Simulation solving method and device for aero-engine and computer equipment

Abstract

The invention relates to a simulation solving method and device for an aero-engine and computer equipment. The method comprises the following steps: acquiring system operation function information, system structure data and system association information among all structural systems of the aero-engine, and constructing sub-simulation operation models of all the structural systems; data interaction association information and operation interaction association information between the structural systems are recognized, so that simulation interaction information between the structural systems is constructed, simulation association processing is conducted on the structural systems, a joint simulation model of the aero-engine is obtained, and the joint simulation model of the aero-engine is obtained on the basis of demand input data of the aero-engine. And generating a joint simulation result of the aero-engine through a joint simulation model, and identifying operation solution data of the aero-engine through a joint simulation solution algorithm. By adopting the method, the simulation efficiency and the simulation convergence robustness of the aero-engine can be improved.

Description

Technical Field

[0001] The present application relates to the technical field of aero-engine modeling and simulation, and particularly to a simulation solution method, device and computer equipment for an aero-engine. Background Art

[0002] During the processes of research and development, improvement, optimization, adjustment, design, transformation, experiment, etc. of an aero-engine, in order to reduce cost losses, safety risks, and operating effects, it is often necessary to model the aero-engine, and then perform the above-mentioned work processes in a way of simulation. Therefore, how to improve the modeling accuracy of the constructed aero-engine model and the simulation operation accuracy of the model is the current research focus.

[0003] The traditional aero-engine simulation modeling method is to construct the entire aero-engine model through single-system simulation modeling. However, single-system modeling cannot simulate the operation process of the entire aero-engine, and there are also large deviations in the simulation results obtained during the simulation process, resulting in poor simulation accuracy of the aero-engine. Summary of the Invention

[0004] Based on this, it is necessary to provide a simulation solution method, device, computer equipment, computer-readable storage medium and computer program product for an aero-engine in view of the above technical problems.

[0005] In a first aspect, the present application provides a simulation solution method for an aero-engine, including:

[0006] Obtain the system operation function information of each structural system of the aero-engine, the system structure data of each structural system, and the system association information between each structural system, and construct a sub-simulation operation model of each structural system based on the system operation function information of each structural system and the system structure data of each structural system;

[0007] Based on the system association information between each structural system, identify the data interaction association information between each structural system and the operation interaction association information between each structural system, and construct the simulation interaction information between each structural system based on the data interaction association information between each structural system and the operation interaction association information between each structural system;

[0008] Based on the simulation interaction information between each structural system, perform simulation association processing on each structural system to obtain the joint simulation model of the aero-engine, and collect the demand input data of the aero-engine;

[0009] Based on the required input data, through the joint simulation model of the aero-engine, generate the joint simulation results of the aero-engine, and based on the joint simulation results, through the joint simulation solution algorithm, identify the operation solution data of the aero-engine.

[0010] Optionally, constructing the sub-simulation operation models of the structure systems based on the system operation function information of the structure systems and the system structure data of the structure systems includes:

[0011] Based on the system structure data of the structure systems, through a 3D modeling program, construct the system structure models of the structure systems, and for each structure system, based on the system operation function information of the structure system, identify the structure operation data of each operation function type;

[0012] Based on the structure operation data of each operation energy supply type, through a data parameter conversion program, convert the structure operation data of each operation function type into the structure operation parameters of each operation function type, and based on the structure operation parameters of each operation function type, adjust the system structure model of the structure system to obtain the sub-simulation operation model of the structure system.

[0013] Optionally, identifying the data interaction correlation information and the operation interaction correlation information between the structure systems based on the system correlation information between the structure systems includes:

[0014] Based on the system correlation information between the structure systems, identify the correlation information of each correlation type between the structure systems, and in the correlation database, query the interaction type to which each correlation type belongs;

[0015] Based on the correlation information of each correlation type corresponding to the data interaction type, identify the data interaction information and the data transmission information between the structure systems, and use the data interaction information and the data transmission information between the structure systems as the data interaction correlation information between the structure systems;

[0016] Based on the correlation information of each correlation type corresponding to the operation interaction type, identify the operation interaction mode and the operation interaction process between the structure systems, and use the operation interaction mode and the operation interaction process between the structure systems as the operation interaction correlation information between the structure systems.

[0017] Optionally, constructing the simulation interaction information between the structure systems based on the data interaction correlation information and the operation interaction correlation information between the structure systems includes:

[0018] Constructing the simulation operation interaction process between the structure systems based on the operation interaction modes and the operation interaction processes between the structure systems;

[0019] Constructing the simulation data interaction process between the structure systems based on the data interaction information and the data transmission information between the structure systems;

[0020] Taking the simulation operation interaction process and the simulation data interaction process between the structure systems as the simulation interaction information between the structure systems.

[0021] Optionally, performing simulation correlation processing on the structure systems based on the simulation interaction information between the structure systems to obtain the co-simulation model of the aero-engine, including:

[0022] Collecting the physical connection information between the structure systems, and performing model connection processing on the sub-simulation operation models of the structure systems based on the physical connection information between the structure systems to obtain the combined three-dimensional structure model of the aero-engine;

[0023] Constructing the simulation interaction parameters between the structure systems in the combined three-dimensional structure model based on the simulation interaction information between the structure systems, and adjusting the combined three-dimensional structure model with the simulation interaction parameters between all the structure systems to obtain the co-simulation model of the aero-engine.

[0024] Optionally, the co-simulation solution algorithm includes the system simulation solution algorithms of each structure system and the system correlation solution algorithm between each structure system. Identifying the operation solution data of the aero-engine based on the co-simulation result through the co-simulation solution algorithm includes:

[0025] Splitting the co-simulation result into the system simulation results of each structure system;

[0026] Identifying the system correlation solution order between the structure systems and the system algorithm solution order corresponding to the system simulation solution algorithms of each structure system based on the simulation interaction information between the structure systems, and calculating the system simulation solution data of each structure system through the system simulation solution algorithms of each structure system according to the simulation solution order of each structure system based on the system simulation results of each structure system;

[0027] Based on the system simulation solution data of each structural system, and according to the system association solution algorithm between each structural system, calculate the operation solution data of the aero-engine.

[0028] In a second aspect, the present application also provides a simulation solution device for an aero-engine, including:

[0029] An acquisition module, configured to acquire the system operation function information of each structural system of the aero-engine, the system structure data of each structural system, and the system association information between each structural system, and based on the system operation function information of each structural system and the system structure data of each structural system, construct a sub-simulation operation model of each structural system;

[0030] A construction module, configured to identify the data interaction association information between each structural system and the operation interaction association information between each structural system based on the system association information between each structural system, and construct the simulation interaction information between each structural system based on the data interaction association information between each structural system and the operation interaction association information between each structural system;

[0031] An acquisition module, configured to perform simulation association processing on each structural system based on the simulation interaction information between each structural system to obtain a joint simulation model of the aero-engine, and acquire the demand input data of the aero-engine;

[0032] An identification module, configured to generate a joint simulation result of the aero-engine through the joint simulation model of the aero-engine based on the demand input data, and identify the operation solution data of the aero-engine through a joint simulation solution algorithm based on the joint simulation result.

[0033] Optionally, the acquisition module is specifically configured to:

[0034] Based on the system structure data of each structural system, construct a system structure model of each structural system through a three-dimensional modeling program, and for each structural system, identify the structural operation data of each operation function type based on the system operation function information of the structural system;

[0035] Based on the structural operation data of each operation energy supply type, convert the structural operation data of each operation function type into structural operation parameters of each operation function type through a data parameter conversion program, and adjust the system structure model of the structural system based on the structural operation parameters of each operation function type to obtain a sub-simulation operation model of the structural system.

[0036] Optionally, the construction module is specifically configured to:

[0037] Based on the system association information between each of the structure systems, identify the association information of each association type between each of the structure systems, and query the interaction type to which each association type belongs in the association database;

[0038] Based on the association information of each association type corresponding to the data interaction type, identify the data interaction information between each of the structure systems and the data transmission information between each of the structure systems, and use the data interaction information between each of the structure systems and the data transmission information between each of the structure systems as the data interaction association information between each of the structure systems;

[0039] Based on the association information of each association type corresponding to the operation interaction type, identify the operation interaction mode between each of the structure systems and the operation interaction process between each of the structure systems, and use the operation interaction mode between each of the structure systems and the operation interaction process between each of the structure systems as the operation interaction association information between each of the structure systems.

[0040] Optionally, the construction module is specifically configured to:

[0041] Based on the operation interaction mode between each of the structure systems and the operation interaction process between each of the structure systems, construct the simulation operation interaction process between each of the structure systems;

[0042] Based on the data interaction information between each of the structure systems and the data transmission information between each of the structure systems, construct the simulation data interaction process between each of the structure systems;

[0043] Use the simulation operation interaction process between each of the structure systems and the simulation data interaction process between each of the structure systems as the simulation interaction information between each of the structure systems.

[0044] Optionally, the acquisition module is specifically configured to:

[0045] Acquire the physical connection information between each of the structure systems, and based on the physical connection information between each of the structure systems, perform model connection processing on the sub-simulation operation models of each of the structure systems to obtain the combined three-dimensional structure model of the aero-engine;

[0046] Based on the simulation interaction information between each of the structure systems, construct the simulation interaction parameters between each of the structure systems in the combined three-dimensional structure model, and adjust the combined three-dimensional structure model with the simulation interaction parameters between all the structure systems to obtain the combined simulation model of the aero-engine.

[0047] Optionally, the identification module is specifically configured to:

[0048] Split the combined simulation results into the system simulation results of each of the structural systems;

[0049] Based on the simulation interaction information between each of the structural systems, identify the system association solution order between each of the structural systems and the system algorithm solution order corresponding to the system simulation solution algorithms of each of the structural systems, and based on the system simulation results of each of the structural systems, according to the simulation solution order of each structural system, respectively calculate the system simulation solution data of each structural system through the system simulation solution algorithms of each structural system;

[0050] Based on the system simulation solution data of each structural system, calculate the operation solution data of the aero-engine according to the system association solution algorithm between each structural system.

[0051] In a third aspect, the present application provides a computer device. The computer device includes a memory and a processor. The memory stores a computer program, and when the processor executes the computer program, the steps of the method according to any one of the first aspects are implemented.

[0052] In a fourth aspect, the present application provides a computer-readable storage medium. A computer program is stored thereon, and when the computer program is executed by a processor, the steps of the method according to any one of the first aspects are implemented.

[0053] In a fifth aspect, the present application provides a computer program product. The computer program product includes a computer program, and when the computer program is executed by a processor, the steps of the method according to any one of the first aspects are implemented.

[0054] The above simulation solution method, device, and computer equipment for an aero-engine obtain the system operation function information of each structural system of the aero-engine, the system structure data of each structural system, and the system association information between each structural system, and construct sub-simulation operation models of each structural system based on the system operation function information of each structural system and the system structure data of each structural system; identify the data interaction association information and the operation interaction association information between each structural system based on the system association information between each structural system, and construct the simulation interaction information between each structural system based on the data interaction association information between each structural system and the operation interaction association information between each structural system; perform simulation association processing on each structural system based on the simulation interaction information between each structural system to obtain the joint simulation model of the aero-engine, and collect the demand input data of the aero-engine; generate the joint simulation result of the aero-engine through the joint simulation model of the aero-engine based on the demand input data, and identify the operation solution data of the aero-engine through the joint simulation solution algorithm based on the joint simulation result. In this solution, after separately performing simulation modeling on each structural system from the system operation function information, system structure data, and system association information of each structural system, the simulation interaction information between each structural system is identified. Finally, based on this simulation interaction information, a joint simulation model of the aero-engine that can separately simulate and jointly perform data interaction is constructed, which not only avoids the problem of large simulation deviation in single-system modeling, but also through this joint simulation model, when simulating the operation of the aero-engine, the simulation operation data and simulation operation results of each system can be separately identified, thereby improving the simulation accuracy of the aero-engine. Finally, in the actual simulation process of this solution, through the constructed joint simulation solution algorithm, the joint simulation result of the aero-engine is solved distributively and jointly in a progressive manner, avoiding the significant increase in the number of solution equations caused by unified modeling, resulting in a significant increase in the solution difficulty, and the problems of long solution time and difficult convergence. Thus, while improving the simulation accuracy of the aero-engine, the simulation efficiency and simulation convergence robustness of the aero-engine are effectively improved. BRIEF DESCRIPTION OF THE DRAWINGS

[0055] In order to more clearly illustrate the technical solutions in the embodiments of the present application or related technologies, the following will briefly introduce the drawings required for use in the description of the embodiments or related technologies. Obviously, the drawings in the following description are only some embodiments of the present application. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts.

[0056] Figure 1Schematic diagram of the simulation solution method of an aeroengine in an embodiment;

[0057] Figure 2 Schematic diagram of the simulation solution example of an aeroengine in an embodiment;

[0058] Figure 3 Structural block diagram of the simulation solution device of an aeroengine in an embodiment;

[0059] Figure 4 Internal structure diagram of a computer device in an embodiment. Detailed implementation manners

[0060] In order to make the objectives, technical solutions and advantages of the present application clearer and more understandable, the present application will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present application, and are not used to limit the present application.

[0061] The simulation solution method of the aeroengine provided by the embodiment of the present application can be applied to the application environment of the joint simulation of multiple systems of the aeroengine. Among them, this method can be applied to a terminal, or to a server, or to a system including a terminal and a server, and is realized through the interaction between the terminal and the server. Among them, the terminal can be, but is not limited to, various personal computers, laptop computers, medium-sized computers, etc. Among them, after the terminal respectively performs simulation modeling on each structural system based on the system operation function information, system structure data, and system association information of each structural system, the simulation interaction information between each structural system is identified. Finally, based on this simulation interaction information, a joint simulation model of the aeroengine that can perform separate simulation and joint data interaction is constructed, which not only avoids the problem of large simulation deviation in single-system modeling, but also through this joint simulation model, when simulating the operation of the aeroengine, the simulation operation data and simulation operation results of each system can be respectively identified, thereby improving the simulation accuracy of the aeroengine. Finally, in the actual simulation process of this solution, through the constructed joint simulation solution algorithm, the joint simulation results of the aeroengine are solved distributively and jointly in a progressive manner, avoiding the problem that the number of solution equations increases significantly after unified modeling, resulting in a significant increase in the difficulty of solution, and being prone to problems such as long solution time and difficult convergence. Therefore, while improving the simulation accuracy of the aeroengine, the simulation efficiency and simulation convergence robustness of the aeroengine are effectively improved.

[0062] In an exemplary embodiment, as Figure 1 shown, a simulation solution method of an aeroengine is provided. Taking this method applied to a terminal as an example, it includes the following steps S101 to S104. Among them:

[0063] Step S101: Obtain the system operation function information of each structural system of the aero-engine, the system structure data of each structural system, and the system association information between each structural system, and construct a sub-simulation operation model for each structural system based on the system operation function information of each structural system and the system structure data of each structural system.

[0064] In this embodiment, in response to the information upload operation of the staff, the terminal obtains the system operation function information of each structural system of the aero-engine, the system structure data of each structural system, and the system association information between each structural system. Among them, each system structure is each equipment structure that makes up the aero-engine. The system structure includes an intake system, a compression system, a combustion chamber system, a turbine system, an exhaust system, a fuel supply system, etc. The system operation function information includes the system function of each system structure and the system operation information of each system structure. The system structure data is the system three-dimensional structure data of each system structure, which can be obtained after the staff performs three-dimensional scanning on each system structure. The system association information between each system structure includes the association information of each association type. Each association type is used to characterize the data interaction association and the operation interaction association between two system structures, etc. The association type includes but is not limited to the data transmission direction type, the data format conversion type, the data transmission restriction type, the operation function interaction type, the operation mode interaction type, and the operation process interaction type, etc. Among them, the association types belonging to the data interaction type include but are not limited to the data transmission direction type, the data format conversion type, and the data transmission restriction type, etc., and the association types belonging to the operation interaction type include but are not limited to the operation function interaction type, the operation mode interaction type, and the operation process interaction type, etc. The specific identification is very high and will be described in detail later. Finally, the terminal constructs a sub-simulation operation model for each structural system based on the system operation function information of each structural system and the system structure data of each structural system. Each sub-simulation operation model can simulate the operation process of the structural system.

[0065] Step S102: Based on the system association information between each structural system, identify the data interaction association information between each structural system and the operation interaction association information between each structural system, and construct the simulation interaction information between each structural system based on the data interaction association information between each structural system and the operation interaction association information between each structural system.

[0066] In this embodiment, the terminal identifies the data interaction association information and the operation interaction association information between each structural system based on the system association information between each structural system, and constructs the simulation interaction information between each structural system based on the data interaction association information and the operation interaction association information between each structural system. Among them, the data interaction association information includes the data interaction information and the data transmission information between each structural system, and the operation interaction association information includes the operation interaction mode and the operation interaction process between each structural system. The specific identification process will be described in detail later. The constructed simulation interaction information between each system is the simulation operation interaction process and the simulation data interaction process between each structural system. The specific construction process will be described in detail later.

[0067] Step S103: Based on the simulation interaction information between each structural system, perform simulation association processing on each structural system to obtain a joint simulation model of the aeroengine, and collect the required input data of the aeroengine.

[0068] In this embodiment, the terminal performs simulation association processing on each structural system based on the simulation interaction information between each structural system to obtain a joint simulation model of the aeroengine, and collects the required input data of the aeroengine. Among them, the simulation association processing process is to perform data association on the simulation operation processes of each structural system, so as to ensure that the joint simulation process between each structural system can be realized during the simulation operation process. The specific association processing process will be described in detail later. Then, the terminal collects the required input data of the aeroengine, and this required input data is the data information corresponding to the operating conditions, operating modes, and operating processes that the staff needs to simulate for the aeroengine. This data information is the data information uploaded by the staff to the terminal and can change with the adjustment of the staff.

[0069] Step S104: Based on the required input data, generate the joint simulation results of the aeroengine through the joint simulation model of the aeroengine, and identify the operation solution data of the aeroengine through the joint simulation solution algorithm based on the joint simulation results.

[0070] In this embodiment, the terminal generates the joint simulation results of the aeroengine through the joint simulation model of the aeroengine based on the required input data, and identifies the operation solution data of the aeroengine through the joint simulation solution algorithm based on the joint simulation results. Among them, the joint simulation solution algorithm includes the system simulation solution algorithms of each structural system and the system association solution algorithms between each structural system, and the solution methods of the system association solution algorithms and the solution methods of the system simulation solution algorithms will be described in detail later.

[0071] Based on the above solution, after separately simulating and modeling each structural system through the system operation function information, system structure data, and system association information of each structural system, the simulation interaction information between each structural system is identified. Finally, based on this simulation interaction information, a joint simulation model of an aeroengine capable of separate simulation and joint data interaction is constructed, which not only avoids the problem of large simulation deviation in single-system modeling, but also through this joint simulation model, when simulating the operation of an aeroengine, the simulation operation data and simulation operation results of each system can be separately identified, thereby improving the simulation accuracy of the aeroengine. Finally, in the actual simulation process of this solution, through the constructed joint simulation solution algorithm, the joint simulation results of the aeroengine are solved distributively and jointly in a progressive manner, avoiding the significant increase in the number of solution equations caused by unified modeling, resulting in a significant increase in the difficulty of solution, and easily causing problems such as long solution time and difficult convergence. Thus, while improving the simulation accuracy of the aeroengine, the simulation efficiency and simulation convergence robustness of the aeroengine are effectively improved.

[0072] Optionally, based on the system operation function information of each structural system and the system structure data of each structural system, a sub-simulation operation model of each structural system is constructed, including: based on the system structure data of each structural system, through a three-dimensional modeling program, a system structure model of each structural system is constructed, and for each structural system, based on the system operation function information of the structural system, the structural operation data of each operation function type is identified; based on the structural operation data of each operation energy supply type, through a data parameter conversion program, the structural operation data of each operation function type is converted into the structural operation data of each operation function type, and based on the structural operation data of each operation function type, the system structure model of the structural system is adjusted to obtain the sub-simulation operation model of the structural system.

[0073] In this embodiment, the terminal constructs the system structure models of each structural system through a 3D modeling program based on the system structure data of each structural system, and for each structural system, based on the system operation function information of the structural system, identifies the structural operation data of each operation function type. Among them, the 3D modeling program is a method of structural modeling based on modeling languages such as Modelica, C / C++, Fortran, and Python. Then, based on the structural operation data of each operation energy supply type, the terminal converts the structural operation data of each operation function type into the structural operation parameters of each operation function type through a data parameter conversion program, and based on the structural operation parameters of each operation function type, adjusts the system structure model of the structural system to obtain the sub-simulation operation model of the structural system. Among them, the data parameter conversion program stores the data conversion instructions between the structural operation data and the structural operation parameters of different operation function types. Then, the terminal generates the structural operation parameters of each operation function type through the data conversion instructions of each operation function type. Among them, each operation function type is the function type corresponding to each operation function included in each structural system. For example, the operation functions of the fuel supply system include the fuel supply function, the fuel regulation function, and the fuel protection function. Then, the operation function types of the fuel supply system include the fuel supply function type, the fuel regulation function type, and the fuel protection function type.

[0074] Based on the above solution, by performing 3D structural modeling on each structural system and splitting and converting based on the structural operation data of each structural system, the sub-simulation operation model of each structural system is generated, improving the operation practicality and simulation accuracy of the constructed sub-simulation operation model.

[0075] Optionally, based on the system association information between each structural system, identify the data interaction association information and the operation interaction association information between each structural system, including: based on the system association information between each structural system, identify the association information of each association type between each structural system, and in the association database, query the interaction type to which each association type belongs; based on the association information of each association type corresponding to the data interaction type, identify the data interaction information and the data transmission information between each structural system, and use the data interaction information and the data transmission information between each structural system as the data interaction association information between each structural system; based on the association information of each association type corresponding to the operation interaction type, identify the operation interaction method and the operation interaction process between each structural system, and use the operation interaction method and the operation interaction process between each structural system as the operation interaction association information between each structural system.

[0076] In this embodiment, the terminal identifies the association information of each association type between each structural system based on the system association information between each structural system, and queries the interaction type to which each association type belongs in the association database. The association database stores the ranges of each interaction type corresponding to the data interaction type and the ranges of each interaction type corresponding to the operation interaction type. Then, the terminal identifies the association types corresponding to the data interaction type and the association types corresponding to the operation interaction type by means of range query.

[0077] Subsequently, the terminal identifies the data interaction information between each structural system and the data transmission information between each structural system based on the association information of each association type corresponding to the data interaction type, and takes the data interaction information between each structural system and the data transmission information between each structural system as the data interaction association information between each structural system. Each association type corresponding to the data interaction type includes the association types for data transmission and the association types for data interaction. The terminal summarizes the association information of the association types for data transmission to obtain the data interaction information between each structural system. Then, the terminal summarizes the association information of the association types for data interaction to obtain the data transmission information between each structural system.

[0078] The terminal identifies the operation interaction mode between each structural system and the operation interaction process between each structural system based on the association information of each association type corresponding to the operation interaction type, and takes the operation interaction mode between each structural system and the operation interaction process between each structural system as the operation interaction association information between each structural system. Each association type corresponding to the operation interaction type includes the association types for the interaction mode and the association types for the interaction process. The terminal summarizes the association information of the association types for the interaction mode to obtain the operation interaction mode between each structural system. Then, the terminal summarizes the association information of the association types for the interaction process to obtain the operation interaction process between each structural system.

[0079] Based on the above solution, by means of data query, the association information is split into the association information of each association type, and the association information of each association type is summarized according to the data interaction type and the operation interaction type respectively, so as to obtain the operation interaction association information between each structural system and the data interaction association information between each structural system, improving the comprehensiveness and accuracy of the identification of the operation interaction association information and the data interaction association information between each structural system.

[0080] Optionally, based on the data interaction correlation information and the operation interaction correlation information between each structural system, construct the simulation interaction information between each structural system, including: based on the operation interaction mode and the operation interaction process between each structural system, construct the simulation operation interaction process between each structural system; based on the data interaction information and the data transmission information between each structural system, construct the simulation data interaction process between each structural system; use the simulation operation interaction process and the simulation data interaction process between each structural system as the simulation interaction information between each structural system.

[0081] In this embodiment, the terminal constructs the simulation operation interaction process between each structural system based on the operation interaction mode and the operation interaction process between each structural system. Among them, the construction method is to use the modeling languages corresponding to languages such as Modelica, C / C++, Fortran, and Python to convert the operation interaction mode and the operation interaction process between each structural system into the operation process between each structural system (including process information such as operation interaction sequence, operation interaction process, and operation interaction scope), so as to obtain the simulation operation interaction process between each structural system.

[0082] Subsequently, the terminal constructs the simulation data interaction process between each structural system based on the data interaction information and the data transmission information between each structural system. Then, the terminal uses the simulation operation interaction process and the simulation data interaction process between each structural system as the simulation interaction information between each structural system. Among them, the construction method is to use the modeling languages corresponding to languages such as Modelica, C / C++, Fortran, and Python to convert the data interaction information and the data transmission information between each structural system into the data transmission process between each structural system (including data interaction information such as data transmission direction, data transmission limit, and data transmission format conversion and adjustment), so as to obtain the simulation data interaction process between each structural system.

[0083] Based on the above solution, by constructing the simulation operation interaction process and the simulation data interaction process between each structural system, the practicality and accuracy of the simulation interaction between each structural system are ensured.

[0084] Optionally, based on the simulation interaction information between each structural system, perform simulation correlation processing on each structural system to obtain a joint simulation model of the aeroengine, including: collecting the physical connection information between each structural system, and based on the physical connection information between each structural system, performing model connection processing on the sub-simulation operation models of each structural system to obtain a joint three-dimensional structural model of the aeroengine; based on the simulation interaction information between each structural system, constructing the simulation interaction parameters between each structural system in the joint three-dimensional structural model, and using the simulation interaction parameters between all structural systems to adjust the joint three-dimensional structural model to obtain a joint simulation model of the aeroengine.

[0085] In this embodiment, the terminal collects the physical connection information between each structural system, and based on the physical connection information between each structural system, performs model connection processing on the sub-simulation operation models of each structural system to obtain a joint three-dimensional structural model of the aeroengine. Among them, the physical connection information is the connection information such as the connection points between two structural systems, the connection methods of each connection point, and the connection angles of each connection point.

[0086] Subsequently, the terminal constructs the simulation interaction parameters between each structural system in the joint three-dimensional structural model based on the simulation interaction information between each structural system, and uses the simulation interaction parameters between all structural systems to adjust the joint three-dimensional structural model to obtain a joint simulation model of the aeroengine. Among them, the terminal presets the parameter conversion strategy corresponding to the simulation data interaction process and the parameter conversion strategy corresponding to the simulation operation interaction process, so as to convert each simulation interaction process into simulation interaction parameters, improving the conversion efficiency of the simulation interaction parameters.

[0087] Based on the above solution, after performing structural connection through the physical connection information, convert the simulation operation interaction process and the simulation data interaction process, and finally construct a joint simulation model of the aeroengine, improving the construction efficiency and practicality of the joint simulation model.

[0088] Optionally, the co-simulation solution algorithm includes the system simulation solution algorithms for each structural system and the system association solution algorithms between each structural system. Based on the co-simulation results, through the co-simulation solution algorithm, the operating solution data of the aero-engine is identified, including: splitting the co-simulation results into the system simulation results of each structural system; based on the simulation interaction information between each structural system, identifying the system association solution order between each structural system and the system algorithm solution order corresponding to the system simulation solution algorithms of each structural system, and based on the system simulation results of each structural system, according to the simulation solution order of each structural system, respectively calculating the system simulation solution data of each structural system through the system simulation solution algorithms of each structural system; based on the system simulation solution data of each structural system, calculating the operating solution data of the aero-engine according to the system association solution algorithm between each structural system.

[0089] In this embodiment, the terminal splits the co-simulation results into the system simulation results of each structural system. Then, the terminal, based on the simulation interaction information between each structural system, identifies the system association solution order between each structural system and the system algorithm solution order corresponding to the system simulation solution algorithms of each structural system, and based on the system simulation results of each structural system, according to the simulation solution order of each structural system, respectively calculates the system simulation solution data of each structural system through the system simulation solution algorithms of each structural system. Finally, based on the system simulation solution data of each structural system, the operating solution data of the aero-engine is calculated according to the system association solution algorithm between each structural system.

[0090] Specifically, in the co-simulation model, there are M subsystem models and N equations to be solved, where N > M and M >= 1. In the i-th subsystem model, there are Ni equations to be solved, i = 1, 2, 3, …, M, Ni >= 0, and N >= , assuming that the simulation calculation at the k-th moment has been completed, the following steps are used to solve the above N equations to be solved at the (k + 1)-th moment, where k >= 0.

[0091] S1. Sort the calculation order according to the connection relationship of each subsystem model in the above co-simulation model to obtain the calculation order sequence of M subsystem models, and go to step S2.

[0092] S2. According to the given calculation order sequence, solve each subsystem in turn. According to the latest input data of each subsystem and the current simulation data of the system, use the solver corresponding to each subsystem to solve the equations to be solved of each subsystem model and update the model interaction interface data; after completing the solution calculation of all subsystem models, go to step S3.

[0093] S3. According to the solution calculation results of each subsystem model, solve the remaining N -

[0094] simulations to be solved in the co - simulation model. If the solution results can converge, go to S4; if the solution results cannot converge, go to step S2.

[0095] S4. Output the operation solution data at the (k + 1) - th moment.

[0096] Based on the above - mentioned scheme, the originally mutually - coupled high - dimensional equations to be solved are decomposed into multiple subsystem models according to different specialties of each subsystem, and then are solved separately according to the solvers required by each specialty. Then, solve the equations to be solved between each subsystem. After all the solutions are completed, the solution calculation of the entire co - simulation model can be realized. In this process, on the one hand, the correctness of the entire solution simulation calculation results is ensured because all the solution equations are satisfied; on the other hand, through the scheme of decomposing and separately solving the equations to be solved, the effect of dimension - reduction calculation is realized, which can reduce the overall solution difficulty and calculation amount and improve the simulation calculation efficiency.

[0097] This application also provides a simulation solution example of an aero - engine. As Figure 2 shown, the specific processing process includes the following steps:

[0098] Step S201, obtain the system operation function information of each structural system of the aero - engine, the system structure data of each said structural system, and the system association information between each said structural system.

[0099] Step S202, based on the system structure data of each said structural system, through a 3D modeling program, construct the system structure model of each said structural system, and for each structural system, based on the system operation function information of the structural system, identify the structural operation data of each operation function type.

[0100] Step S203, based on the structural operation data of each operation energy supply type, through a data parameter conversion program, convert the structural operation data of each said operation function type into the structural operation parameters of each said operation function type, and based on the structural operation parameters of each said operation function type, adjust the system structure model of the structural system to obtain the sub - simulation operation model of the structural system.

[0101] Step S204, based on the system association information between each said structural system, identify the association information of each association type between each said structural system, and in the association database, query the interaction type to which each association type belongs.

[0102] Step S205: Based on the association information of each association type corresponding to the data interaction type, identify the data interaction information and the data transmission information between each of the structural systems, and use the data interaction information and the data transmission information between each of the structural systems as the data interaction association information between each of the structural systems.

[0103] Step S206: Based on the association information of each association type corresponding to the operation interaction type, identify the operation interaction mode and the operation interaction process between each of the structural systems, and use the operation interaction mode and the operation interaction process between each of the structural systems as the operation interaction association information between each of the structural systems.

[0104] Step S207: Based on the operation interaction mode and the operation interaction process between each of the structural systems, construct the simulation operation interaction process between each of the structural systems.

[0105] Step S208: Based on the data interaction information and the data transmission information between each of the structural systems, construct the simulation data interaction process between each of the structural systems.

[0106] Step S209: Use the simulation operation interaction process and the simulation data interaction process between each of the structural systems as the simulation interaction information between each of the structural systems.

[0107] Step S210: Collect the physical connection information between each of the structural systems, and based on the physical connection information between each of the structural systems, perform model connection processing on the sub-simulation operation models of each of the structural systems to obtain the combined three-dimensional structure model of the aero-engine.

[0108] Step S211: Based on the simulation interaction information between each of the structural systems, construct the simulation interaction parameters between each of the structural systems in the combined three-dimensional structure model, and use the simulation interaction parameters between all the structural systems to adjust the combined three-dimensional structure model to obtain the combined simulation model of the aero-engine.

[0109] Step S212: Collect the required input data of the aero-engine.

[0110] Step S213: Split the combined simulation result into the system simulation results of each of the structural systems.

[0111] Step S214: Based on the simulation interaction information between the structure systems, identify the system association solution sequence between the structure systems and the system algorithm solution sequence corresponding to the system simulation solution algorithms of each structure system. And based on the system simulation results of each structure system, calculate the system simulation solution data of each structure system through the system simulation solution algorithms of each structure system according to the simulation solution sequence of each structure system.

[0112] Step S215: Based on the system simulation solution data of each structure system, calculate the operation solution data of the aero-engine according to the system association solution algorithm between each structure system.

[0113] It should be understood that although the steps in the flowcharts involved in the above embodiments are displayed in sequence according to the arrows, these steps are not necessarily executed in the order indicated by the arrows. Unless there is a clear description in this article, the execution of these steps has no strict order limit, and these steps can be executed in other orders. Moreover, at least a part of the steps in the flowcharts involved in the above embodiments may include multiple steps or multiple stages. These steps or stages are not necessarily executed at the same time, but can be executed at different times. The execution order of these steps or stages is not necessarily sequential, but can be executed alternately or in turn with at least a part of other steps or steps or stages in other steps.

[0114] Based on the same inventive concept, an embodiment of the present application further provides a simulation solution device for an aero-engine for implementing the above-mentioned simulation solution method for an aero-engine. The solution provided by this device for solving problems is similar to the solution described in the above method. Therefore, the specific limitations in one or more embodiments of the following simulation solution device for an aero-engine can refer to the limitations on the simulation solution method for an aero-engine in the above text, and will not be repeated here.

[0115] In an exemplary embodiment, as Figure 3 shown, a simulation solution device for an aero-engine is provided, including: an acquisition module 310, a construction module 320, a collection module 330, and an identification module 340, where:

[0116] The acquisition module 310 is configured to acquire the system operation function information of each structure system of the aero-engine, the system structure data of each structure system, and the system association information between each structure system, and construct a sub-simulation operation model of each structure system based on the system operation function information of each structure system and the system structure data of each structure system.

[0117] A construction module 320, configured to identify the data interaction correlation information and the operation interaction correlation information between each of the structural systems based on the system correlation information between the structural systems, and construct the simulation interaction information between each of the structural systems based on the data interaction correlation information and the operation interaction correlation information between each of the structural systems;

[0118] An acquisition module 330, configured to perform simulation correlation processing on each of the structural systems based on the simulation interaction information between each of the structural systems to obtain a combined simulation model of the aeroengine, and acquire the required input data of the aeroengine;

[0119] An identification module 340, configured to generate a combined simulation result of the aeroengine through the combined simulation model of the aeroengine based on the required input data, and identify the operation solution data of the aeroengine through a combined simulation solution algorithm based on the combined simulation result.

[0120] Optionally, the obtaining module 310 is specifically configured to:

[0121] Based on the system structure data of each of the structural systems, construct a system structure model of each of the structural systems through a 3D modeling program, and for each structural system, identify the structural operation data of each operation function type based on the system operation function information of the structural system;

[0122] Based on the structural operation data of each operation energy supply type, convert the structural operation data of each operation function type into the structural operation parameters of each operation function type through a data parameter conversion program, and adjust the system structure model of the structural system based on the structural operation parameters of each operation function type to obtain a sub-simulation operation model of the structural system.

[0123] Optionally, the construction module 320 is specifically configured to:

[0124] Based on the system correlation information between each of the structural systems, identify the correlation information of each correlation type between each of the structural systems, and query the interaction type to which each correlation type belongs in the correlation database;

[0125] Based on the correlation information of each correlation type corresponding to the data interaction type, identify the data interaction information and the data transmission information between each of the structural systems, and use the data interaction information and the data transmission information between each of the structural systems as the data interaction correlation information between each of the structural systems;

[0126] Based on the association information of each association type corresponding to the operation interaction type, identify the operation interaction method and the operation interaction process between each of the structure systems, and use the operation interaction method and the operation interaction process between each of the structure systems as the operation interaction association information between each of the structure systems.

[0127] Optionally, the construction module 320 is specifically configured to:

[0128] Based on the operation interaction method and the operation interaction process between each of the structure systems, construct a simulation operation interaction process between each of the structure systems;

[0129] Based on the data interaction information and the data transmission information between each of the structure systems, construct a simulation data interaction process between each of the structure systems;

[0130] Use the simulation operation interaction process and the simulation data interaction process between each of the structure systems as the simulation interaction information between each of the structure systems.

[0131] Optionally, the acquisition module 330 is specifically configured to:

[0132] Acquire the physical connection information between each of the structure systems, and based on the physical connection information between each of the structure systems, perform model connection processing on the sub-simulation operation models of each of the structure systems to obtain the combined three-dimensional structure model of the aero-engine;

[0133] Based on the simulation interaction information between each of the structure systems, construct the simulation interaction parameters between each of the structure systems in the combined three-dimensional structure model, and adjust the combined three-dimensional structure model with the simulation interaction parameters between all the structure systems to obtain the combined simulation model of the aero-engine.

[0134] Optionally, the identification module 340 is specifically configured to:

[0135] Split the combined simulation result into the system simulation results of each of the structure systems;

[0136] Based on the simulation interaction information between each of the structure systems, identify the system association solution order between each of the structure systems and the system algorithm solution order corresponding to each system simulation solution algorithm of each of the structure systems, and based on the system simulation results of each of the structure systems, according to the simulation solution order of each structure system, calculate the system simulation solution data of each structure system through the system simulation solution algorithm of each structure system respectively;

[0137] Based on the system simulation solution data of each structural system, calculate the operation solution data of the aeroengine according to the system association solution algorithm between each structural system.

[0138] Each module in the above aeroengine simulation solution device can be implemented in whole or in part by software, hardware, and their combination. Each of the above modules can be embedded in or independent of the processor in the computer device in the form of hardware, or stored in the memory of the computer device in the form of software, so that the processor can call and execute the operations corresponding to each of the above modules.

[0139] In an exemplary embodiment, a computer device is provided. The computer device can be a terminal, and its internal structure diagram can be as Figure 4 shown. The computer device includes a processor, a memory, an input / output interface, a communication interface, a display unit, and an input device. Among them, the processor, the memory, and the input / output interface are connected through a system bus, and the communication interface, the display unit, and the input device are connected to the system bus through the input / output interface. Among them, the processor of the computer device is used to provide computing and control capabilities. The memory of the computer device includes a non-volatile storage medium and an internal memory. The non-volatile storage medium stores an operating system and a computer program. The internal memory provides an environment for the operation of the operating system and the computer program in the non-volatile storage medium. The input / output interface of the computer device is used for exchanging information between the processor and external devices. The communication interface of the computer device is used for communicating with external terminals in a wired or wireless manner, and the wireless manner can be implemented through WIFI, a mobile cellular network, NFC (Near Field Communication), or other technologies. When the computer program is executed by the processor, it implements a method for simulating and solving an aeroengine. The display unit of the computer device is used to form a visually visible picture, which can be a display screen, a projection device, or a virtual reality imaging device. The display screen can be a liquid crystal display screen or an electronic ink display screen. The input device of the computer device can be a touch layer covering the display screen, or a button, a trackball, or a touchpad provided on the housing of the computer device, or an external keyboard, a touchpad, or a mouse, etc.

[0140] Those skilled in the art can understand that Figure 4 the structure shown in

[0141] In an exemplary embodiment, a computer device is provided, including a memory and a processor. A computer program is stored in the memory, and when the processor executes the computer program, the steps of the simulation solution method for an aeroengine are implemented.

[0142] In an embodiment, a computer-readable storage medium is provided, on which a computer program is stored. When the computer program is executed by a processor, the steps of the simulation solution method for an aeroengine are implemented.

[0143] In an embodiment, a computer program product is provided, including a computer program. When the computer program is executed by a processor, the steps of the simulation solution method for an aeroengine are implemented.

[0144] It should be noted that the user information (including but not limited to user device information, user personal information, etc.) and data (including but not limited to data for analysis, stored data, displayed data, etc.) involved in this application are all information and data authorized by the user or fully authorized by all parties, and the collection, use, and processing of relevant data need to comply with relevant regulations.

[0145] Those of ordinary skill in the art can understand that all or part of the processes in the methods of the above embodiments can be completed by instructing relevant hardware through a computer program. The computer program can be stored in a non-volatile computer-readable storage medium. When the computer program is executed, it can include the processes of the embodiments of the above methods. Among them, any reference to a memory, database, or other medium used in the embodiments provided in the present application can include at least one of non-volatile and volatile memories. Non-volatile memories can include read-only memory (ROM), magnetic tapes, floppy disks, flash memories, optical memories, high-density embedded non-volatile memories, resistive random access memories (ReRAM), magnetoresistive random access memories (MRAM), ferroelectric random access memories (FRAM), phase change memories (PCM), graphene memories, etc. Volatile memories can include random access memory (RAM) or external cache memories, etc. By way of illustration and not limitation, RAM can be in various forms, such as static random access memory (SRAM) or dynamic random access memory (DRAM), etc. The databases involved in the embodiments provided in the present application can include at least one of relational databases and non-relational databases. Non-relational databases can include distributed databases based on blockchain, etc., without limitation. The processors involved in the embodiments provided in the present application can be general-purpose processors, central processing units, graphics processing units, digital signal processors, programmable logic devices, data processing logics based on quantum computing, etc., without limitation.

[0146] The technical features of the above embodiments can be combined arbitrarily. For the sake of brevity of description, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, it should be considered as the scope recorded in this specification.

[0147] The above-described embodiments merely represent several implementation manners of the present application. The description thereof is relatively specific and detailed, but it should not be construed as a limitation on the patent scope of the present application. It should be noted that for those of ordinary skill in the art, without departing from the concept of the present application, several modifications and improvements can still be made, and these all belong to the protection scope of the present application. Therefore, the protection scope of the present application should be subject to the appended claims.

Claims

1. A simulation solution method for an aircraft engine, characterized in that: The method comprises: Acquire system operation function information of each structural system of the aircraft engine, system structure data of each structural system, and system association information between each structural system, and construct a sub-simulation operation model of each structural system based on the system operation function information of each structural system and the system structure data of each structural system; Based on the system association information between the structural systems, identifying the data interaction association information between the structural systems and the operation interaction association information between the structural systems, and constructing the simulation interaction information between the structural systems based on the data interaction association information between the structural systems and the operation interaction association information between the structural systems; Based on the simulation interaction information between the structural systems, the structural systems are subjected to simulation association processing to obtain a joint simulation model of the aircraft engine, and demand input data of the aircraft engine is collected; Based on the demand input data, a joint simulation result of the aircraft engine is generated through the joint simulation model of the aircraft engine, and based on the joint simulation result, an operation solution data of the aircraft engine is identified through a joint simulation solution algorithm.

2. The method according to claim 1, characterized in that The sub-simulation operation model of each structural system is constructed based on the system operation function information of each structural system and the system structure data of each structural system, including: Based on the system structure data of each of the structural systems, a system structure model of each of the structural systems is constructed through a three-dimensional modeling program, and for each structural system, based on the system operation function information of the structural system, structural operation data of each operation function type is identified; Based on the structural operation data of each operation energy supply type, the structural operation data of each operation function type is converted into structural operation parameters of each operation function type through a data parameter conversion program, and based on the structural operation parameters of each operation function type, the system structure model of the structural system is adjusted to obtain a sub-simulation operation model of the structural system.

3. The method according to claim 1, characterized in that The step of identifying data interaction association information between the structural systems and operation interaction association information between the structural systems based on the system association information between the structural systems includes: Based on the system association information between the structural systems, identifying the association information of each association type between the structural systems, and querying the interaction type to which each association type belongs in the association database; Based on the association information of each association type corresponding to the data interaction type, the data interaction information between each of the structural systems and the data transmission information between each of the structural systems are identified, and the data interaction information between each of the structural systems and the data transmission information between each of the structural systems are used as the data interaction association information between each of the structural systems; Based on the association information of each association type corresponding to the operation interaction type, the operation interaction mode between each of the structural systems and the operation interaction process between each of the structural systems are identified, and the operation interaction mode between each of the structural systems and the operation interaction process between each of the structural systems are used as the operation interaction association information between each of the structural systems.

4. The method according to claim 3, characterized in that The constructing simulation interaction information between the structural systems based on the data interaction association information between the structural systems and the operation interaction association information between the structural systems comprises: Based on the operation interaction mode and the operation interaction process between the structural systems, construct a simulation operation interaction process between the structural systems; Based on the data interaction information between the structural systems and the data transmission information between the structural systems, construct a simulation data interaction process between the structural systems; The simulation operation interaction process between the structural systems and the simulation data interaction process between the structural systems are used as the simulation interaction information between the structural systems.

5. The method according to claim 4, characterized in that The method of performing simulation association processing on each of the structural systems based on the simulation interaction information between the structural systems to obtain a joint simulation model of the aircraft engine includes: Collecting physical connection information between the structural systems, and based on the physical connection information between the structural systems, performing model connection processing on the sub-simulation operation models of the structural systems to obtain a joint three-dimensional structural model of the aircraft engine; Based on the simulation interaction information between the structural systems, the simulation interaction parameters between the structural systems in the joint three-dimensional structural model are constructed, and the simulation interaction parameters between all the structural systems are used to adjust the joint three-dimensional structural model to obtain the joint simulation model of the aircraft engine.

6. The method according to claim 1, characterized in that The joint simulation solution algorithm includes a system simulation solution algorithm for each structural system and a system association solution algorithm between each structural system. Based on the joint simulation result, the operation solution data of the aircraft engine is identified by the joint simulation solution algorithm, including: Splitting the joint simulation result into system simulation results of each of the structural systems; Based on the simulation interaction information between the structural systems, the system association solution order between the structural systems and the system algorithm solution order corresponding to the system simulation solution algorithm of each structural system are identified; and based on the system simulation results of each structural system, according to the simulation solution order of each structural system, the system simulation solution data of each structural system is calculated respectively by the system simulation solution algorithm of each structural system; Based on the system simulation solution data of each structural system and according to the system association solution algorithm between each structural system, the operation solution data of the aircraft engine is calculated.

7. A simulation solution device for an aircraft engine, characterized in that: The device comprises: An acquisition module, used to acquire system operation function information of each structural system of the aircraft engine, system structure data of each structural system, and system association information between each structural system, and to construct a sub-simulation operation model of each structural system based on the system operation function information of each structural system and the system structure data of each structural system; A construction module, used to identify data interaction association information between the structural systems and operation interaction association information between the structural systems based on the system association information between the structural systems, and to construct simulation interaction information between the structural systems based on the data interaction association information between the structural systems and the operation interaction association information between the structural systems; A collection module, used for performing simulation association processing on each of the structural systems based on the simulation interaction information between the structural systems, obtaining a joint simulation model of the aircraft engine, and collecting required input data of the aircraft engine; An identification module is used to generate a joint simulation result of the aircraft engine through a joint simulation model of the aircraft engine based on the required input data, and to identify the operation solution data of the aircraft engine through a joint simulation solution algorithm based on the joint simulation result.

8. A computer device comprising a memory and a processor, wherein the memory stores a computer program, wherein: When the processor executes the computer program, the steps of the method according to any one of claims 1 to 6 are implemented.

9. A computer-readable storage medium having a computer program stored thereon, characterized in that: When the computer program is executed by a processor, the steps of the method according to any one of claims 1 to 6 are implemented.

10. A computer program product, comprising a computer program, characterized in that When the computer program is executed by a processor, the steps of the method according to any one of claims 1 to 6 are implemented.

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