Model-based deep space exploration communication constellation system design method
By constructing a unified digital model, high-quality digital development of the deep space exploration communication constellation system was achieved, solving the problems of poor data consistency, weak traceability, and low collaborative efficiency in traditional design methods, and enabling rapid iterative optimization and accurate input of design schemes.
Patent Information
- Application Number
- CN202610493607.0
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2026-04-15
- Publication Date
- 2026-07-14
AI Technical Summary
Traditional spacecraft design methods suffer from poor data consistency, weak traceability, low collaborative efficiency, and difficulty in change analysis in deep space exploration constellation systems, making it difficult to support rapid iterative optimization of high-density, giant, complex, and multi-body collaborative systems.
A model-based design approach is adopted, which uses a unified digital model as a single data source to achieve logical progression and closed-loop iteration of requirements analysis, top-level architecture, detailed design and simulation verification, and generate satellite development task book.
It achieves data consistency and traceability across the entire chain, improves design quality, supports cross-unit collaborative design, reduces development risks, and ensures rapid convergence and optimization of design schemes.
Smart Images
Figure CN122389577A_ABST
Abstract
Description
Technical Field
[0001] This invention belongs to the field of spacecraft digital technology, specifically relating to a model-based design method for deep space exploration communication constellation systems. Background Technology
[0002] The deep space exploration communication constellation system is a dynamic network consisting of a large number of satellites, orbital relay stations and extraterrestrial nodes. It provides relay communication services through inter-satellite laser links. The system can adapt to the deep space environment, support multiple concurrent missions, and provide real-time and reliable communication and navigation services for deep space exploration and even further interstellar travel. The constellation system is moving from a single spacecraft to a giant and complex system with multiple bodies working together.
[0003] Traditional spacecraft design relies heavily on documents to convey engineering information, with numerous requirements, design parameters, and verification results scattered across various documents. This design paradigm reveals the following shortcomings when dealing with high-density, massive, complex, and multi-body collaborative deep space exploration constellation systems:
[0004] First, data consistency is poor and difficult to maintain. Information such as system requirements, architecture design, interface definitions, and performance parameters generated during the design process are scattered across different documents. When design changes occur, it is difficult to ensure that all documents are updated synchronously, easily leading to inconsistencies and affecting the accuracy of engineering decisions.
[0005] Secondly, traceability is weak. The traceability relationship between top-level mission requirements and bottom-level satellite design specifications relies solely on textual descriptions in documents, lacking an effective correlation mechanism. When requirements change, it is difficult to quickly analyze the scope and extent of their impact, leading to difficulties in change management.
[0006] Secondly, collaboration efficiency is low. The constellation system involves multiple stakeholders, including launch vehicles, launch sites, and tracking and control stations. Information is exchanged between these units via documents, which can easily lead to misunderstandings and high communication costs. Furthermore, the specialized design and verification work in different disciplines is fragmented, making cross-departmental and cross-professional collaborative optimization difficult.
[0007] Finally, impact analysis of changes is difficult. Due to the scattered and unrelated nature of the information, correlation analysis of design issues requires consulting a large number of documents, which is extremely labor-intensive and difficult, making it difficult to support rapid iterative optimization and affecting the overall project design progress and quality.
[0008] With the rapid increase in complexity of deep space exploration constellation systems, the omissions and mismatches inherent in traditional systems engineering methods will become more pronounced. There is an urgent need for a new design methodology to address the challenges faced throughout the entire lifecycle of research and development, design, integration, and verification. This methodology should shift from a document-centric to a model-centric approach, ensuring data consistency, continuity, and traceability to support the high-quality development of constellation systems. Summary of the Invention
[0009] To address the aforementioned technical issues, this invention provides a model-based design method for deep space exploration communication constellation systems. Using a unified digital model as a single data source, the method logically advances and iterates through a forward design chain of "problem domain - solution domain," integrating requirements analysis, top-level architecture, detailed design, and simulation verification, ultimately automatically generating a satellite development task book.
[0010] To achieve the above objectives, the present invention adopts the following technical solution:
[0011] A model-based design method for deep space exploration communication constellation systems includes:
[0012] Build a unified digital model as a single data source throughout the entire lifecycle;
[0013] During the requirements analysis phase, based on the unified digital model, stakeholders and their interaction interfaces are captured through business scenario analysis, and the top-level service indicators of the system are decomposed to construct a problem domain model.
[0014] In the top-level modeling stage of the system, the system capabilities and system architecture are analyzed in a white-box manner using the problem domain model as input, generating a preliminary design scheme containing the first key parameter, and associating the first key parameter with the top-level service indicator. The first key parameter is used to describe the constellation configuration and coverage capability.
[0015] In the system detailed design and modeling stage, the preliminary design scheme is used as input to refine the system behavior that realizes the system capability and the physical implementation of the system architecture, and generate a detailed design scheme containing a second key parameter. The second key parameter is obtained by refining and decomposing the first key parameter and is used to describe the satellite energy balance state.
[0016] By integrating professional simulation tools, the second key parameter in the detailed design scheme is calculably verified and simulated, and the first key parameter in the preliminary design scheme is automatically updated based on the simulation results, thereby realizing closed-loop design iteration.
[0017] Based on the detailed design scheme after iterative convergence, the satellite development task book is automatically extracted and generated from the unified digital model.
[0018] Furthermore, the construction of a unified digital model as a single data source throughout the entire lifecycle includes: introducing a predefined general model library and meta-model for deep space exploration communication constellation systems, and standardizing the identification of model elements according to unified modeling and naming specifications.
[0019] Furthermore, the process of capturing stakeholders and their interaction interfaces through business scenario analysis includes: performing use case function analysis on three core business scenarios: operation and maintenance, communication services, and constellation deployment; identifying stakeholders by dividing functional activities; and inferring the interfaces and interaction items between stakeholders and the constellation system based on the temporal sequence of activities and data transmission.
[0020] Furthermore, associating the first key parameter with the top-level service indicator includes: constructing a top-level service indicator decomposition view in the unified digital model, decomposing the top-level service indicator into the next-level problem domain indicator, and establishing a traceability relationship from the first key parameter to the top-level service indicator. The first key parameter includes at least one of orbital altitude, orbital inclination, and constellation phase factor.
[0021] Furthermore, the detailed design includes: in the unified digital model, using a time-series view to design the power supply switching and communication process in the communication service, and using a functional decomposition view to design the positioning and timing and positioning service process in the navigation service.
[0022] Furthermore, the second key parameter includes at least one of the following: load power consumption index, bus voltage, and depth of discharge, which are obtained by index decomposition of the first key parameter.
[0023] Furthermore, the integrated professional simulation tool performs calculable verification of the second key parameter in the detailed design scheme, and automatically updates the first key parameter in the preliminary design scheme based on the simulation results, including:
[0024] External configuration simulation, coverage analysis, and energy balance simulation tools can be invoked through parameter diagrams or UI interfaces. The simulation results are read in XML file format and fed back to the unified digital model to automatically update the first key parameter values and drive iterative optimization of the design scheme.
[0025] Furthermore, the automatic extraction and generation of the satellite development task book from the unified digital model includes: based on the decomposition and tracing relationship from top-level service indicators to satellite indicators, extracting functional requirements from the requirements analysis view and quantitative indicators from the general table view from the unified digital model, and aggregating them to form a satellite development task book containing technical indicator requirements and performance parameters.
[0026] In a second aspect, 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 model-based deep space exploration communication constellation system design method.
[0027] 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 model-based deep space exploration communication constellation system design method.
[0028] The beneficial effects of this invention are as follows:
[0029] First, it achieves data consistency and traceability across the entire chain. By constructing a unified digital model as a single data source, it integrates requirements, design, simulation, and verification information onto a single platform, completely resolving the problems of scattered information and poor data consistency in traditional document-based design. End-to-end traceability, from top-level service indicators to detailed satellite indicators, enables rapid and automated analysis of the impact of requirement changes, significantly improving design quality.
[0030] Second, it enables the modeling, encapsulation, and reuse of design knowledge. By introducing a general model library, meta-models, and standardized naming, the design experience of domain experts is transformed into reusable digital assets, avoiding redundant modeling, supporting collaborative design and knowledge transfer across models and units, and improving development efficiency.
[0031] Third, it enables closed-loop iterative optimization of the design scheme. By deeply integrating the system model with professional simulation tools, it enables calculable verification of key parameters such as configuration, coverage, link budget, and energy balance, and automatically updates model parameters based on simulation results, driving the design scheme to converge quickly, ensuring "correct on the first try," and reducing development risks.
[0032] Fourth, it enables the automatic generation of satellite development task specifications. Based on the decomposition and traceability relationship of requirements and indicators, functional requirements and quantitative indicators are automatically extracted from a unified digital model and aggregated to form a satellite development task specification. This eliminates errors and ambiguities introduced by manual writing, provides accurate input for downstream development, and comprehensively enhances the digital and intelligent development capabilities of the deep space exploration constellation system. Attached Figure Description
[0033] Figure 1 This is a schematic diagram of the model-based deep space exploration communication constellation system design method of the present invention;
[0034] Figure 2 This is a schematic diagram illustrating the principles of operation and maintenance scenarios. Detailed Implementation
[0035] The present invention will be further described below with reference to the accompanying drawings and embodiments.
[0036] like Figure 1As shown, this invention provides a model-based design method for deep space exploration communication constellation systems. The core of this method lies in using a unified digital model as a single data source and employing a forward design chain of "problem domain - solution domain" to logically advance and iterate through requirements analysis, top-level architecture, detailed design, and simulation verification, ultimately automatically generating a satellite development mission statement. The specific implementation includes the following steps:
[0037] Step 1: Build a unified digital model as a single data source throughout the entire lifecycle;
[0038] Step 2: In the requirements analysis phase, based on the unified digital model, capture stakeholders and their interaction interfaces through business scenario analysis, decompose the system's top-level service indicators, and construct a problem domain model.
[0039] Step 3: In the top-level modeling stage of the system, the system capabilities and system architecture are analyzed in a white-box manner using the problem domain model as input, a preliminary design scheme containing the first key parameter is generated, and the first key parameter is associated with the top-level service indicator.
[0040] Step 4: In the system detailed design and modeling stage, taking the preliminary design scheme as input, refine the design of the system behavior that realizes the system capability and the physical implementation of the system architecture, and generate a detailed design scheme containing the second key parameter. The second key parameter is obtained by refining and decomposing the first key parameter.
[0041] Step 5: Integrate professional simulation tools to perform calculable verification of the second key parameter in the detailed design scheme, and automatically update the first key parameter in the preliminary design scheme based on the simulation results to achieve closed-loop design iteration;
[0042] Step 6: Based on the detailed design scheme after iterative convergence, automatically extract and generate the satellite development task book from the unified digital model.
[0043] In step 1, to achieve data consistency throughout the entire lifecycle, this invention first constructs a unified digital model as a single data source throughout the entire lifecycle. This model is not simply a digitization of documents, but rather uses the SysML modeling language to express various engineering information such as system requirements, structure, behavior, and parameters in the form of standardized model elements, and establishes the relationships between them to form a highly integrated digital system definition.
[0044] To achieve collaborative modeling across multiple units, this invention introduces a predefined general model library and meta-model for deep space exploration communication constellation systems. The general model library encapsulates mature design modules accumulated from past projects, such as typical spaceborne payload models, communication link models, and orbital configuration models. The meta-model defines constellation-specific model element types, such as "stakeholders," "constellation," and "links," as well as their semantic relationships. At the operational level, by adding model library files using the "project usage" function, these predefined models can be directly referenced in new projects, avoiding redundant modeling. When it is necessary to convert existing general SysML model elements into meta-model elements conforming to the system's specifications, the "Refactor-Convert To" function can be used to complete the conversion with a single click, ensuring the semantic accuracy of the model elements.
[0045] Meanwhile, this invention standardizes the identification of model elements based on unified modeling and naming conventions. The modeling conventions clarify the model's organizational structure, organizing it hierarchically into problem domain black-box, problem domain white-box, and solution domains, facilitating quick location and understanding of model content by designers from different disciplines. The naming conventions specify the ID naming rules for various model elements; for example, business requirements are prefixed with "R2-DSEL-BR", functional use cases with "R2-DSEL-UC", and performance requirements with "R3-DSEL-PR", etc. In practice, right-clicking a model element and selecting the "Element Numbering" function enters the ID editing interface, allowing for standardized naming of elements such as requirements and use cases according to the conventions. Through these methods, the data source, consistency, and reusability of the model are ensured during collaborative modeling among participating units.
[0046] In step 2, during the requirements analysis phase, this invention conducts use case function analysis on three core business scenarios: operation and maintenance, communication services, and constellation deployment. It identifies stakeholders and their interaction interfaces, forms a system task boundary and functional requirements system, and constructs a problem domain model describing "what the system does".
[0047] Taking operation and maintenance scenarios as an example, such as Figure 2As shown (other scenarios are similar and not shown separately to avoid redundancy), this scenario includes sub-use cases such as constellation operation and maintenance, constellation management, constellation health management, and interference avoidance. By functionally decomposing these sub-use cases, we can further clarify which external entities the system needs to interact with. For example, in the constellation operation and maintenance function, the deep space exploration constellation needs to process remote control information from the telemetry and control system and send telemetry information back to it; it also needs to process daily remote control information from the telemetry and control system and send daily maintenance telemetry information back to it. Therefore, we can infer that the telemetry and control system is the core stakeholder in the constellation operation and maintenance scenario. They have telemetry and control interfaces and power supply interfaces with the constellation, and the interaction items are remote control commands and telemetry data, respectively.
[0048] Taking a communication service scenario as an example, this scenario includes sub-use cases such as telemetry and control communication, relay communication, network communication, and laser communication. Taking laser communication as an example, functional activity analysis reveals that: both communicating parties receive and process their respective platform status and ephemeris information, thereby calculating and initially adjusting the line-of-sight pointing of the communication payload to complete coarse alignment. Subsequently, by actively transmitting signal light, the receiver scans and initially acquires the signal within its acquisition field of view, achieving signal synchronization and fine alignment. Afterward, both parties complete a handshake confirmation by exchanging, receiving, and responding to "response light".
[0049] Taking constellation deployment as an example, this scenario includes sub-use cases such as orbital deployment, network establishment and link building, network replenishment deployment, and satellite deorbiting. Taking orbital deployment as an example, after the launch vehicle system completes rocket launch and satellite separation, the telemetry and control system receives the orbital insertion command and transmits antenna deployment commands and Earth-to-ground commands to the satellite. After the satellite completes its orbital status settings, it transmits telemetry data back to the telemetry and control system. Therefore, it can be inferred that the launch vehicle system, launch site system, and telemetry and control system are all core stakeholders in the constellation deployment scenario.
[0050] Through the above systematic analysis of the three major business scenarios, this invention has fully captured all stakeholders of the deep space exploration constellation system, including the launch vehicle system, launch site system, telemetry and control system, etc., and clarified the interface relationships and interaction items between each stakeholder and the constellation system.
[0051] In step 3, after identifying stakeholders and their interaction interfaces, the present invention further captures and decomposes the system's top-level service metrics (MOE). MOE is a quantitative indicator used from the perspective of stakeholders to measure the effectiveness of system task completion, such as coverage, positioning accuracy, and system availability.
[0052] This invention constructs a MOE (Mean Exchange Effectiveness) index decomposition view within a unified digital model, progressively decomposing top-level service indicators into next-level problem domain indicators and establishing a traceability relationship from preliminary design parameters to top-level service indicators. Taking coverage area as an example, it is influenced by multiple underlying design parameters such as orbital altitude, orbital inclination, and constellation phase factor. The index decomposition view clearly demonstrates the constraints between the MOE index "coverage area" and design parameters such as "orbital altitude," "orbital inclination," and "constellation phase factor." Furthermore, "orbital altitude" and "orbital inclination" are also affected by factors such as frequency and orbital data constraints and launch site capability constraints; these constraints are also recorded in the model.
[0053] In the subsequent preliminary configuration design, designers can perform parametric design in the model based on the aforementioned constraints. When the orbital altitude parameter is adjusted, the model can automatically calculate its impact on coverage indicators and indicate whether the top-level mission requirements are met. This direct traceability from design parameters to top-level indicators provides a quantitative basis for the evaluation and selection of design schemes, avoiding the problem of design results being disconnected from mission requirements in traditional design models.
[0054] After completing the problem domain modeling, this invention enters the system top-level modeling stage. Using the problem domain model as input, the system capabilities and architecture are analyzed in a white-box manner to generate a preliminary design scheme containing the first key parameters, thus forming a top-level scheme describing "how the system is implemented".
[0055] In terms of system capability design, this invention provides a preliminary design for four core capabilities: autonomous operation capability, constellation deployment capability, operation and maintenance capability, and communication service capability. Taking autonomous operation capability as an example, an activity diagram is used to model the autonomous and safe operation mechanism, including the execution logic of behaviors such as orbit control, attitude control, fault diagnosis, fault recovery, and collision avoidance, clarifying the autonomous operation process of the satellite in the absence of ground telemetry and control support. Taking constellation deployment capability as an example, a functional decomposition view is used to design sub-capabilities such as satellite deorbiting from the orbital plane, clarifying the behavioral sequence and execution mechanism of each deployment stage.
[0056] In terms of system architecture design, this invention provides a preliminary design for constellation composition, inter-satellite interfaces, space-to-ground links, and interference avoidance strategies. Regarding constellation composition, the deep space exploration constellation is defined as a hybrid constellation network topology consisting of geostationary orbit satellites and frozen orbit satellites to achieve high coverage and leverage its powerful communication and information service capabilities. For inter-satellite interfaces, an internal interface view clarifies the inter-satellite interfaces between geostationary orbit satellites and frozen orbit satellites, as well as the inter-satellite data transmitted through these interfaces, including data from different orbits and data from the same orbit. Regarding space-to-ground links, an internal interface view clarifies the interface relationships between satellites and the probe and the telemetry, tracking, and command (TT&C) system, and classifies them according to physical link type, such as TT&C links and power supply links. Regarding interference avoidance strategies, three main categories of strategies are designed: multi-domain fusion interference avoidance strategies, space domain isolation interference avoidance strategies, and power domain interference avoidance strategies. The applicable interference scenarios and adjustment parameters for each strategy are also clearly defined.
[0057] Through the above design, a preliminary design scheme is generated that includes key parameters such as orbital altitude, orbital inclination, constellation phase factor, satellite mass, and payload power consumption. These key parameters are then linked to top-level service indicators through a traceability relationship.
[0058] In step 4, regarding the detailed design of system behavior, this invention provides detailed modeling of the core processes of communication and navigation services. For communication services, sub-processes such as power supply switching and intra-satellite beam switching for laser link establishment are designed. Taking power supply switching as an example, a timing view is used to describe in detail the signaling interaction process when the link switches during satellite movement, including the complete process of measurement report reporting, switching decision, resource allocation, and path update, and the branch processing logic under different network conditions is implemented using the alt operator. For navigation services, functions such as navigation information, positioning services, and positioning and timing are designed. Taking positioning and timing as an example, a functional decomposition view is used to describe in detail the complete service process of satellite acquiring monitoring data, transmitting it to the telemetry and control system, uploading orbit determination information to the satellite, generating positioning and timing signals, and completing reception and calculation.
[0059] Regarding the detailed design of the system architecture, this invention provides a refined definition of the satellite's physical architecture, internal interfaces, and external interfaces. In terms of the satellite physical architecture, it clarifies that the satellite consists of two main parts: the payload and the satellite platform. The payload is further subdivided into integrated processing payloads, inter-satellite laser payloads, power supply payloads, navigation payloads, etc., while the satellite platform is further subdivided into integrated electronics, telemetry, tracking and command (TT&C), and structural subsystems. Regarding internal interfaces, the connection relationships and flow directions between various payloads are clearly defined through an internal interface view, such as the control interface between the integrated processing payload and the inter-satellite laser payload. Regarding external interfaces, the interface types and interaction content between the satellite and external systems are clearly defined through an internal interface view, such as communication interfaces, navigation service interfaces, and TT&C system interfaces.
[0060] Through the above detailed design, the macroscopic first key parameters such as orbital altitude and constellation phase are further refined into specific second key parameters such as payload power consumption indicators, operating mode definition, interface protocol specifications, data transmission rate, and storage capacity requirements.
[0061] In step 5, to ensure the long-term reliable operation of the constellation system in orbit, this invention performs Failure Mode and Effects Analysis (FMEA) on the system. First, a meta-model library of failure modes, failure causes, and failure effects is established, and common failure types and their characteristics are encapsulated in the form of standardized model elements for easy reuse in different project models.
[0062] In the specific analysis process, FMEA analysis tables are used to identify and evaluate fault items at the constellation and satellite levels. Each fault item is represented by an FMEA project element, including attributes such as fault function, fault mode, fault cause, impact of superior fault, final fault impact, severity, and probability of occurrence. Among them, the fault function is associated with the corresponding functional module in the previous functional design; the attributes such as fault mode, fault cause, and fault impact are selected and called from a pre-established meta-model library to ensure the consistency of terminology; severity and probability of occurrence are enumerated parameters for designers to rate based on engineering experience.
[0063] After completing the severity level and probability rating, the system automatically calculates the risk index based on the preset risk index evaluation principle. This principle divides the severity into four levels: I, II, III, and IV, and the probability of occurrence into five levels: A, B, C, D, and E. The risk index values from 1 to 20 are obtained through a two-dimensional matrix combination, which are used to quantitatively assess the risk level of each failure item and provide key inputs for subsequent reliability design.
[0064] Based on FMEA analysis results, this invention derives satellite reliability requirements within a unified digital model. Specific quantitative reliability indicators, such as mean time between failures (MTBF), mission success rate, and on-orbit lifespan, are added to the satellite platform, functional modules, and communication links of both geostationary orbit and frozen orbit satellites, providing reliability constraints for subsequent detailed satellite design.
[0065] To ensure the feasibility and optimality of the design scheme, this invention integrates professional simulation tools to perform calculable verification of the second key parameter in the detailed design scheme, and automatically updates the corresponding first key parameter in the preliminary design scheme based on the simulation results, thereby realizing closed-loop iteration of the design.
[0066] In constellation configuration simulation, this invention calls the .M file of an external configuration simulation tool (such as STK) through a parametric design view, passing the first key parameters defined in the model, such as orbital altitude, orbital inclination, and number of satellites, as input to the simulation tool. After completing coverage and visibility analysis, the simulation tool outputs optimized orbital parameters and saves them in XML file format. This invention automatically updates the model with parameters such as orbital altitude, orbital inclination, number of satellites per orbit, and constellation phase factor from the simulation results by reading the XML file, achieving iterative optimization of the initial design scheme.
[0067] In terms of energy balance simulation, this invention first clarifies the on / off status and load power of each payload at different times based on the satellite's working area division and working mode definition. For example, an energy balance calculation model is constructed using parameter diagrams, describing the power consumption parameters of various power-consuming units such as the integrated processing payload, inter-satellite laser payload, and navigation payload, as well as the power consumption parameters of various subsystems such as the telemetry and control subsystem, attitude and orbit control subsystem, integrated electronic subsystem, and power supply subsystem, as input value attributes. The power consumption calculation logic is embedded in the constraint module in the form of an .M file, connecting the input parameters to the constraint module, and calling simulation tools to obtain the changes in bus voltage and discharge depth.
[0068] When simulation results show that the battery discharge depth exceeds the safety threshold or the bus voltage fluctuation exceeds the allowable range, designers can adjust the operating mode definition, optimize the load switching sequence, or adjust design parameters such as solar panel area and battery capacity. The adjusted parameters are automatically updated in the model, triggering a new round of simulation verification until the energy balance requirements are met. This closed-loop iterative mechanism from detailed design to top-level design ensures rapid convergence and optimization of the design scheme.
[0069] In step 6, based on the decomposition and tracing relationship from top-level service indicators to satellite indicators, the present invention automatically extracts and generates satellite development task books from the unified digital model, providing accurate input basis for downstream satellite development units.
[0070] Regarding satellite development requirements, all satellite-related functional, performance, and interface requirements were extracted using a requirements analysis view. These requirements had already been decomposed and traced back to each other during the previous design process. For example, the orbital altitude requirements were derived from the top-level coverage indicators, the payload power consumption requirements were derived from the communication service design, and the reliability requirements were derived from FMEA analysis. These requirements were then categorized and organized using requirement groups and satellite requirement elements. The requirement IDs were uniformly prefixed with "R3-DSEL-PR" to identify the satellite's performance requirements within the three functional domains, forming a structured list of satellite development requirements.
[0071] Regarding satellite development indicators, quantitative indicators required for satellite development are extracted using general tabular charts. These indicators are categorized according to professional fields, such as power supply link indicators, navigation indicators, and energy balance indicators. Each indicator includes specific numerical requirements, test conditions, tolerance ranges, and other information, presented clearly in tabular form.
[0072] Ultimately, the aforementioned satellite development requirements and quantitative indicators were aggregated to form a complete satellite development mission statement. This mission statement was automatically generated directly from the model, eliminating errors and ambiguities that might be introduced by manual writing, ensuring consistency throughout the entire chain from top-level mission requirements to detailed satellite specifications, and providing a unique and accurate basis for subsequent detailed satellite design, manufacturing, testing, and verification.
[0073] In summary, this invention, through the aforementioned steps and with a unified digital model at its core, establishes a complete positive design closed loop, encompassing requirements analysis, top-level design, detailed design, failure analysis, simulation verification, and mission specification generation. This method fundamentally changes the traditional document-centric design model, enabling high-quality digital development of deep space exploration communication constellation systems and effectively solving long-standing technical challenges in aerospace engineering, such as poor data consistency, weak traceability, low collaborative efficiency, and difficulties in change analysis.
[0074] In a second aspect, 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 model-based deep space exploration communication constellation system design method.
[0075] 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 model-based deep space exploration communication constellation system design method.
[0076] 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. A model-based design method for deep space exploration communication constellation systems, characterized in that, include: Build a unified digital model as a single data source throughout the entire lifecycle; During the requirements analysis phase, based on the unified digital model, stakeholders and their interaction interfaces are captured through business scenario analysis, and the top-level service indicators of the system are decomposed to construct a problem domain model. In the top-level modeling stage of the system, the system capabilities and system architecture are analyzed in a white-box manner using the problem domain model as input, generating a preliminary design scheme containing the first key parameter, and associating the first key parameter with the top-level service indicator. The first key parameter is used to describe the constellation configuration and coverage capability. In the system detailed design and modeling stage, the preliminary design scheme is used as input to refine the system behavior that realizes the system capability and the physical implementation of the system architecture, and generate a detailed design scheme containing a second key parameter. The second key parameter is obtained by refining and decomposing the first key parameter and is used to describe the satellite energy balance state. By integrating professional simulation tools, the second key parameter in the detailed design scheme is calculably verified and simulated, and the first key parameter in the preliminary design scheme is automatically updated based on the simulation results, thereby realizing closed-loop design iteration. Based on the detailed design scheme after iterative convergence, the satellite development task book is automatically extracted and generated from the unified digital model.
2. The model-based deep space exploration communication constellation system design method according to claim 1, characterized in that, The construction of a unified digital model as a single data source throughout the entire lifecycle includes: introducing a predefined general model library and meta-model for deep space exploration and communication constellation systems, and standardizing the identification of model elements according to unified modeling and naming specifications.
3. The model-based deep space exploration communication constellation system design method according to claim 1, characterized in that, The process of capturing stakeholders and their interaction interfaces through business scenario analysis includes: performing use case function analysis on three core business scenarios: operation and maintenance, communication services, and constellation deployment; identifying stakeholders by dividing functional activities; and inferring the interfaces and interaction items between stakeholders and the constellation system based on the temporal sequence of activities and data transmission.
4. The model-based deep space exploration communication constellation system design method according to claim 1, characterized in that, The step of associating the first key parameter with the top-level service indicator includes: constructing a top-level service indicator decomposition view in the unified digital model, decomposing the top-level service indicator into the next level of problem domain indicators, and establishing a traceability relationship from the first key parameter to the top-level service indicator. The first key parameter includes at least one of orbital altitude, orbital inclination, and constellation phase factor.
5. The model-based deep space exploration communication constellation system design method according to claim 1, characterized in that, The detailed design includes: in the unified digital model, using a time-series view to design the power supply switching and communication process in the communication service, and using a functional decomposition view to design the positioning and timing and positioning service process in the navigation.
6. The model-based deep space exploration communication constellation system design method according to claim 5, characterized in that, The second key parameter includes at least one of the following: load power consumption index, bus voltage, and depth of discharge, which are obtained by decomposing the first key parameter into an index.
7. The model-based deep space exploration communication constellation system design method according to claim 1, characterized in that, The integrated professional simulation tool verifies the second key parameter in the detailed design scheme through calculation and automatically updates the first key parameter in the preliminary design scheme based on the simulation results, including: External configuration simulation, coverage analysis, and energy balance simulation tools can be invoked through parameter diagrams or UI interfaces. The simulation results are read in XML format and fed back to the unified digital model to automatically update the first key parameter values and drive the iterative optimization of the design scheme.
8. The model-based deep space exploration communication constellation system design method according to claim 1, characterized in that, The automatic extraction and generation of the satellite development task book from the unified digital model includes: Based on the decomposition and tracing relationship from top-level service indicators to satellite indicators, functional requirements in the demand analysis view and quantitative indicators in the general table view are extracted from the unified digital model and aggregated to form a satellite development task book containing technical indicator requirements and performance parameters.
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 model-based deep space exploration communication constellation system design method according to 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 model-based deep space exploration communication constellation system design method as described in any one of claims 1-8.