An integrated development method for the digital twin model of an aircraft

Abstract

This application belongs to the field of digital simulation modeling and relates to a method for integrated development of an aircraft digital twin model. The method includes: Step S1, determining the digital twin model construction strategy for each application scenario as: dividing the equipment system of the aircraft into a control part and a controlled object part, and establishing various digital twin configurations of the virtual-real combination of the control part and the controlled object part according to the virtual-real combined digital twin modeling method; Step S2, reusing the physical architecture of the equipment system to generate a multi-disciplinary simulation architecture for the application scenario; Step S3, constructing digital twin models for each simulation unit in the equipment system through mechanism, data, or a combination of mechanism and data; Step S4, integrating, configuring, and jointly simulating the digital twin models of each simulation unit by constructing a multi-disciplinary joint simulation flexible framework. This application reduces the complexity of the integration of multi-disciplinary digital twin models and improves the dynamic adjustment efficiency of the simulation architecture in each development stage.

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:

[0004] 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;

[0005] Step S2, reusing the physical architecture of the equipment system to generate a multidisciplinary simulation architecture under the application scenario;

[0006] Step S3, constructing a digital twin model of mechanism, data, or mechanism and data fusion for each simulation unit in the equipment system;

[0007] Step S4: By building a multidisciplinary joint simulation flexible framework, the digital twin models of each simulation unit are integrated, configured and jointly simulated.

[0008] 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.

[0009] 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:

[0010] Step S11: Determine the framework of the digital twin configuration as follows:

[0011] M = F (Mc, Mp, Mr, Me);

[0012] Wherein, M is the digital twin configuration of the equipment system of the aircraft, F is the framework function, Mc represents the simulation models of the various components of the control part, Mp represents the simulation models of the various components of the controlled object part, Mr represents the input / output interfaces between the components, and Me represents the system operating environment;

[0013] Wherein, Mc = Ψ(Fc(Xc, Yc, Pc), φc); Mp = Ψ(Fp(Xp, Yp, Pp), φp);

[0014] 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 parameters of the simulation model of the control part, Fc represents the surrogate model function of the control part, φc represents the conversion 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 parameters of the simulation model of the controlled object part, Fp represents the surrogate model function of the simulation model of the controlled object part, and φp represents the conversion logic between the input and output of the simulation model of the controlled object part;

[0015] Step S12: When both the control part and the controlled object part adopt the mechanism modeling algorithm, by adjusting the accuracy parameters of φc and φp, respectively construct the mechanism simulation models of the control part and the controlled object to establish multi-disciplinary digital twin configurations with different accuracies; when both the control part and the controlled object adopt the data modeling algorithm, by adjusting the accuracy parameters of φc and φp, respectively construct the data simulation models of the control part and the controlled object to establish multi-disciplinary digital twin configurations with different accuracies; when one of the control part and the controlled object part adopts the mechanism modeling algorithm and the other adopts the data modeling algorithm, the digital twin configuration of the equipment system is transformed into a virtual-real fusion multi-disciplinary digital twin configuration, and by adjusting the accuracy parameters of φc and φp, respectively construct the mechanism simulation model of the control part and the digital simulation model of the controlled object part to establish multi-disciplinary digital twin configurations with different accuracies.

[0016] Preferably, step S2 further includes:

[0017] Step S21: Shield the interfaces in the physical architecture that are irrelevant to the characteristics corresponding to the application scenario, and only publish the physical interfaces related to the application scenario externally;

[0018] Step S22: Further refine the selected physical interfaces into simulation variables;

[0019] Step S23: Set simulation parameters for each simulation unit in the physical architecture.

[0020] Preferably, in step S23, by adjusting the simulation parameters, the multidisciplinary simulation architecture is dynamically reconstructed.

[0021] Preferably, step S3 further includes:

[0022] When the simulation scenario mechanism of the simulation unit is clear and the mechanism simulation calculation efficiency meets the design iteration requirements, an equation-based mechanism modeling method is used to establish the digital twin model of the simulation unit; when the simulation scenario mechanism of the simulation unit is unclear, a data-based modeling method is used 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, a mechanism and data fusion modeling method is used to establish the digital twin model of the simulation unit.

[0023] Preferably, using the mechanism and data fusion modeling method to establish the digital twin model of the simulation unit includes:

[0024] 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, and a large number of simulation sample data are generated by using the corrected mechanism model. Based on the simulation sample data, a fitting algorithm is used to establish the digital twin model;

[0025] 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, the test data and the simulation sample data are fused with multi-source data, and based on the fused data, a fitting algorithm is used to establish the digital twin model.

[0026] Preferably, the multidisciplinary joint simulation flexible framework sequentially includes a resource layer, an interface layer, a connection layer, an architecture layer, and an application layer from bottom to top, so as to isolate the application layer and the resource layer, standardize and encapsulate the digital twin model interfaces of each simulation unit, and drive the hot plugging of various simulation resources in the multidisciplinary simulation architecture through parameter configuration.

[0027] Preferably, step S4 further includes:

[0028] A joint simulation configuration matrix is established, and 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 configuration 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.

[0029] This application reduces the complexity of the integration of multidisciplinary digital twin models and improves the efficiency of dynamic adjustment of the simulation architecture in each development stage. Description of the Drawings

[0030] Figure 1 is a flowchart of a preferred embodiment of the method for integrated development of the aircraft digital twin model of this application.

[0031] Figure 2 is this application Figure 1 Schematic diagram of the digital twin modeling strategy driven by the mechanism model in the illustrated embodiment.

[0032] Figure 3 is this application Figure 1 Schematic diagram of the digital twin modeling strategy driven by the data model in the illustrated embodiment.

[0033] Figure 4 is this application Figure 1 Schematic diagram of the digital twin modeling strategy jointly driven by the mechanism model and the data model in the illustrated embodiment.

[0034] Figure 5 is this application Figure 1 Schematic diagram of the flexible framework structure of the multidisciplinary joint simulation in the illustrated embodiment.

[0035] Figure 6 is a schematic diagram of the structure of the multidisciplinary digital twin distributed joint simulation system solution.

[0036] Figure 7 is a schematic diagram of the information interaction of the multidisciplinary digital twin joint simulation system. Detailed Embodiment

[0037] To make the purpose, technical solutions, and advantages of the implementation of this application clearer, the technical solutions in the implementation manners of this application will be described in more detail below with reference to the accompanying drawings in the implementation manners of this application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions from beginning to end. The described implementation manners are part of the implementation manners of this application, rather than all of the implementation manners. The implementation manners described below with reference to the accompanying drawings are exemplary and are intended to explain this application and should not be construed as limiting this application. Based on the implementation manners in this application, all other implementation manners obtained by those of ordinary skill in the art without creative efforts belong to the scope of protection of this application. The implementation manners of this application will be described in detail below with reference to the accompanying drawings.

[0038] This application provides a method for integrated development of an aircraft digital twin model, as Figure 1 shown, mainly including:

[0039] Step S1. Determine the digital twin model construction strategy for each application scenario as follows: Divide the equipment system of the aircraft into a control part and a controlled object part, and establish various digital twin configurations of the virtual-real combination of the control part and the controlled object part according to the virtual-real combined digital twin modeling method.

[0040] Step S2. Reuse the physical architecture of the equipment system to generate a multidisciplinary simulation architecture for the application scenario.

[0041] Step S3. Build digital twin models for each simulation unit in the equipment system through mechanism, data, or a combination of mechanism and data.

[0042] Step S4. Integrate, configure, and conduct joint simulation on the digital twin models of each simulation unit by constructing a multidisciplinary joint simulation flexible framework.

[0043] In this application, in Step S1, first formulate the integrated development strategy for the digital twin model of the aircraft, then in Step S2, build a multidisciplinary simulation architecture according to the strategy, in Step S3, model each simulation unit in the multidisciplinary simulation architecture, and finally in Step S4, integrate and configure each simulation unit to achieve joint simulation.

[0044] In some optional implementation manners, 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. Among them, the instruction unit is used to receive 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 state of the actuator.

[0045] In some optional implementation manners, in Step S1, establishing various digital twin configurations of the virtual-real combination of the control part and the controlled object part includes:

[0046] Step S11. Determine the framework of the digital twin configuration as:

[0047] M = F(Mc, Mp, Mr, Me);

[0048] Where M is the digital twin configuration of the equipment system of the aircraft, F is the framework function, Mc represents the simulation models of each component of the control part, Mp represents the simulation models of each component of the controlled object part, Mr represents the input-output interfaces between components, which is stable and unchanged when the physical architecture remains the same, and Me represents the system operating environment, which is simplified here as two types: non-real-time environment and real-time environment, and is specifically related to the operating system of the simulation model and the simulation communication protocol.

[0049] where, Mc = Ψ(Fc(Xc, Yc, Pc), φc); Mp = Ψ(Fp(Xp, Yp, Pp), φp);

[0050] where, Ψ is a 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 surrogate model function of the control part, φc represents the conversion 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 surrogate model function of the simulation model of the controlled object part, and φp represents the conversion logic between the input and output of the simulation model of the controlled object part;

[0051] 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, respectively construct the mechanism simulation models of the control part and the controlled object 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, respectively construct the data simulation models of the control part and the controlled object to establish multidisciplinary digital twin configurations with different precisions; when one of the control part and the controlled object part adopts the mechanism modeling algorithm and the other adopts the data modeling algorithm, the digital twin configuration of the equipment system is transformed into a virtual-real fusion multidisciplinary digital twin configuration. By adjusting the precision parameters of φc and φp, respectively construct the mechanism simulation model of the control part and the digital simulation model of the controlled object part to establish multidisciplinary digital twin configurations with different precisions.

[0052] In this embodiment, in step S21, the context information that remains stable in the simulation model under different co-simulation scenarios and the specific implementation logic of the dynamically changing simulation model are decoupled hierarchically to adapt to the rapid transformation of the co-simulation configuration. To this end, the simulation models Mc of the components in the control part and the simulation models Mp of the components in the controlled object part are further refined. Among them, in the expressions of Mc and Mp, the surrogate model functions Fc of the control part and the surrogate model functions Fp of the simulation models of the controlled object part are only related to the inputs, outputs, and adjustable parameters of the models, and the transformation logics 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 algorithms (i.e., the above transformation logics φc and φp) and the system operating environment Me. Thus, in subsequent steps, different simulation systems can be quickly integrated, configured, and flexibly transformed by reusing the co-simulation surrogate model and selecting different model implementation algorithms according to the engineering application scenarios. In step S22, when both the control part and the controlled object part can adopt mechanism modeling algorithms, as Figure 2 shown, or they can both adopt data modeling algorithms, as Figure 3 shown, or they can be used in combination, as Figure 4 shown. In the above-mentioned multiple embodiments, by adjusting the accuracy parameters of φc and φp, data simulation models of the control part and the controlled object are respectively constructed, and multidisciplinary digital twin configurations with different accuracies can be established.

[0053] In some alternative embodiments, step S2 further includes:

[0054] Step S21: Shield the interfaces in the physical architecture that are irrelevant to the characteristics corresponding to the application scenario, and only publish the physical interfaces related to the application scenario externally;

[0055] Step S22: Further refine the selected physical interfaces into simulation variables;

[0056] Step S23: Set simulation parameters for each simulation unit in the physical architecture.

[0057] In this embodiment, in step S22, the simulation variables include simulation input variables and simulation output variables. The simulation input variables represent the input values calculated by the simulation unit during simulation operation, and the simulation output variables represent the outputs calculated by the simulation unit during operation. During a simulation solution process, the simulation output variables change with the change of the simulation input variables. In step S23, the simulation parameters represent the initial data of the simulation unit set before the start of the simulation operation, and the simulation parameters remain unchanged during a simulation solution process, thereby transforming the physical architecture of the equipment system into a multidisciplinary simulation architecture under the application scenario.

[0058] In some alternative embodiments, in step S23, the multidisciplinary simulation architecture is dynamically reconfigured by adjusting the simulation parameters.

[0059] In some alternative embodiments, step S3 further includes:

[0060] When the simulation scenario mechanism of the simulation unit is clear and the mechanism simulation calculation efficiency meets the design iteration requirements, an equation-based mechanism modeling method is used to establish the digital twin model of the simulation unit; when the simulation scenario mechanism of the simulation unit is not clear, a data-based modeling method is used 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, a mechanism and data fusion modeling method is used to establish the digital twin model of the simulation unit.

[0061] In some alternative embodiments, using the mechanism and data fusion modeling method to establish the digital twin model of the simulation unit includes:

[0062] 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, and a large number of simulation sample data are generated using the corrected mechanism model. Based on the simulation sample data, a fitting algorithm is used to establish the digital twin model;

[0063] 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, the test data and the simulation sample data are subjected to multi-source data fusion, and based on the fusion data, a fitting algorithm is used to establish the digital twin model.

[0064] In some alternative embodiments, the multidisciplinary joint simulation flexible framework sequentially includes a resource layer, an interface layer, a connection layer, an architecture layer, and an application layer from bottom to top, so as to isolate the application layer and the resource layer, standardize and encapsulate the digital twin model interfaces of each simulation unit, and drive the hot plugging of various simulation resources in the multidisciplinary simulation architecture through parameter configuration.

[0065] Reference Figure 5, in this embodiment, a cloud architecture and a DDS communication method are adopted to establish a hierarchical and decoupled distributed flexible simulation architecture. At the resource layer, virtual machine technology is used to virtualize each simulation node, and a dynamically adjustable simulation resource pool is established. The digital twin models of specific nodes can be dynamically distributed to the corresponding simulation nodes for calculation. At the interface layer, the FMI standard is used to standardize and encapsulate the digital twin model interfaces of each simulation unit, shielding the differences in the model interfaces of different simulation software, and driving the hot plugging of various simulation resources in the simulation architecture through parameter configuration. At the connection layer, a DDS data exchange network centered on data is established. The input and output variables of each simulation link are uniformly named according to a unique name, and the data mapping relationship of each simulation link is established through name matching. Data communication is carried out between each simulation link and the DDS service. At the architecture layer, through the simulation agent model, the configuration of digital twin models in different disciplines such as mechanical, hydraulic, electrical, and fuel, and the ICD interface management are carried out. At the application layer, the configuration of multi-disciplinary digital twin models is completed.

[0066] The configuration of the application layer mainly depends on the co-simulation configuration matrix. For example, in some alternative embodiments, step S4 further includes:

[0067] Establish a co-simulation configuration matrix, where the configuration matrix includes a first variable used to represent the type change of the digital twin configuration and a second variable used to represent the accuracy change of the same type of digital twin configuration; by selecting different types of digital twin configurations in the configuration matrix and the accuracy selection of the digital twin configuration, drive the integration of the digital twin models of each simulation unit, and drive the integrated multi-disciplinary digital twin model to carry out simulation according to a preset co-simulation scheduling algorithm.

[0068] As Figure 6 shown, according to the configuration matrix, through the configuration of the simulation configuration, drive the rapid combination and model integration of the digital twin models of each simulation unit, establish an aircraft multi-disciplinary digital twin model, and distribute the digital twin models of different links to different simulation resource nodes; according to Figure 7The scheduling algorithm shown drives the integrated multidisciplinary digital twin model to conduct simulations. Before the simulation starts, the simulation master node initializes the variable parameters of the simulation models of each node by remotely invoking the FMU (Functional Mock-up Unit) programs of the four slave nodes through remote services, and then starts the simulation. During the solution calculation process of each time step, the master control node invokes each slave node to conduct the solution of the current time step through remote services. The FMU unit of each node independently executes the solution of the current time step, and then obtains the calculation results of each FMU unit according to the communication time step agreed upon in the co-simulation. The input for the next time step calculation is set to the corresponding FMU unit according to the input-output rules specified in the ICD interface, and the FMU unit is called to execute the solution of the next time step, and so on until the simulation ends.

[0069] The advantages of this application are as follows: For the process of multidisciplinary digital twin simulation verification of aircraft, a digital twin method integrating mechanism and data is adopted to describe the process of digital twin model planning, development, and integrated configuration, including the unified modeling framework for aircraft multidisciplinary digital twins, the digital twin development method driven by mechanism and data, and the integrated and configuration methods for multidisciplinary digital twin models. For the first time, a configuration method and a model development method for aircraft multidisciplinary digital twins driven by mechanism and data are proposed, which solve the contradictions between the accuracy and efficiency of aircraft multidisciplinary digital twin models, the difficulties in integrating multidisciplinary digital twin models, and the low efficiency of dynamic adjustment of simulation architectures in each development stage. It can support the agile design iteration and multidisciplinary integrated verification of aircraft systems and is in line with engineering practical applications.

[0070] As described above, the above are only the specific implementation manners of this application, but the protection scope of this application is not limited thereto. Any changes or substitutions that can be easily thought of by those skilled in the art within the technical scope disclosed in this application should be covered within the protection scope of this application. Therefore, the protection scope of this application should be subject to the protection scope of the claimed rights.

Claims

1. A method for integrated development of an aircraft digital twin model, characterized in that: include: Step S1, determining the digital twin model strategy under each application scenario: including dividing the equipment system of the aircraft 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: Integrate, configure and jointly simulate the digital twin models of each simulation unit by building a multidisciplinary joint simulation flexible framework; 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; 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.

2. 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.

3. The aircraft digital twin model integrated development method according to claim 2, characterized in that: In step S23, the multidisciplinary simulation framework is dynamically reconstructed by adjusting the simulation parameters.

4. 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.

5. The aircraft digital twin model integrated development method according to claim 4, 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.

6. 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.

7. The aircraft digital twin model integrated development method according to claim 1, characterized in that: 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.

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