Aircraft digital twin model integrated development method

Abstract

The invention belongs to the field of digital simulation modeling, and relates to an aircraft digital twin model integrated development method. The method comprises the following steps: S1, determining a digital twinborn model construction strategy in each application scene: dividing an equipment system of an aircraft into a control part and a controlled object part, and establishing various digital twinborn configurations of virtual-real combination of the control part and the controlled object part according to a virtual-real combined digital twinborn modeling method; s2, multiplexing the physical architecture of the equipment system, and generating a multidisciplinary simulation architecture in an application scene; s3, performing mechanism, data or mechanism and data fused digital twin model construction on each simulation unit in the equipment system; and S4, performing integration, configuration and joint simulation on the digital twin model of each simulation unit by constructing a multidisciplinary joint simulation flexible framework. According to the method, the complexity of multidisciplinary digital twin model integration is reduced, and the dynamic adjustment efficiency of the simulation architecture in each development stage is improved.

Description

Technical Field

[0001] The present application relates to the field of digital simulation modeling, and in particular to an integrated development method for an aircraft digital twin model. Background Art

[0002] At present, modeling and simulation methods are widely used in aircraft development to carry out design selection, scheme trade-offs and design verification. However, the existing modeling methods are mainly mechanism modeling, and are mainly used for modeling and simulation of a single discipline or process. The confidence of simulation models for complex multidisciplinary problems is low, the simulation model interfaces of various components are not unified, the joint simulation lacks configuration control, and the dynamic adjustment efficiency of the simulation architecture at each development stage is low, which makes it difficult to meet the requirements of agile design iteration and multidisciplinary integrated verification of aircraft systems. Summary of the invention

[0003] In order to solve the above problems, this application provides an integrated development method of an aircraft digital twin model, which mainly includes: Step S1, determining the digital twin model construction strategy under each application scenario: dividing the aircraft equipment system into a control part and a controlled object part, and establishing various digital twin configurations of the control part and the controlled object part in a virtual-real combination according to the digital twin modeling method of combining virtual and real; Step S2, reusing the physical architecture of the equipment system to generate a multidisciplinary simulation architecture under the application scenario; Step S3, constructing a digital twin model of mechanism, data, or mechanism and data fusion for each simulation unit in the equipment system; Step S4: By building a multidisciplinary joint simulation flexible framework, the digital twin models of each simulation unit are integrated, configured and jointly simulated.

[0004] Preferably, in step S1, the control part includes an instruction unit and a control unit, and the controlled object part includes an execution unit and a feedback unit, wherein the instruction unit is used to receive an operation instruction input, the control unit is used to convert the operation instruction into a control instruction according to a specified control algorithm, the execution unit is used to drive the actuator to move according to the control instruction, and the feedback unit is used to feedback the operating status of the actuator.

[0005] Preferably, in step S1, various digital twin configurations of virtual and real combinations of the control part and the controlled object part are established, including: Step S11: Determine the framework of the digital twin configuration as follows: M = F (Mc, Mp, Mr, Me); Wherein, M is the digital twin configuration of the aircraft's equipment system, F is the framework function, Mc represents the simulation model of each component of the control part, Mp represents the simulation model of each component of the controlled object part, Mr represents the input and output interface between the components, and Me represents the system operating environment; Among them, Mc=Ψ(Fc(Xc,Yc,Pc),φc); Mp=Ψ(Fp(Xp,Yp,Pp),φp); Wherein, Ψ is the simulation model function, Xc represents the input interface vector of the simulation model of the control part, Yc represents the output interface vector of the simulation model of the control part, Pc represents the adjustable parameter of the simulation model of the control part, Fc represents the proxy model function of the control part, φc represents the transformation logic between the input and output of the simulation model of the control part, Xp represents the input vector of the simulation model of the controlled object part, Yp represents the output vector of the simulation model of the controlled object part, Pp represents the adjustable parameter of the simulation model of the controlled object part, Fp represents the proxy model function of the simulation model of the controlled object part, and φp represents the transformation logic between the input and output of the simulation model of the controlled object part; Step S12: When both the control part and the controlled object part adopt the mechanism modeling algorithm, by adjusting the precision parameters of φc and φp, the mechanism simulation models of the control part and the controlled object are respectively constructed to establish multidisciplinary digital twin configurations with different precisions; when both the control part and the controlled object adopt the data modeling algorithm, by adjusting the precision parameters of φc and φp, the data simulation models of the control part and the controlled object are respectively constructed to establish multidisciplinary digital twin configurations with different precisions; when one part of the control part and the controlled object part adopts the mechanism modeling algorithm and the other part adopts the data modeling algorithm, the digital twin configuration of the equipment system is converted into a multidisciplinary digital twin configuration that integrates virtual and real, and by adjusting the precision parameters of φc and φp, the mechanism simulation model of the control part and the digital simulation model of the controlled object part are respectively constructed to establish multidisciplinary digital twin configurations with different precisions.

[0006] Preferably, step S2 further comprises: Step S21: shielding interfaces in the physical architecture that are irrelevant to the characteristics corresponding to the application scenario, and only publishing physical interfaces related to the application scenario; Step S22, further refining the selected physical interface into simulation variables; Step S23: setting simulation parameters for each simulation unit in the physical architecture.

[0007] Preferably, in step S23, the multidisciplinary simulation framework is dynamically reconstructed by adjusting the simulation parameters.

[0008] Preferably, step S3 further comprises: When the simulation scenario mechanism of the simulation unit is clear and the mechanism simulation calculation efficiency meets the design iteration requirements, the equation-based mechanism modeling method is adopted to establish the digital twin model of the simulation unit; when the simulation scenario mechanism of the simulation unit is unclear, the data-based modeling method is adopted to establish the digital twin model of the simulation unit; when the simulation scenario mechanism of the simulation unit is clear but the mechanism simulation calculation efficiency cannot meet the design iteration requirements, the mechanism and data fusion modeling method is adopted to establish the digital twin model of the simulation unit.

[0009] Preferably, the modeling method of mechanism and data fusion is adopted to establish the digital twin model of the simulation unit, including: When the sample size of the test data is less than the set value, the test data is used to identify and correct the parameters of the mechanism model, a large amount of simulation sample data is generated using the corrected mechanism model, and the digital twin model is established based on the simulation sample data using a fitting algorithm; When the sample size of the test data is not less than the set value, the mechanism model is used to simulate and generate simulation sample data, and the test data and the simulation sample data are fused by multi-source data. Based on the fused data, a fitting algorithm is used to establish the digital twin model.

[0010] Preferably, the multidisciplinary joint simulation flexible framework includes a resource layer, an interface layer, a connection layer, an architecture layer and an application layer from bottom to top, thereby isolating the application layer and the resource layer, standardizing the encapsulation of the digital twin model interface of each simulation unit, and driving the hot plugging of various simulation resources in the multidisciplinary simulation architecture through parameter configuration.

[0011] Preferably, step S4 further comprises: A joint simulation configuration configuration matrix is ​​established, wherein the configuration matrix includes a first variable for characterizing the type change of the digital twin configuration and a second variable for characterizing the accuracy change of the same type of digital twin configuration; by selecting different types of digital twin configurations and the accuracy of the digital twin configurations in the configuration matrix, the integration of the digital twin models of each simulation unit is driven, and according to the preset joint simulation scheduling algorithm, the integrated multidisciplinary digital twin model is driven to carry out simulation.

[0012] This application reduces the complexity of integrating multidisciplinary digital twin models and improves the efficiency of dynamic adjustment of simulation architecture at each development stage. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] Figure 1 It is a flowchart of a preferred embodiment of the aircraft digital twin model integrated development method of the present application.

[0014] Figure 2 This application Figure 1Schematic diagram of the digital twin modeling strategy driven by the mechanism model of the illustrated embodiment.

[0015] Figure 3 This application Figure 1 A schematic diagram of a digital twin modeling strategy driven by a data model in the illustrated embodiment.

[0016] Figure 4 This application Figure 1 A schematic diagram of a digital twin modeling strategy jointly driven by a mechanism model and a data model in the illustrated embodiment.

[0017] Figure 5 This application Figure 1 Schematic diagram of the multidisciplinary joint simulation flexible framework structure of the illustrated embodiment.

[0018] Figure 6 It is a schematic diagram of the structure of the multidisciplinary digital twin distributed joint simulation system solution.

[0019] Figure 7 It is a schematic diagram of information interaction of multidisciplinary digital twin joint simulation system. DETAILED DESCRIPTION

[0020] In order to make the purpose, technical scheme and advantages of the implementation of this application clearer, the technical scheme in the implementation of this application will be described in more detail in combination with the drawings in the implementation of this application. In the drawings, the same or similar reference numerals throughout represent the same or similar elements or elements with the same or similar functions. The described implementation is a part of the implementation of this application, not all of the implementations. The implementation described below with reference to the drawings is exemplary and is intended to be used to explain this application, and cannot be understood as a limitation on this application. Based on the implementation in this application, all other implementations obtained by ordinary technicians in this field without making creative work are within the scope of protection of this application. The implementation of this application is described in detail below in combination with the drawings.

[0021] This application provides an integrated development method for an aircraft digital twin model, such as Figure 1 As shown, it mainly includes: Step S1, determining the digital twin model construction strategy under each application scenario: dividing the aircraft equipment system into a control part and a controlled object part, and establishing various digital twin configurations of the control part and the controlled object part in a virtual-real combination according to the digital twin modeling method of combining virtual and real; Step S2, reusing the physical architecture of the equipment system to generate a multidisciplinary simulation architecture under the application scenario; Step S3, constructing a digital twin model of mechanism, data, or mechanism and data fusion for each simulation unit in the equipment system; Step S4: By building a multidisciplinary joint simulation flexible framework, the digital twin models of each simulation unit are integrated, configured and jointly simulated.

[0022] In step S1, the present application first formulates an integrated development strategy for the aircraft digital twin model, then in step S2, builds a multidisciplinary simulation architecture according to the strategy, in step S3, models each simulation unit in the multidisciplinary simulation architecture, and finally in step S4, integrates and configures each simulation unit to achieve joint simulation.

[0023] In some optional embodiments, in step S1, the control part includes an instruction unit and a control unit, and the controlled object part includes an execution unit and a feedback unit, wherein the instruction unit is used to receive an operation instruction input, the control unit is used to convert the operation instruction into a control instruction according to a specified control algorithm, the execution unit is used to drive the actuator to move according to the control instruction, and the feedback unit is used to feedback the operating status of the actuator.

[0024] In some optional implementations, in step S1, establishing various types of digital twin configurations of virtual and real combinations of the control part and the controlled object part includes: Step S11: Determine the framework of the digital twin configuration as follows: M = F (Mc, Mp, Mr, Me); Among them, M is the digital twin configuration of the aircraft's equipment system, F is the framework function, Mc represents the simulation model of each component of the control part, Mp represents the simulation model of each component of the controlled object part, Mr represents the input and output interface between the components, and this part remains stable when the physical architecture remains unchanged, and Me represents the system operating environment, which is simplified here as two types: non-real-time environment and real-time environment, which is specifically related to the simulation model running operating system and simulation communication protocol.

[0025] Among them, Mc=Ψ(Fc(Xc,Yc,Pc),φc); Mp=Ψ(Fp(Xp,Yp,Pp),φp); Wherein, Ψ is the simulation model function, Xc represents the input interface vector of the simulation model of the control part, Yc represents the output interface vector of the simulation model of the control part, Pc represents the adjustable parameter of the simulation model of the control part, Fc represents the proxy model function of the control part, φc represents the transformation logic between the input and output of the simulation model of the control part, Xp represents the input vector of the simulation model of the controlled object part, Yp represents the output vector of the simulation model of the controlled object part, Pp represents the adjustable parameter of the simulation model of the controlled object part, Fp represents the proxy model function of the simulation model of the controlled object part, and φp represents the transformation logic between the input and output of the simulation model of the controlled object part; Step S12: When both the control part and the controlled object part adopt the mechanism modeling algorithm, by adjusting the precision parameters of φc and φp, the mechanism simulation models of the control part and the controlled object are respectively constructed to establish multidisciplinary digital twin configurations with different precisions; when both the control part and the controlled object adopt the data modeling algorithm, by adjusting the precision parameters of φc and φp, the data simulation models of the control part and the controlled object are respectively constructed to establish multidisciplinary digital twin configurations with different precisions; when one part of the control part and the controlled object part adopts the mechanism modeling algorithm and the other part adopts the data modeling algorithm, the digital twin configuration of the equipment system is converted into a multidisciplinary digital twin configuration that integrates virtual and real, and by adjusting the precision parameters of φc and φp, the mechanism simulation model of the control part and the digital simulation model of the controlled object part are respectively constructed to establish multidisciplinary digital twin configurations with different precisions.

[0026] In this embodiment, in step S21, the stable and unchanged context information in the simulation model under different joint simulation scenarios is hierarchically decoupled from the dynamic and changing specific implementation logic of the simulation model to adapt to the rapid transformation of the joint simulation configuration. To this end, the simulation model Mc of each component of the control part and the simulation model Mp of each component of the controlled object part are further refined, wherein, in the expressions of Mc and Mp, the proxy model function Fc of the control part and the proxy model function Fp of the simulation model of the controlled object part are only related to the input, output and adjustable parameters of the model, and the transformation logic φc and φp are only related to different model implementation algorithms. It can be seen that the equipment system M of the aircraft is only related to the model implementation algorithm (that is, the above-mentioned transformation logic φc and φp) and the system operating environment Me, so that in the subsequent steps, different simulation systems can be rapidly integrated, rapidly configured and flexibly transformed by reusing the joint simulation proxy model and selecting different model implementation algorithms according to the engineering application scenarios. In step S22, when the control part and the controlled object part can both adopt the mechanism modeling algorithm, such as Figure 2 As shown, data modeling algorithms can also be used, such as Figure 3 As shown, it can also be mixed, such as Figure 4 In the above-mentioned multiple embodiments, by adjusting the precision parameters of φc and φp and respectively constructing the data simulation models of the control part and the controlled object, a multidisciplinary digital twin configuration with different precisions can be established.

[0027] In some optional implementations, step S2 further includes: Step S21: shielding interfaces in the physical architecture that are irrelevant to the characteristics corresponding to the application scenario, and only publishing physical interfaces related to the application scenario; Step S22, further refining the selected physical interface into simulation variables; Step S23: setting simulation parameters for each simulation unit in the physical architecture.

[0028] In this embodiment, in step S22, the simulation variables include simulation input variables and simulation output variables, wherein the simulation input variables represent the input values ​​calculated by the simulation unit during the simulation run, and the simulation output variables represent the outputs calculated by the simulation unit during the run, and during a simulation solution, the simulation output variables change with the changes in the simulation input variables. In step S23, the simulation parameters represent the initial data of the simulation unit set before the simulation run begins, and the simulation parameters remain unchanged during a simulation solution, thereby converting the physical architecture of the equipment system into a multidisciplinary simulation architecture under the application scenario.

[0029] In some optional implementations, in step S23, the multidisciplinary simulation framework is dynamically reconstructed by adjusting the simulation parameters.

[0030] In some optional implementations, step S3 further includes: When the simulation scenario mechanism of the simulation unit is clear and the mechanism simulation calculation efficiency meets the design iteration requirements, the equation-based mechanism modeling method is adopted to establish the digital twin model of the simulation unit; when the simulation scenario mechanism of the simulation unit is unclear, the data-based modeling method is adopted to establish the digital twin model of the simulation unit; when the simulation scenario mechanism of the simulation unit is clear but the mechanism simulation calculation efficiency cannot meet the design iteration requirements, the mechanism and data fusion modeling method is adopted to establish the digital twin model of the simulation unit.

[0031] In some optional implementations, the modeling method of mechanism and data fusion is adopted to establish the digital twin model of the simulation unit, including: When the sample size of the test data is less than the set value, the test data is used to identify and correct the parameters of the mechanism model, a large amount of simulation sample data is generated using the corrected mechanism model, and the digital twin model is established based on the simulation sample data using a fitting algorithm; When the sample size of the test data is not less than the set value, the mechanism model is used to simulate and generate simulation sample data, and the test data and the simulation sample data are fused by multi-source data. Based on the fused data, a fitting algorithm is used to establish the digital twin model.

[0032] In some optional embodiments, the multidisciplinary joint simulation flexible framework includes a resource layer, an interface layer, a connection layer, an architecture layer and an application layer from bottom to top, thereby isolating the application layer and the resource layer, standardizing the encapsulation of the digital twin model interface of each simulation unit, and driving the hot plugging of various simulation resources in the multidisciplinary simulation architecture through parameter configuration.

[0033] refer to Figure 5In this embodiment, a cloud architecture and a DDS communication method are used to establish a distributed flexible simulation architecture with hierarchical decoupling. At the resource layer, virtual machine technology is used to virtualize each simulation node and establish a dynamically adjustable simulation resource pool. The digital twin model of a specific node can be dynamically distributed to the corresponding simulation node for calculation; at the interface layer, the FMI standard is used to standardize and encapsulate the digital twin model interface of each simulation unit, shield the differences in the interfaces of different simulation software models, and drive the hot plugging of various simulation resources in the simulation architecture through parameter configuration; at the connection layer, a data-centric DDS data exchange network is established, and the input and output variables of each simulation link are uniformly named according to a unique name. The data mapping relationship of each simulation link is established through name matching, and data communication is carried out between each simulation link and the DDS service; at the architecture layer, the configuration and ICD interface management of digital twin models of different disciplines such as machinery, hydraulics, electricity, and fuel are carried out through the simulation proxy model; at the application layer, the configuration of the multi-disciplinary digital twin model is completed.

[0034] The configuration of the application layer mainly depends on the joint simulation configuration matrix. For example, in some optional implementations, step S4 further includes: A joint simulation configuration configuration matrix is ​​established, wherein the configuration matrix includes a first variable for characterizing the type change of the digital twin configuration and a second variable for characterizing the accuracy change of the same type of digital twin configuration; by selecting different types of digital twin configurations and the accuracy of the digital twin configurations in the configuration matrix, the integration of the digital twin models of each simulation unit is driven, and according to the preset joint simulation scheduling algorithm, the integrated multidisciplinary digital twin model is driven to carry out simulation.

[0035] like Figure 6 As shown in the figure, according to the configuration matrix, through the configuration of the simulation configuration, the rapid combination and model integration of the digital twin models of each simulation unit are driven to establish a multidisciplinary digital twin model of the aircraft, and the digital twin models of different links are distributed to different simulation resource nodes; according to Figure 7 The scheduling algorithm shown drives the integrated multidisciplinary digital twin model to carry out simulation. Before the simulation starts, the simulation master node calls the FMU (Functional Mock-up Unit) programs of the four slave nodes through remote services to initialize the variable parameters of the simulation models of each node, and then starts the simulation; in the solution calculation process of each step, the master control node calls each slave node through remote services to carry out the current step solution, and each node FMU unit independently executes the current step solution, and then obtains the calculation results of each FMU unit according to the communication step agreed upon in the joint simulation, and sets the input of the next step calculation to the corresponding FMU unit according to the input and output rules specified by the ICD interface, and calls the FMU unit to execute the next step solution, and the cycle is executed until the end of the simulation.

[0036] The advantages of this application are: for the multidisciplinary digital twin simulation and verification process of aircraft, the digital twin method of mechanism and data fusion is used to explain the digital twin model planning, development and integration configuration process, including the unified modeling framework of multidisciplinary digital twin of aircraft, the digital twin development method driven by mechanism and data, and the multidisciplinary digital twin model integration and configuration method. It is the first time to propose a multidisciplinary digital twin configuration configuration method and model development method for aircraft driven by mechanism and data, which solves the contradiction between the accuracy and efficiency of the multidisciplinary digital twin model of aircraft, the difficulty in integrating the multidisciplinary digital twin model, and the low efficiency of dynamic adjustment of the simulation architecture in each development stage. It can support the agile design iteration and multidisciplinary integration verification of the aircraft system, and is in line with actual engineering applications.

[0037] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. A method for integrated development of an aircraft digital twin model, characterized in that: include: Step S1, determining the digital twin model construction strategy under each application scenario: dividing the aircraft equipment system into a control part and a controlled object part, and establishing various digital twin configurations of the control part and the controlled object part in a virtual-real combination according to the digital twin modeling method of combining virtual and real; Step S2, reusing the physical architecture of the equipment system to generate a multidisciplinary simulation architecture under the application scenario; Step S3, constructing a digital twin model of mechanism, data, or mechanism and data fusion for each simulation unit in the equipment system; Step S4: By building a multidisciplinary joint simulation flexible framework, the digital twin models of each simulation unit are integrated, configured and jointly simulated.

2. The aircraft digital twin model integrated development method according to claim 1, characterized in that: In step S1, the control part includes an instruction unit and a control unit, and the controlled object part includes an execution unit and a feedback unit, wherein the instruction unit is used to receive an operation instruction input, the control unit is used to convert the operation instruction into a control instruction according to a specified control algorithm, the execution unit is used to drive the actuator to move according to the control instruction, and the feedback unit is used to feedback the operating status of the actuator.

3. The aircraft digital twin model integrated development method according to claim 1, characterized in that: In step S1, various digital twin configurations of virtual and real combinations of the control part and the controlled object part are established, including: Step S11: Determine the framework of the digital twin configuration as follows: M = F (Mc, Mp, Mr, Me); Wherein, M is the digital twin configuration of the aircraft's equipment system, F is the framework function, Mc represents the simulation model of each component of the control part, Mp represents the simulation model of each component of the controlled object part, Mr represents the input and output interface between the components, and Me represents the system operating environment; Among them, Mc=Ψ(Fc(Xc,Yc,Pc),φc); Mp=Ψ(Fp(Xp,Yp,Pp),φp); Wherein, Ψ is the simulation model function, Xc represents the input interface vector of the simulation model of the control part, Yc represents the output interface vector of the simulation model of the control part, Pc represents the adjustable parameter of the simulation model of the control part, Fc represents the proxy model function of the control part, φc represents the transformation logic between the input and output of the simulation model of the control part, Xp represents the input vector of the simulation model of the controlled object part, Yp represents the output vector of the simulation model of the controlled object part, Pp represents the adjustable parameter of the simulation model of the controlled object part, Fp represents the proxy model function of the simulation model of the controlled object part, and φp represents the transformation logic between the input and output of the simulation model of the controlled object part; Step S12: When both the control part and the controlled object part adopt the mechanism modeling algorithm, by adjusting the precision parameters of φc and φp, the mechanism simulation models of the control part and the controlled object are respectively constructed to establish multidisciplinary digital twin configurations with different precisions; when both the control part and the controlled object adopt the data modeling algorithm, by adjusting the precision parameters of φc and φp, the data simulation models of the control part and the controlled object are respectively constructed to establish multidisciplinary digital twin configurations with different precisions; when one part of the control part and the controlled object part adopts the mechanism modeling algorithm and the other part adopts the data modeling algorithm, the digital twin configuration of the equipment system is converted into a multidisciplinary digital twin configuration that integrates virtual and real, and by adjusting the precision parameters of φc and φp, the mechanism simulation model of the control part and the digital simulation model of the controlled object part are respectively constructed to establish multidisciplinary digital twin configurations with different precisions.

4. The aircraft digital twin model integrated development method according to claim 1, characterized in that: Step S2 further comprises: Step S21: shielding interfaces in the physical architecture that are irrelevant to the characteristics corresponding to the application scenario, and only publishing physical interfaces related to the application scenario; Step S22, further refining the selected physical interface into simulation variables; Step S23: setting simulation parameters for each simulation unit in the physical architecture.

5. The aircraft digital twin model integrated development method according to claim 4, characterized in that: In step S23, the multidisciplinary simulation framework is dynamically reconstructed by adjusting the simulation parameters.

6. The aircraft digital twin model integrated development method according to claim 1, characterized in that: Step S3 further comprises: When the simulation scenario mechanism of the simulation unit is clear and the mechanism simulation calculation efficiency meets the design iteration requirements, the equation-based mechanism modeling method is adopted to establish the digital twin model of the simulation unit; when the simulation scenario mechanism of the simulation unit is unclear, the data-based modeling method is adopted to establish the digital twin model of the simulation unit; when the simulation scenario mechanism of the simulation unit is clear but the mechanism simulation calculation efficiency cannot meet the design iteration requirements, the mechanism and data fusion modeling method is adopted to establish the digital twin model of the simulation unit.

7. The aircraft digital twin model integrated development method according to claim 6, characterized in that: The modeling method of mechanism and data fusion is adopted to establish the digital twin model of the simulation unit, including: When the sample size of the test data is less than the set value, the test data is used to identify and correct the parameters of the mechanism model, a large amount of simulation sample data is generated using the corrected mechanism model, and the digital twin model is established based on the simulation sample data using a fitting algorithm; When the sample size of the test data is not less than the set value, the mechanism model is used to simulate and generate simulation sample data, and the test data and the simulation sample data are fused by multi-source data. Based on the fused data, a fitting algorithm is used to establish the digital twin model.

8. The aircraft digital twin model integrated development method according to claim 1, characterized in that: The multidisciplinary joint simulation flexible framework includes a resource layer, an interface layer, a connection layer, an architecture layer and an application layer from bottom to top, thereby isolating the application layer and the resource layer, standardizing the encapsulation of the digital twin model interface of each simulation unit, and driving the hot plugging of various simulation resources in the multidisciplinary simulation architecture through parameter configuration.

9. The aircraft digital twin model integrated development method according to claim 1, characterized in that: Step S4 further comprises: A joint simulation configuration matrix is ​​established, wherein the configuration matrix includes a first variable for characterizing the type change of the digital twin configuration and a second variable for characterizing the accuracy change of the same type of digital twin configuration; by selecting different types of digital twin configurations and the accuracy of the digital twin configurations in the configuration matrix, the integration of the digital twin models of each simulation unit is driven, and according to the preset joint simulation scheduling algorithm, the integrated multidisciplinary digital twin model is driven to carry out simulation.

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