MBSE-based aircraft undercarriage system model integration method

Abstract

The invention discloses an MBSE-based aircraft undercarriage system model integration method, and belongs to the technical field of system engineering. The method comprises the following steps: constructing an aircraft undercarriage system architecture, a classification mapping of simulation design information and a GOPPRR-E element model, and a meta-model library; constructing an architecture model according to a demand-function-logic-physical process, and generating a Simulink simulation model according to the architecture; a simulation model semantic mapping rule is constructed according to an OSLC specification, and design information is analyzed to establish an integrated data model; and a Simulink simulation tool integration adapter is constructed, and a tool interoperation service based on Web is provided. According to the method, a multidisciplinary model can be accurately constructed, uniform expression of architecture and simulation models and semantic consistency of heterogeneous models are realized, two-way transmission of cross-domain information and interoperation between tools are supported, the problem of interoperation between architecture modeling and simulation modeling tools in aircraft undercarriage system design is effectively solved, and the design efficiency is improved.

Description

Technical Field

[0001] The present invention relates to the technical field of system engineering, and in particular to an aircraft landing gear system model integration method based on MBSE. Background Art

[0002] With the continuous evolution of space exploration mission requirements, the design complexity of components, interfaces, etc. in the existing aerospace equipment design process has increased exponentially, which has brought challenges to the cognitive load of designers and forced the design mode of aerospace equipment to transform from a document-based system engineering design mode to a model-based system engineering design mode. Model-based systems engineering (MBSE) supports formalization, modeling, design, analysis and verification in the entire life cycle of product and system development through models, providing solutions to the development challenges of complex systems. However, the most mainstream MBSE modeling language for aerospace equipment is the SysML modeling language. Although the language provides a limited number of metamodels, it can describe the requirements, behaviors, components and performance of aerospace equipment by combining metamodels in a graphical modeling way. However, its abstract and simplified characteristics still require engineers to manually identify and establish the conversion relationship between multi-system and multi-disciplinary design information of aerospace equipment and SysML modeling symbols in the process of engineering application. In addition, there is a phenomenon of design information loss in the process of expressing design information of different disciplines through the same modeling elements, and there are problems of inaccurate modeling expression and incomplete discipline information, as follows:

[0003] The aircraft landing gear system is a key component that undertakes the take-off and landing functions of the aircraft. It is a typical complex system with high complexity and large number. Its design and performance are directly related to the safety of the aircraft. The main functions of the aircraft landing gear system include supporting the weight of the aircraft body, absorbing the impact of landing, providing the ability to control the aircraft body on the ground, and realizing reliable retraction and extension behavior in the flight state. Due to the complexity and variability of the aircraft operating environment, the aircraft landing gear system needs to withstand dynamic loads, vibrations and stresses under various working conditions, and the design requirements are extremely high. In the design process of the aircraft landing gear system, multi-department collaborative design and simulation verification of key indicators are required. The traditional document-based overall design model of the aircraft landing gear system is dominated by the overall design department. The form of multi-department collaborative design faces problems such as delayed design verification, inefficient cross-departmental collaborative communication, and inability to achieve design traceability.

[0004] At present, as a new overall design mode, model-based system engineering (MBSE) has been widely used in the overall design of complex systems such as aviation power equipment and high-speed trains. It can realize the verification of the system in the early design stage and improve the consistency and traceability of the design scheme. At present, the overall design trend of the aircraft landing gear system is to adopt the design mode based on MBSE, and realize the design of the aircraft landing gear system by constructing the architecture model and simulation model of the aircraft landing gear system respectively. In the design process, the engineers first establish the architecture model of the aircraft landing gear system, describe the requirements, composition, behavior, interface, etc. of the aircraft landing gear system, such as the structure and mechanical performance indicators of the aircraft landing gear system, and finally generate the design scheme. Subsequently, the simulation model is constructed or converted based on the architecture model, and the key performance indicators and dynamic behaviors of the aircraft landing gear system in the architecture model design scheme are verified through the simulation model, such as the mechanical response of the aircraft landing gear system, the retraction and extension behavior, etc. In the design process, it may be necessary to repeatedly reconstruct the system architecture model according to the simulation verification results, and generate the simulation model again for simulation. For the integration process of architecture model and simulation model, the core is to achieve interoperability between architecture modeling and simulation modeling tools. Interoperability refers to the ability of architecture, modeling and other tools and their models to seamlessly exchange and use data. Since the architecture model and simulation model use different modeling tools, the underlying code implementation mechanisms of different modeling tools are incompatible, and different modeling tools use different modeling languages, the semantics and syntax of the constructed models are heterogeneous. The meaning of the model is described by semantics and syntax, and the semantic syntax of the model is the carrier of the meaning of the model. Both the architecture modeling tool and the simulation verification tool parse and interpret their own semantics and syntax through their own compilation mechanisms. However, due to the heterogeneity of semantics and syntax used by different modeling tools, their compilation mechanisms are incompatible with other languages. In the design process of aircraft landing gear system, the multi-architecture unified modeling language KARMA is used to model the architecture of the aircraft landing gear system. Simulink is usually used to simulate the retraction and extension load of the aircraft landing gear system, and AMEsim is used to simulate the hydraulic retraction and extension of the aircraft landing gear system. Simulink describes the simulation model through ordinary differential equations (ODE), and AMEsim describes the simulation model through partial differential equations (PDE). ODE and PDE equations cannot be read or model parsed in the architecture modeling tool, and KARMA language cannot be read or model parsed in the simulation modeling tool.This brings about interoperability challenges between architecture modeling and simulation modeling tools, which directly leads to the inability to exchange design information between architecture models and simulation models and difficulty in effective integration.

[0005] There are many ways to integrate the architecture model with the simulation model, such as model conversion, ontology technology, etc. The existing model integration technology has the defects of unidirectional conversion between models and the inability to formally represent interfaces, which leads to the inability to achieve bidirectional transmission of cross-domain information and interface interoperability between different models.

[0006] In the existing aircraft landing gear system design process, the same model is repeatedly constructed and it is difficult to maintain model consistency. There is an urgent need for a model integration technology to promote the improvement of aircraft landing gear system design efficiency. Summary of the invention

[0007] The purpose of the present invention is to provide an aircraft landing gear system model integration method based on MBSE, which solves the interoperability problem between architecture modeling and simulation modeling tools in the design process of the aircraft landing gear system.

[0008] To achieve the above object, the present invention provides an aircraft landing gear system model integration method based on MBSE, comprising the following steps:

[0009] S1, construct the classification mapping process of aircraft landing gear system architecture design information, simulation design information and GOPPRR-E meta-metamodel, and build the meta-model library of GOPPRR-E;

[0010] S2. Build the aircraft landing gear system architecture model according to the demand-function-logic-physical process, and generate a simulation model through the simulation scheme in the architecture model;

[0011] S3, constructing the simulation model semantic mapping rules according to the OSLC specification and establishing the integrated data model of the simulation model by parsing the simulation model design information;

[0012] S4. Build a Simulink simulation tool integration adapter to provide Web-based tool interoperability services.

[0013] Preferably, in step S1, the GOPPRR-E meta-metamodel includes seven basic meta-metamodel elements: view, object, endpoint, attribute, relationship, role, and extension.

[0014] Preferably, in step S1, the GOPPRR-E metamodel library includes a graph metamodel, an object metamodel, a point metamodel, an attribute metamodel, a relationship metamodel, a role metamodel and extensions, which are used to define an architecture model and a simulation scheme of an aircraft landing gear system.

[0015] Preferably, in step S2, the requirement-function-logic-physical design process includes four steps: requirement analysis, function analysis, logical architecture design and physical architecture design, and the construction of models at different levels is supported and implemented through the constructed metamodel library.

[0016] Preferably, in step S2, the simulation model used is a Simulink simulation model, and the design of the aircraft landing gear system is ultimately implemented into the calculation and simulation analysis of key performance indicators through the Simulink simulation tool and model.

[0017] Preferably, in step S2, a code generation script is written through the generation capability of KARMA itself to convert the physical simulation scheme constructed in the aircraft landing gear system architecture model into an executable M file, and the aircraft landing gear system simulation model is obtained by running the generated M file.

[0018] Preferably, in step S3, according to the model structure in the simulation model, the key information of the model parameters and the operation interface of the corresponding tool for adding, deleting, modifying and checking, an integrated data model for model integration is constructed based on the Open Service for Lifecycle Collaboration (OSLC) integration specification. The semantic mapping rules of simulation, architecture model and integration service are established according to the OSLC specification. The OSLC specification is composed of core specifications and domain specifications, wherein the core specification specifies and describes the core integration concepts of the OSLC specification and the common features supported by the OSLC service;

[0019] The OSLC core model includes service provider catalog, service providers, services, and resources;

[0020] Based on the core model and semantic mapping rules of OSLC, an information transfer path is built between the architecture and simulation model to achieve semantic consistency and interoperability between different tools and models.

[0021] Preferably, in step S3, semantic mapping rules of simulation, architecture model and integration service are established according to OSLC specification, wherein OSLC specification is composed of core specification and domain specification, wherein core specification specifies and describes the core integration concept of OSLC specification and the common features supported by OSLC service;

[0022] The OSLC core model includes service provider catalog, service providers, services, and resources;

[0023] Based on the core model and semantic mapping rules of OSLC, an information transfer path is built between the architecture and simulation model to achieve semantic consistency and interoperability between different tools and models.

[0024] Preferably, in step S3, the simulation model is analyzed for data to obtain the model structure, model parameters and the operation interface of adding, deleting, modifying and checking the Simulink model, so as to ensure that the model data can be smoothly integrated;

[0025] After the simulation model data is successfully parsed, the reading and modification of the simulation model data is realized, and the simulation model data can be correctly mapped according to the semantic mapping rules.

[0026] Preferably, in step S4, according to semantic mapping rules and data parsing technology, a Simulink tool integration adapter is constructed to perform operation services such as adding, deleting, modifying and checking the meta-models such as models, subsystems and modules in the simulation model, so as to realize the formal representation of the simulation model information, thereby realizing the two-way transmission of cross-domain information and realizing the interoperability between different domain models in heterogeneous tools;

[0027] The Simulink tool integration adapter is the tool implementation carrier of the OSLC core model and semantic mapping rules.

[0028] Therefore, the present invention adopts an aircraft landing gear system model integration method based on MBSE with the above structure, which has the following beneficial effects:

[0029] (1) The present invention is developed based on the KARMA language and GOPPRR-E modeling mechanism. By using the seven types of GOPPRR-E (view-object-endpoint-attribute-relationship-role-extension) meta-model elements, a multidisciplinary model of the aircraft landing gear system can be accurately constructed. It has a high degree of abstraction and flexibility, can cope with the complexity of different disciplines, and express the design elements of the aircraft landing gear system clearly, completely, and unambiguously.

[0030] (2) The present invention is developed based on the Simulink simulation mechanism. Through the Simulink simulation tool and model, the design of the aircraft landing gear system is finally implemented into the calculation and simulation analysis of key performance indicators.

[0031] (3) The present invention supports unified modeling of multiple disciplines and systems. Through the combination of GOPPRR-E meta-metamodels, the design information of multiple fields such as mechanics, hydraulics, and control in the aircraft landing gear system can be accurately described. The knowledge and information of each discipline can be accurately captured and expressed. Not only can the physical composition of the aircraft landing gear system be described, but also its internal interaction relationship and technical parameters can be expressed, ensuring the accuracy of the model expression.

[0032] (4) The present invention provides a simulation model generated from a simulation scheme in an architecture model. By using the code generation capability of KARMA itself, a code generation script is written to convert the Simulink simulation diagram in the aircraft landing gear architecture model into an executable M file. This enables rapid generation of a simulation model based on the design information in the architecture, and ensures consistency between the simulation scheme in the architecture model and the simulation model.

[0033] (5) The present invention constructs a model semantic mapping relationship, including constructing semantic mapping rules between the OSLC core model, the KARMA architecture model and the Simulink simulation model, and realizes the unified expression of the aircraft landing gear system architecture model and the simulation model through the OSLC core model, eliminating the semantic and grammatical heterogeneity of the architecture model and the simulation model. Based on the mapping rules, an information transmission path is constructed between the architecture and the simulation model, which can realize the implementation of the aircraft landing gear system integration service and realize the interoperability of the model between heterogeneous tools.

[0034] (6) The present invention provides Simulink simulation model data parsing, which parses the simulation model in a standardized eXtensible markup language (XML) format, and uses a DOM parsing method to parse the simulation model, and represents it as a tree structure, so as to facilitate reading the data in the model. After the simulation model data is successfully parsed, the simulation model data can be read and modified, and the simulation model data can be correctly mapped according to the semantic mapping rules.

[0035] (7) The present invention constructs a Simulink simulation tool adapter. Through semantic mapping rules and data parsing technology, it can access the information of the simulation model and perform model operations in the Simulink adapter, thereby realizing bidirectional transmission of cross-domain information. Services such as adding, deleting, modifying, and checking models, subsystems, and modules are constructed on the tool adapter to realize the formal representation of simulation model information, thereby realizing the interoperability between models in different domains among heterogeneous tools and the consistent bidirectional transmission of aircraft landing gear design information between architecture modeling tools and simulation verification tools.

[0036] The technical solution of the present invention is further described in detail below through the accompanying drawings and embodiments. BRIEF DESCRIPTION OF THE DRAWINGS

[0037] Figure 1 It is a schematic diagram of the process framework of an aircraft landing gear system model integration method based on MBSE of the present invention;

[0038] Figure 2 It is a schematic diagram of a method for constructing a metamodel of an aircraft landing gear system of an aircraft landing gear system model integration method based on MBSE of the present invention;

[0039] Figure 3 A schematic diagram of an aircraft landing gear system architecture modeling process of an aircraft landing gear system model integration method based on MBSE of the present invention;

[0040] Figure 4 A schematic diagram of the aircraft landing gear simulation model construction process of an aircraft landing gear system model integration method based on MBSE of the present invention;

[0041] Figure 5 A schematic diagram of the OSLC core model and model mapping relationship of an aircraft landing gear system model integration method based on MBSE of the present invention;

[0042] Figure 6 A schematic diagram of the aircraft landing gear system simulation model analysis process of an aircraft landing gear system model integration method based on MBSE of the present invention;

[0043] Figure 7 It is a schematic diagram of the architecture model of a landing gear retraction and extension performance simulation scheme of an aircraft landing gear system model integration method based on MBSE of the present invention;

[0044] Figure 8 It is a schematic diagram of a landing gear retraction and extension performance simulation model of an aircraft landing gear system model integration method based on MBSE of the present invention;

[0045] Fig. 9 A schematic diagram of an aircraft landing gear system design process of an aircraft landing gear system model integration method based on MBSE of the present invention;

[0046] Fig.10 The present invention is a schematic diagram of an aircraft landing gear system simulation model integration method based on MBSE for the present invention; wherein: a. a diagram of the first simulation result of retracting and extending the actuator cylinder; d. a diagram of a model of a simulation scheme architecture that is changed; c. a diagram of a simulation model that is changed; d. a diagram of a second simulation result of retracting and extending the actuator cylinder. DETAILED DESCRIPTION

[0047] The technical solution of the present invention is further described below through the accompanying drawings and embodiments.

[0048] Unless otherwise defined, the technical terms or scientific terms used in the present invention should be understood by people with ordinary skills in the field to which the present invention belongs. The words "first", "second" and similar words used in the present invention do not indicate any order, quantity or importance, but are only used to distinguish different components. "Include" or "comprise" and similar words mean that the elements or objects appearing before the word include the elements or objects listed after the word and their equivalents, without excluding other elements or objects. "Connect" or "connected" and similar words are not limited to physical or mechanical connections, but may include electrical connections, whether direct or indirect. "Up", "down", "left", "right" and the like are only used to indicate relative positional relationships. When the absolute position of the described object changes, the relative positional relationship may also change accordingly.

[0049] OSLC is a technical specification proposed by IBM for tool integration and collaboration within the MBSE lifecycle. It can provide a unified method to manage and operate various models and their data in lifecycle management tools. The OSLC specification consists of core specifications and domain specifications. The core specification specifies and describes the core integration concepts of the OSLC specification and the common features supported by OSLC services. The OSLC core model includes the service provider directory, service providers, services, and resources.

[0050] The present invention constructs an integrated data model for model integration based on the OSLC integration specification. The OSLC integration specification is a set of technical specifications for integrating tools within the MBSE life cycle. OSLC provides a unified compilation mechanism. First, through the unified description of data resources in OSLC, the different semantics and syntaxes existing in the architecture model and the simulation model are standardized and converted into a unified integrated data model, so that heterogeneous models are consistent at the semantic and grammatical levels; secondly, by calling the REST API to compile the unified integrated data model, the models generated by the heterogeneous tools are constructed into a Web-based interoperability service.

[0051] Example

[0052] like Figure 1 As shown, the present invention provides an aircraft landing gear system model integration method based on MBSE, comprising the following steps:

[0053] Step S1, construct the classification mapping process of aircraft landing gear system architecture design information, simulation design information and GOPPRR-E meta-meta model, and build the GOPPRR-E meta-model library. Figure 2 As shown, the mapping relationship between the meta-meta-model and the meta-model of the present invention is shown.

[0054] Specifically, according to the seven types of meta-meta-models including view, object, endpoint, attribute, relationship, role and extension provided by GOPPRR-E modeling theory, combined with the multidisciplinary design information analysis of aircraft landing gear system, a meta-model library of aircraft landing gear system and the association relationship between meta-models are formed by constructing a classification mapping between the aircraft landing gear system architecture design information, simulation design information and GOPPRR-E meta-meta-model.

[0055] The metamodel library of the aircraft landing gear system includes a graph metamodel, an object metamodel, a point metamodel, an attribute metamodel, a relationship metamodel, a role metamodel, and an extended metamodel.

[0056] According to the GOPPRR-E modeling theory, the graph metamodel is used to analyze a certain viewpoint of the system and describe the system in a block diagram. For example, the subsystem of the aircraft landing gear is expressed by a graph metamodel with internal components and behavioral interfaces. The object metamodel is the main element in the model, which is used to represent an entity. It can exist alone or be linked to other objects. For example, the electronic control subsystem and the retracting subsystem of the aircraft landing gear are each expressed by an object metamodel. The relationship metamodel is connected to the object through roles to indicate how the objects are connected. For example, the electrical signal interaction between the electronic control subsystem and the retracting subsystem is expressed and connected through relationships. The point metamodel should be attached to the object to represent the port connecting the object and the role. For example, the object metamodel of the electronic control subsystem has endpoint metamodels of different fields such as the current port. The attribute metamodel is used to define and describe the characteristics of some metatypes (objects, roles and relationships). Attributes cannot exist alone and should be attached to other meta-metamodels to represent their characteristics. For example, the object metamodel of the electric control subsystem has not only the metamodel of the name and other attributes, but also the metamodel of the power attribute required in the electrical field design. The role metamodel should be at both ends of the relationship to indicate how the objects are connected. For example, the two ends of the current relationship metamodel are the interaction start role metamodel and the interaction end metamodel. The extended metamodel represents the additional constraint relationship between the above metamodels. For example, the metamodel of the electric control subsystem can be further expanded into the metamodel of the component view of the electric control subsystem by decomposing the constraint relationship.

[0057] Step S2, constructing the aircraft landing gear system architecture model according to the demand-function-logic-physical process, and generating a simulation model through the simulation solution in the architecture model.

[0058] Specifically, according to the design requirements of the aircraft landing gear system and in accordance with the demand-function-logic-physical design process, the metamodel of the aircraft landing gear system is organized and instantiated, and the aircraft landing gear system architecture model such as structure, activity, and simulation scheme is constructed. The code generation capability is used to write a code generation script to convert the simulation scheme model in the architecture model into an executable M file and obtain the aircraft landing gear system simulation model, so as to quickly generate a simulation model according to the design information in the architecture model and ensure the consistency of the model.

[0059] Based on the overall design process of the Requirements-Function-Logic-Physical (RFLP) model, starting from the aircraft level, system level and subsystem level, a model of the aircraft landing gear system from requirements to functions to logic to physics is constructed, such as Figure 3 As shown. First, starting from the system mission requirements and stakeholder requirements, the requirements of the aircraft landing gear system are summarized. Then, according to the system requirements, the functional design of the aircraft landing gear system is proposed, including system context, use case analysis, functional activities, etc. Subsequently, the logic design work is carried out according to the use case activity analysis, the internal interface interaction design is carried out according to the subsystem, the use case activity analysis is refined, and the actuator retraction and extension load is analyzed. Finally, a physical simulation architecture diagram is established to decompose the internal components and analyze the parameters of the aircraft landing gear.

[0060] By using KARMA's own code generation capabilities, a code generation script is written to convert the Simulink simulation diagram in the aircraft landing gear architecture model into an executable M file. Figure 4 The simulation model construction process of building Simulink metamodel, model and code generation is demonstrated. The code generation script consists of rules such as creating M files, creating and opening Simulink models, adding modules, adding module connection relationships, and setting module parameters. Objects, attributes, and relationships in the Simulink simulation diagram are stripped by different rules, combined according to the order of rules, and finally reconstructed into MATLAB code. By running the generated M file, the simulation model of the aircraft landing gear system is obtained and simulated.

[0061] Step S3: constructing simulation model semantic mapping rules according to OSLC specifications and establishing an integrated data model of the simulation model by parsing the simulation model design information.

[0062] Specifically, by uniformly describing data resources in OSLC, the different semantics and syntaxes in the architecture model and simulation model are standardized and converted into a unified integrated data model, so that heterogeneous models are consistent in semantics and syntax. By parsing the simulation model design information, key information such as model structure and model parameters in the simulation model and the corresponding tool operation interfaces such as add, delete, modify and query are obtained, and an integrated data model for model integration is constructed based on the OSLC integration specification.

[0063] According to the OSLC specification, it is necessary to establish semantic mapping rules between the OSLC core model, KARMA architecture model and Simulink simulation model. The semantic mapping rules between the OSLC core model and the aircraft landing gear system architecture model and simulation model are shown in Table 1. The OSLC core model realizes the unified expression of the aircraft landing gear system architecture model and simulation model, eliminating the semantic and grammatical heterogeneity of the architecture model and simulation model. Based on this mapping rule, the integration service of the aircraft landing gear system can be realized, and the interoperability of models between heterogeneous tools can be achieved.

[0064] The architecture model and simulation model semantics of the aircraft landing gear system are mapped to the OSLC core model respectively, such as Figure 5 As shown in the figure, the mapping relationship between OSLC specification and the semantics of architecture model and simulation model is shown by corresponding to the OSLC core model form.

[0065] Table 1 OSLC core model and model mapping objects

[0066]

[0067]

[0068] Parse the simulation model data to obtain key information such as the model structure and model parameters of the simulation model and the operation interface of the Simulink model such as adding, deleting, modifying and checking to ensure that the model data can be smoothly integrated. When parsing the aircraft landing gear simulation model, it is necessary to search and extract the parameters and properties of each module and subsystem, as well as the relationship between different modules and subsystems. The analysis process of the aircraft landing gear system simulation model is as follows: Figure 5 As shown. The data parsing process is carried out in a deep search manner. First, the name, type and other information of the top-level elements (modules, subsystems) in the model are searched, and the information is recorded. Starting from the top-level element, the position and other parameters of the element are searched downward and the information is recorded. If the top-level element is a subsystem, the search for the elements contained therein continues downward. After all searches are completed, the parsed data is output to generate a model data tree.

[0069] The simulation model built by Simulink can use the unified standard eXtensible markup language (XML) format to store data. XML files have a fixed structure, with hierarchical relationships such as root elements, child elements, and attributes, and are nested by multiple tags. This structured method makes the hierarchical relationship of the data clear and has a strong regularity, and can quickly and accurately extract the required content. The simulation model is parsed using the DOM parsing method and represented as a tree structure to facilitate reading the data in the model. Since DOM parsing parses the data into a tree structure, similar to the XML file format, a mapping relationship between the aircraft landing gear system simulation model and the XML file can be established, as shown in Table 2.

[0070] Table 2 Mapping relationship between simulation model and XML file

[0071]

[0072]

[0073] First search the XML file for <model>The tag records all the information of the aircraft landing gear system simulation model, including content structure and configuration information. In the XML file, the entire content structure of the simulation model is regarded as a complete system, so the first <system>, the first <system>The complete model structure of the simulation model is included. Next, search for the next level The Name attribute in the tag indicates the parameter name, which records the parameter name and value related to the model. After recording the basic parameters of the model, locate <block>tags to search for elements in the simulation model. <block> The BlockType attribute of the tag indicates the element type, the Name attribute indicates the element name, and the SID attribute indicates the element ID. Then search for the next level< / block> < / block> Tag, record the parameter name and value of the current element. If the current element type is "Subsystem", it means that the element is a subsystem, and <block>The tag is nested <system>Tags, need to continue parsing <system>If the element type is other than , it means that the element is a module. Repeat the above process until all <block>Tags. Last searched to <line> After the tag, search for the nested< / line> < / block> < / system> < / system> < / block> Tag, record the parameter name and value of the current connection. After all searches are completed, the data parsing of the aircraft landing gear system simulation model is completed to form a model data tree.

[0074] After the simulation model data is successfully parsed, the reading and modification of the simulation model data is realized, and the simulation model data can be correctly mapped according to the semantic mapping rules.

[0075] Step S4: construct a Simulink simulation tool integration adapter to provide a Web-based tool interoperability service.

[0076] Specifically, the tool adapter is the tool implementation carrier of the OSLC core model and semantic mapping rules. Through semantic mapping rules and data parsing technology, it is possible to access the information of the simulation model and operate the model in the Simulink adapter, realize the two-way transmission of cross-domain information, and then realize the interoperability between different domain models in heterogeneous tools.

[0077] After completing the simulation model data parsing, in order to realize the construction of the Simulink tool adapter, it is also necessary to generate services for operations such as adding, deleting, modifying, and checking the simulation model data. The following services for simulation model elements are built in the Simulink tool adapter:

[0078] 1) Model service: query the internal structure / metadata of the model (creator, modification time, etc.);

[0079] 2) Subsystem services: query / add / delete subsystems, query / modify subsystem internal structure / subsystem parameters;

[0080] 3) Module service: query / add / delete modules, query / modify module parameters (attributes, location, etc.);

[0081] 4) Connection service: query / add / delete connection;

[0082] By building the above services in the tool adapter, the formal representation of simulation model information can be achieved, and by reusing the above services, the consistent two-way transmission of aircraft landing gear design information between architecture modeling tools and simulation verification tools can be achieved.

[0083] According to the above process, the construction of the landing gear system architecture model and simulation model is completed. When the landing gear system requirements change, the engineering staff changes the corresponding indicators of the architecture model, and changes the landing gear system simulation model through the model integration service platform to adjust the corresponding parameters. Subsequently, the simulation model is simulated to obtain the simulation results, and the results are fed back to the architecture model to achieve two-way transmission of cross-domain information.

[0084] The specific plan is as follows:

[0085] (1) Model construction:

[0086] Construct the architectural model of the landing gear system. Based on the requirements-function-logic-physical (RFLP) modeling process, starting from the aircraft level, system level and subsystem level, a model of the landing gear system from requirements to functions to logic to physics is constructed, such as Figure 3 shown.

[0087] First, we summarize the landing gear system requirements based on the system mission requirements and stakeholder requirements. Then, we propose the landing gear system functional design based on the system requirements, including system context, use case analysis, functional activities, etc. Then, we carry out the logic design work based on the use case activity analysis, and carry out the internal interface design based on the subsystem.

[0088] Interactively design and refine the use case activity analysis, and analyze the actuator retraction and extension load. Finally, establish a physical simulation architecture diagram to decompose and analyze the internal components and parameters of the landing gear.

[0089] During the retraction and extension process of the landing gear system, the force form of the retraction and extension actuator is relatively complex. It not only needs to bear the weight of the system and the friction accompanying the retraction and extension process, but also needs to bear other related external forces such as the aerodynamic drag generated by the retraction and extension action of the landing gear during flight. During the retraction and extension process, due to the change in the shape of the landing gear, the load caused by its force will change dynamically. This paper simulates and verifies the dynamic load of the actuator of the landing gear system, so as to ensure that the actuator of the landing gear system has sufficient safety margin during the retraction and extension process.

[0090] The mass force P of the landing gear system in a steady airflow environment m for

[0091]

[0092] Among them, P m The direction is vertically downward; G t Part of the weight is used to rotate the landing gear; It is the overload when the landing gear is retracted or extended, which is generally not greater than 2.0. In the present invention, it is 2.0.

[0093] Mass force P m Moment M about the fixed point m for:

[0094] M m =P m rsinφ;

[0095] Where r is the distance between the center of mass of the landing gear and the fixed point; φ is the landing gear movement angle, and the angle range is 0°~105°

[0096] When the landing gear is retracted or extended, the aircraft is in the take-off or landing stage, and the aircraft body will have a certain pitch angle. After considering the pitch angle, the mass moments of the retracted and released landing gear system can be obtained as follows:

[0097]

[0098] The aerodynamic resistance of the landing gear system is the superposition of the aerodynamic resistance of each mechanical structure, and its direction points to the direction of airflow. The aerodynamic resistance of each mechanical structure is P adi for:

[0099]

[0100] Among them, C xi is the resistance coefficient of each mechanical structure; S i is the projected area of ​​each mechanical structure on the plane perpendicular to the airflow; ρ0 is the air density when the landing gear is retracted or extended; It is the maximum flight speed when the landing gear is retracted or extended.

[0101] Aerodynamic torque M ad for

[0102]

[0103] Among them, P adi As the aircraft retracts or extends the landing gear, b i It is the distance from the aerodynamic resistance of each mechanical structure to the fixed shaft force arm, and its value changes with the retraction and extension process.

[0104] After inputting the relevant parameters, the aerodynamic torque of the landing gear system when it is retracted and released is:

[0105]

[0106] The friction force P generated by the retracting and extending cylinder during the retraction and extension process f for:

[0107] P f =(0.18~0.4)P aa

[0108] Among them, P aa is a combined load, which is generated by the superposition of the landing gear mass force and the aerodynamic drag; in the present invention, the friction coefficient is 0.4.

[0109] Total load P of the landing gear system retraction and extension actuator act is the sum of the loads in the above cases, and its calculation formula is as follows:

[0110] P act =(M m +M ad ) / d+P f ;

[0111] Among them, d is the lever arm of the retracting and extending actuator on the landing gear shaft, and its value changes with the retracting and extending process.

[0112] According to the above-mentioned dynamic load calculation mechanism of the landing gear system retraction and extension cylinder, a load simulation scheme of the landing gear system is established through KARMA, such as Figure 7 As shown, in this scheme, 0-8s is the landing gear system release time, 8-11s is the landing gear system ground taxiing time, and 11-20s is the landing gear retraction time.

[0113] Finally, the landing gear retraction and extension performance simulation scheme architecture model is converted into a MATLAB code file through KARMA's code generation technology. After execution, a Simulink simulation model is generated, such as Figure 8 shown.

[0114] (2) Integrated Implementation

[0115] During the landing gear system design process, the process is as follows Fig. 9 First, after the overall department completes the construction of the landing gear system architecture model and generates a simulation model, it passes the model to the design departments in various fields for collaboration. Secondly, the load simulation department simulates the key indicators of the landing gear system's actuator retraction and extension performance. The simulation results are shown in Fig.10 (a) As the maximum value of the dynamic load in the simulation results exceeds the permissible load of 200MPa, the model of the physical components of the landing gear system and the simulation scheme were changed in the structural model. While the landing gear's own gravity and aerodynamic resistance remain unchanged, the engineers changed the lubrication form of the retracting and extending cylinder to reduce the friction during the retraction and extension process, so that the maximum load of the retracting and extending cylinder during the retraction and extension process is lower than the permissible load.

[0116] First, in the landing gear retraction and extension performance simulation scheme in the architecture model, the engineers changed the parameter of Gain1 from 0.4 to 0.3. That is, due to the change in the lubrication form of the retraction and extension cylinder, its friction coefficient decreased, thus reducing the friction of the retraction and extension cylinder. Fig.10 (b) As shown in the figure, due to the change of the architecture model, generating a new model again through the simulation solution in the architecture model will cause repeated construction of the simulation model, making it difficult to maintain the consistency of the management model.

[0117] Therefore, the Simulink adapter is used to modify the simulation model, and after the modification is completed, the simulation is directly performed in the tool adapter. Subsequently, the Simulink adapter is opened and the simulation model is entered, where all models, subsystems, modules and their detailed structure, location, and parameter information can be seen. The simulation model is modified in the same way as the simulation scheme in the architecture model and saved to obtain the modified simulation model, as shown in the figure. Fig.10 Click Simulate in the adapter to verify the load of the retractable and extended actuator for the new simulation model. The results are shown in Fig.10 (d) shows that the verification result shows that the maximum load is lower than the allowable load.

[0118] Therefore, the present invention adopts the above-mentioned aircraft landing gear system model integration method based on MBSE, and uses the seven-class meta-meta-model of view-object-endpoint-attribute-relationship-role-extension (GOPPRR-E) provided by KARMA language to construct the aircraft landing gear system architecture model, and then generates a simulation model through the simulation scheme in the architecture model, constructs model semantic mapping rules and establishes an integrated data model of the simulation model by parsing the simulation model content, so that the semantics of heterogeneous models are consistent, and then constructs a simulation tool adapter to achieve unified compilation of heterogeneous data, as well as integration of architecture model and simulation model. It can solve the interoperability problem between architecture modeling and simulation modeling tools in the design process of aircraft landing gear system.

[0119] Finally, it should be noted that the above embodiments are only used to illustrate the technical solution of the present invention rather than to limit it. Although the present invention has been described in detail with reference to the preferred embodiments, those skilled in the art should understand that they can still modify or replace the technical solution of the present invention with equivalents, and these modifications or equivalent replacements cannot cause the modified technical solution to deviate from the spirit and scope of the technical solution of the present invention. < / system> < / system> < / model>

Claims

1. An aircraft landing gear system model integration method based on MBSE, characterized by: The following steps are involved: S1, construct the classification mapping process of aircraft landing gear system architecture design information, simulation design information and GOPPRR-E meta-metamodel, and build the meta-model library of GOPPRR-E; S2. Build the aircraft landing gear system architecture model according to the demand-function-logic-physical process, and generate a simulation model through the simulation scheme in the architecture model; S3, constructing the simulation model semantic mapping rules according to the OSLC specification and establishing the integrated data model of the simulation model by parsing the simulation model design information; S4. Build a Simulink simulation tool integration adapter to provide Web-based tool interoperability services.

2. The aircraft landing gear system model integration method based on MBSE according to claim 1, characterized in that: In step S1, the GOPPRR-E meta-metamodel includes seven basic meta-metamodel elements: view, object, endpoint, attribute, relationship, role, and extension.

3. The aircraft landing gear system model integration method based on MBSE according to claim 1, characterized in that: In step S1, the GOPPRR-E metamodel library includes a graph metamodel, an object metamodel, a point metamodel, an attribute metamodel, a relationship metamodel, a role metamodel and extensions, which are used to define the architecture model and simulation scheme of the aircraft landing gear system.

4. The aircraft landing gear system model integration method based on MBSE according to claim 1, characterized in that: In step S2, the requirement-function-logic-physical design process includes four steps: requirement analysis, function analysis, logical architecture design and physical architecture design. The construction of models at different levels is supported and implemented through the constructed metamodel library.

5. The aircraft landing gear system model integration method based on MBSE according to claim 1, characterized in that: In step S2, the simulation model used is a Simulink simulation model. The design of the aircraft landing gear system is finally implemented into the calculation and simulation analysis of key performance indicators through the Simulink simulation tool and model.

6. The aircraft landing gear system model integration method based on MBSE according to claim 1, characterized in that: In step S2, a code generation script is written through the generation capability of KARMA to convert the physical simulation scheme constructed in the aircraft landing gear system architecture model into an executable M file. By running the generated M file, the aircraft landing gear system simulation model is obtained.

7. The aircraft landing gear system model integration method based on MBSE according to claim 1, characterized in that: In step S3, according to the model structure in the simulation model, key information of model parameters and the operation interface of the corresponding tool for adding, deleting, modifying and checking, an integrated data model for model integration is constructed based on the OSLC integration specification.

8. The aircraft landing gear system model integration method based on MBSE according to claim 1, characterized in that: In step S3, semantic mapping rules between simulation, architecture model and integration service are established according to OSLC specification. OSLC specification is composed of core specification and domain specification. The core specification specifies and describes the core integration concept of OSLC specification and the common features supported by OSLC service. The OSLC core model includes service provider catalog, service providers, services, and resources; Based on the core model and semantic mapping rules of OSLC, an information transfer path is built between the architecture and simulation model to achieve semantic consistency and interoperability between different tools and models.

9. The aircraft landing gear system model integration method based on MBSE according to claim 1, characterized in that: In step S3, the simulation model is analyzed to obtain the model structure, model parameters and the operation interface of adding, deleting, modifying and checking the Simulink model, so as to ensure that the model data can be smoothly integrated; After the simulation model data is successfully parsed, the reading and modification of the simulation model data is realized, and the simulation model data can be correctly mapped according to the semantic mapping rules.

10. The aircraft landing gear system model integration method based on MBSE according to claim 1, characterized in that: In step S4, according to the semantic mapping rules and data parsing technology, a Simulink tool integration adapter is constructed to perform operation services such as adding, deleting, modifying and checking the meta-models such as models, subsystems and modules in the simulation model, so as to realize the formal representation of the simulation model information, and then realize the two-way transmission of cross-domain information, and realize the interoperability between different domain models in heterogeneous tools; The Simulink tool integration adapter is the tool implementation carrier of the OSLC core model and semantic mapping rules.

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