Spacecraft overall domain model construction method of digital meta-model

Abstract

The invention discloses a method for constructing a spacecraft overall domain model of a digital meta-model, and relates to the technical field of spacecraft design and MBSE. The method comprises the following steps: extracting spacecraft design domain knowledge; constructing a meta-model in the field of spacecraft design; generating a spacecraft overall domain model by using the meta-model; the domain model is applied to the spacecraft design process, the incidence relation between design information is analyzed, the system design process is deduced in the forward direction, the spacecraft design process is optimized, and automation and intelligentization of design are achieved. The spacecraft design domain knowledge is extracted, the spacecraft design domain meta-model is constructed, the spacecraft overall domain model is generated through the meta-model, the domain model can be applied to the spacecraft design process, the method has the advantages of being uniform in data source, short in iteration period, high in expansibility and the like, the system-level development cost can be further reduced, and the development efficiency is improved. Automation and intelligentization of the design are realized, and the design efficiency and quality of the spacecraft are improved.

Description

Technical Field

[0001] The present invention belongs to the field of spacecraft design and MBSE technology, and in particular relates to a method for constructing a spacecraft overall domain model of a digital meta-model. Background Art

[0002] With the rapid development of aerospace technology, the design and manufacture of spacecraft have become increasingly complex. The spacecraft system is a multidisciplinary cross-coupled system; with the development of technology, the complexity and variability of the system are increasing. During its system development process, the system is often designed by different departments.

[0003] For example, Chinese patent CN113655998A provides a method for transforming a target model into a UML requirement model, including the following steps: (1) completing the annotation of the target model so that the target model can be transformed; (2) designing transformation rules and transformation algorithms to map the target model to UML; (3) verifying the correctness of the transformation method. A method for transforming a target model into a UML model, Goa l 2UML, is proposed. This method can achieve a smooth transition from user requirements to system requirements based on user requirements extraction. This will greatly reduce the workload of building a system requirement model. Further, users can improve the system requirement model and combine it with the RM2PT requirement prototyping tool to achieve requirement confirmation and iterative evolution. For example, Chinese patent CN116149617A provides a spacecraft modeling method encapsulation based on the SysML language, step one: constructing a model framework, this step constructs a model organization structure in the architecture design software CATIAMagi c, and the model organization structure includes the contents contained in the models in the system and subsystem; step two: template encapsulation; step three: creating a new model; a SysML model organization structure is proposed for spacecraft, which can guide designers in modeling and unify modeling ideas.

[0004] Since different fields, departments and designers have their own unique domain knowledge, and the unified modeling language UML and the system modeling language SysML cannot directly build the corresponding domain knowledge base, the overall design of spacecraft is not only inefficient, but also difficult to ensure the accuracy and reliability of the design. In order to improve the efficiency and quality of design, an automated and intelligent design method is needed. Summary of the invention

[0005] The purpose of the present invention is to provide a method for constructing a spacecraft overall domain model based on a digital meta-model, which belongs to the field of MBSE (Model-Based Systems Engineering) technology. By extracting spacecraft design domain knowledge, constructing a spacecraft design domain meta-model, and using the meta-model to generate a spacecraft overall domain model, the efficiency and quality of spacecraft design are improved, thereby solving the existing problems.

[0006] In order to solve the above technical problems, the present invention is achieved through the following technical solutions:

[0007] The present invention is a method for constructing a spacecraft overall domain model based on a digital metamodel. The metamodel, as an effective knowledge representation and reasoning tool, can be used to construct a spacecraft overall domain model, realize the automated application and reasoning of design knowledge, and improve the efficiency of spacecraft design. The method specifically includes the following steps:

[0008] Step SS01: Extracting spacecraft design elements: Extracting elements from the spacecraft system through element extraction method, abstracting them into corresponding conceptual models, and analyzing the spacecraft system design process based on demand;

[0009] Step SS02: Use the class diagram of the unified modeling language to create a spacecraft domain metamodel, standardize the model elements and the relationship between model elements, and extend the SysML language;

[0010] Step SS03: Generate the overall domain model of the spacecraft using the domain metamodel;

[0011] Step SS04: Apply the overall domain model to the spacecraft design process, analyze the correlation between design information, and forward-deduce the system design process to achieve automation and intelligence of the design.

[0012] Furthermore, the design elements include the structure, performance, function, payload and scientific objectives of the spacecraft.

[0013] Furthermore, the domain metamodel includes design rules, design constraints and design patterns.

[0014] Furthermore, the overall domain model includes a spacecraft requirement model, a functional model, a performance model and an architecture model.

[0015] Furthermore, the requirement model describes the stakeholders and stakeholder needs at different stages of the entire life cycle of spacecraft design; the functional model describes the functional scenarios of the spacecraft to realize the carrying of stakeholder needs; the performance model describes the performance characteristics of the spacecraft, including propulsion capability, communication capability, navigation capability, etc.; the architecture model describes the physical structure of the spacecraft, including the location and connection relationship of each subsystem.

[0016] Furthermore, in step SS02, the method for constructing the spacecraft design domain metamodel is:

[0017] Step S021: extracting concepts such as ontology, relationship and constraint from the spacecraft domain knowledge;

[0018] Step S022: performing abstract syntax description according to the four-layer representation mechanism of MOF;

[0019] Step S023: Use UML class diagram to define abstract syntax of ontology, relationship and constraint;

[0020] Step S024: Based on the abstract syntax, obtain each model element in the abstract syntax;

[0021] Step S025: Identify the general metamodel in SysML that is most similar to other semantics, and define corresponding representation methods and symbols for each model element as the specific syntax corresponding to the model element;

[0022] Step S026: Based on the general metamodel, SysML is extended by creating a stereotype to construct a domain metamodel of the spacecraft system.

[0023] Furthermore, in step SS02, when necessary, labels and constraints are used to describe the newly created domain metamodel in more detail.

[0024] Furthermore, in step SS02, based on the SysML specification, a common metamodel with the most appropriate semantics is selected as a template, and the stereotype element representing the domain metamodel is bound to the basic template element through a corresponding relationship.

[0025] Furthermore, the domain metamodel includes an element metamodel and a relationship metamodel. The element metamodel includes: mechanism, goal, condition, location, requirement, executor, indicator, resource, activity, etc.; the relationship metamodel is extended based on the three major relationships of association, dependency and generalization specified in the SysML specification.

[0026] Furthermore, the spacecraft design process includes requirement analysis, functional decomposition, architecture design and analysis verification.

[0027] The present invention has the following beneficial effects:

[0028] The present invention constructs a meta-model of the spacecraft design domain by extracting knowledge in the field of spacecraft design, and uses the meta-model to generate an overall spacecraft domain model; the domain model can be applied to the spacecraft design process, and has the characteristics of unified data source, short iteration cycle, and strong scalability. It can further shorten the development cost of the system level, realize the automation and intelligence of the design, and improve the efficiency and quality of spacecraft design.

[0029] Of course, any product implementing the present invention does not necessarily need to achieve all of the advantages described above at the same time. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the accompanying drawings required for describing the embodiments will be briefly introduced below. Obviously, the accompanying drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other accompanying drawings can be obtained based on these accompanying drawings without paying creative work.

[0031] Figure 1 A flow chart of a method for constructing a spacecraft overall domain model of a digital meta-model of the present invention;

[0032] Figure 2 The spacecraft domain knowledge extraction graph of the present invention;

[0033] Figure 3 Obtaining result maps for the spacecraft domain concept of the present invention;

[0034] Figure 4 The spacecraft domain metamodel diagram of the present invention;

[0035] Figure 5 The spacecraft requirement model diagram of the present invention;

[0036] Figure 6 A functional model diagram of the spacecraft of the present invention;

[0037] Figure 7 A diagram of the spacecraft architecture model of the present invention;

[0038] Figure 8 This is a requirement coverage matrix diagram of the present invention. DETAILED DESCRIPTION

[0039] In the following description, specific details such as specific system structures, technologies, etc. are provided for the purpose of illustration rather than limitation, so as to provide a thorough understanding of the embodiments of the present application. However, it should be clear to those skilled in the art that the present application may also be implemented in other embodiments without these specific details. In other cases, detailed descriptions of well-known systems, devices, circuits, and methods are omitted to prevent unnecessary details from obstructing the description of the present application.

[0040] It should be understood that when used in the present specification and the appended claims, the term "comprising" indicates the presence of described features, wholes, steps, operations, elements and / or components, but does not exclude the presence or addition of one or more other features, wholes, steps, operations, elements, components and / or combinations thereof.

[0041] It should also be understood that the term “and / or” used in the specification and appended claims refers to any and all possible combinations of one or more of the associated listed items, and includes these combinations.

[0042] As used in the specification and appended claims of this application, the term "if" can be interpreted as "when" or "uponce" or "in response to determining" or "in response to detecting", depending on the context. Similarly, the phrase "if it is determined" or "if [described condition or event] is detected" can be interpreted as meaning "uponce it is determined" or "in response to determining" or "uponce [described condition or event] is detected" or "in response to detecting [described condition or event]", depending on the context.

[0043] In addition, in the description of the present application specification and the appended claims, the terms "first", "second", "third", etc. are only used to distinguish the descriptions and cannot be understood as indicating or implying relative importance.

[0044] References to "one embodiment" or "some embodiments" etc. described in the specification of this application mean that one or more embodiments of the present application include specific features, structures or characteristics described in conjunction with the embodiment. Therefore, the statements "in one embodiment", "in some embodiments", "in some other embodiments", "in some other embodiments", etc. that appear in different places in this specification do not necessarily refer to the same embodiment, but mean "one or more but not all embodiments", unless otherwise specifically emphasized in other ways. The terms "including", "comprising", "having" and their variations all mean "including but not limited to", unless otherwise specifically emphasized in other ways.

[0045] Embodiment 1:

[0046] The present invention is a method for constructing a spacecraft overall domain model based on a digital metamodel to improve the efficiency and quality of spacecraft design. The metamodel, as an effective knowledge representation and reasoning tool, can be used to construct a spacecraft overall domain model, realize the automated application and reasoning of design knowledge, and improve the efficiency of spacecraft design. Figure 1 As shown, the specific steps include:

[0047] Step 1: Extracting spacecraft design domain knowledge, where the spacecraft design domain knowledge includes design elements such as spacecraft structure, performance, function, payload, scientific objectives, etc.;

[0048] Step 2: Construct a spacecraft design domain metamodel, wherein the domain metamodel includes design rules, design constraints, and design patterns;

[0049] Step 3: Generate a spacecraft overall domain model using the metamodel, wherein the overall domain model includes a spacecraft requirement model, a functional model, a performance model, and an architecture model;

[0050] Step 4: Apply the domain model to the spacecraft design process to realize the automation and intelligence of the design; the spacecraft design process includes requirements analysis, functional decomposition, architecture design and analysis verification.

[0051] As an embodiment provided by the present invention, preferably, in the step 2, the method for constructing the spacecraft design domain metamodel is:

[0052] Extract concepts such as ontology, relationships, and constraints from the domain knowledge related to spacecraft;

[0053] Abstract syntax description is performed according to the four-layer representation mechanism of MOF;

[0054] Use UML class diagrams to define abstract syntax for ontologies, relationships, and constraints;

[0055] Based on the abstract syntax, each model element in the abstract syntax is obtained;

[0056] Identify the common metamodel in SysML that is most similar to other semantics, and define corresponding representation methods and symbols for each model element as the specific syntax corresponding to the model element;

[0057] Based on the general metamodel, SysML is extended by creating stereotypes to construct the domain metamodel of the spacecraft system.

[0058] As an embodiment provided by the present invention, preferably, in the step 2, when necessary, labels and constraints are used to describe the newly created domain-related metamodel in more detail.

[0059] As an embodiment provided by the present invention, preferably, in the step 2, based on the SysML specification, a general metamodel with the most appropriate semantics is selected as a template, and the Stereotype element representing the domain metamodel is bound to the basic template element through a corresponding relationship.

[0060] As an embodiment provided by the present invention, preferably, the present invention extracts the domain knowledge of spacecraft design, constructs a metamodel of the domain of spacecraft design, and generates a spacecraft overall domain model using the metamodel. The present invention can apply the domain model to the spacecraft design process, has the characteristics of unified data source, short iteration cycle, strong expansibility, etc., can further shorten the system-level development cost, realize the automation and intelligence of design, and improve the efficiency and quality of spacecraft design.

[0061] Embodiment 2:

[0062] Based on the first embodiment, the present invention is a method for constructing a spacecraft overall domain model based on a digital metamodel. The metamodel, as an effective knowledge representation and reasoning tool, can be used to construct a spacecraft overall domain model, realize the automated application and reasoning of design knowledge, and improve the efficiency of spacecraft design. The method specifically includes the following steps:

[0063] Step SS01: Extract spacecraft design elements: Extract important elements from the spacecraft system through the element extraction method, and abstract them into corresponding conceptual models, and analyze the spacecraft system design process based on demand; extract concepts such as ontology, relationship and constraint from the domain knowledge related to the spacecraft, and describe them in abstract syntax according to the four-layer representation mechanism of MOF, and use UML class diagram to define the abstract syntax of the above domain knowledge. On the basis of the abstract syntax, for each element in the abstract syntax, first identify the general metamodel in SysML that is most similar to other semantics, and define the corresponding representation method and symbol as its specific syntax for each model element. On the basis of the general metamodel, SysML is extended by creating a stereotype to construct a domain metamodel of the spacecraft system. When necessary, use labels and constraints to describe the newly created domain-related metamodel in more detail;

[0064] Step SS02: Use the class diagram of the unified modeling language to create a spacecraft domain metamodel, standardize the model elements and the relationship between model elements, and extend the SysML language;

[0065] Step SS03: Generate the overall domain model of the spacecraft using the domain metamodel;

[0066] Step SS04: Apply the overall domain model to the spacecraft design process, analyze the correlation between design information, and forward-deduce the system design process to achieve automation and intelligence of the design.

[0067] As an embodiment provided by the present invention, preferably, the elements of the spacecraft system are extracted, and the granularity of the elements is determined according to the problems that the system needs to solve and is decomposed layer by layer. From the whole to the part, the elements that can fully reflect the characteristics of the system are extracted. The elements extracted from the spacecraft system must be different and non-overlapping, and must be comprehensive. Mutual heterogeneity means that the extracted elements cannot be repeated, and the extraction is carried out according to the idea of ​​layer by layer, so as to ensure that the most appropriate set of elements can be extracted. Comprehensiveness means that the elements extracted from the spacecraft system are complementary. The spacecraft system is a complete whole. The extracted element set should be able to reflect the composition characteristics of the entire system. The relationship between the elements should be able to reflect the correlation between the various components of the system. The set of elements and element relationships can fully reflect the true composition of the spacecraft system and can reconstruct the system.

[0068] As an embodiment provided by the present invention, preferably, the source of the knowledge base in the field of spacecraft design is mainly books or journals such as "Spacecraft System Design" and "China Aerospace", authoritative website reports such as NASA and ESA, detailed explanations of encyclopedic knowledge, and knowledge tables formed by manually sorted and translated authoritative website reports. According to the data type, it can be divided into structured, semi-structured and unstructured data.

[0069] As an embodiment provided by the present invention, preferably, the spacecraft design domain knowledge source is used as input, and a conceptual model is constructed to capture entity instances. Centered on the entity instance "manned spacecraft", the entity instance results obtained are as follows: Figure 2 shown. Figure 2 It includes entity instances (represented by rectangles) and relationships between entity instances (represented by line segments). Figure 2 It is only used to indicate the results; unclear fonts do not affect understanding.

[0070] As an embodiment provided by the present invention, preferably, Figure 3 As shown in the figure, when constructing a conceptual model to capture entity instances, the entity instances are clustered and comprehensively analyzed, similar items are merged, and entity instances that do not meet the standards are deleted. Relationships between entity instances are established, such as association, generalization, dependency, etc., and entity instances are abstracted to the domain entity level to obtain domain entities.

[0071] As an embodiment provided by the present invention, preferably, the domain metamodel includes design rules, design constraints and design patterns. The metamodel is constructed based on the MOF architecture standard according to the design object, design goal and design principle. The metamodel layer uses the Unified Modeling Language (UML) and the System Modeling Language (SysML) as the language basis to construct the meta-data and spacecraft semantic description. The metamodel layer uses the class diagram of the Unified Modeling Language to create a spacecraft metamodel, standardizes the model elements and the relationship between their elements, and creates a stereotype (Stereotype) of the spacecraft domain knowledge by expanding the SysML language to carry the overall domain design information of the spacecraft. The model layer uses the expanded domain modeling language and combines the spacecraft design experience to use the stereotype of the overall domain of the spacecraft to create a system model of the spacecraft. The information layer forms a product instance by assigning values ​​to the system model, and forms a logic, mechanism, and component instance library using instance models of different design schemes.

[0072] As an embodiment provided by the present invention, preferably, based on the SysML specification, a general metamodel with the most appropriate semantics is selected as a template, and the Stereotype element representing the domain metamodel is bound to the basic template element through a corresponding relationship, as shown in the following Table 1:

[0073] Table 1

[0074]

[0075]

[0076]

[0077] In this embodiment, the spacecraft design domain metamodel is constructed according to Table 1, including element metamodel and relationship metamodel. The main types of element metamodels are: mechanism, goal, condition, location, requirement, executor, indicator, resource, activity, etc. Figure 4 As shown: The relational metamodel is extended based on the three major relationships specified in the SysML specification: association, dependency, and generalization.

[0078] As an embodiment provided by the present invention, preferably, the overall domain model of the spacecraft includes a demand model, a functional model, a performance model, an architecture model, etc. The demand model describes the stakeholders and stakeholder needs at different stages of the entire life cycle of the spacecraft design; the functional model describes the functional scenarios of the spacecraft to realize the carrying of the needs of the stakeholders; the performance model describes the performance characteristics of the spacecraft, including propulsion capability, communication capability, navigation capability, etc.; the architecture model describes the physical structure of the spacecraft, including the location and connection relationship of each subsystem.

[0079] As an embodiment provided by the present invention, preferably, Figure 5 As shown, the requirement model comprehensively collects and records the needs and expectations of various stakeholders in mission implementation, and transforms mission objectives and related needs into clear and identifiable mission requirement model elements.

[0080] As an embodiment provided by the present invention, preferably, Figure 6 As shown, the functional model takes the task requirement model as input, decomposes the capabilities required to achieve task objectives and meet task requirements, and derives the system functions required to meet the capabilities.

[0081] As an embodiment provided by the present invention, preferably, Figure 7 As shown, the system architecture is preliminarily determined by combining the task requirement model and the functional model.

[0082] As an embodiment provided by the present invention, preferably, the domain model is applied to the spacecraft design process, the correlation between the design information is analyzed, and the system design process is forward deduced to optimize the spacecraft design process and realize the automation and intelligence of the design.

[0083] As an embodiment provided by the present invention, preferably, the rationality of the system model design and the coverage of requirements are verified by describing the information flow, function flow and state flow between modules of the manned spacecraft system. The strict logical relationship of each design stage is used to strictly ensure the consistency and verifiability of the changes between requirements, functions, behaviors, activities and architectures.

[0084] As an embodiment provided by the present invention, preferably, Figure 8 As shown in the figure, the spacecraft design changes are analyzed and verified mainly by building analysis models and traceability models, and the coordination, accuracy and completeness of the system are confirmed by executing analysis models and traceability models, thus completing the analysis and verification of the system model. The requirement derivation matrix is ​​used to check whether the capability requirements are fully covered.

[0085] A method for constructing a spacecraft overall domain model based on a digital meta-model can apply the domain model to the spacecraft design process. It has the characteristics of unified data source, short iteration cycle, and strong expansibility. It can further reduce the system-level development cost, realize the automation and intelligence of design, and improve the efficiency and quality of spacecraft design.

[0086] The present invention relates to Figure 2-7 , are all for the purpose of expressing "illustration" rather than showing specific element contents, so unclear text in the drawings does not affect the understanding of this solution.

[0087] In the description of this specification, the description with reference to the terms "one embodiment", "example", "specific example", etc. means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic representation of the above terms does not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described can be combined in any one or more embodiments or examples in a suitable manner.

[0088] The preferred embodiments of the present invention disclosed above are only used to help illustrate the present invention. The preferred embodiments do not describe all the details in detail, nor do they limit the invention to the specific implementation methods described. Obviously, many modifications and changes can be made according to the content of this specification. This specification selects and specifically describes these embodiments in order to better explain the principles and practical applications of the present invention, so that those skilled in the art can understand and use the present invention well. The present invention is limited only by the claims and their full scope and equivalents.

Claims

1. A method for constructing a spacecraft overall domain model based on a digital meta-model, characterized in that: The following steps are involved: Step SS01: extract the design elements in the spacecraft system through the element extraction method and abstract them into the corresponding conceptual model; Step SS02: Use the class diagram of the unified modeling language to create a spacecraft domain metamodel, standardize the model elements and the relationship between model elements, and extend the SysML language; Step SS03: Generate the overall domain model of the spacecraft using the domain metamodel; Step SS04: Apply the overall domain model to the spacecraft design process, analyze the correlation between design information, and forward deduce the system design process.

2. The method for constructing a spacecraft overall domain model of a digital meta-model according to claim 1 is characterized in that: The design elements include the spacecraft's structure, performance, functions, payload, and scientific objectives.

3. The method for constructing a spacecraft overall domain model of a digital meta-model according to claim 1 is characterized in that: The domain metamodel includes design rules, design constraints and design patterns.

4. The method for constructing a spacecraft overall domain model of a digital meta-model according to claim 1, characterized in that: The overall domain model includes a spacecraft requirement model, a functional model, a performance model and an architecture model.

5. The method for constructing a spacecraft overall domain model of a digital meta-model according to claim 1 or 4, characterized in that: The requirement model is used to describe the stakeholders and stakeholder needs at different stages of the entire life cycle of spacecraft design; the functional model is used to describe the functional scenarios of the spacecraft; the performance model is used to describe the performance characteristics of the spacecraft, which include propulsion capability, communication capability, and navigation capability; the architecture model is used to describe the physical structure of the spacecraft, including the location and connection relationship of each subsystem.

6. The method for constructing a spacecraft overall domain model of a digital meta-model according to claim 1, characterized in that: In step SS02, the method for constructing the spacecraft design domain metamodel is: Step S021: extracting ontology, relationship and constraint concepts from the spacecraft domain knowledge base; Step S022: performing abstract syntax description according to the four-layer representation mechanism of MOF; Step S023: Use UML class diagram to define abstract syntax of ontology, relationship and constraint; Step S024: Based on the abstract syntax, obtain each model element in the abstract syntax; Step S025: Identify the general metamodel in SysML that is most similar to other semantics, and define corresponding representation methods and symbols for each model element as the specific syntax corresponding to the model element; Step S026: Based on the general metamodel, SysML is extended by creating stereotypes to construct a domain metamodel of the spacecraft system.

7. The method for constructing a spacecraft overall domain model of a digital meta-model according to claim 6 is characterized in that: In step SS02, labels and constraints are used to describe the newly created domain metamodel.

8. The method for constructing a spacecraft overall domain model of a digital meta-model according to claim 6 is characterized in that: In the step SS02, based on the SysML specification, a general metamodel with the most appropriate semantics is selected as a template, and the construction type elements representing the domain metamodel are bound to the template elements through corresponding relationships.

9. The method for constructing a spacecraft overall domain model of a digital meta-model according to claim 8, characterized in that: The domain metamodel includes element metamodel and relational metamodel. The element metamodel includes: mechanism, goal, condition, location, requirement, executor, indicator, resource and activity. The relational metamodel is extended based on the three major relationships of association, dependency and generalization stipulated in the SysML specification.

10. The method for constructing a spacecraft overall domain model of a digital meta-model according to claim 1, characterized in that: The spacecraft design process includes requirement analysis, functional decomposition, architecture design and analysis verification.

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