A product configuration method based on the modularization of aero-engine unit

Abstract

The present application provides a product configuration method based on the modularization of aero-engine unit bodies, belonging to the technical field of aero-engines. The method includes dividing an aero-engine into multiple unit bodies based on requirement analysis, where each unit body includes multiple configuration schemes; for each unit body, obtaining the attribute information of each configuration scheme, and determining whether the configuration scheme meets the preset unit body warehousing criteria based on the attribute information; based on the compliant configuration schemes and the corresponding attribute information, constructing a unit body module database, where each configuration scheme corresponds to a unit body module; based on the target requirements of a new product, determining the target unit body and the corresponding design requirements; based on the unit body module database, performing the configuration combination of each unit body module that meets the design requirements of the target unit body, and optimizing the configuration combination based on the unit body module unit values to obtain the final complete product design scheme. This can reduce the design cost, shorten the product maturity cycle, and support the rapid series development and derivative development of products.

Description

Technical Field

[0001] This application relates to the technical field of aero-engines, and in particular to a product configuration method based on the modularization of aero-engine unit bodies. Background Art

[0002] The development of China's aero-engine industry faces the dilemma that the research and development of advanced aero-engine products lags behind the equipment requirements. On the one hand, the product configuration is deeply coupled with technology, and there are difficulties in the effective application and transformation of technology. On the other hand, the aero-engine research and development requirements in the early stage are often relatively single, and the configurations of different types of aero-engines are basically the same. However, with the increasing multi-dimensional and systematic development requirements of aero-engines, the demand for new configuration aero-engine products is becoming more urgent. The existing single-configuration R & D mode can no longer meet the major requirements of rapid product improvement and agile derivative development.

[0003] In the field of aircraft, there are similar research results in the civil aircraft industry. For example, a civil aircraft configuration-based configuration management method and device proposed in Patent CN111177847B mainly describes the configuration-based configuration management method in the field of civil aircraft, focusing on the configuration baseline and configuration change management process based on the configuration library. The interfaces of each configuration item in civil aircraft are relatively clear. However, in the field of aero-engines, various technologies are highly integrated, and it is extremely difficult to quickly generate product configurations based on configurations.

[0004] During the development process of aero-engines, a mode of managing and transmitting design data with the BOM structure tree as the carrier has basically been formed, but it only basically involves drawings and models, and the management of supporting technical documents cannot be covered. At the same time, a complete design BOM can only represent the state of one design scheme. Since the design BOM does not associate configuration information, lot effectiveness and other information, when facing the requirements of multiple configuration schemes, a completely new design BOM needs to be established for each requirement to represent different configuration states. Therefore, it will result in a multiple increase in workload and the difficulty of state management. The inability to reuse the same technical points will also lead to a large waste of resources, and it is impossible to achieve rapid product improvement and agile derivative. Summary of the Invention

[0005] In view of this, the embodiments of this application provide a product configuration method based on the modularization of aero-engine unit bodies, construct a unit body module library that can be flexibly combined and quickly reused for use scenarios, solve the major requirements of aero-engine derivatives in multiple use scenarios, and shorten the development cycle of aero-engine series products.

[0006] The embodiments of this application provide a product configuration method based on the modularization of aero-engine unit bodies, and the method includes:

[0007] Based on requirements analysis, an aero-engine is divided into multiple unit bodies, and each unit body includes multiple different configuration schemes;

[0008] For each unit body, obtain the attribute information of each configuration scheme;

[0009] For each unit body, based on the attribute information, determine whether the configuration scheme of the unit body meets the preset unit body warehousing criteria;

[0010] Based on the configuration schemes that meet the preset unit body warehousing criteria and the corresponding attribute information, construct a unit body module database. Each configuration scheme and its corresponding attribute information constitute a unit body module in the unit body module database, and one attribute information of a configuration scheme is a unit body module unit value;

[0011] Based on the target requirements of the new product, determine the target unit bodies and the design requirements of each target unit body;

[0012] Based on the unit body module database, perform configuration combinations of each unit body module that meet the design requirements of the target unit body, and optimize the configuration combinations based on the unit body module unit values to obtain the final complete product design scheme.

[0013] According to a specific implementation manner of an embodiment of the present application, the dividing the aero-engine into multiple unit bodies based on requirements analysis includes:

[0014] Obtain the engine pedigree plan;

[0015] Conduct product requirements analysis based on the engine pedigree plan;

[0016] Based on the product requirements analysis, carry out the design of the engine logical architecture and physical architecture;

[0017] Based on the design of each architecture, perform performance decoupling and physical decoupling on the physical architecture of the engine, complete the unit body division, and clarify the functions, performances, and interface characteristics of each unit body. After the unit body is verified to meet the requirements and the technology is mature, use the relevant characteristic data as the attribute information within the unit body module.

[0018] According to a specific implementation manner of an embodiment of the present application, the attribute information includes technology maturity, performance interface index information, physical interface index information, life index information, general quality characteristic index information, and the composition information of the unit body module. The general quality characteristic index information includes maintainability parameters, safety parameters, and supportability parameters. The composition information of the unit body module includes a list of subordinate components, a list of supporting production documents, verification results, and review reports.

[0019] According to a specific implementation manner of an embodiment of the present application, the method further includes:

[0020] Naming the unit body module with a unit body module name;

[0021] Encoding the unit body module to form a unit body module code;

[0022] Encoding the configuration scheme of each unit body to form a unit body module configuration code;

[0023] Rating the technical maturity level of the unit body module, with the levels divided from level one to level nine;

[0024] Based on the unit body module name, unit body module code, unit body module configuration code, and attribute information, forming a unit body module definition attribute table.

[0025] According to a specific implementation manner of an embodiment of the present application, the preset unit body warehousing criterion includes the following judgment criteria in sequence:

[0026] The unit body module has a unit body module definition attribute table and has been reviewed, signed, and released;

[0027] The unit body module definition attribute table is complete, and the data in the table can be recognized and called by a computer;

[0028] The unit body module code has a unique number, and the numbering rule of the unit body module code meets the requirements of the database numbering rule;

[0029] The unit body module configuration code has a unique configuration number, and the numbering rule of the unit body module configuration code meets the requirements of the database numbering rule;

[0030] The unit body module has undergone a technical maturity assessment, and the technical maturity level reaches above level six;

[0031] The composition information of the unit body module is complete.

[0032] According to a specific implementation manner of an embodiment of the present application, determining the target unit body and the design requirements of each target unit body based on the target requirements of the new product includes:

[0033] Based on the target requirements of the new product, conducting a logical architecture analysis;

[0034] Based on the results of the logical architecture analysis, conducting a subsystem composition definition and interface interaction analysis at the physical implementation level to determine the preliminary interfaces and physical compositions;

[0035] Based on the engine configuration and the results of the design scheme, clarify the structural objects and their characteristic factors of the unit division, preliminarily clarify the main physical components of the engine, and sort out the characteristic factors of its structural features, spatial distribution, function allocation, and performance indicators; conduct an analysis of the correlation relationships between components and optimize the unit correlation matrix to form a division scheme for the target unit and the design requirements for the target unit.

[0036] According to a specific implementation manner of an embodiment of the present application, based on the unit module database, perform configuration combinations of each unit module that meet the design requirements of the target unit, and optimize the configuration combinations based on the unit values of the unit modules to obtain a final complete product design scheme, including:

[0037] For each target unit, based on the design requirements of the target unit, screen out multiple unit modules from the unit module database;

[0038] For each target unit, compare the unit values of each screened unit module with the design requirements, calculate the matching values, and screen out several alternative unit modules;

[0039] Combine the alternative unit modules of all target units to obtain multiple configuration combinations, calculate the effectiveness trade-off values for each configuration combination, and based on the calculation results, screen out the optimal configuration combination, and use this optimal configuration combination as the final complete product design scheme.

[0040] According to a specific implementation manner of an embodiment of the present application, the calculating the matching values and screening out several alternative unit modules includes:

[0041] Calculate the matching values, and the calculation formula for the matching values is:

[0042]

[0043] where P is the matching value, V im is the m-th relevant parameter value of the i-th type of attribute information in the unit value of the unit module, V tim is the m-th relevant parameter value of the i-th type of attribute information proposed by the unit design requirements, k i is the weight value of the i-th type of attribute information in the unit value of the unit module, where i = 1 is the performance interface type index information, i = 2 is the physical interface type index, i = 3 is the life type index information, i = 4 is the general quality characteristic type index information, k i takes values that meet the following requirements:

[0044] 0.4 ≤ k1 ≤ 0.8,

[0045] 0.4 ≤ k2 ≤ 0.9,

[0046] 0 ≤ k3 ≤ 0.5,

[0047] 0 ≤ k4 ≤ 0.5,

[0048] k1 + k2 + k3 + k4 = 1;

[0049] Obtain the matching value P of each unit module. When P ≥ 0.85, the unit module can be used as one of the alternative unit modules.

[0050] According to a specific implementation manner of an embodiment of the present application, the calculation formula of the effectiveness trade-off value is as follows:

[0051]

[0052] where Q is the effectiveness trade-off value, P n is the matching value of the nth unit module under the current configuration combination, T n is the technology maturity of the nth unit module under the current configuration combination, IND i is the numerical value of the simulation calculation verification result of the current configuration combination, IND ti is the numerical value of the design requirement index proposed in the target requirements of the new product.

[0053] According to a specific implementation manner of an embodiment of the present application, for each target unit, based on the design requirements of the target unit, calculate the matching values of each unit module, and screen several alternative unit modules, including:

[0054] Determine the target unit that needs to optimize the unit module from the target units;

[0055] For each target unit that needs to optimize the unit module, calculate the matching values of each unit module, and screen several alternative unit modules.

[0056] Advantageous effects:

[0057] The product configuration method based on the modularization of aero-engine unit in the embodiments of the present application is based on the design results of the engine unit. Effective data information is extracted to form a unit module library. The unit modules are called according to the unit design requirements, and a product configuration plan is quickly configured and combined. Specifically, it includes the following features: First, a method for quickly configuring new or improved and modified aero-engine products is proposed. The unit design requirements are matched using the unit module database, and the matching value of the unit value of the unit module is calculated based on the unit basic data. The matching degree between the unit value of the unit module and the target value is measured by this value, and alternative solutions are screened out. Second, combining the matching value of the unit value of the unit module, the technology maturity, the simulation results of the engine design plan, etc., a calculation method for the effectiveness trade-off value of the engine configuration plan is proposed to support the decision-making layer to weigh and decide the optimal plan from multiple alternative solutions. Third, through unit design and division, the highly integrated engine unit is decoupled, and key performance and physical interface information are extracted and assigned a unique configuration number for subsequent retrieval and call.

[0058] Therefore, the method of the present application configures the configuration based on the development requirements of aero-engines, further identifies key technologies, drives basic research and technological breakthroughs, combines the design results of aero-engine units, and constructs a unit module library that can be flexibly combined and quickly reused for different usage scenarios. Only the units that need to optimize the configuration plan are subject to matching calculation and trade-off, reducing the design cost. The unit configurable modules are constructed with the proven breakthrough results, realizing the decoupling of products and technologies, products and unit modules, accelerating the maturity of key technologies and their rapid configuration applications, shortening the product maturity cycle, reducing the design cycle of product improvement, modification or derivative development by more than 50%, and reducing the repetitive workload by more than 80%.

[0059] Based on the normalization verification platform, through the separation of configuration and technology, the technical requirements are deconstructed, and through configuration reuse, a "general platform architecture + unit module" R & D mode is formed to support the rapid series development and derivative development of products, solve the major requirements for the derivation of engines in multiple usage scenarios, and shorten the development cycle of aero-engine series products. Brief Description of the Drawings

[0060] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings required for the embodiments will be briefly introduced below. 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.

[0061] Figure 1 It is the overall flowchart of the product configuration method based on the modularization of aero-engine unit according to an embodiment of the present invention;

[0062] Figure 2 Schematic diagram of unit module configuration according to an embodiment of the present invention;

[0063] Figure 3 Schematic diagram of engine product pedigree according to an embodiment of the present invention;

[0064] Figure 4 Schematic diagram of the process of demand analysis according to an embodiment of the present invention;

[0065] Figure 5 Schematic diagram of unit division according to an embodiment of the present invention;

[0066] Figure 6 Schematic diagram of unit module library according to an embodiment of the present invention;

[0067] Figure 7 Schematic diagram of engine configuration representation according to an embodiment of the present invention. Detailed implementation manners

[0068] The embodiments of the present application will be described in detail below with reference to the accompanying drawings.

[0069] The following uses specific specific examples to illustrate the implementation manners of the present application. Those skilled in the art can easily understand other advantages and effects of the present application from the content disclosed in this specification. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments. The present application can also be implemented or applied through other different specific implementation manners. Various details in this specification can also be modified or changed based on different viewpoints and applications without departing from the spirit of the present application. It should be noted that, without conflict, the following embodiments and the features in the embodiments can be combined with each other. All other embodiments obtained by those of ordinary skill in the art based on the embodiments in the present application without making creative efforts belong to the scope of protection of the present application.

[0070] It should be noted that the following describes various aspects of the embodiments within the scope of the appended claims. It should be obvious that the aspects described herein can be embodied in a wide variety of forms, and any specific structure and / or function described herein is illustrative only. Based on the present application, those skilled in the art should understand that one aspect described herein can be implemented independently of any other aspect, and two or more of these aspects can be combined in various ways. For example, any number of aspects described herein can be used to implement the device and / or practice the method. Additionally, this device and / or this method can be implemented using other structures and / or functionality in addition to one or more of the aspects described herein.

[0071] It should also be noted that the illustrations provided in the following embodiments only schematically illustrate the basic concept of the present application. The illustrations only show the components related to the present application, rather than being drawn according to the number, shape, and size of the components in actual implementation. The type, quantity, and proportion of each component in actual implementation can be arbitrarily changed, and the component layout type may also be more complex.

[0072] In addition, in the following description, specific details are provided to facilitate a thorough understanding of the examples. However, those skilled in the art will understand that the described aspects can be practiced without these specific details.

[0073] The present application proposes a product configuration method based on the modularization of aero-engine unit bodies. The premise of implementing this method is to adhere to two basic principles: 1) Through unit body development or technical research, the unit body modules that have been fully verified can be included in the unit body module library; 2) The prerequisite for unit body modularization is to decouple the performance and structure of each unit body during the unit body division process, and clarify its performance and physical interface parameters as the retrievable configuration attributes of the unit body module.

[0074] The overall idea of the product rapid configuration proposed by the present application is as follows: First, based on the existing products or technical research topics, through work such as requirement analysis, architecture design, and unit body division definition, decouple the unit bodies, extract key information such as interface parameters, realize unit body modularization, and after passing the access review of the unit body module database, include it in the database management. Subsequently, when developing new products or improving and modifying products, also according to the requirement analysis, architecture design, and unit body division process, clarify the unit body module requirements and design requirements, and through the matching calculation of the requirements and the basic data of the unit body module, screen out multiple directly configurable unit body modules to form the engine design BOM, which can be directly used in subsequent production and manufacturing activities through corresponding trade-off calculations and review decisions, realizing rapid improvement and modification of products and agile derivative development. The overall idea is as Figure 2 shown.

[0075] The following refers to Figures 1 to 7 to describe in detail the product configuration method based on the modularization of aero-engine unit bodies of the present application.

[0076] In one embodiment, a product configuration method based on the modularization of aero-engine unit bodies is proposed, and the method includes:

[0077] Step 1: Based on requirement analysis, divide the aero-engine into multiple unit bodies, and each unit body includes multiple different configuration schemes;

[0078] Step 2: For each unit body, obtain the attribute information of each configuration scheme;

[0079] Step 3. For each unit body, determine whether the configuration scheme of the unit body meets the preset unit body warehousing criteria based on the attribute information;

[0080] Step 4. Based on the configuration schemes that meet the preset unit body warehousing criteria and the corresponding attribute information, construct a unit body module database. Each configuration scheme and its corresponding attribute information constitute a unit body module in the unit body module database, and one attribute information of a configuration scheme is a unit body module unit value;

[0081] Step 5. Based on the target requirements of the new product, determine the target unit bodies and the design requirements for each target unit body;

[0082] Step 6. Based on the unit body module database, perform configuration combinations of the unit body modules that meet the design requirements of the target unit bodies, and optimize the configuration combinations based on the unit body module unit values to obtain the final complete product design scheme.

[0083] In this embodiment, based on the development requirements of aero-engines, the configuration is configured, and then the key technologies are identified to drive basic research and technological breakthroughs. Combining the design results of aero-engine unit bodies, a unit body module library that can be flexibly combined and quickly reused for multiple usage scenarios is constructed. The unit body configurable modules are constructed with the proven breakthrough results to decouple the product from technology and the product from the unit body modules, accelerate the maturity of key technologies and their rapid configuration applications, shorten the product maturity cycle, reduce the design cycle of product improvement, modification or derivative development by more than 50%, and reduce the repetitive workload by more than 80%. Based on the normalized verification platform, through the separation of configuration and technology, the technical requirements are deconstructed, and through the reuse of configurations, a "general platform architecture + unit body module" R & D mode is formed to support the rapid series development and derivative development of products.

[0084] In a specific implementation manner, based on the requirement analysis, the aero-engine is divided into multiple unit bodies, including the following steps:

[0085] Obtain the engine pedigree plan, which is used to define information such as the platform, series, usage, and layout of the aero-engine, as the top-level input. The engine product pedigree is referred to Figure 3 ;

[0086] Conduct product requirement analysis based on the engine pedigree plan;

[0087] Based on the product requirement analysis, carry out the design of the engine logical architecture and physical architecture;

[0088] Based on various architecture designs, perform performance decoupling and physical decoupling on the physical architecture of the engine, complete the unit division, and clarify the functions, performance, and interface characteristics of each unit. After the unit is verified to meet the requirements and the technology is mature, the relevant characteristic data is used as attribute information within the unit module.

[0089] Specifically, the following contents are included when implementing:

[0090] (a) Engine lineage planning: Engine lineage planning is reflected by the engine planning tree, which is divided according to the engine usage scenarios and power requirements;

[0091] (b) Based on the lineage planning, conduct product requirement analysis, as shown in Figure 4 , take the top-level input files, specifications, etc. as the initial requirement inputs. After sorting and preliminary analysis, with the system boundary as the constraint, form the initial requirements; based on multiple rounds of communication and coordination with the customer side, driven by the key issues concerned by the customer, obtain the engine-level requirements for the whole machine, provide input conditions for work such as architecture design and requirement allocation, and at the same time provide support for the technology research and development plan, etc.;

[0092] (c) Based on the product requirement analysis, carry out the design of the engine's logical architecture and physical architecture; according to the engine functions identified from the requirements and the preliminary logical architecture design results, determine the engine's logical architecture. Based on the engine's logical architecture, identify and establish the subsystems required by the engine, make adaptive improvements in aspects such as manufacturability and producibility in the design of each subsystem architecture, and absorb the mature physical architecture design experience of foreign engines of the same type to establish the engine's physical architecture;

[0093] (d) Based on the architecture design, perform performance decoupling and physical decoupling on the physical architecture of the engine product, complete the unit division, divide the engine into multiple units, as shown in Figure 5 , and clarify the functions, performance, and interface characteristics of each unit.

[0094] (e) According to the requirement analysis, architecture design, unit design requirements, etc., carry out unit development and verification, and at the same time conduct technology research and development on technologies with low maturity, form the configuration schemes subordinate to the unit, construct a design scheme for each configuration scheme, and the design scheme includes the unit design BOM. As the maturity of the technology research and development meets the requirements, the technology will support the design scheme.

[0095] In one embodiment, the attribute information includes technology maturity, performance interface index information, physical interface index information, lifespan index information, general quality characteristic index information, and the composition information of the unit module. The general quality characteristic index information includes maintainability parameters, safety parameters, and supportability parameters. The composition information of the unit module includes a list of subordinate components, a list of supporting production documents, verification results, and review reports.

[0096] Further, the method further includes:

[0097] Naming the unit module with a unit module name;

[0098] Encoding the unit module to form a unit module code;

[0099] Encoding the configuration scheme of each unit to form a unit module configuration code;

[0100] Rating the technology maturity of the unit module, with the levels ranging from level 1 to level 9;

[0101] Based on the unit module name, unit module code, unit module configuration code, and attribute information, form a unit module definition attribute table.

[0102] In specific implementation, for the same unit A, there may be multiple configuration schemes, such as "configuration scheme 1", "configuration scheme 2", etc., which are used to represent different design schemes or different states of the same unit. Different "configuration schemes" are uniquely identified and distinguished by the "unit module configuration code". The process of assigning values to the attribute information, as well as the processes of naming, encoding, and identifying the technology maturity, are also the definition processes of the unit module. The finally formed unit module definition attribute table is shown in Table 1.

[0103] Table 1 Unit module definition attribute table

[0104]

[0105]

[0106] In one embodiment, the preset unit warehousing criteria include the following judgment criteria in sequence:

[0107] The unit module has a unit module definition attribute table and has been signed and released;

[0108] The unit module definition attribute table is complete, and the data in the table can be recognized and called by the computer;

[0109] The unit module code has a unique number, and the numbering rule of the unit module code meets the requirements of the database numbering rule;

[0110] The unit module configuration code has a unique configuration number, and the numbering rule of the unit module configuration code meets the requirements of the database numbering rule;

[0111] The unit module has passed the technology readiness assessment, and the technology readiness has reached level six or above;

[0112] The composition information of the unit module is complete.

[0113] During specific implementation, when judging whether the composition information of the unit module is complete, generally, it is to judge whether the data such as drawings, models, and supporting documents included in the component structure tree subordinate to the unit module are complete and have all been released; whether the form of the subordinate design BOM architecture meets the basic requirements of design BOM construction. Combining the aero-engine system engineering theory, aero-engine development experience, and the requirements for the use of unit module data, a preset unit warehousing criterion is formed. When judging whether it meets the preset unit warehousing criterion, it is judged one by one according to each item. When each item meets the requirements, it meets the preset unit warehousing criterion. After the access review of each unit module, a unit module access review report is formed, and the unit module data packet can be incorporated into the unit module database for management.

[0114] The unit module library is the basis for the unit module configuration and is a collection of all unit modules and unit module unit values, as Figure 6 shown. The unit module library incorporates all unit modules that have passed the access review into the unit module list, and takes their unit module unit values and corresponding coding, naming information, technology readiness, etc. as attachment data, establishing a one-to-one association relationship with the unit module. The unit module unit values can be screened, queried, and called through the unit module library.

[0115] In one embodiment, based on the target requirements of the new product, determining the target unit bodies and the design requirements of each target unit body includes:

[0116] Carrying out logical architecture analysis based on the target requirements of the new product;

[0117] Based on the results of the logical architecture analysis, carrying out subsystem composition definition and interface interaction analysis at the physical implementation level to determine the preliminary interfaces and physical compositions;

[0118] According to the engine configuration and the results of the scheme design, clarifying the unit body division structure object and its characteristic factors, preliminarily clarifying the main physical composition of the engine, and sorting out the characteristic factors of its structural characteristics, spatial distribution, function allocation, and performance indicators; carrying out the analysis of the correlation relationship between components and optimizing the unit body correlation matrix to form the division scheme of the target unit body and the design requirements of the target unit body.

[0119] In specific implementation, the division of the target unit body can be carried out through the following two steps:

[0120] a. Product requirement analysis and logical architecture design:

[0121] When developing a new product or improving and modifying an existing product, first, clarify the usage requirements of the engine. For example, when developing an aeroengine that provides a certain state of thrust, a requirement for the engine to possess a certain ability is put forward. Based on the research and development requirements of the engine, carry out logical architecture design, define the logical subsystems of the engine at the logical level, analyze the interaction relationships between the logical subsystems, and define how to achieve external functions, etc.

[0122] b. Physical architecture design and unit body division:

[0123] Based on the results of logical architecture analysis, carry out the definition of subsystem composition and interface interaction analysis at the physical implementation level, and determine the preliminary interfaces, physical compositions, etc. According to the engine configuration and the results of the scheme design, clarify the structure objects and their characteristic factors for unit body division, preliminarily clarify the main physical components of the engine, and sort out the characteristic factors such as their structural characteristics, spatial distribution, function allocation, performance indicators, etc. Through the analysis of the correlation relationships between components and the optimization of the unit body correlation matrix, etc., a unit body division scheme and unit body design requirements are formed.

[0124] Through the above steps, multiple unit bodies such as unit body 1, unit body 2, unit body 3, unit body 4, unit body 5, and unit body 6 are divided, and the design requirements and relevant parameters such as functions, performances, structures, and interfaces related to each unit body are put forward.

[0125] Furthermore, based on the unit body module database, configure and combine each unit body module that meets the design requirements of the target unit body to obtain the final complete product design scheme, including:

[0126] For each target unit body, based on the design requirements of the target unit body, screen out multiple unit body modules from the unit body module database;

[0127] For each target unit body, compare the unit body module unit values of each screened unit body module with the design requirements, calculate the matching values, and screen out several alternative unit body modules;

[0128] Combine the alternative unit body modules of all target unit bodies to obtain multiple configuration combinations, calculate the effectiveness trade-off values for each configuration combination, and based on the calculation results, screen out the optimal configuration combination, and take this optimal configuration combination as the final complete product design scheme.

[0129] In specific implementation, for example, for the engine configuration requirement of "XXX01001", in the unit module library, according to the design requirement constraints such as the function, performance, structure, and interface of unit 1, four unit modules, namely "unit module 1", "unit module 2", "unit module 3", and "unit module 4", are selected. By computer matching using the unit values corresponding to the unit modules, the design requirements of unit 1 can be met.

[0130] Based on the unit values of each unit module and the actual needs and design requirements of the unit, calculate the matching value P of the unit module unit value. The formula is as follows:

[0131]

[0132] Where P is the matching value, V im is the m-th relevant parameter value of the i-th type of attribute information in the unit value of the unit module, and V tim is the m-th relevant parameter value of the i-th type of attribute information proposed by the unit design requirements, and k i is the weight value of the i-th type of attribute information in the unit value of the unit module. Among them, i = 1 is the performance interface type index information, i = 2 is the physical interface type index, i = 3 is the life type index information, and i = 4 is the general quality characteristic type index information. For the value of k i , according to the project development experience value, the following requirements need to be met:

[0133] 0.4 ≤ k1 ≤ 0.8,

[0134] 0.4 ≤ k2 ≤ 0.9,

[0135] 0 ≤ k3 ≤ 0.5,

[0136] 0 ≤ k4 ≤ 0.5,

[0137] k1 + k2 + k3 + k4 = 1;

[0138] Obtain the matching value P of each unit module. When P ≥ 0.85, the unit module can be used as one of the alternative unit modules.

[0139] Specifically, for the value of k i , the weight values of each parameter can also be further divided according to the specific parameters within each type of attribute information. For example:

[0140] For the performance interface type index: select k 11 = 0.2 for performance index 1, k 12 = 0.15 for performance index 2, and k 13 = 0.1 for performance index 3;

[0141] Physical interface class indicators: k of physical indicator 1 21 = 0.2, k of physical indicator 2 22 = 0.3;

[0142] Lifetime class indicators: k of physical indicator 1 31 = 0.05;

[0143] Through the above unit value matching value calculation method, the detailed scoring results can be obtained as shown in Table 2. According to the calculation results, "unit 1" and "unit 2" are selected as alternative solutions.

[0144] Table 2 Calculation results of unit value matching values

[0145]

[0146] Furthermore, the matching value calculation is performed to screen several alternative unit body modules, including:

[0147] Perform the matching value calculation, and the calculation formula for the matching value is:

[0148]

[0149] where P is the matching value, V im is the m-th relevant parameter value of the i-th type of attribute information in the unit value of the unit body module, V tim is the m-th relevant parameter value of the i-th type of attribute information proposed by the unit body design requirements, k i is the weight value of the i-th type of attribute information in the unit value of the unit body module, where i = 1 is the performance interface class indicator information, i = 2 is the physical interface class indicator, i = 3 is the lifetime class indicator information, i = 4 is the general quality characteristic class indicator information, and k i takes values that satisfy the following requirements:

[0150] 0.4 ≤ k1 ≤ 0.8,

[0151] 0.4 ≤ k2 ≤ 0.9,

[0152] 0 ≤ k3 ≤ 0.5,

[0153] 0 ≤ k4 ≤ 0.5,

[0154] k1 + k2 + k3 + k4 = 1;

[0155] Obtain the matching value P of each unit body module. When P ≥ 0.85, the unit body module can be used as one of the alternative unit body modules.

[0156] In one embodiment, the calculation formula for the effectiveness trade-off value is:

[0157]

[0158] Among them, Q is the effectiveness trade-off value, and P n is the matching value of the nth unit module under the current configuration combination, T n is the technology maturity of the nth unit module under the current configuration combination, IND i is the numerical value of the simulation calculation verification result of the current configuration combination, IND ti is the numerical value of the design requirement index proposed in the target requirements of the new product.

[0159] In specific implementation, generally, during the development or improvement and modification of new products, limited by the complexity and high coupling of aeroengines, new configuration scheme unit bodies are generally not selected on a large scale. Instead, while ensuring that most unit bodies remain unchanged, individual unit bodies are improved in design or new configuration schemes are selected. Therefore, the permutations and combinations of new engine configuration schemes usually do not be excessive.

[0160] According to the configuration combination results, an engine unit body configuration table is generated, as shown in Figure 7 , according to the configuration table combination, the product data management system screens and combines according to the unit module configuration code to form an engine design BOM for a single configuration, and the system calls a program to output the engine design scheme and model. Through a mature engine simulation software, based on the performance model and physical model, after simulating the performance and strength of the engine, the effectiveness trade-off value Q of the engine configuration scheme (configuration combination) is calculated according to the calculation formula. Particularly, when there are "non-passing items" in the simulation calculation verification,

[0161] According to the configuration combination results of the unit modules, "Configuration Combination 1", "Configuration Combination 2", "Configuration Combination 3", and "Configuration Combination 4" are formed in total. The calculation and sorting results of the effectiveness trade-off value Q of each configuration combination are shown in Table 3. The results show that the Q value of "Configuration Combination 2" ranks first, and this Configuration Combination 1 can be used as the preferred scheme.

[0162] Table 3 Calculation and sorting results of the effectiveness trade-off value Q of the configuration scheme

[0163]

[0164] Submit the engine design BOM, the calculation and sorting result table of the effectiveness trade-off value Q for each configuration plan, and relevant supporting materials (such as technology maturity evaluation reports, simulation verification reports, etc.) for review, and the project decision-making level is responsible for reviewing and confirming the materials. Based on the sorting result of the engine design plan after decision-making trade-off, select "Configuration Combination 2" as the optimal plan. Issue the design BOM and the engine unit configuration table generated based on "Configuration Combination 2" to the manufacturing unit for carrying out relevant production activities. Specifically, it is necessary to conduct a review of the engine configuration plan completed for the configuration combination. The decision-making level conducts a trade-off and decision through a meeting review method based on the sorting result of the effectiveness trade-off value Q of the engine configuration plan, relevant supporting materials, etc., to determine the final engine design plan, form a supporting design BOM for the finally confirmed design plan, and issue it to the contractor for the next production and manufacturing activities.

[0165] In one embodiment, for each target unit body, calculate the matching value of each unit body module based on the design requirements of the target unit body, and screen several alternative unit body modules, including:

[0166] From the target unit body, determine the target unit body that needs to optimize the unit body module;

[0167] For each target unit body that needs to optimize the unit body module, calculate the matching value of each unit body module, and screen several alternative unit body modules.

[0168] In specific implementation, during the process of new product development or improvement and modification, due to the complexity and high coupling of aero-engines, generally, unit bodies of new configuration plans are not selected on a large scale. Instead, while ensuring that most unit bodies remain unchanged (the same unit bodies as in the original design), individual unit bodies are improved in design or new configuration plans are selected, realizing the rapid reuse of unit body modules. Only the unit bodies that need to optimize the configuration plan are subject to matching calculation and trade-off, reducing the design cost, accelerating the maturity of key technologies and the rapid configuration application, and shortening the product maturity cycle.

[0169] The embodiment provided by the present invention configures the configuration based on the development requirements of aero-engines, further identifies key technologies, drives basic research and technological breakthroughs, and combines the design results of aero-engine unit bodies to construct a unit body module library that can be flexibly combined and rapidly reused for multiple usage scenarios. Only the unit bodies that need to optimize the configuration plan are subject to matching calculation and trade-off, reducing the design cost. Construct unit body configurable modules with proven breakthrough results, realize the decoupling of products and technologies, products and unit body modules, accelerate the maturity of key technologies and the rapid configuration application, shorten the product maturity cycle, reduce the design cycle of product improvement, modification or derivative development by more than 50%, and reduce the repetitive workload by more than 80%;

[0170] Based on the normalization verification platform, by separating the configuration from the technology, deconstructing the technology requirements, and reusing the configuration, a R & D mode of "general platform architecture + unit module" is formed to support the rapid series development and derivative development of products.

[0171] The above is only the specific implementation manner of this application, but the protection scope of this application is not limited thereto. Any changes or substitutions that can be easily thought of by those skilled in the art within the technical scope disclosed by this application should be covered within the protection scope of this application. Therefore, the protection scope of this application shall be subject to the protection scope of the claims.

Claims

1. A product configuration method based on the modularization of aero-engine unit modules, characterized in that The method includes: Based on requirements analysis, an aeroengine is divided into multiple unit bodies, and each unit body includes multiple different configuration schemes; For each unit body, obtain the attribute information of each configuration scheme; For each unit body, based on the attribute information, determine whether the configuration scheme of the unit body meets the preset unit body warehousing criteria; Based on the configuration schemes that meet the preset unit body warehousing criteria and the corresponding attribute information, construct a unit body module database. Each configuration scheme and its corresponding attribute information form a unit body module in the unit body module database, and an attribute information of a configuration scheme is a unit body module unit value; Based on the target requirements of the new product, determine the target unit bodies and the design requirements of each target unit body; Based on the unit body module database, perform configuration combinations of each unit body module that meet the design requirements of the target unit body, and optimize the configuration combinations based on the unit body module unit values to obtain the final complete product design scheme, including: For each target unit body, based on the design requirements of the target unit body, screen out multiple unit body modules from the unit body module database; for each target unit body, compare the unit body module unit value of each screened unit body module with the design requirements, calculate the matching value, and screen out several alternative unit body modules; combine the alternative unit body modules of all target unit bodies to obtain multiple configuration combinations, calculate the effectiveness trade-off value for each configuration combination, and based on the calculation results, screen out the optimal configuration combination and use this optimal configuration combination as the final complete product design scheme; The calculating the matching value and screening out several alternative unit body modules includes: Calculate the matching value, and the calculation formula of the matching value is: ， Among them, P is the matching value, V im is the m-th relevant parameter value of the i-th type of attribute information in the unit module unit value, V tim is the m-th relevant parameter value of the i-th type of attribute information proposed by the unit design requirements, k i is the weight value of the i-th type of attribute information in the unit module unit value, where i = 1 is the performance interface class index information, i = 2 is the physical interface class index, i = 3 is the life class index information, i = 4 is the general quality characteristic class index information, k i takes values that meet the following requirements: 0.4≤k1≤0.8， 0.4≤k2≤0.9, 0≤k3≤0.5, 0≤k4≤0.5， k1 + k2 + k3 + k4 = 1; Obtain the matching value P of each unit body module. When P ≥ 0.85, this unit body module can be used as one of the alternative unit body modules.

2. The product configuration method based on the modularization of aero-engine unit modules according to claim 1, characterized in that, The dividing the aeroengine into multiple unit bodies based on requirements analysis includes: Obtain the engine pedigree plan; Conduct product requirements analysis based on the engine pedigree plan; Based on the product requirements analysis, carry out the design of the engine logical architecture and physical architecture; Based on each architecture design, perform performance decoupling and physical decoupling on the physical architecture of the engine, complete the unit body division, and clarify the functions, performances, and interface characteristics of each unit body. After the unit body is verified to meet the requirements and the technology is mature, use the relevant characteristic data as the attribute information within the unit body module.

3. The product configuration method based on the modularization of aero-engine unit modules according to claim 1, wherein The attribute information includes technology maturity, performance class interface index information, physical interface class index information, life class index information, general quality characteristic class index information, and the composition information of the unit body module. The general quality characteristic class index information includes maintainability parameters, safety parameters, and supportability parameters. The composition information of the unit body module includes the list of subordinate components, the list of supporting production documents, verification results, and review reports.

4. The product configuration method based on the modularization of aero-engine unit modules according to claim 3, characterized in that, The method further includes: Name the unit body module; Encode the unit body module to form a unit body module code; Encode the configuration plan of each unit body to form a unit body module configuration code; Grade the technical maturity of the unit body module, and the grades are divided into level 1 to level 9; Based on the unit body module name, unit body module code, unit body module configuration code and attribute information, form a unit body module definition attribute table.

5. The product configuration method based on the modularization of an aero-engine unit as claimed in claim 4, wherein The preset unit body warehousing criteria include the following judgment criteria carried out in sequence: The unit body module has a unit body module definition attribute table and has passed review, signature and release; The unit body module definition attribute table is complete, and the data in the table can be recognized and called by the computer; The unit body module code has a unique number, and the numbering rule of the unit body module code meets the requirements of the database numbering rule; The unit body module configuration code has a unique configuration number, and the numbering rule of the unit body module configuration code meets the requirements of the database numbering rule; The unit body module has passed the technical maturity assessment, and the technical maturity has reached level 6 or above; The composition information of the unit body module is complete.

6. The product configuration method based on the modularization of aero-engine unit modules according to claim 1, characterized in that, Based on the target requirements of the new product, determine the target unit bodies and the design requirements of each target unit body, including: Based on the target requirements of the new product, carry out logical architecture analysis; Based on the results of the logical architecture analysis, carry out subsystem composition definition and interface interaction analysis at the physical implementation level to determine the preliminary interfaces and physical compositions; According to the engine configuration and the results of the scheme design, clarify the unit body division structure object and its characteristic factors, initially clarify the main physical composition of the engine, and sort out the characteristic factors of its structural characteristics, spatial distribution, function allocation, and performance indicators; conduct an analysis of the correlation relationship between components and optimize the unit body correlation matrix to form a division scheme of the target unit body and the design requirements of the target unit body.

7. The product configuration method based on the modularization of aero-engine unit modules according to claim 1, characterized in that, The calculation formula of the effectiveness trade-off value is: , Among them, Q is the effectiveness trade-off value, and P n is the matching value of the nth unit module under the current configuration combination, T n is the technology maturity of the nth unit module under the current configuration combination, IND i is the numerical value of the simulation calculation verification result of the current configuration combination, IND ti is the numerical value of the design requirement index proposed in the target requirements of the new product.

8. The product configuration method based on the modularization of aero-engine unit modules according to claim 1, characterized in that, For each target unit body, calculate the matching value of each unit body module based on the design requirements of the target unit body, and screen several alternative unit body modules, including: From the target unit bodies, determine the target unit bodies that need to optimize the unit body module; For each target unit body that needs to optimize the unit body module, calculate the matching value of each unit body module and screen several alternative unit body modules.

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