Deep space exploration constellation system integration simulation verification method
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- DEEP SPACE EXPLORATION TECH (BEIJING) CO LTD
- Filing Date
- 2026-03-24
- Publication Date
- 2026-06-23
Smart Images
Figure CN122263267A_ABST
Abstract
Description
Technical Field
[0001] This invention belongs to the field of aerospace digital simulation and verification technology, specifically involving an integrated simulation and verification method for deep space exploration constellation systems. Background Technology
[0002] Deep space exploration constellation systems are massive and complex systems consisting of hundreds to tens of thousands of satellites distributed globally. Their design process involves deep coupling of multiple disciplines, including orbital configuration, communication coverage, configuration maintenance, and energy balance. To ensure the correctness and reliability of the design scheme before system construction, it is essential to conduct thorough analysis, modeling, and simulation verification of the overall scheme and key technologies.
[0003] Traditional spacecraft simulation verification typically employs a "document-driven" model: designers first write design documents, simulation engineers manually build simulation models based on these documents, and the simulation results are then fed back to the designers in the form of reports. This model works well for single-satellite or small-scale constellations, but it reveals the following shortcomings when dealing with giant and complex systems such as deep-space exploration constellations:
[0004] First, there is a disconnect between design and simulation data. Design models and simulation models are built by different teams in different software environments, and there is a lack of direct data correlation between the two. Changes in design parameters are difficult to be promptly transmitted to the simulation model, and simulation results cannot be automatically written back to the design model, resulting in a disconnect between design and simulation, long verification cycles, and low efficiency.
[0005] Secondly, multidisciplinary simulation tools are difficult to coordinate. Constellation system verification typically requires the integrated use of multiple specialized software tools, such as orbit simulation tools (e.g., STK), numerical calculation tools (e.g., Matlab), and network simulation tools. These tools operate independently, with inconsistent data formats and interface standards, making it difficult to achieve joint simulation and data interoperability among multiple tools.
[0006] Secondly, collaborative development among multiple entities faces the challenge of network isolation. The development of constellation systems often involves multiple participating parties, including overall system developers, satellite developers, telemetry and control (TT&C) units, and launch site operators. These entities' networks are often isolated, making it impossible to deploy a unified real-time messaging middleware. Traditional API- or DDS-based co-simulation solutions are difficult to implement in this environment.
[0007] Finally, the verification process lacks an automated closed loop. In traditional verification processes, simulation results require manual analysis, judgment, and modification of design parameters, which is not only inefficient but also prone to human error. When multiple rounds of iterative optimization are required, the labor and time costs increase dramatically.
[0008] Therefore, there is an urgent need for an integrated simulation verification method that can break down the data barriers between design models and simulation models, support multi-tool joint simulation, adapt to multi-unit network isolation environments, and achieve automated closed-loop iteration, so as to support the efficient and high-quality development of deep space exploration constellation systems. Summary of the Invention
[0009] To address the aforementioned technical issues, this invention provides an integrated simulation verification method for deep space exploration constellation systems. It constructs a standardized message bus using CSV files as a cross-domain transmission carrier, establishing a bidirectional data channel between the design model and multidisciplinary simulation tools. This enables an unattended, automated iterative closed loop of "parameter export → simulation execution → result write-back → model update," resolving the problem of data fragmentation between design and simulation in multi-unit network isolation environments.
[0010] To achieve the above objectives, the present invention adopts the following technical solution:
[0011] An integrated simulation and verification method for deep space exploration constellation systems includes:
[0012] Step 1: Obtain a digital design model of the constellation system that includes a four-level structure: requirements, functions, logic, and physical.
[0013] Step 2: Construct a standardized message bus based on CSV files to establish bidirectional data connections between the digital design model and multiple external professional simulation tools;
[0014] Step 3: Extract design parameters from the digital design model and encapsulate them into a first CSV file. Transmit the first CSV file to an external simulation tool via the message bus to drive it to perform simulations of coverage analysis, configuration maintenance, and energy balance.
[0015] Step 4: Listen to the message bus, obtain the second CSV file output by the external simulation tool, and parse the simulation result data in it;
[0016] Step 5: Automatically write the simulation result data back to the digital design model, triggering the automatic update of the corresponding design parameters in the digital design model;
[0017] Step 6: Repeat steps 1-5 until the simulation result data meets the preset verification conditions or optimization objectives, and generate a simulation verification report.
[0018] Furthermore, in step 2, the standardized message bus uses CSV files as the sole carrier for cross-domain data transmission. In an environment of collaborative development by multiple units and network isolation, real-time monitoring and automatic transmission of CSV files in a specified directory are achieved by deploying file monitoring units in each unit, thus avoiding the need to deploy a unified real-time message middleware.
[0019] Furthermore, in step 3, when the first CSV file is transmitted to an external simulation tool via the message bus to drive it to perform coverage analysis, configuration maintenance, and energy balance simulation, the input parameters and output parameters are associated through a predefined parameter mapping relationship; the first CSV file contains at least one of the following design parameters: orbital altitude, orbital inclination, solar array area, battery capacity, and payload power consumption.
[0020] Furthermore, in step 4, the second CSV file contains at least one of the following simulation result parameters: coverage weight, continuous coverage time, average number of visible satellites, discharge depth, and drift amount.
[0021] Furthermore, in step 5, after the simulation result data is automatically written back to the digital design model, the consistency check and correlation impact analysis of the model are triggered, and the traceability relationship between each design parameter and the top-level service indicator in the model is automatically updated.
[0022] Furthermore, in step 6, when the simulation results do not meet the verification conditions, the design parameters are automatically adjusted and the simulation is re-driven, forming an unattended iterative closed loop of "design parameter export - simulation execution - result write-back - model update".
[0023] Furthermore, the simulation verification report generated in step 6 includes design compliance conclusions, key indicator margin analysis, multi-scheme trade-off results, and marks the parameter items that do not meet the indicator requirements and their deviations.
[0024] Furthermore, the CSV file includes file naming conventions, header definitions, and data area structures, supporting multi-round iteration identification and the organization of time-varying data.
[0025] Secondly, the present invention provides an electronic device, comprising: one or more processors; and a memory for storing one or more programs; wherein, when the one or more programs are executed by the one or more processors, the one or more processors implement the aforementioned integrated simulation verification method for deep space exploration constellation systems.
[0026] Thirdly, the present invention provides a computer-readable storage medium having executable instructions stored thereon, which, when executed by a processor, enable the processor to implement the aforementioned integrated simulation and verification method for deep space exploration constellation systems.
[0027] The beneficial effects of this invention are as follows:
[0028] First, it achieves a two-way closed-loop connection between design and simulation. By constructing a standardized message bus based on CSV files, it breaks down the data barriers between digital design models and multidisciplinary simulation tools. Design parameters can be automatically exported to drive simulation, and simulation results can be automatically written back to update the model, completely solving the problems of separation between design and simulation and data asynchrony in the traditional model.
[0029] Second, it adapts to network isolation environments in collaborative research and development among multiple units. Addressing the practical challenges of network isolation among participating units and the inability to deploy a unified message middleware, CSV files are used as the sole carrier for cross-domain data transmission. Automated data interaction is achieved through a file monitoring mechanism, which neither alters the existing network topology of each unit nor requires the deployment of additional complex middleware, making it highly applicable to various projects.
[0030] Third, it enables unattended automated iterative verification. Through an automated closed-loop mechanism of "parameter export → simulation execution → result write-back → model update," multiple rounds of simulation iterations can be completed without manual intervention until the verification conditions or optimization goals are met. Compared with the traditional manual mode, verification efficiency is improved by several times, significantly shortening the development cycle.
[0031] Fourth, enhance the comprehensiveness and traceability of design verification. After simulation results are automatically written back to the model, the traceability relationship between each design parameter and the top-level service indicator is updated synchronously, and the indicator satisfaction status is calculated in real time. The final simulation verification report includes design compliance conclusions, key indicator margin analysis, and multi-scheme trade-off results, providing quantitative basis for system decision-making. Attached Figure Description
[0032] Figure 1 This is a schematic diagram of the integrated simulation verification method for deep space exploration constellation system of the present invention. Detailed Implementation
[0033] The present invention will be further described below with reference to the accompanying drawings and embodiments.
[0034] like Figure 1 As shown, this invention provides an integrated simulation verification method for deep space exploration constellation systems, including:
[0035] Step 1: Obtain a digital design model of the constellation system that includes a four-level structure: requirements, functions, logic, and physical.
[0036] Step 2: Construct a standardized message bus based on CSV files to establish bidirectional data connections between the digital design model and multiple external professional simulation tools;
[0037] Step 3: Extract design parameters from the digital design model and encapsulate them into a first CSV file. Transmit the first CSV file to an external simulation tool via the message bus to drive it to perform simulations of coverage analysis, configuration maintenance, and energy balance.
[0038] Step 4: Listen to the message bus, obtain the second CSV file output by the external simulation tool, and parse the simulation result data in it;
[0039] Step 5: Automatically write the simulation result data back to the digital design model, triggering the automatic update of the corresponding design parameters in the digital design model;
[0040] Step 6: Repeat steps 1-5 until the simulation result data meets the preset verification conditions or optimization objectives, and generate a simulation verification report.
[0041] In step 1, the design of the constellation system begins with requirements. The technical process of research and development is controlled through requirements management, and the overall model of the deep space exploration constellation and the architecture of the deep space exploration constellation system are modeled through requirements analysis. Based on an improved methodology applicable to deep space exploration engineering, the requirements are decomposed and refined into problem domain black boxes, problem domain white boxes, and solution domains for deep space exploration constellation system modeling.
[0042] In the problem domain, the focus is on modeling the constellation's top-level capabilities. Activity diagrams and block definition diagrams are used to initially divide the constellation's functions and components. The external environment and external interfaces of the constellation are outlined in the form of internal block diagrams and tables. In the solution domain, starting from the constellation's configuration parameters, activity diagrams are used to illustrate each stage of the constellation's lifecycle, such as launch and networking. Based on this, activity diagrams, state machine diagrams, and other diagrams are used to analyze the unique service and maintenance processes of each stage.
[0043] As shown in Table 1, the requirements layer is used to carry the top-level mission requirements and stakeholder demands of the constellation system, including modeling steps such as mission requirement analysis, business scenario analysis, and stakeholder analysis. The functional layer describes the typical business capabilities that the constellation system should possess, mainly including constellation deployment capabilities, autonomous operation capabilities, constellation service capabilities, and constellation operation and maintenance capabilities. The logical layer defines the constellation system's architecture and interface relationships, including constellation configuration, inter-satellite links, and space-to-ground links. The physical layer describes the payload configuration and individual unit composition of the satellite platform, including detailed definitions of the payload and the satellite platform.
[0044] Table 1
[0045] In step 2, to achieve multi-tool joint simulation, the interactive form and content of the joint simulation verification process are constructed with CSV files as the core. CSV files, with their convenient and effective method of file identification, are a file encoding format that can carry simulation data and are easy to implement without requiring secondary development on the original basis, serving as the joint simulation verification message bus. In a multi-unit collaborative development environment with network isolation, CSV files are used as the sole carrier for cross-domain data transmission. Real-time monitoring and automatic transmission of CSV files in designated directories are achieved by deploying file monitoring units in each unit, avoiding the deployment of a unified real-time message middleware. Specifically, the design concept of CSV files as the data exchange carrier is as follows:
[0046] Standardized structure definition:
[0047] File naming conventions: A set of naming rules is used to include key metadata, such as project ID_simulation type_tool name_timestamp.csv, to facilitate automatic identification and processing by the system.
[0048] Table header design: The first row (header) clearly defines the meaning, unit, data type (such as string, float, int), and possible valid range of each column of data. This is key to achieving consistent semantic understanding between tools.
[0049] Data area: Starting from the second row, this contains the actual data. Each row can represent a simulation scenario, a satellite, or a set of parameters for a time step.
[0050] Content and data mapping:
[0051] The “first CSV file” (design parameter file) may contain columns that correspond to key design parameters extracted from the digital design model, such as satellite_id, orbit_altitude_km, orbit_inclination_deg, solar_panel_area_m2, battery_capacity_Ah, payload_power_W, etc.
[0052] The "second CSV file" (simulation result file) contains columns that correspond to the output of external simulation tools, such as coverage_redundancy, max_gap_duration_min, average_visible_sats, battery_DOD_percent, drift_rate_deg_per_day, etc.
[0053] Parameter mapping: The system will pre-define or configure each column in the design parameter CSV, the corresponding column in the simulation result CSV, and how they correspond back to the specific parameter attributes in the digital design model. This is the foundation for achieving "automatic write-back" and "triggered update".
[0054] Supports iteration and serialization:
[0055] The CSV file may contain columns such as iteration_id and scenario_id to distinguish different design iteration rounds or simulation schemes.
[0056] For time-varying data (such as orbital sequences), different time points may be represented by multiple rows, or the data may be organized through multiple related CSV files.
[0057] In step 3, when driving the external simulation tool to perform coverage analysis, orbital altitude and orbital inclination are used as inputs, and the continuous coverage time and average number of visible satellites are output. By exporting the input parameters as CSV files and transmitting them to the simulation program, a single set of data can serve as a scheme for one coverage characteristic analysis, and multiple sets of analysis scheme parameters can be obtained by transmitting multiple input files.
[0058] When driving external simulation tools to perform configuration maintenance analysis, the inputs are track height, track inclination, and control accuracy threshold. The outputs are out-of-tolerance time, control timing, track surface drift, and phase drift. Based on the parametric model design, an instance table is used to input the input parameters as default values for key identification parameters. These values are then exported as a CSV file and stored in the co-simulation's monitoring program before being transmitted to the simulation program for simulation.
[0059] When driving external simulation tools to perform energy balance analysis, the system takes the power consumption of each payload, the definition of the operating mode, the solar panel area, and the battery capacity as inputs, and outputs the depth of discharge, bus voltage, and remaining battery capacity. The system designs the intrinsic principles of satellite energy balance through parameter diagrams, using the power consumption parameters of each payload as value attributes. The corresponding power consumption calculations are embedded in the constraint module in .M file format, and the parameters are used as inputs to connect to the constraint module for simulation.
[0060] In step 4, the system can monitor the status of the simulation platform receiving design model parameter transmissions and provide online feedback on the calculation progress. After the configuration design simulation is completed, the system outputs optimized parameters such as orbital altitude, orbital inclination, number of satellites per orbit, number of orbits, and constellation phase factor. After the coverage characteristic analysis is completed, the system outputs parameters such as coverage multiplicity, continuous coverage time, and average number of visible satellites. After the configuration maintenance analysis is completed, the system outputs parameters such as out-of-tolerance time, control timing, orbital plane drift, and phase drift.
[0061] In step 5, the simulation result data parsed from the second CSV file is automatically written back to the digital design model according to the predefined parameter mapping relationship, corresponding to the value attributes or constraint attributes of the first design parameter, and triggering the model's consistency check and correlation impact analysis. Through the co-simulation message bus centered on the CSV file, bidirectional data transmission between the design model and the simulation model is achieved, and the simulation result data is automatically written back to the design model, completing the design closed-loop iteration.
[0062] In step 6, it is assumed that the coverage weight is ≥2 and the discharge depth is ≤40% as the verification conditions. When the simulation results do not meet the verification conditions, the design parameters such as the orbital height and solar wing area are automatically adjusted and the simulation is re-driven to form an unattended iterative closed loop of "design parameter export → simulation execution → result write-back → model update" until the verification conditions are met or the preset maximum number of iterations is reached.
[0063] After each simulation result is written back to the digital design model, the traceability relationship between each design parameter and the top-level service indicator in the model is automatically updated, and the satisfaction of the top-level service indicator is recalculated. By conducting traceability coverage confirmation of the preliminary system design requirements and task requirements, as well as traceability coverage confirmation of the single-satellite development requirements and the preliminary system design requirements, the integrity and traceability of the requirements are ensured.
[0064] The design parameters and final simulation results data at each level are extracted from the digital design model after iterative convergence. A simulation verification report, including design compliance conclusions, key indicator margin analysis, and multi-scheme trade-offs, is automatically generated according to a predefined report template. As shown in Table 1, corresponding to the "Deep Space Exploration Constellation System Design Comprehensive Verification" step, a traceability coverage verification of the system's preliminary design requirements and mission requirements, as well as a traceability coverage verification between requirements at each level and design elements, is conducted. Parameters that do not meet the indicator requirements and their deviations are marked in the simulation verification report.
[0065] In summary, this invention, through the above steps, constructs a standardized message bus using CSV files as the cross-domain transmission carrier, opening up a bidirectional data channel between the design model and multidisciplinary simulation tools. It realizes an unattended, automated iterative closed loop of "parameter export → simulation execution → result write-back → model update," effectively solving the problem of data separation between design and simulation in a multi-unit collaborative development environment.
[0066] Secondly, the present invention provides an electronic device, comprising: one or more processors; and a memory for storing one or more programs; wherein, when the one or more programs are executed by the one or more processors, the one or more processors implement the aforementioned integrated simulation verification method for deep space exploration constellation systems.
[0067] Thirdly, the present invention provides a computer-readable storage medium having executable instructions stored thereon, which, when executed by a processor, enable the processor to implement the aforementioned integrated simulation and verification method for deep space exploration constellation systems.
[0068] The specific embodiments described above further illustrate the purpose, technical solution, and beneficial effects of the present invention. It should be understood that the above descriptions are merely specific embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.
Claims
1. An integrated simulation and verification method for deep space exploration constellation systems, characterized in that, include: Step 1: Obtain a digital design model of the constellation system that includes a four-level structure: requirements, functions, logic, and physical. Step 2: Construct a standardized message bus based on CSV files to establish bidirectional data connections between the digital design model and multiple external professional simulation tools; Step 3: Extract design parameters from the digital design model and encapsulate them into a first CSV file. Transmit the first CSV file to an external simulation tool via the message bus to drive it to perform simulations of coverage analysis, configuration maintenance, and energy balance. Step 4: Listen to the message bus, obtain the second CSV file output by the external simulation tool, and parse the simulation result data in it; Step 5: Automatically write the simulation result data back to the digital design model, triggering the automatic update of the corresponding design parameters in the digital design model; Step 6: Repeat steps 1-5 until the simulation result data meets the preset verification conditions or optimization objectives, and generate a simulation verification report.
2. The integrated simulation verification method for deep space exploration constellation systems according to claim 1, characterized in that, In step 2, the standardized message bus uses CSV files as the sole carrier for cross-domain data transmission. In an environment of multi-unit collaborative development and network isolation, real-time monitoring and automatic transmission of CSV files in a specified directory are achieved by deploying file monitoring units in each unit, thus avoiding the need to deploy a unified real-time message middleware.
3. The integrated simulation verification method for deep space exploration constellation systems according to claim 1, characterized in that, In step 3, when the first CSV file is transmitted to an external simulation tool via the message bus and driven to perform coverage analysis, configuration maintenance, and energy balance simulation, the input parameters and output parameters are associated through a predefined parameter mapping relationship; the first CSV file contains at least one of the following design parameters: orbital altitude, orbital inclination, solar array area, battery capacity, and payload power consumption.
4. The integrated simulation verification method for deep space exploration constellation systems according to claim 1, characterized in that, In step 4, the second CSV file shall contain at least one of the following simulation result parameters: coverage weight, continuous coverage time, average number of visible satellites, discharge depth, and drift amount.
5. The integrated simulation verification method for deep space exploration constellation systems according to claim 1, characterized in that, In step 5, after the simulation result data is automatically written back to the digital design model, the consistency check and correlation impact analysis of the model are triggered, and the traceability relationship between each design parameter and the top-level service indicator in the model is automatically updated.
6. The integrated simulation verification method for deep space exploration constellation systems according to claim 1, characterized in that, In step 6, when the simulation results do not meet the verification conditions, the design parameters are automatically adjusted and the simulation is re-driven, forming an unattended iterative closed loop of "design parameter export - simulation execution - result write-back - model update".
7. The integrated simulation verification method for deep space exploration constellation systems according to claim 1, characterized in that, The simulation verification report generated in step 6 includes design compliance conclusions, key indicator margin analysis, multi-scheme trade-off results, and marks the parameter items that do not meet the indicator requirements and their deviations.
8. The integrated simulation verification method for deep space exploration constellation systems according to claim 1, characterized in that, The CSV file includes file naming conventions, header definitions, and data area structures, and supports multi-round iteration identification and time-varying data organization.
9. An electronic device, characterized in that, include: One or more processors; Memory, used to store one or more programs; When one or more programs are executed by the one or more processors, the one or more processors implement the integrated simulation verification method for deep space exploration constellation systems as described in any one of claims 1-8.
10. A computer-readable storage medium, characterized in that, It stores executable instructions that, when executed by a processor, enable the processor to implement the integrated simulation and verification method for deep space exploration constellation systems as described in any one of claims 1-8.