be stored in a computer-readable storage medium, such as ROM / RAM, magnetic disk, optical disk, etc., and includes several instructions to enable a computer device (which can be a personal computer, server, or network device, etc.) to execute the methods described in each embodiment or some parts of the embodiments.

[0062] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit them; although the present invention has been described in detail with reference to the foregoing embodiments, those of ordinary skill in the art should understand that they can still modify the technical solutions recorded in the foregoing embodiments, or perform equivalent replacements for some of the technical features; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A method for using a digital SOMT architecture for aerospace target simulation, characterized in that: include: S1. Build a distributed space target orbital dynamics algorithm service, classify the orbital dynamics algorithm by algorithm, and realize the algorithm service encapsulation and call; S2. Define the space-air simulation model template SOMT, pre-calculate and cache the position, velocity and attitude data of space targets, and respond to time messages and discrete event messages; S3, based on orbital dynamics algorithm service and aerospace simulation model template SOMT, relying on the basic engine, through microservice cloud architecture and message-driven technology, provides space target simulation services and outputs standardized simulation results; Among them, the aerospace simulation model template SOMT application services include: satellite model simulation, ground station model simulation, rocket model simulation, surface target model simulation, sensor model simulation and communication payload model simulation.

2. The method for using the SOMT architecture according to claim 1, characterized in that: The orbital dynamics algorithms are classified into the following categories: Orbital dynamics calculation algorithms: including numerical scorer, numerical extrapolation algorithm, analytical extrapolation algorithm, numerical orbit determination least squares algorithm and analytical orbit determination estimation algorithm; Coordinate system algorithm: coordinate system algorithm and conversion algorithm between coordinate systems; Planetary algorithms: including ellipsoid algorithms for the Earth, Moon, and other planets in the solar system; Spacecraft attitude algorithm: defines the attitude of the spacecraft, including Earth pointing, Sun pointing, orbital coordinate system attitude bias and inertial pointing attitude algorithm; Orbital dynamics perturbation algorithms: atmosphere algorithm, gravity field algorithm, thrust control algorithm, light pressure algorithm, solid tide algorithm and ocean tide algorithm; Orbital algorithms: including Kepler roots, Cartesian orbital roots and near-circular orbital algorithms; Time algorithm: includes time definition and time conversion.

3. The method for using the SOMT architecture according to claim 2, characterized in that: The algorithm service packaging types include: orbit prediction, orbit determination, ground point target visibility analysis, satellite payload ground area visibility analysis, perigee and apogee prediction, terminator prediction, station tracking prediction, earth and moon shadow prediction, longitude crossing prediction, latitude crossing prediction, spacecraft attitude prediction analysis, orbit change strategy generation, inter-satellite visibility analysis, coordinate conversion, time conversion and collision warning.

4. The method for using the SOMT architecture according to claim 1, characterized in that: The standardized simulation result types include: satellite position velocity, visible arc time window, station tracking three-point forecast, collision warning analysis structure, equipment tracking RAE measurement data and root number forecast.

5. The method for using the SOMT architecture according to claim 1, characterized in that: The aerospace simulation model template SOMT format includes general fields and individual fields.

6. The method for using the SOMT architecture according to claim 1, characterized in that: The method for creating the aerospace simulation model template SOMT comprises: S21, instantiating the model according to the type of the spatial target object, and presetting the initial state of the model; S22, initialize the object, input the orbit parameters and the time period of the simulation scene into the model, calculate the relevant simulation data of the object, maintain the object MAP table, and store it in the data cache unit.

7. The method for using the SOMT architecture according to claim 1, characterized in that: The space-air simulation model template SOMT is applied to satellite model simulation service, including the steps of: S31, triggering the satellite model initialization process, receiving input orbital parameters and extrapolation model type, parsing the input satellite orbital parameters and parsing the input orbital extrapolation model; S32, determining whether the satellite orbit parameter is a HPOP parameter; S33, if yes, go to S34, otherwise go directly to S35; S34, analytical perturbation parameters; S35, extrapolate and calculate satellite ephemeris data, cache the satellite ephemeris data, maintain the satellite object MAP table, insert a new object, and send a message that the satellite object creation is completed.

8. The method for using the SOMT architecture according to claim 1, characterized in that: The step of responding to the time message comprises: S41, receiving and parsing a time synchronization message; S42, searching the object list, obtaining the ephemeris time window of the object, and checking the end time point of the ephemeris time window of the object; S43, determine whether the time window needs to be updated, if yes, proceed to S44, otherwise directly execute S45; S44, updating the time window of the object and sending a new ephemeris message of the object; S45. Determine whether it is the last object, if yes, end the response, otherwise continue to execute S42.

9. The method for using the SOMT architecture according to claim 1, characterized in that: The discrete event includes a track change event, and responding to the track change event message includes the steps of: S51, receiving and parsing a message of a track change event in the message; S52, generating a track change strategy queue, and reading the track change strategy queue; S53, generating ephemeris to the next orbit change time according to the acceleration component of the orbit change, and retrieving the orbital elements according to the orbit change time point; S54, determine whether it is the last track change, if not, read the next queue and execute S53, if yes, execute S55; S55, generating ephemeris according to the acceleration component of the orbit change to the simulation end time, updating the ephemeris data in the object cache, and ending the response.

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