Product configuration method based on aero-engine unit modularization

Abstract

The invention provides a product configuration method based on aero-engine unit body modularization, and belongs to the technical field of aero-engines, the method comprises the steps that an aero-engine is divided into a plurality of unit bodies based on demand analysis, and each unit body comprises a plurality of configuration schemes; for each unit body, acquiring attribute information of each configuration scheme, and judging whether the configuration scheme conforms to a preset unit body storage criterion or not based on the attribute information; based on the conformed configuration schemes and the corresponding attribute information, a unit module database is constructed, and each configuration scheme corresponds to one unit module; determining a target unit body and a corresponding design requirement based on a new product target demand; and based on the unit module database, performing configuration combination of each unit module meeting the target unit design requirements, and performing optimization on the configuration combination based on the unit values of the unit modules to obtain a final complete product design scheme. The design cost can be reduced, the product maturation period is shortened, and rapid series development and derived development of products are supported.

Description

Technical Field

[0001] The present application relates to the field of aero-engine technology, and in particular to a product configuration method based on modularization of aero-engine units. Background Art

[0002] The development of my country's aviation engine industry faces the dilemma that the research and development of advanced aviation engine products lags behind equipment demand. On the one hand, the reason is that there are difficulties in the deep coupling of product configuration and technology and the effective application and transformation of technology; on the other hand, the early development needs of aviation engines are often relatively simple, and the configurations of different types of aviation engines are basically the same. However, as the development needs of aviation engines tend to be more multi-dimensional and systematic, the demand for aviation engine products with new configurations is becoming more urgent. The existing single configuration R&D model can no longer meet the major needs of rapid product improvement and modification and agile derivative development.

[0003] In the field of aircraft, the civil aircraft industry has similar research results, such as the patent CN111177847B proposed a configuration management method and device for civil aircraft. This patent mainly describes the 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 interface of each configuration item of civil aircraft is relatively clear, while in the field of aircraft engines, various technologies are highly integrated, and it is extremely difficult to achieve rapid combination based on configuration to generate product configuration.

[0004] In the process of aircraft engine development, a model has been basically formed to manage and transmit design data with the BOM structure tree as the carrier, but it basically only involves drawings and models, and the management of supporting technical documents cannot be covered. At the same time, a complete design BOM can only express the status of one design scheme. Since the design BOM does not have associated configuration information, unit validity and other information, when facing the needs of multiple configuration schemes, it is necessary to re-establish a new set of design BOMs for each requirement to represent different configuration states, which will result in an exponential increase in workload and difficulty in status management. The inability to reuse the same technical points will also lead to a substantial waste of resources, and it is impossible to achieve rapid improvement and modification of products and agile derivation. Summary of the invention

[0005] In view of this, an embodiment of the present application provides a product configuration method based on the modularization of aircraft engine units, constructs a unit module library that can be flexibly combined and quickly reused for usage scenarios, solves the major needs of engine derivation in multiple usage scenarios, and shortens the development cycle of aircraft engine series products.

[0006] The present application embodiment provides a product configuration method based on modularization of an aircraft engine unit, the method comprising:

[0007] Based on demand analysis, the aircraft engine is divided into multiple units, each of which includes multiple different configuration schemes;

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

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

[0010] Based on the configuration schemes that meet the preset unit storage criteria and the corresponding attribute information, a unit module database is constructed, each configuration scheme and its corresponding attribute information constitute a unit module in the unit module database, and one attribute information of a configuration scheme is a unit module unit value;

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

[0012] Based on the unit body module database, configuration combinations of each unit body module that meet the design requirements of the target unit body are performed, and the configuration combinations are optimized based on the unit body module unit values ​​to obtain a final complete product design solution.

[0013] According to a specific implementation of the embodiment of the present application, the aircraft engine is divided into multiple units based on demand analysis, including:

[0014] Get engine pedigree planning;

[0015] Conduct product demand analysis based on engine family planning;

[0016] Based on product demand analysis, design the engine logical architecture and physical architecture;

[0017] Based on the design of each architecture, the physical architecture of the engine is decoupled in terms of performance and physics, the unit division is completed, and the function, performance and interface characteristics of each unit are clarified. After the unit is verified to meet the requirements and the technology is mature, the relevant characteristic data will be used as attribute information within the unit module.

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

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

[0020] Name the unit module;

[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] The technical maturity of the unit modules is graded from level 1 to level 9;

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

[0025] According to a specific implementation of the embodiment of the present application, the preset unit storage criteria include the following judgment criteria performed in sequence:

[0026] The unit module has a unit module definition attribute table and has been reviewed and published;

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

[0028] The unit module code has a unique number, and the numbering rules of the unit module code meet the requirements of the database numbering rules;

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

[0030] The unit module has undergone technical maturity assessment and the technical maturity has reached level 6 or above;

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

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

[0033] Conduct logical architecture analysis based on the target requirements of new products;

[0034] Based on the results of the logical architecture analysis, the subsystem composition definition and interface interaction analysis are carried out at the physical implementation level to determine the preliminary interface and physical composition;

[0035] According to the engine configuration and scheme design results, the unit division structural objects and their characteristic factors are clarified, the main physical components of the engine are preliminarily clarified, and the characteristic factors of its structural characteristics, spatial distribution, functional allocation, and performance indicators are sorted out; the correlation relationship between parts is analyzed and the unit association matrix is ​​optimized to form the division scheme of the target unit and the design requirements of the target unit.

[0036] According to a specific implementation of the embodiment of the present application, the configuration combination of each unit body module that meets the design requirements of the target unit body is performed based on the unit body module database, and the configuration combination is optimized based on the unit body module unit value to obtain the final complete product design solution, including:

[0037] For each target unit body, based on the design requirements of the target unit body, a plurality of unit body modules are selected from the unit body module database;

[0038] For each target unit body, the unit body module unit value of each unit body module screened out is compared with the design requirements, the matching value is calculated, and a number of candidate unit body modules are screened;

[0039] The candidate unit body modules of all target unit bodies are combined to obtain multiple configuration combinations, and the effectiveness trade-off value of each configuration combination is calculated. Based on the calculation results, the optimal configuration combination is screened out and the optimal configuration combination is used as the final complete product design solution.

[0040] According to a specific implementation of the embodiment of the present application, the matching value calculation and screening of a plurality of candidate unit modules include:

[0041] The matching value is calculated, and the calculation formula of the matching value is:

[0042]

[0043] Among them, P is the matching value, V im is the mth relevant parameter value of the i-th type of attribute information in the unit value of the unit module, V tim The mth relevant parameter value of the i-th type of attribute information proposed for the unit design requirement, k i is the weight value of the i-th attribute information in the unit value of the unit module, where i=1 is the performance interface index information, i=2 is the physical interface index, i=3 is the life index information, i=4 is the general quality characteristic index information, and k i The value of meets 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] The matching value P of each unit cell module is obtained. When P≥0.85, the unit cell module can be used as one of the candidate unit cell modules.

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

[0051]

[0052] Among them, 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 I ND is the technical maturity of the nth unit module under the current configuration combination, i The simulation result value of the current configuration combination is verified by I ND ti The numerical value of the design requirement indicators proposed in the target needs of the new product.

[0053] According to a specific implementation of the embodiment of the present application, for each target unit body, the matching value of each unit body module is calculated based on the design requirements of the target unit body, and a number of candidate unit body modules are screened, including:

[0054] From the target unit bodies, determine the target unit body whose unit body module needs to be optimized;

[0055] For each target unit body that needs to optimize the unit body module, the matching value of each unit body module is calculated, and a number of candidate unit body modules are screened.

[0056] Beneficial effects:

[0057] The product configuration method based on the modularization of aircraft engine units in the embodiment of the present application is based on the engine unit design results, extracts valid data information and forms a unit module library, calls the unit modules according to the unit design requirements, and quickly configures and combines to form a product configuration configuration scheme, which specifically includes the following features: First, a method for quickly configuring new products or improved and modified products of aircraft engines is proposed, and the unit module database is used to match the unit design requirements, and the matching value of the unit module unit value is calculated based on the unit basic data. The matching degree between the unit module unit value and the target value is measured by this value, and the alternative scheme is screened out; second, combined with the matching value of the unit module unit value, the technical maturity, the simulation results of the engine design scheme, etc., a method for calculating the effectiveness trade-off value of the engine configuration scheme is proposed to support the decision-making layer to weigh and decide on the optimal scheme from multiple alternative schemes; third, through unit design and division, the highly integrated engine unit is decoupled, and the key performance and physical interface information is extracted, and a unique configuration number is assigned to it for subsequent retrieval and calling.

[0058] Therefore, the method of the present application is based on the configuration configuration required for aircraft engine development, and then identifies key technologies, drives basic research and technical breakthroughs, and combines the design results of aircraft engine units to construct a unit module library that can be flexibly combined and quickly reused for usage scenarios. It is only necessary to match and calculate the trade-offs for the units that need to optimize the configuration scheme, thereby reducing design costs. The unit configurable modules are constructed with verified research results to achieve decoupling of products and technologies, and products and unit modules, accelerate the maturity of key technologies and 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 repetitive workload by more than 80%.

[0059] Based on a normalized verification platform, by separating configuration from technology, deconstructing technical requirements, and through configuration reuse, a "general platform architecture + unit module" R&D model is formed to support rapid series development and derivative development of products, solve major needs for engine derivatives 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 use in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0061] Figure 1 It is an overall flow chart of a product configuration method based on modularization of an aircraft engine unit according to an embodiment of the present invention;

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

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

[0064] Figure 4 A schematic diagram of a flow chart of demand analysis according to an embodiment of the present invention;

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

[0066] Figure 6 is a schematic diagram of a unit cell module library according to an embodiment of the present invention;

[0067] Figure 7 The figure shows a schematic diagram of an engine configuration according to an embodiment of the present invention. DETAILED DESCRIPTION

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

[0069] The following describes the implementation methods of the present application through specific examples, and those skilled in the art can easily understand other advantages and effects of the present application from the contents 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 methods, and the details in this specification can also be modified or changed in various ways based on different viewpoints and applications without departing from the spirit of the present application. It should be noted that, in the absence of conflict, the following embodiments and the features in the embodiments can be combined with each other. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in the field without making creative work belong to the scope of protection of the present application.

[0070] It should be noted that various aspects of the embodiments within the scope of the appended claims are described below. It should be apparent that the aspects described herein can be embodied in a wide variety of forms, and any specific structure and / or function described herein is merely illustrative. Based on the present application, it should be understood by those skilled in the art that an 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. In addition, other structures and / or functionalities other than one or more of the aspects described herein can be used to implement this device and / or practice this method.

[0071] It should also be noted that the illustrations provided in the following embodiments are only schematic illustrations of 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. In actual implementation, the type, quantity and proportion of each component may be changed at will, and the component layout may also be more complicated.

[0072] Additionally, in the following description, specific details are provided to facilitate a thorough understanding of the examples. However, it will be understood by those skilled in the art that the aspects described may be practiced without these specific details.

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

[0074] The overall idea of ​​rapid product configuration proposed in this application is: first, based on existing products or technical research projects, through demand analysis, architecture design, unit division definition and other work, the unit is decoupled, and after extracting key information such as interface parameters, the unit is modularized, and after passing the unit module database access review, it is included in the database management. Subsequently, when developing new products or improving and modifying products, the unit module requirements and design requirements are clarified in accordance with the demand analysis, architecture design, and unit division process. Through the matching calculation of the requirements and the basic data of the unit module, multiple unit modules that can be directly configured and used are selected to form an engine design BOM. After the corresponding trade-off calculation and review decision-making, it can be directly used in subsequent production and manufacturing activities to achieve rapid product improvement and modification and agile derivative development. The overall idea is as follows Figure 2 shown.

[0075] Refer to the following Figures 1 to 7 The product configuration method based on modularization of aircraft engine units of the present application is described in detail.

[0076] In one embodiment, a product configuration method based on modularization of an aircraft engine unit is proposed, the method comprising:

[0077] Step 1: Based on demand analysis, the aircraft engine is divided into multiple units, each unit including 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, judging whether the configuration scheme of the unit body meets the preset unit body storage criteria based on the attribute information;

[0080] Step 4: construct a unit module database based on the configuration schemes that meet the preset unit storage criteria and the corresponding attribute information, each configuration scheme and its corresponding attribute information constitute a unit module in the unit module database, and one attribute information of one configuration scheme is one unit module unit value;

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

[0082] Step 6: Based on the unit body module database, configure and combine the various unit body modules that meet the design requirements of the target unit body, optimize the configuration combination based on the unit body module unit value, and obtain the final complete product design solution.

[0083] In this embodiment, the configuration is configured based on the aircraft engine development requirements, and then the key technologies are identified, basic research and technical breakthroughs are driven, and combined with the aircraft engine unit design results, a unit module library that can be flexibly combined and quickly reused for multiple usage scenarios is constructed, and the unit configurable modules are constructed with the verified research results to achieve decoupling of products and technologies, products and unit modules, accelerate the maturity of key technologies and rapid configuration and application, shorten the product maturity cycle, reduce the design cycle of product improvement, modification or derivative development by more than 50%, and reduce repetitive workload by more than 80%; based on the normalized verification platform, the configuration and technology are separated, the technical requirements are deconstructed, and the configuration is reused to form a "general platform architecture + unit module" research and development model to support rapid series development and derivative development of products.

[0084] In a specific embodiment, the step of dividing the aircraft engine into a plurality of units based on demand analysis includes the following steps:

[0085] Obtain engine pedigree planning, which is used to define the platform, series, purpose, layout and other information of aircraft engines. It is used as the top-level input for engine product pedigree reference. Figure 3 ;

[0086] Conduct product demand analysis based on engine family planning;

[0087] Based on product demand analysis, design the engine logical architecture and physical architecture;

[0088] Based on the design of each architecture, the physical architecture of the engine is decoupled in terms of performance and physics, the unit division is completed, and the function, performance and interface characteristics of each unit are clarified. After the unit is verified to meet the requirements and the technology is mature, the relevant characteristic data will be used as attribute information within the unit module.

[0089] The specific implementation includes the following contents:

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

[0091] (b) Conduct product demand analysis based on genealogy planning, see Figure 4 , taking the top-level input files, specifications and standards as the initial demand input, after sorting and preliminary analysis, with the system boundary as the constraint, the initial demand is formed; based on multiple rounds of communication and coordination with the customer, with the customer's key concerns as the driving force, the engine whole-machine level demand is obtained, which provides input conditions for architecture design, demand allocation and other work, and also provides support for technical research plans;

[0092] (c) Based on product demand analysis, the engine logical architecture and physical architecture design were carried out; the engine logical architecture was determined based on the engine functions identified by the demand and the preliminary logical architecture design results; based on the engine logical architecture, the subsystems required for the engine were identified and established; adaptive improvements were made in the manufacturability and producibility of the architecture design of each subsystem; and the mature physical architecture design experience of similar foreign engines was absorbed to establish the engine physical architecture;

[0093] (d) Based on the architecture design, the physical architecture of the engine product is decoupled in terms of performance and physics, and the unit division is completed. The engine is divided into multiple units, such as Figure 5 As shown, the functions, performance and interface characteristics of each unit are clearly defined.

[0094] (e) Carry out unit development and verification based on demand analysis, architecture design, unit design requirements, etc. At the same time, carry out technical research on technologies with lower maturity, form unit subordinate configuration plans, and build a design plan for each configuration plan. The design plan includes the unit design BOM. When the maturity of the technical research meets the requirements, the technology will support the design plan.

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

[0096] Furthermore, the method further comprises:

[0097] Name the unit module;

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

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

[0100] The technical maturity of the unit modules is graded from level 1 to level 9;

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

[0102] In specific implementation, for the same unit A, there may be multiple configuration schemes such as "Configuration Scheme 1" and "Configuration Scheme 2" to represent different design schemes or different states of the same unit. Different "configuration schemes" are uniquely identified and distinguished by "unit module configuration codes". The process of assigning values ​​to attribute information, as well as naming and coding, and the process of identifying the technical maturity is also the process of defining the unit module, and the final unit module definition attribute table is formed, refer to Table 1.

[0103] Table 1 Unit module definition attribute table

[0104]

[0105]

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

[0107] The unit module has a unit module definition attribute table and has been reviewed and published;

[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 rules of the unit module code meet the requirements of the database numbering rules;

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

[0111] The unit module has undergone technical maturity assessment and the technical maturity has reached level 6 or above;

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

[0113] In specific implementation, when judging whether the composition information of the unit module is complete, it is generally judged whether the drawings, models, supporting documents and other data contained in the component structure tree under the unit module are complete and have been released; whether the subordinate design BOM architecture meets the basic requirements for the construction of the design BOM. Combining the theory of aero-engine system engineering, aero-engine development experience and the requirements for the use of unit module data, a preset unit entry criterion is formed. When judging whether it meets the preset unit entry criterion, each one is judged one by one. When each one meets the requirements, it meets the preset unit entry criterion. After the access review of each unit module, a unit module access review report is formed, and the unit module data package can be included in the unit module database for management.

[0114] The unit module library is the basis of unit module configuration and is a collection of all unit modules and unit module unit values, such as Figure 6 As shown. The unit module library includes all unit modules that have passed the access review into the unit module list, and establishes a one-to-one association relationship with the unit module by including its unit module unit value and corresponding coding, naming information, technical maturity, etc. as attachment data. The unit module unit value can be screened, queried and called through the unit module library.

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

[0116] Conduct logical architecture analysis based on the target requirements of new products;

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

[0118] According to the engine configuration and scheme design results, the unit division structural objects and their characteristic factors are clarified, the main physical components of the engine are preliminarily clarified, and the characteristic factors of its structural characteristics, spatial distribution, functional allocation, and performance indicators are sorted out; the correlation relationship between parts is analyzed and the unit association matrix is ​​optimized to form the division scheme of the target unit and the design requirements of the target unit.

[0119] In specific implementation, the target unit body can be divided through the following two steps:

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

[0121] When developing new products or improving or remodeling products, the first step is to clarify the engine usage requirements. For example, if you want to develop an aircraft engine that provides thrust in a certain state, you need to have a certain capability. Based on the engine development requirements, you can design the logical architecture, define the engine logical subsystems at the logical level, analyze the interaction between the logical subsystems, and define how to implement external functions.

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

[0123] Based on the results of the logical architecture analysis, the subsystem composition definition and interface interaction analysis are carried out at the physical implementation level to determine the preliminary interface, physical composition, etc. According to the engine configuration and scheme design results, the unit division structure objects and their characteristic factors are clarified, the main physical components of the engine are preliminarily clarified, and its structural characteristics, spatial distribution, functional allocation, performance indicators and other characteristic factors are sorted out. According to the analysis of the association relationship between parts and the optimization of the unit association matrix, the unit division scheme and unit design requirements are formed.

[0124] Through the above steps, multiple units such as unit 1, unit 2, unit 3, unit 4, unit 5, unit 6, etc. are divided, and design requirements and related parameters such as functions, performance, structure, interface, etc. related to each unit are proposed.

[0125] Furthermore, based on the unit body module database, configuration combinations of each unit body module that meet the design requirements of the target unit body are performed to obtain a final complete product design solution, including:

[0126] For each target unit body, based on the design requirements of the target unit body, a plurality of unit body modules are selected from the unit body module database;

[0127] For each target unit body, the unit body module unit value of each unit body module screened out is compared with the design requirements, the matching value is calculated, and a number of candidate unit body modules are screened;

[0128] The candidate unit body modules of all target unit bodies are combined to obtain multiple configuration combinations, and the effectiveness trade-off value of each configuration combination is calculated. Based on the calculation results, the optimal configuration combination is screened out and the optimal configuration combination is used as the final complete product design solution.

[0129] In the specific implementation, for example, for the "XXX01001" engine configuration requirements, in the unit module library, according to the design requirements and constraints such as the function, performance, structure, interface, etc. of unit 1, four unit modules, namely "unit module 1", "unit module 2", "unit module 3" and "unit module 4" are selected, and the unit module unit values ​​corresponding to the unit modules are matched by computer to meet the design requirements of unit 1.

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

[0131]

[0132] Among them, P is the matching value, V im is the mth relevant parameter value of the i-th type of attribute information in the unit value of the unit module, V tim The mth relevant parameter value of the i-th type of attribute information proposed for the unit design requirement, k i is the weight value of the i-th attribute information in the unit value of the unit module, where i=1 is the performance interface index information, i=2 is the physical interface index, i=3 is the life index information, and i=4 is the general quality characteristic index information. i The value of needs to meet the following requirements based on the project development experience:

[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] The matching value P of each unit cell module is obtained. When P≥0.85, the unit cell module can be used as one of the candidate unit cell modules.

[0139] Specifically, for k i The value of can also be divided into detailed weight values ​​for each parameter according to the specific parameters in each type of attribute information, for example:

[0140] For performance interface indicators: select k of performance indicator 1 11 =0.2, performance index 2 k 12 =0.15, performance index 3 k 13 =0.1;

[0141] Physical interface index: physical index 1 k 21 =0.2, physical index 2 k 22 =0.3;

[0142] Lifespan index: Physical index 1 k 31 =0.05;

[0143] Through the above calculation method of unit value matching value, 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 alternatives.

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

[0145]

[0146] Furthermore, the matching value calculation is performed to screen a number of candidate unit modules, including:

[0147] The matching value is calculated, and the calculation formula of the matching value is:

[0148]

[0149] Among them, P is the matching value, V im is the mth relevant parameter value of the i-th type of attribute information in the unit value of the unit module, V tim The mth relevant parameter value of the i-th type of attribute information proposed for the unit design requirement, k i is the weight value of the i-th attribute information in the unit value of the unit module, where i=1 is the performance interface index information, i=2 is the physical interface index, i=3 is the life index information, i=4 is the general quality characteristic index information, and k i The value of meets 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] The matching value P of each unit cell module is obtained. When P≥0.85, the unit cell module can be used as one of the candidate unit cell modules.

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

[0157]

[0158] Among them, 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 I ND is the technical maturity of the nth unit module under the current configuration combination, i The simulation result value of the current configuration combination is verified by I ND ti The numerical value of the design requirement indicators proposed in the target needs of the new product.

[0159] In specific implementation, usually, during the process of developing new products or improving and remodeling, due to the complexity and high coupling of aircraft engines, new configuration units are not generally selected on a large scale. Instead, while ensuring that most units remain unchanged, individual units are improved or new configurations are selected. Therefore, the number of permutations and combinations of new engine configurations is usually not too many.

[0160] Generate the engine unit configuration table according to the configuration combination results, see Figure 7 According to the configuration table combination, the product data management system selects the combination according to the unit module configuration code to form a single configuration engine design BOM, and the system calls the program to output the engine design plan and model. Through mature engine simulation software, based on performance models and physical models, the engine is simulated in terms of performance and strength, and the effectiveness trade-off value Q of the engine configuration plan (configuration combination) is calculated according to the calculation formula. In particular, when the simulation calculation verification has a "failed item",

[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. The calculation and ranking 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 solution.

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

[0163]

[0164] The engine design BOM, the calculation and ranking results of the effectiveness trade-off value Q of each configuration scheme, and related supporting materials (such as technology maturity evaluation report, simulation verification report, etc.) are submitted for review together, and the project decision-making level is responsible for reviewing and confirming the materials. Based on the ranking results of the engine design scheme after decision-making and weighing, "Configuration Combination 2" is selected as the optimal solution. The design BOM and engine unit configuration table generated based on "Configuration Combination 2" are issued to the manufacturing unit for related production activities. Specifically, it is necessary to conduct an audit of the engine configuration scheme after the configuration combination is completed. The decision-making level will conduct a meeting review based on the ranking results of the effectiveness trade-off value Q of the engine configuration scheme, related supporting materials, etc., to weigh and make decisions to determine the final engine design scheme, form the supporting design BOM of the final confirmed design scheme, and issue it to the contracting unit to carry out the next step of production and manufacturing activities.

[0165] In one embodiment, for each target unit body, the matching value of each unit body module is calculated based on the design requirements of the target unit body, and a plurality of candidate unit body modules are screened, including:

[0166] From the target unit bodies, determine the target unit body whose unit body module needs to be optimized;

[0167] For each target unit body that needs to optimize the unit body module, the matching value of each unit body module is calculated, and a number of candidate unit body modules are screened.

[0168] During specific implementation, during the process of developing new products or improving and remodeling them, due to the complexity and high coupling of aircraft engines, units with new configuration schemes are generally not selected on a large scale. Instead, while ensuring that most units remain unchanged (the same units as in the original design), individual units are improved or new configuration schemes are selected, thereby achieving rapid reuse of unit modules. Only matching calculations and trade-offs need to be made for units that require optimized configuration schemes, thereby reducing design costs, accelerating the maturity of key technologies and rapid configuration applications, and shortening product maturity cycles.

[0169] The embodiments provided by the present invention are based on the configuration configuration required for aircraft engine development, and then identify key technologies, drive basic research and technical breakthroughs, and combine the design results of aircraft engine units to build a unit module library that can be flexibly combined and quickly reused for multiple usage scenarios. It is only necessary to match and calculate the trade-offs for the units that need to optimize the configuration scheme, thereby reducing design costs. The unit configurable module is constructed based on the verified research results to achieve the decoupling of products and technologies, and products and unit modules, accelerate the maturity of key technologies and 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 repetitive workload by more than 80%;

[0170] Based on a normalized verification platform, we separate configuration from technology, deconstruct technical requirements, and through configuration reuse, we form a "general platform architecture + unit module" R&D model to support rapid series development and derivative development of products.

[0171] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. A product configuration method based on modularization of aircraft engine units, characterized in that: The method comprises: Based on demand analysis, the aircraft engine is divided into multiple units, each of which includes multiple different configuration schemes; For each unit body, obtain the attribute information of each configuration scheme; For each unit body, judging whether the configuration scheme of the unit body meets the preset unit body storage criteria based on the attribute information; Based on the configuration schemes that meet the preset unit storage criteria and the corresponding attribute information, a unit module database is constructed, each configuration scheme and its corresponding attribute information constitute a unit module in the unit module database, and one attribute information of a configuration scheme is a unit module unit value; Based on the target requirements of the new product, determine the target unit and the design requirements of each target unit; Based on the unit body module database, configuration combinations of each unit body module that meet the design requirements of the target unit body are performed, and the configuration combinations are optimized based on the unit body module unit values ​​to obtain a final complete product design solution.

2. The product configuration method based on modularization of aircraft engine units according to claim 1, characterized in that: Based on the demand analysis, the aircraft engine is divided into multiple units, including: Get engine pedigree planning; Conduct product demand analysis based on engine family planning; Based on product demand analysis, design the engine logical architecture and physical architecture; Based on the design of each architecture, the physical architecture of the engine is decoupled in terms of performance and physics, the unit division is completed, and the function, performance and interface characteristics of each unit are clarified. After the unit is verified to meet the requirements and the technology is mature, the relevant characteristic data will be used as attribute information within the unit module.

3. The product configuration method based on modularization of aircraft engine units according to claim 1, characterized in that: The attribute information includes technology maturity, performance interface indicator information, physical interface indicator information, life indicator information, general quality characteristic indicator information and unit module composition information. The general quality characteristic indicator information includes maintainability parameters, safety parameters and security parameters. The unit module composition information includes a list of subordinate components, a list of supporting production documents, verification results and a review report.

4. The product configuration method based on modularization of aircraft engine units according to claim 3 is characterized in that: The method further comprises: Name the unit module; Encoding the unit body module to form a unit body module code; Encoding the configuration scheme of each unit body to form a unit body module configuration code; The technical maturity of the unit modules is graded from level 1 to level 9; Based on the unit module name, unit module code, unit module configuration code and attribute information, a unit module definition attribute table is formed.

5. The product configuration method based on modularization of aircraft engine units according to claim 4 is characterized in that: The preset unit storage criteria include the following judgment criteria performed in sequence: The unit module has a unit module definition attribute table and has been reviewed and published; The unit module definition attribute table is complete, and the data in the table can be recognized and called by the computer; The unit module code has a unique number, and the numbering rules of the unit module code meet the requirements of the database numbering rules; The unit module configuration code has a unique configuration number, and the numbering rule of the unit module configuration code meets the database numbering rule requirements; The unit module has undergone technical maturity assessment and the technical maturity has reached level 6 or above; The composition information of the unit module is complete.

6. The product configuration method based on modularization of aircraft engine units according to claim 1, characterized in that: Determining the target unit and the design requirements of each target unit based on the target requirements of the new product includes: Conduct logical architecture analysis based on the target requirements of new products; Based on the results of the logical architecture analysis, the subsystem composition definition and interface interaction analysis are carried out at the physical implementation level to determine the preliminary interface and physical composition; According to the engine configuration and scheme design results, the unit division structural objects and their characteristic factors are clarified, the main physical components of the engine are preliminarily clarified, and the characteristic factors of its structural characteristics, spatial distribution, functional allocation, and performance indicators are sorted out; the correlation relationship between parts is analyzed and the unit association matrix is ​​optimized to form the division scheme of the target unit and the design requirements of the target unit.

7. The product configuration method based on modularization of aircraft engine units according to claim 1, characterized in that: The method of performing configuration combinations of each unit body module that meets the design requirements of the target unit body based on the unit body module database, and optimizing the configuration combinations based on the unit body module unit values ​​to obtain a final complete product design solution includes: For each target unit body, based on the design requirements of the target unit body, a plurality of unit body modules are selected from the unit body module database; For each target unit body, the unit body module unit value of each unit body module screened out is compared with the design requirements, the matching value is calculated, and a number of candidate unit body modules are screened; The candidate unit body modules of all target unit bodies are combined to obtain multiple configuration combinations, and the effectiveness trade-off value of each configuration combination is calculated. Based on the calculation results, the optimal configuration combination is screened out and the optimal configuration combination is used as the final complete product design solution.

8. The product configuration method based on modularization of aircraft engine units according to claim 7 is characterized in that: The matching value calculation is performed to screen a number of candidate unit modules, including: The matching value is calculated, and the calculation formula of the matching value is: Among them, P is the matching value, V im is the mth relevant parameter value of the i-th type of attribute information in the unit value of the unit module, V tim The mth relevant parameter value of the i-th type of attribute information proposed for the unit design requirement, k i is the weight value of the i-th attribute information in the unit value of the unit module, where i=1 is the performance interface index information, i=2 is the physical interface index, i=3 is the life index information, i=4 is the general quality characteristic index information, and k i The value of meets 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; The matching value P of each unit cell module is obtained. When P≥0.85, the unit cell module can be used as one of the candidate unit cell modules.

9. The product configuration method based on modularization of aircraft engine units according to claim 7, characterized in that: The calculation formula of the effectiveness trade-off value is: Among them, 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 technical maturity of the nth unit module under the current configuration combination, IND i The simulation result value of the current configuration combination is verified, IND ti The numerical value of the design requirement indicators proposed in the target needs of the new product.

10. The product configuration method based on modularization of aircraft engine units according to claim 7, characterized in that: For each target unit body, the matching value of each unit body module is calculated based on the design requirements of the target unit body, and a number of candidate unit body modules are screened, including: From the target unit bodies, determine the target unit body whose unit body module needs to be optimized; For each target unit body that needs to optimize the unit body module, the matching value of each unit body module is calculated, and a number of candidate unit body modules are screened.

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