A virtual test method and system for aero-engines based on digital twin

Abstract

The present invention provides a digital-twin-based virtual test method and system for aeroengines, which relates to the technical field of aeroengine virtual test. The method includes respectively inputting the flight envelope data of different models of aeroengines and building models of flight envelope data for different models of aeroengines; respectively inputting various engine discipline models of different models of aeroengines and building aeroengine twin models for different models of aeroengines; respectively inputting various test bench discipline models of different types of test benches and building test bench twin models for different types of test benches; performing digital virtual tests on aeroengines according to the flight envelope data models, aeroengine twin models and test bench twin models; and performing multi-dimensional analysis and display on the data of the entire process of digital virtual tests. The present invention has the advantages of realizing the complementarity between the virtual and the real, and having a clearer, more comprehensive and reliable test process.

Description

Technical Field

[0001] The present invention relates to the technical field of aero-engine virtual test, and in particular, to a method and system for aero-engine virtual test 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 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 engineering development and design validation stages 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, high-altitude simulation tests, environmental tests, and flight tests, etc.). Due to 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 in traditional physical aero-engine tests, and the huge consumption of time, resources, and physical aero-engines in traditional physical aero-engine tests, it 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 real, 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 aero-engine virtual test based on digital twin, which can achieve a test that combines virtual and real, with a clearer, more comprehensive, and reliable process.

[0006] The present invention is realized through the following technical solutions:

[0007] A method for aero-engine virtual test based on digital twin includes the following steps:

[0008] Input the flight envelope data of different models of aero-engines respectively, and build models of flight envelope data for different models of aero-engines;

[0009] Input various engine discipline models of different models of aero-engines respectively, where the engine discipline models include thermodynamic models, structural mechanics models, acoustic models, and environmental models of generators, and build aero-engine twin models for different models of aero-engines;

[0010] Input various bench discipline models of different types of test benches respectively. The bench discipline models include the thermodynamic model, structural mechanics model, acoustic model, and environmental model of the bench, and build the twin models of the test benches for different types of benches respectively;

[0011] Conduct digital virtual tests of aero-engines based on the flight envelope data model, the aero-engine twin model, and the test bench twin model;

[0012] Conduct multi-dimensional analysis and display of the data throughout the process of the digital virtual test, 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.

[0013] Preferably, the method for building the flight envelope data model is as follows:

[0014] Import and convert the formats of the flight envelope data in different formats, and display the flight envelope data in a graphical form;

[0015] Manage the flight envelope data item by item according to different models of aero-engines;

[0016] Build and encapsulate the flight envelope data model, and configure the data interaction interface of the data model.

[0017] Preferably, the method for building the aero-engine twin model is as follows:

[0018] 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;

[0019] Build the aero-engine twin model according to the corresponding mechanism principle of the aero-engine, 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.

[0020] Preferably, the method for building the test bench twin model is as follows:

[0021] Import and verify various discipline models of different types of test benches, and then manage the discipline models item by item according to different types of test benches;

[0022] Build the test bench twin model according to the corresponding mechanism principle of the test bench, configure the information flow and energy flow between multiple discipline models of the test bench, and configure the interaction interface of the test bench twin model.

[0023] Preferably, the method for conducting digital virtual tests of aero-engines is as follows:

[0024] Create a digital virtual test project for different models of aero-engines;

[0025] 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;

[0026] 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;

[0027] Configure the test project parameters;

[0028] 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;

[0029] 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;

[0030] Configure and adjust the aero-engine twin model and its parameters through the parameter configuration adjustment interface panel of the aero-engine twin model.

[0031] Preferably, the test project parameters include the test duration and the number of tests.

[0032] Preferably, the method for comparative fitting analysis based on the aero-engine historical test data, the aero-engine in-service field operation data, and the digital virtual test results is as follows:

[0033] 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;

[0034] Obtain the result data of the digital virtual test of the aero-engine of the current test model, perform feature analysis and annotation, and perform graphic and text visual display;

[0035] According to the data feature analysis and annotation results, select the corresponding data from the aero-engine historical test data and the aero-engine in-service field operation data for comparative fitting analysis.

[0036] Preferably, the method for selecting the corresponding data for comparative fitting analysis is as follows:

[0037] 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.

[0038] Preferably, the flight envelope data includes flight speed, flight altitude, overload, and environmental temperature.

[0039] The present invention also provides a digital twin-based aeroengine virtual test system, which is applied to the above-mentioned digital twin-based aeroengine virtual test method, and includes:

[0040] A flight envelope data model module, which is used to respectively input the flight envelope data of different models of aeroengines and build flight envelope data models for different models of aeroengines;

[0041] An aeroengine twin model module, which is used to respectively input various engine discipline models of different models of aeroengines. The engine discipline models include the thermodynamic model, structural mechanics model, acoustic model, and environmental model of the generator, and build aeroengine twin models for different models of aeroengines;

[0042] A test bench twin model module, which is used to respectively 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 build test bench twin models for different types of test benches;

[0043] An aeroengine digital virtual test module, which is used to perform aeroengine digital virtual tests according to the flight envelope data model, aeroengine twin model, and test bench twin model;

[0044] An aeroengine virtual test data analysis module, which is used to perform multi-dimensional analysis and display of the data in the whole process of digital virtual tests, and perform comparative fitting analysis based on aeroengine historical test data, aeroengine physical field operation data, and digital virtual test results.

[0045] The technical solution of the present invention has at least the following advantages and beneficial effects:

[0046] The present invention makes up for the deficiencies in traditional aeroengine 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;

[0047] By organically combining physical tests and virtual tests, the present invention realizes the complementarity and mutual reference between the virtual and the real, and can be improved in a spiral manner, continuously improving the overall development level of aeroengines and achieving the development goals faster and better;

[0048] The present invention saves test resources, avoids the problem of large material consumption in traditional tests, and at the same time saves test time, with high cost performance;

[0049] The test process, data, etc. of the present invention are highly transparent, which improves the observability and interpretability of the test;

[0050] The present invention is reasonably designed and easy to implement. It can be applied not only in the field of aero-engine development, but also in related fields of different industries such as aircraft development, space equipment development, and other equipment development, and has certain demonstration and promotion value. BRIEF DESCRIPTION OF THE DRAWINGS

[0051] Figure 1 It is a schematic flow chart of the virtual test method for aero-engines based on digital twin provided in Embodiment 1 of the present invention;

[0052] Figure 2 It is a schematic principle diagram of the virtual test system for aero-engines based on digital twin provided in Embodiment 2 of the present invention. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0053] 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 described and shown in the drawings here can be arranged and designed in various different configurations.

[0054] Embodiment 1

[0055] This embodiment provides a virtual test method for aero-engines based on digital twin. Refer to Figure 1 , and it includes the following steps:

[0056] Conduct flight envelope data model modeling: Enter 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;

[0057] Conduct 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 conduct modeling of the aero-engine twin model for different models of aero-engines;

[0058] Conduct 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 bench, and conduct modeling of the test bench twin model for different types of benches;

[0059] Digital virtual test of aero-engine: Conduct a digital virtual test of the aero-engine according to the flight envelope data model, the aero-engine twin model, and the test bench twin model;

[0060] Conduct data analysis and visualization of virtual test: Conduct multi-dimensional analysis and display of the data throughout the digital virtual test, and conduct comparative fitting analysis based on the historical test data of the aero-engine, the in-service operation data of the physical aero-engine, and the results of the digital virtual test.

[0061] In the solution of this embodiment, the digital virtual test of the aero-engine, the aero-engine twin model, and the test bench twin model obtained by modeling will all be 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 aero-engine twin model, and the test bench twin model, 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 data throughout the virtual test process. Finally, based on the historical test data (virtual test / physical test data) of the aero-engine, the in-service operation data of the physical aero-engine, 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 manner.

[0062] In this embodiment, the method for modeling the flight envelope data model is as follows:

[0063] Import and convert the format of the flight envelope data in different formats, and display the flight envelope data in a graphical form;

[0064] Manage the flight envelope data item by item according to different models of aero-engines;

[0065] Conduct modeling encapsulation of the flight envelope data and configure the data interaction interface of the data model.

[0066] When importing and performing format conversion, flight envelope data in different formats such as.opju,.xlx,.xlsx, etc. are imported. For the.opju format flight envelope data, it can be converted into structured flight envelope data in the.xlx or.xlsx format, and the structured flight envelope data in the.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.

[0067] 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 the data interaction interfaces of the data model are configured to support the use when 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:

[0068] Use the panda library in Python to read the flight envelope data of different models of aero-engines imported and converted into the.xlx or.xlsx format;

[0069] According to the data structure of the.xlx or.xlsx format table, use an object-oriented method to represent the data model through classes;

[0070] Package the read flight envelope data in the.xlx or.xlsx format into the defined data model;

[0071] Expose the interface of the data model by defining functions or class methods.

[0072] As a preferred solution, the method for modeling the aero-engine twin model is:

[0073] Import and verify multiple discipline models of different models of aero-engines, and then manage the discipline models item by item according to different models of aero-engines;

[0074] Build an aero-engine twin model according to the corresponding mechanism principle of the aero-engine, configure the information flow and energy flow between multiple discipline models of the aero-engine, and configure the interaction interface of the aero-engine twin model.

[0075] Specifically, first, import multidisciplinary models such as the aerodynamic thermodynamics model, structural mechanics model, and control system model of different types of aero-engines, 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-engines, aiming to support the invocation during the modeling process of the aero-engine twin model. Then, based on the imported multidisciplinary models of different types of aero-engines, in a multidisciplinary coupling modeling environment / tools, construct twin models of different types of aero-engines according to the mechanism principle of a specific type of aero-engine, and configure the information flow and energy flow between the multidisciplinary 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 as follows:

[0076] In a multidisciplinary coupling modeling environment / tools, create an empty twin model of a specific type of aero-engine;

[0077] According to the structural composition of the specified type of aero-engine, select the corresponding aerodynamic thermodynamics model, structural mechanics model, control system model, etc. from the imported multidisciplinary models;

[0078] According to the mechanism principle of the specified type of aero-engine, configure the interaction interfaces and parameter quantities of the multidisciplinary models. For example, set the fuel adjustment signal interface and parameter quantity, surge margin control signal interface and parameter quantity for the control system model to interact with the aerodynamic thermodynamics model, the air energy flow interface and parameter quantity between the turbine model and the combustion chamber model inside the aerodynamic thermodynamics model, and the structural mechanics model will transmit the thermal barrier coating failure signal and turbine blade temperature overlimit data to the control system model through the thermal barrier coating failure signal interface;

[0079] For the interaction interfaces of the configured multidisciplinary models, add a parameter configuration adjustment interface panel to support dynamic parameter adjustment during the execution of virtual tests;

[0080] After completing the configuration of the interaction interfaces and parameter quantities of the multidisciplinary models, connect the lines and configure the parameter quantities according to the interaction characteristics between the multidisciplinary models (such as information flow interaction, energy flow interaction);

[0081] After completing the above steps, for the constructed aero-engine twin model, configure its interaction interfaces and parameter quantities. For example: thrust output interface and parameter quantity, temperature output interface and parameter quantity, voltage output interface and parameter quantity, hydraulic power output interface and parameter quantity.

[0082] For the constructed twin model of the aero-engine, 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 process of the aero-engine.

[0083] Next, the method for modeling the twin model of the test bench is preferably as follows:

[0084] Import and verify multiple 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;

[0085] Construct a twin model of the test bench according to the mechanism principle corresponding to 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 twin model of the test bench.

[0086] Specifically, in this step, first import multiple disciplinary models such as thermodynamic models, structural mechanics models, acoustic models, and environmental models of different types of aero-engine test benches, and verify the imported multiple disciplinary 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 model entries according to different types of aero-engine test benches to support the call during the modeling process of the aero-engine twin model. Then, according to the imported multiple disciplinary models of different types of aero-engine test benches, in the multi-disciplinary coupling modeling environment / tools, construct twin models of different types of aero-engine test benches according to the mechanism principle of different types of aero-engine test benches, and configure the information flow and energy flow between the multiple disciplinary models of the test bench. Then, for the constructed twin model of the aero-engine test bench, configure its model interaction interfaces, such as: thrust input interface, temperature input interface, voltage input interface, hydraulic power input interface, etc., to support the configuration of information flow and energy flow between models during the digital virtual test process of the aero-engine. The modeling method in this step can be as follows:

[0087] In the multi-disciplinary coupling modeling environment / tools, create an empty twin model of a specific type of aero-engine test bench (such as a ground test stand twin model, a high-altitude simulation test stand twin model, a compressor test bench twin model);

[0088] According to the structural composition of the specific type of aero-engine test bench, select the corresponding thermodynamic model, structural mechanics model, acoustic model, environmental model, etc. from the imported multiple disciplinary models;

[0089] According to the mechanism principle of the aero-engine test bench of specific types, configure the interaction interfaces and parameter quantities of multi-disciplinary models. For example, the thermodynamics 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;

[0090] After completing the configuration of the interaction interfaces and parameter quantities of the multi-disciplinary models, according to the interaction characteristics between the multi-disciplinary models (such as information flow interaction, energy flow interaction), conduct wiring and configure the parameter quantities;

[0091] After completing the above steps, for the twin model of the aero-engine test bench constructed, configure its interaction interfaces and parameter quantities, 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.

[0092] As a preferred solution of this embodiment, the method for conducting digital virtual tests of aero-engines can be:

[0093] Create digital virtual test projects for different models of aero-engines;

[0094] 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;

[0095] 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;

[0096] Configure the test project parameters;

[0097] Generate a simulation scheduling task, and drive the flight envelope data model, the aero-engine twin model, and the test bench twin model to conduct simulations;

[0098] 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;

[0099] Through the parameter configuration adjustment interface panel of the aero-engine twin model, configure and adjust the aero-engine twin model and its parameters.

[0100] Furthermore, the test project parameters include the test duration and the number of tests.

[0101] The following is a specific implementation case of a test operation:

[0102] Creation of a digital virtual test project for an aero-engine: Create a digital virtual test project for a specified model of aero-engine, and add content such as the name and description of the virtual test project.

[0103] Model retrieval and invocation: Retrieve and select from the created flight envelope data model, aero-engine twin model, and test bench twin model, and then import them into the corresponding digital virtual test project of the aero-engine.

[0104] 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.

[0105] Configuration of parameters for the virtual test project: After completing the definition of the information flow and energy flow configuration between the flight envelope data model, aero-engine twin model, and test bench twin model, configure and manage the test project-related parameters such as the test duration and number of tests for the digital virtual test. During the execution of the virtual test, the flight envelope data model, aero-engine twin model, and test bench twin model will be scheduled for simulation execution according to the configured parameters such as the test duration and number of tests.

[0106] Execution of the virtual test: According to the configured parameters such as the test duration and number of tests, and the definition of the information flow and energy flow configuration between the 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.

[0107] Monitoring of the virtual test execution process: According to the interaction interfaces between the models, configure and select a signal monitoring scheme that meets the requirements to monitor the data interaction of the information flow and energy flow between the models. Configure the virtual test execution monitoring scheme to monitor the process of the models being scheduled for execution, and obtain and store the corresponding monitoring data.

[0108] Parameter tuning of the aero-engine twin model: Dynamically configure and adjust the parameters of the aero-engine twin model and its internal models to achieve a man-in-the-loop dynamic simulation test during the virtual simulation process. At the same time, record the data of the virtual test execution process after the dynamic configuration adjustment.

[0109] Finally, the method for comparative fitting analysis based on the historical test data of aero-engines, the in-service field operation data of aero-engine physical objects, and the digital virtual test results is preferably as follows:

[0110] Carry out itemized classification management on the historical test data of the aero-engines and the in-service field operation data of the aero-engine physical objects of different models, and conduct visual display;

[0111] Obtain the result data of the digital virtual test of the aero-engine of the current test model, conduct feature analysis and annotation, and conduct graphic and text visual display;

[0112] According to the data feature analysis and annotation results, select corresponding data from the historical test data of the aero-engines and the in-service field operation data of the aero-engine physical objects for comparative fitting analysis.

[0113] On this basis, the method for selecting corresponding data for comparative fitting analysis is as follows:

[0114] Under the condition of the same flight envelope data, conduct data curve comparative fitting on the historical test data of the aero-engines and the in-service field operation data of the aero-engine physical objects.

[0115] Meanwhile, the flight envelope data includes flight speed, flight altitude, overload, and environmental temperature.

[0116] When conducting data analysis of the test, the specific operation cases are as follows:

[0117] Historical test data management: Carry out itemized classification management on the historical test data of the aero-engines of different models imported and the digital virtual test results, and conduct visual display for use when analyzing the digital virtual test data. The digital virtual test results are also the results of the current test.

[0118] In-service field operation data management: Carry out itemized classification management on the in-service field operation data of the aero-engine physical objects of different models imported, and conduct visual display for use when analyzing the digital virtual test data.

[0119] Data analysis and visualization of the current 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 being scheduled for execution, etc.), conduct feature analysis and annotation on the obtained digital virtual test results, such as design indicators such as thrust output value, temperature output value, voltage output value, and hydraulic power output value of the aero-engine twin model under specific flight parameters, and conduct graphic and text visual display on these output values.

[0120] Comparative analysis based on historical test data and in-service operation data: Select the historical test data and in-service operation data of the aero-engine to be compared. According to the data characteristic analysis and annotation results, select the corresponding data from the historical test data / in-service operation data for comparative fitting analysis. For example, under the same flight envelope data conditions (the same flight speed, flight altitude, overload, and ambient temperature scenarios), compare and fit the data curves of the test data and in-service operation data. The analysis results can be presented in a graphical and visual manner to assist in the iterative design of aero-engines.

[0121] Embodiment 2

[0122] This embodiment provides a virtual test system for aero-engines based on digital twin. Refer to Figure 2 , and is applied to a virtual test method for aero-engines based on digital twin in the above embodiment, including:

[0123] The flight envelope data model module is mainly used for flight envelope data modeling and management. Specifically, enter the flight envelope data of different models of aero-engines respectively, and perform flight envelope data model modeling for different models of aero-engines.

[0124] The aero-engine twin model module is mainly used for pedestrian aero-engine multidisciplinary models and aero-engine twin modeling. Specifically, enter various engine discipline models of different models of aero-engines respectively. The engine discipline models include the thermodynamic model, structural mechanics model, acoustic model, and environmental model of the generator, and perform aero-engine twin model modeling for different models of aero-engines.

[0125] The test bench twin model module is used to enter the test bench multidisciplinary model and test bench twin modeling. Specifically, enter various bench discipline models of different types of test benches respectively. The bench discipline models include the thermodynamic model, structural mechanics model, acoustic model, and environmental model of the bench, and perform test bench twin model modeling for different types of benches.

[0126] 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 achieve aero-engine digital virtual test project management, and mainly performs aero-engine digital virtual tests based on the flight envelope data model, aero-engine twin model, and test bench twin model.

[0127] The virtual test data analysis module of an aero-engine mainly functions in virtual test data analysis, visualization of analysis results, management of historical test data, and management of historical outfield data. It is used for multi-dimensional analysis and display of data throughout the digital virtual test process, and conducts comparative fitting analysis based on the historical test data of aero-engines, the in-service outfield operation data of aero-engine physical objects, and the digital virtual test results.

[0128] 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, various modifications and variations can be made to the present invention. Any modifications, equivalent replacements, improvements, 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; Conduct multi-dimensional analysis and display of data from the entire digital virtual test process, and conduct comparative fitting analysis based on historical test data of aircraft engines, actual field operation data of aircraft engines, and digital virtual test results; 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.

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 test engineering parameters include test duration and test number.

6. 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.

7. The method for virtual testing of an aero-engine based on digital twin according to claim 6, 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.

8. The method for virtual testing of an aero-engine based on digital twin according to claim 7, characterized in that: The flight envelope data includes flight speed, flight altitude, overload and ambient temperature.

9. 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 8, 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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