Aero-engine virtual test method and system based on digital twinning

Abstract

The invention provides an aero-engine virtual test method and system based on digital twinning, and relates to the technical field of aero-engine virtual tests.The method comprises the steps that flight envelope data of different models of aero-engines are input respectively, and flight envelope data model modeling is conducted on the different models of aero-engines; inputting various engine subject models of different types of aero-engines respectively, and performing aero-engine twin model modeling on the different types of aero-engines respectively; respectively inputting various rack subject models of different types of test racks, and respectively modeling test rack twinborn models for the different types of racks; according to the flight envelope data model, the aero-engine twinborn model and the test bench twinborn model, performing an aero-engine digital virtual test; and performing multi-dimensional analysis and display on the data of the whole process of the digital virtual test. The method has the advantages that virtual-real complementation is achieved, the process is clearer, and the test is more comprehensive and reliable.

Description

Technical Field

[0001] The present invention relates to the technical field of virtual testing of aero - engines, and more particularly, to a method and system for virtual testing of aero - engines based on digital twin. Background Art

[0002] During the stages of engineering development, design validation, and production validation of aero - engines, it is necessary to conduct various types of tests with high complexity and diversity on the physical aero - engines to verify whether the various indicators of the aero - engines meet the design requirements.

[0003] The tests in the stages of engineering development and design validation are particularly numerous. For example, aero - engine component tests (including inlet duct tests, compressor tests, combustion chamber tests, afterburner tests, nozzle tests, accessory tests, and strength and vibration tests of parts and components, etc.), aero - engine whole - machine tests (including whole - machine ground tests, altitude simulation tests, environmental tests, and flight tests, etc.). Traditional physical tests of aero - engines have problems such as a small number of measurement points, inability to measure in some parts, invisibility of flow lines and separations, and unclear analysis of dynamic changes. Moreover, traditional physical tests of aero - engines consume a huge amount of time, resources, and physical aero - engines, which is not conducive to the rapid, efficient, and high - quality design, research, development, production, and manufacturing of aero - engines.

[0004] Therefore, it is necessary to optimize the test method of aero - engines to achieve a test that combines virtual and physical aspects, with a clearer, more comprehensive, and reliable process. Summary of the Invention

[0005] The purpose of the present invention is to provide a method and system for virtual testing of aero - engines based on digital twin, which can achieve a test that combines virtual and physical aspects, with a clearer, more comprehensive, and reliable process.

[0006] The present invention is achieved through the following technical solutions: A method for virtual testing of aero - engines based on digital twin, comprising the following steps: Input the flight envelope data of different models of aero - engines respectively, and build a flight envelope data model for different models of aero - engines; Input various engine discipline models of different models of aero - engines respectively, where the engine discipline models include the thermodynamic model, structural mechanics model, acoustic model, and environmental model of the generator, and build an aero - engine twin model for different models of aero - engines; Input various test bench discipline models of different types of test benches respectively, where the test bench discipline models include the thermodynamic model, structural mechanics model, acoustic model, and environmental model of the test bench, and build a test bench twin model for different types of test benches; Conduct digital virtual tests on aero - engines based on the flight envelope data model, the aero - engine twin model, and the test bench twin model; Conduct multi - dimensional analysis and display of the data throughout the digital virtual test process, and perform comparative fitting analysis based on the historical test data of aero - engines, the in - field operation data of aero - engine physical objects, and the results of digital virtual tests.

[0007] Preferably, the method for modeling the flight envelope data model is as follows: Import and convert the formats of the flight envelope data in different formats, and display the flight envelope data in a graphical form; Manage the flight envelope data item - by - item according to different models of aero - engines; Perform modeling encapsulation of the flight envelope data model and configure the data interaction interface of the data model.

[0008] Preferably, the method for modeling the aero - engine twin model is as follows: Import and verify multiple disciplinary models of different models of aero - engines, and then manage the disciplinary models item - by - item according to different models of aero - engines; Construct the aero - engine twin model according to the corresponding mechanism principle of the aero - engine, configure the information flow and energy flow between multiple disciplinary models of the aero - engine, and configure the interaction interface of the aero - engine twin model.

[0009] Preferably, the method for modeling the test bench twin model is as follows: Import and verify multiple disciplinary models of different types of test benches, and then manage the disciplinary models item - by - item according to different types of test benches; Construct the test bench twin model according to the corresponding mechanism principle of the test bench, configure the information flow and energy flow between multiple disciplinary models of the test bench, and configure the interaction interface of the test bench twin model.

[0010] Preferably, the method for conducting digital virtual tests on aero - engines is as follows: Create digital virtual test projects for different models of aero - engines; Retrieve and select the required flight envelope data model, the aero - engine twin model, and the test bench twin model, and import them into the digital virtual test project; For the flight envelope data model, the aero - engine twin model, and the test bench twin model, configure the information flow and energy flow between the models according to the data interaction mechanism between the models and the defined model interaction interface; Configure the test project parameters; Generate simulation scheduling tasks and drive the flight envelope data model, the aero-engine twin model, and the test bench twin model to perform simulations; Monitor the data interaction of information flow and energy flow between models, monitor the process of model scheduling and execution, and obtain and store the monitoring data; Through the parameter configuration adjustment interface panel of the aero-engine twin model, configure and adjust the aero-engine twin model and its parameters.

[0011] Preferably, the test engineering parameters include test duration and number of tests.

[0012] Preferably, the method for comparative fitting analysis based on aero-engine historical test data, aero-engine in-service field operation data, and digital virtual test results is as follows: Perform itemized classification management on the aero-engine historical test data and the aero-engine in-service field operation data of different models of aero-engines, and perform visual display; Obtain the result data of the aero-engine digital virtual test of the current test model, perform feature analysis and annotation, and perform graphic and text visual display; According to the data feature analysis and annotation results, select corresponding data from the aero-engine historical test data and the aero-engine in-service field operation data for comparative fitting analysis.

[0013] Preferably, the method for selecting corresponding data for comparative fitting analysis is as follows: Under the condition of the same flight envelope data, perform data curve comparative fitting on the aero-engine historical test data and the aero-engine in-service field operation data.

[0014] Preferably, the flight envelope data includes flight speed, flight altitude, overload, and ambient temperature.

[0015] The present invention also provides a digital-twin-based aero-engine virtual test system, which is applied to the above-mentioned digital-twin-based aero-engine virtual test method, and includes: A flight envelope data model module, which is used to respectively input the flight envelope data of different models of aero-engines and build flight envelope data models for different models of aero-engines; An aero-engine twin model module, which is used to respectively input various engine discipline models of different models of aero-engines. The engine discipline models include the thermodynamic model, structural mechanics model, acoustic model, and environment model of the generator, and build aero-engine twin models for different models of aero-engines; The test bench twin model module is used to separately input various bench discipline models of different types of test benches. The bench discipline models include the thermodynamic model, structural mechanics model, acoustic model, and environmental model of the test bench, and the test bench twin models are built for different types of test benches respectively. The aero-engine digital virtual test module is used to conduct aero-engine digital virtual tests based on the flight envelope data model, aero-engine twin model, and test bench twin model. The aero-engine virtual test data analysis module is used to conduct multi-dimensional analysis and display of the data throughout the digital virtual test process, and conduct comparative fitting analysis based on the historical test data of the aero-engine, the in-service operation data of the aero-engine physical object, and the results of the digital virtual test.

[0016] The technical solution of the present invention has at least the following advantages and beneficial effects: The present invention makes up for the deficiencies existing in traditional aero-engine physical tests. At the same time, physical tests can provide a large amount of necessary data and information for the confirmation of digital virtual tests, and can also discover mechanism problems that cannot be covered in virtual tests. By organically combining physical tests and virtual tests, the present invention realizes the complementarity and mutual reference between the virtual and the real, and the spiral improvement, which can continuously improve the overall development level of aero-engines and achieve the development goals faster and better. The present invention saves test resources, avoids the problem of large material consumption in traditional tests, saves test time at the same time, and has a high cost performance. The test process, data, etc. of the present invention are highly transparent, which improves the observability and interpretability of the test. The present invention is reasonably designed and easy to implement. It can not only be applied to the aero-engine development field, but also be applied to different industries and related fields such as aircraft development, space equipment development, and other equipment development, and has certain demonstration and promotion value. Brief Description of the Drawings

[0017] Figure 1 It is a schematic flow chart of the aero-engine virtual test method based on digital twin provided in Embodiment 1 of the present invention. Figure 2 It is a schematic principle diagram of the aero-engine virtual test system based on digital twin provided in Embodiment 2 of the present invention. Detailed Embodiments

[0018] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are some, but not all, of the embodiments of the present invention. The components of the embodiments of the present invention usually described and shown in the drawings here can be arranged and designed in various different configurations.

[0019] Embodiment 1 This embodiment provides a virtual test method for an aero-engine based on digital twin. Refer to Figure 1 , and it includes the following steps: Perform flight envelope data model modeling: Enter the flight envelope data of different models of aero-engines respectively, and perform modeling of the flight envelope data model for different models of aero-engines; Perform aero-engine twin model modeling: Enter various engine discipline models of different models of aero-engines. The engine discipline models include the thermodynamic model, structural mechanics model, acoustic model, and environmental model of the generator, and perform modeling of the aero-engine twin model for different models of aero-engines; Perform test bench twin model modeling: Enter various bench discipline models of different types of test benches. The bench discipline models include the thermodynamic model, structural mechanics model, acoustic model, and environmental model of the test bench, and perform modeling of the test bench twin model for different types of benches; Aero-engine digital virtual test: Perform aero-engine digital virtual test according to the flight envelope data model, aero-engine twin model, and test bench twin model; Perform virtual test data analysis and visualization display: Perform multi-dimensional analysis and display on the data of the entire process of the digital virtual test, and perform comparative fitting analysis based on the historical test data of the aero-engine, the in-service operation data of the aero-engine physical object, and the results of the digital virtual test.

[0020] In the solution of this embodiment, the digital virtual test of the aero-engine, the twin model of the aero-engine, and the twin model of the test bench obtained by modeling are all stored and used for model retrieval and invocation according to requirements in the digital virtual test of the aero-engine. In this embodiment, by inputting and managing the flight envelope data of different models of aero-engines, constructing an interactive interface for the corresponding flight envelope data model and configuration data model, and importing and managing multi-disciplinary models such as the aerodynamic thermodynamics model, structural mechanics model, and control system model of different models of aero-engines, and constructing twin models of different models of aero-engines and their data interaction interfaces and parameter configuration adjustment interface panels, and importing and managing multi-disciplinary models such as the thermodynamics model, structural mechanics model, acoustic model, and environmental model of different types of test benches, and constructing twin models of different types of test benches and their data interaction interfaces, a digital virtual test project of different models of aero-engines can be created. Select the flight envelope data model, the twin model of the aero-engine, and the twin model of the test bench, and configure the information flow and energy flow relationships between the models and configure the test parameters to realize multi-dimensional analysis and display of the whole process data of the virtual test. Finally, based on the historical test data of the aero-engine (virtual test / physical test data), the physical field operation data of the aero-engine in-service, combined with the results of the current digital virtual test, refined comparative fitting analysis can be carried out, and the analysis results can be displayed in a visual way.

[0021] In this embodiment, the method for modeling the flight envelope data model is as follows: Import and convert the format of the flight envelope data in different formats, and display the flight envelope data in a graphical form; Manage the flight envelope data item by item according to different models of aero-engines; Perform modeling encapsulation of the flight envelope data and configure the data interaction interface of the data model.

[0022] When importing and converting the format, import the flight envelope data in different formats such as.opju,.xlx,.xlsx, etc. The flight envelope data in.opju format can be converted into structured flight envelope data in.xlx or.xlsx format, and the structured flight envelope data in.xlx and.xlsx formats can also be converted into.opju format files, and the flight envelope data is displayed in a graphical form. At the same time, the imported flight envelope data is managed item by item according to different models of aero-engines.

[0023] Then, specific modeling is carried out. According to the flight envelope data of different models of aero-engines imported, data modeling is performed in a standardized data encapsulation format. And configure the data interaction interface of the data model to support the use in configuring the information flow and energy flow between models during the digital virtual test of aero-engines. The specific implementation method of modeling can be: Use the panda library in Python to read and convert the flight envelope data of different models of aero-engines imported into the.xlx or.xlsx format; According to the data structure of the.xlx or.xlsx format table, use an object-oriented approach to represent the data model through classes; Encapsulate the read flight envelope data in the.xlx or.xlsx format into the defined data model; Expose the interface of the data model by defining functions or class methods.

[0024] As a preferred solution, the method for modeling the aero-engine twin model is: Import and verify various discipline models of different models of aero-engines, and then manage the discipline models item by item according to different models of aero-engines; Build an aero-engine twin model according to the corresponding mechanism principle of the aero-engine, and configure the information flow and energy flow between various discipline models of the aero-engine, and configure the interaction interface of the aero-engine twin model.

[0025] Specifically, first import various discipline models such as the aerodynamic thermodynamics model, structural mechanics model, and control system model of different models of aero-engines, and verify the imported multi-discipline models according to the FMI standard to check whether the imported models meet the FMI standard (check whether the simulation parameters and model parameters of the models meet the requirements). At the same time, manage the models item by item according to different models of aero-engines, aiming to support the call during the modeling process of the aero-engine twin model. Then, according to the imported multi-discipline models of different models of aero-engines, in a multi-discipline coupling modeling environment / tools, build twin models of different models of aero-engines according to the mechanism principle of a specific model of aero-engine, and configure the information flow and energy flow between the multi-discipline models of the aero-engine (such as the control system model inputs fuel adjustment signals and surge margin control signals to the aerodynamic thermodynamics model, and there is an air energy flow interaction between the turbine model and the combustion chamber model inside the aerodynamic thermodynamics model). The specific modeling method is: Create an empty twin model of a specific model of aero-engine in a multi-discipline coupling modeling environment / tools; According to the structural composition of the specified model of aero-engine, select the corresponding aerodynamic thermodynamics model, structural mechanics model, control system model, etc. from the imported multi-discipline models; According to the mechanism principle of a specified type of aero-engine, configure the interaction interfaces and parameter quantities of multi-disciplinary models. For example, for the control system model, set the fuel regulation signal interface and parameter quantities for interaction with the aerodynamic thermodynamics model, the surge margin control signal interface and parameter quantities, the air energy flow interfaces and parameter quantities of the turbine model and the combustion chamber model inside the aerodynamic thermodynamics model. The structural mechanics model will transmit the thermal barrier coating failure signal and the turbine blade temperature overlimit data to the control system model through the thermal barrier coating failure signal interface; For the interaction interfaces of the configured multi-disciplinary models, add a parameter configuration adjustment interface panel to support dynamic parameter adjustment during the execution of virtual tests; After completing the configuration of the multi-disciplinary model interaction interfaces and parameter quantities, according to the interaction characteristics between multi-disciplinary models (such as information flow interaction, energy flow interaction), connect the lines and configure the parameter quantities; After completing the above steps, for the constructed aero-engine twin model, configure its interaction interfaces and parameter quantities, such as: thrust output interface and parameter quantities, temperature output interface and parameter quantities, voltage output interface and parameter quantities, hydraulic power output interface and parameter quantities.

[0026] For the constructed aero-engine twin model, configure its model interaction interfaces, such as: thrust output interface, temperature output interface, voltage output interface, hydraulic power output interface, etc., to support the configuration of information flow and energy flow between models during the digital virtual test of the aero-engine.

[0027] Next, the method for modeling the twin model of the test bench is preferably: Import and verify multi-disciplinary models of different types of test benches, and then manage the model entries of the disciplinary models according to different types of test benches; According to the mechanism principle corresponding to the test bench, construct the twin model of the test bench, configure the information flow and energy flow between the multi-disciplinary models of the test bench, and configure the interaction interfaces of the twin model of the test bench.

[0028] Specifically, in this step, first import multidisciplinary models such as thermodynamic models, structural mechanics models, acoustic models, and environmental models of different types of aero-engine test stands, and verify the imported multidisciplinary models according to the FMI standard to check whether the imported models meet the FMI standard (check whether the simulation parameters and model parameters of the models meet the requirements). At the same time, perform model itemized management according to different types of aero-engine test stands to support the invocation during the modeling of aero-engine twin models. Then, based on the imported multidisciplinary models of different types of aero-engine test stands, in a multidisciplinary coupling modeling environment / tool, construct twin models of different types of aero-engine test stands according to the mechanism principles of different types of aero-engine test stands, and configure the information flow and energy flow between the multidisciplinary models of the test stands. Then, configure the model interaction interfaces for the constructed twin models of aero-engine test stands, such as: thrust input interface, temperature input interface, voltage input interface, hydraulic power input interface, etc., to support the use in configuring the information flow and energy flow between models during the digital virtual test of aero-engines. The modeling method in this step can be as follows: In a multidisciplinary coupling modeling environment / tool, create an empty twin model of a specific type of aero-engine test stand (such as a ground test stand twin model, a high-altitude simulation test stand twin model, a compressor test stand twin model); According to the structural composition of a specific type of aero-engine test stand, select the corresponding thermodynamic model, structural mechanics model, acoustic model, environmental model, etc. from the imported multidisciplinary models; According to the mechanism principle of a specific type of aero-engine test stand, configure the interaction interfaces and parameter quantities of the multidisciplinary models. For example, the thermodynamic model transfers heat radiation and convection data to the structural mechanics model through the high-temperature gas flow signal interface, and the structural mechanics model transfers structural vibration data to the acoustic model through the structural vibration signal interface; After completing the configuration of the interaction interfaces and parameter quantities of the multidisciplinary models, perform wiring and configure the parameter quantities according to the interaction characteristics between the multidisciplinary models (such as information flow interaction, energy flow interaction); After completing the above steps, configure the interaction interfaces and parameter quantities for the constructed twin models of aero-engine test stands, such as: thrust input interface and parameter quantity, temperature input interface and parameter quantity, voltage input interface and parameter quantity, hydraulic power input interface and parameter quantity.

[0029] As a preferred solution of this embodiment, the method for performing digital virtual tests on aero-engines can be: Create digital virtual test projects for different models of aero-engines; Retrieve and select the required flight envelope data model, the aero-engine twin model, and the test bench twin model, and import them into the digital virtual test project; For the flight envelope data model, the aero-engine twin model, and the test bench twin model, configure the information flow and energy flow between the models according to the data interaction mechanism between the models and the defined model interaction interfaces; Configure the test project parameters; Generate a simulation scheduling task and drive the flight envelope data model, the aero-engine twin model, and the test bench twin model to perform simulations; Monitor the data interaction of the information flow and energy flow between the models, monitor the process of the models being scheduled and executed, and obtain and store the monitoring data; Configure and adjust the aero-engine twin model and its parameters through the parameter configuration adjustment interface panel of the aero-engine twin model.

[0030] Furthermore, the test project parameters include the test duration and the number of tests.

[0031] The following is a specific implementation case of a test operation: Creation of aero-engine digital virtual test project: Create a digital virtual test project for a specified model of aero-engine, and add content such as the name of the virtual test project and the project description.

[0032] Model retrieval and call: Retrieve and select from the created flight envelope data model, aero-engine twin model, and test bench twin model, and then they can be imported into the corresponding aero-engine digital virtual test project.

[0033] Configuration of information flow and energy flow between models: For the selected flight envelope data model, aero-engine twin model, and test bench twin model, configure the information flow and energy flow between the models according to the data interaction mechanism between the models and the defined model interaction interfaces. For example, the flight speed interface, flight altitude interface, and ambient temperature interface defined by the flight envelope data model input flight parameter excitations (including flight speed, flight altitude, and ambient temperature parameters) to the aero-engine twin model; the thrust output interface, temperature output interface, voltage output interface, and hydraulic power output interface defined by the aero-engine twin model input thrust, voltage, and hydraulic power excitations to the test bench twin model.

[0034] Virtual test engineering parameter configuration: After completing the configuration definition of information flow and energy flow among the flight envelope data model, aero-engine twin model, and test bench twin model, configure and manage test engineering-related parameters such as test duration and number of tests for digital virtual tests. During the execution of virtual tests, the flight envelope data model, aero-engine twin model, and test bench twin model will be scheduled for simulation execution according to parameters such as test duration and number of tests defined in the configuration.

[0035] Virtual test execution: According to parameters such as test duration and number of tests defined in the configuration, as well as the configuration definition of information flow and energy flow among models, the system generates simulation scheduling tasks and drives the flight envelope data model, aero-engine twin model, and test bench twin model for simulation execution.

[0036] Virtual test execution process monitoring: According to the interaction interfaces between models, configure and select a signal monitoring scheme that meets the requirements to monitor the data interaction of information flow and energy flow between models. Configure the virtual test execution monitoring scheme to monitor the process of model scheduling and execution, and obtain and store the corresponding monitoring data.

[0037] Parameter tuning of aero-engine twin model: Dynamically configure and adjust the parameters of the aero-engine twin model and its internal models to achieve human-in-the-loop dynamic simulation tests during virtual simulation. At the same time, record the data of the virtual test execution process after dynamic configuration adjustment.

[0038] Finally, the method for comparative fitting analysis based on aero-engine historical test data, aero-engine physical field operation data, and digital virtual test results is preferably: Carry out itemized classification management of the aero-engine historical test data and the aero-engine physical field operation data of different models of aero-engines, and conduct visual display; Obtain the result data of the aero-engine digital virtual test of the current test model, conduct feature analysis and annotation, and conduct graphic and text visual display; According to the results of data feature analysis and annotation, select corresponding data from the aero-engine historical test data and the aero-engine physical field operation data for comparative fitting analysis.

[0039] On this basis, the method for selecting corresponding data for comparative fitting analysis is: Under the condition of the same flight envelope data, conduct data curve comparative fitting on the aero-engine historical test data and the aero-engine physical field operation data.

[0040] At the same time, the flight envelope data includes flight speed, flight altitude, overload, and ambient temperature.

[0041] When analyzing the data of the experiment, the specific operation cases are as follows: Historical test data management: Conduct itemized classification management on the historical test data of aero-engines of different models imported and the digital virtual test results, and perform visual display for use when analyzing digital virtual test data. The digital virtual test results are the results of the current test.

[0042] Field operation data management: Conduct itemized classification management on the field operation data of physical aero-engines of different models imported, and perform visual display for use when analyzing digital virtual test data.

[0043] Analysis and visualization of the current digital virtual test: Obtain the digital virtual test results of the target model aero-engine (including data interaction monitoring data between models, monitoring data during the process of model scheduling and execution, etc.), conduct feature analysis and annotation on the obtained digital virtual test results. For example, under specific flight parameters, design indicators such as the thrust output value, temperature output value, voltage output value, and hydraulic power output value of the aero-engine twin model are analyzed, and graphic and text visualization displays are performed on these output values.

[0044] Comparative analysis based on historical test data and field operation data: Select the historical test data of the aero-engine and the field operation data of the physical aero-engine that need to be compared. According to the results of data feature analysis and annotation, select the corresponding data from the historical test data / field operation data of the physical aero-engine for comparative fitting analysis. For example, under the same flight envelope data conditions (the same flight speed, flight altitude, overload, and environmental temperature scenarios), conduct data curve comparative fitting on the test data and field operation data, and the analysis results can be displayed in a graphic and text visualization manner to assist in the iterative design of the aero-engine.

[0045] Embodiment 2 This embodiment provides a digital-twin-based aero-engine virtual test system. Refer to Figure 2 , and apply it to a digital-twin-based aero-engine virtual test method in the above embodiment, including: A flight envelope data model module, mainly used for flight envelope data modeling and management. Specifically, input the flight envelope data of different models of aero-engines respectively, and conduct modeling of the flight envelope data model for different models of aero-engines. The aero-engine twin model module is mainly used for the multi-disciplinary model of civilian aero-engines and the twin modeling of aero-engines. Specifically, various engine discipline models of different models of aero-engines are respectively input. The engine discipline models include the thermodynamic model, structural mechanics model, acoustic model, and environmental model of the generator, and the twin models of aero-engines are respectively modeled for different models of aero-engines; The test bench twin model module is used for inputting the multi-disciplinary model of the test bench and the twin modeling of the test bench. Specifically, various bench discipline models of different types of test benches are respectively input. The bench discipline models include the thermodynamic model, structural mechanics model, acoustic model, and environmental model of the bench, and the twin models of the test bench are respectively modeled for different types of benches; The aero-engine digital virtual test module imports and manages the flight envelope data model, aero-engine twin model, and test bench twin model respectively to realize the engineering management of aero-engine digital virtual tests. The aero-engine digital virtual tests are mainly carried out based on the flight envelope data model, aero-engine twin model, and test bench twin model; The aero-engine virtual test data analysis module mainly includes functions such as virtual test data analysis, visualization of analysis results, management of historical test data, and management of historical field data. It is used for multi-dimensional analysis and display of the data in the whole process of digital virtual tests, and conducts comparative fitting analysis based on the historical test data of aero-engines, the in-field operation data of aero-engine physical objects, and the results of digital virtual tests.

[0046] The above are only the preferred embodiments of the present invention and are not intended to limit the present invention. For those skilled in the art, the present invention can have various changes and modifications. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included within the protection scope of the present invention.

Claims

1. A virtual test method for an aero-engine based on digital twin, characterized in that: The following steps are involved: The flight envelope data of different types of aircraft engines are input respectively, and the flight envelope data models of different types of aircraft engines are modeled respectively; Inputting a variety of engine subject models of different types of aircraft engines respectively, wherein the engine subject models include a thermodynamic model, a structural mechanics model, an acoustic model, and an environmental model of the generator, and modeling the aircraft engine twin models of different types of aircraft engines respectively; Input various test bench subject models of different types of test benches respectively, wherein the test bench subject models include the test bench's thermodynamic model, structural mechanics model, acoustic model, and environmental model, and model the test bench twin models of different types of test benches respectively; Conduct digital virtual testing of aircraft engines based on the flight envelope data model, aircraft engine twin model and test bench twin model; The data of the entire digital virtual test process is analyzed and displayed in multiple dimensions, and a comparative fitting analysis is performed based on historical aero-engine test data, actual aero-engine field operation data, and digital virtual test results.

2. The method for virtual testing of an aero-engine based on digital twin according to claim 1, characterized in that: The method for modeling the flight envelope data model is: Importing and converting the flight envelope data in different formats, and displaying the flight envelope data in a graphical form; According to different types of aircraft engines, the flight envelope data is managed in an itemized manner; Perform flight envelope data modeling and encapsulation, and configure the data interaction interface of the data model.

3. The method for virtual testing of an aero-engine based on digital twin according to claim 1, characterized in that: The method for modeling the twin model of an aero-engine is as follows: Import and verify various subject models of different types of aircraft engines, and then manage the subject models in terms of model items according to different types of aircraft engines; According to the corresponding mechanism principles of aircraft engines, a twin model of aircraft engines is constructed, and the information flow and energy flow between various subject models of aircraft engines are configured, and the interactive interface of the twin model of aircraft engines is configured.

4. The method for virtual testing of an aero-engine based on digital twin according to claim 1, characterized in that: The method for modeling the test bench twin model is: Import and verify various subject models of different types of test benches, and then manage the subject models in model entry according to different types of test benches; According to the corresponding mechanism principles of the test bench, a twin model of the test bench is constructed, and the information flow and energy flow between the multi-disciplinary models of the test bench are configured, and the interactive interface of the twin model of the test bench is configured.

5. The method for virtual testing of an aero-engine based on digital twin according to claim 1, characterized in that: The method for conducting a digital virtual test of an aeroengine is as follows: Create digital virtual test projects for different types of aircraft engines; Retrieving and selecting the required flight envelope data model, the aircraft engine twin model and the test bench twin model, and importing them into the digital virtual test project; For the flight envelope data model, the aircraft engine twin model and the test bench twin model, according to the data interaction mechanism between the models and the defined model interaction interface, configure the information flow and energy flow between the models; Configure test engineering parameters; Generate simulation scheduling tasks and drive the flight envelope data model, aircraft engine twin model and test bench twin model to simulate; Monitor the data interaction of information flow and energy flow between models, monitor the process of model scheduling and execution, and obtain and store monitoring data; The aircraft engine twin model and its parameters are configured and adjusted through the parameter configuration adjustment interface panel of the aircraft engine twin model.

6. The method for virtual testing of an aero-engine based on digital twin according to claim 5, characterized in that: The test engineering parameters include test duration and test number.

7. The method for virtual testing of an aero-engine based on digital twin according to claim 1, characterized in that: The method for comparative fitting analysis based on historical test data of aircraft engines, actual field operation data of aircraft engines and digital virtual test results is as follows: Performing item-based classification management on the historical test data of the aircraft engines and the actual field operation data of the aircraft engines of different models, and performing visual display; Obtaining result data of the digital virtual test of the aircraft engine of the currently tested model, performing feature analysis and annotation, and performing graphic and text visualization; According to the data feature analysis and annotation results, corresponding data are selected from the historical test data of the aircraft engine and the actual field operation data of the aircraft engine for comparative fitting analysis.

8. The method for virtual testing of an aero-engine based on digital twin according to claim 7, characterized in that: The method for selecting corresponding data for comparative fitting analysis is: Under the same flight envelope data conditions, data curve comparison and fitting are performed on the historical test data of the aircraft engine and the actual field operation data of the aircraft engine.

9. The digital twin-based aero-engine virtual test method according to claim 8, characterized in that: The flight envelope data includes flight speed, flight altitude, overload and ambient temperature.

10. An aero-engine virtual test system based on digital twin, applied to an aero-engine virtual test method based on digital twin according to any one of claims 1 to 9, characterized in that: include: The flight envelope data model module is used to input the flight envelope data of different types of aircraft engines and build flight envelope data models for different types of aircraft engines; The aircraft engine twin model module is used to input a variety of engine subject models of different types of aircraft engines, including the thermodynamic model, structural mechanics model, acoustic model, and environmental model of the generator, and to model the aircraft engine twin models for different types of aircraft engines; The test bench twin model module is used to input various test bench subject models of different types of test benches, including the test bench thermodynamic model, structural mechanics model, acoustic model, and environmental model, and model the test bench twin models of different types of test benches respectively; The digital virtual test module for aircraft engines is used to conduct digital virtual tests of aircraft engines based on the flight envelope data model, the aircraft engine twin model and the test bench twin model; The aircraft engine virtual test data analysis module is used to perform multi-dimensional analysis and display of data from the entire digital virtual test process, and to conduct comparative fitting analysis based on historical aircraft engine test data, actual aircraft engine field operation data, and digital virtual test results.

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