Aircraft product configuration item division adjustment management method

Abstract

The invention belongs to the field of aircraft research and development process construction technology management, and relates to an aircraft product configuration item division adjustment management method. The method comprises the steps of S1, classifying configuration items according to design data types, and dividing the configuration items into a machine body structure class, a matched product class, a pipeline class, a wire harness class, a guarantee equipment class and a technical data class; s2, performing configuration item selection step by step based on an aircraft product decomposition structure, and forming three types of resource trees of universal configuration, selected installation items and customized items from a project level, an aircraft level, a system level, a subsystem level and a subsystem level; s3, starting configuration item division in the detailed preliminary design stage, wherein each configuration item is divided according to a specified division principle; and S4, in a detailed design stage and an engineering change stage, performing content adjustment on each configuration item by adopting a graded auditing and signing process. The technical state management efficiency of the whole life cycle of the aircraft is improved.

Description

Technical Field

[0001] This application belongs to the field of aircraft R&D process construction technology management, specifically involving a management method for the division and adjustment of aircraft product configuration items. Background Technology

[0002] The aircraft development product data adopts a modular simplified configuration management method for technical status control. The core control point of the modular simplified configuration management method is the division and change management of product configuration items. As the basic control unit for relevant parties and development units to carry out model technical status management, the selection and division of configuration items is one of the important tasks of technical status identification, especially having a significant impact on the full life cycle technical status control among various research and development units in subsequent stages such as trial production and flight testing.

[0003] Currently, the classification of configuration items still largely draws on the historical status of existing aircraft models, which cannot adapt to the development needs of the next generation of aircraft. The classification principle is too simplistic and requires the assistance of the process department to establish it, which seriously affects scientific research and trial production. Furthermore, the construction and adjustment of configuration items lack perfect control measures, which can lead to loss of control over the physical technical status, especially during the aircraft trial production stage. Summary of the Invention

[0004] To address the aforementioned issues, this application provides a method for managing the classification and adjustment of aircraft product configuration items, which mainly includes:

[0005] Step S1: Classify the configuration items according to the design data type, dividing them into body structure, supporting products, pipelines, wiring harnesses, support equipment, and technical data.

[0006] Step S2: Based on the aircraft product decomposition structure, configuration item selection is carried out step by step, forming three types of resource trees: general configuration, optional items, and customized items from the project level, aircraft level, system level, subsystem level, and subsystem level.

[0007] Step S3: Initiate configuration item division during the detailed preliminary design phase, including dividing each configuration item according to the specified division principles;

[0008] Step S4: During the detailed design and engineering change phases, a tiered review and approval process is used to adjust the content of each configuration item.

[0009] Preferably, in step S3, when dividing the configuration items, the selected items include:

[0010] Projects that are outsourced for manufacturing, projects delivered separately, projects installed separately, projects involving the docking and assembly of modules and system filling during sub-assembly, projects involving the installation of modules of the system and the installation of equipment, conduits and wiring harnesses throughout the machine during final assembly, projects with selections, optional installations and multiple options specified in the overall plan, projects that are installed in conjunction with selected projects, projects that are replaced during the installation of optional projects, projects that involve separate changes to control components or parts, projects that involve multi-configuration serialization and modular design, projects with specified high-risk characteristics and backup projects that replace projects with such high-risk characteristics, projects with specified complexity interfaces with other projects, projects with specified support and maintenance conditions, projects related to testing and modification, independently managed drawings, finished equipment installation models, drawings and software configuration items, and interface control documents.

[0011] Preferably, in step S3, the specified division principles include:

[0012] For manufacturing purposes, select units whose functional and physical characteristics can be managed separately as configuration items.

[0013] Preferably, step S3 further includes:

[0014] The components are divided into configuration items according to their structural design, process separation surfaces, and assembly sequence.

[0015] Structural components based on process frame are expressed through the first variable configuration item (VCI) and are divided into configuration items as a sub-item of the configuration item;

[0016] The connectors that connect the variable configuration item (VCI) structure of the body are expressed through the second variable configuration item (VCI) and are divided into configuration items as a sub-item of the configuration item;

[0017] The supporting components that support the moving structure are expressed through the third variable configuration item (VCI) and are divided into configuration items as a sub-item of the configuration item.

[0018] Components with interchangeability requirements are expressed through the fourth variable configuration item (VCI) and are divided into configuration items as a sub-item of the configuration item.

[0019] The components used to strengthen the body structure are expressed through the fifth variable configuration item (VCI) and are divided into configuration items as a sub-item of the configuration item.

[0020] The connecting components and joints that bear and transmit specified loads are expressed through the sixth variable configuration item (VCI) and are divided into configuration items as a sub-item of the configuration item;

[0021] The structure of the multi-scheme design is expressed through multiple seventh variable configuration items (VCIs), which are used as multiple sub-items of the configuration item for configuration item division;

[0022] The molding method of composite materials is expressed through the eighth variable configuration term (VCI) and is divided into configuration terms as a sub-term of the configuration term.

[0023] Preferably, in step S3, when expressing the second variable configuration item VCI and the third variable configuration item VCI, the second variable configuration item VCI and the third variable configuration item VCI are further decomposed according to the process steps and design tasks.

[0024] Preferably, in step S4, different approval processes and division of responsibilities are used for different stages, namely the detailed design stage and the engineering change stage.

[0025] Preferably, in step S4, when making engineering changes to the connector expressed by the second variable configuration item VCI, the method further includes assessing the scope of the change's impact based on a dynamic impact propagation model. The formula for calculating the impact degree E of the model is as follows:

[0026] ;

[0027] Where k is the number of associated VCIs directly or indirectly affected by the change. Let the keyness weight of the j-th associated VCI be... To demonstrate the strength of the dependency between the j-th VCI and the currently modified VCI, Let j be the total number of dependencies for the j-th VCI. To influence the number of hops required to propagate to the j-th VCI;

[0028] If E > 0.8, it is considered a major change, and a high-level review in the tiered approval process is initiated; if E ≤ 0.3, it is authorized for fast-track approval.

[0029] This application ensures the applicability of configuration item selection, classification, and adjustment management throughout the entire aircraft development process, laying the foundation for improving the efficiency of technical status management throughout the aircraft's life cycle and realizing single-flight management. Attached Figure Description

[0030] Figure 1 This is a flowchart of a preferred embodiment of the aircraft product configuration item classification and adjustment management method of this application.

[0031] Figure 2 This application Figure 1 The flowchart for adjusting the configuration items in the illustrated embodiment is shown. Detailed Implementation

[0032] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are only some, not all, of the embodiments of this application. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain this application, and should not be construed as limiting this application. All other embodiments obtained by those skilled in the art based on the embodiments of this application without creative effort are within the scope of protection of this application. The embodiments of this application will be described in detail below with reference to the accompanying drawings.

[0033] This application provides a method for managing the classification and adjustment of aircraft product configuration items, such as... Figures 1-2 As shown, it mainly includes:

[0034] Step S1: Classify the configuration items according to the design data type, dividing them into body structure, supporting products, pipelines, wiring harnesses, support equipment, and technical data.

[0035] Step S2: Based on the aircraft product decomposition structure, configuration item selection is carried out step by step, forming three types of resource trees: general configuration, optional items, and customized items from the project level, aircraft level, system level, subsystem level, and subsystem level.

[0036] Step S3: Initiate configuration item division during the detailed preliminary design phase, including dividing each configuration item according to the specified division principles;

[0037] Step S4: During the detailed design and engineering change phases, a tiered review and approval process is used to adjust the content of each configuration item.

[0038] Configuration items are the basic control units for technical status management. Their fundamental purpose is to address the problem of "loss of control over physical technical status" that arises in the development of next-generation aircraft. Therefore, their classification is closely related to later life-cycle activities such as production, flight testing, and maintenance, rather than being merely a product of the design phase.

[0039] This application first defines the categories of configuration items in step S1, that is, the "horizontal" classification of configuration items, and clarifies which types of product data need to be managed as configuration items, mainly including the following categories.

[0040] (1) Body structure category: The design elements are the body structure without system installation parts, such as frames, beams, skins, and covers. When dividing into modules, the separation surface between structural functions and processes should be given priority, and all structural design modules should be kept within the same section as much as possible.

[0041] (2) Supporting products category: The design elements are supporting products and their on-machine screw-on mounting parts. Supporting products include accessories such as finished end connectors, rear accessories, and LRU mounting parts. On-machine screw-on mounting parts include brackets, shock absorbers, bolts, nuts, etc. Supporting product modules should be divided down to the installation unit level. Each independent installation unit and its accessories (including mounting parts) should be divided into independent modules.

[0042] (3) Piping components: Design elements include pipes, pipe fittings, and pipe threaded installation components, such as clamps, pipe clips, bolts, and nuts. The classification criteria include two aspects: First, pipes are generally divided into modules according to their main compartment and system / subsystem. For example, all pipes of the hydraulic system in the emergency power compartment can be divided into a separate module, and the fuel system pipes in the emergency power compartment can be divided into a separate module. Second, pipe installation components, such as pipe clips and clamps, are generally divided into modules according to compartment and system, and are also allowed to be included in the conduit module. For example, the hydraulic system pipe installation components in the left equipment compartment are divided into a separate module, and the fuel system pipe installation components in the emergency power compartment are divided into a separate module.

[0043] (4) Wire harnesses: The design elements are the three-dimensional model design of wire harnesses and their installation, mainly including wire harnesses, wire harness terminal connectors, wire harness screw-on mounting parts (clamps, bolts, etc.), negative line devices and their screw-on mounting parts, etc. The division criteria include three aspects: First, the negative line device of each compartment is divided into separate modules; second, each wire harness is divided into a wire harness module; third, wire harness mounting parts are divided into modules according to compartment, for example, the low-frequency wire harness mounting parts of the left equipment compartment are divided into a separate module.

[0044] (5) Support equipment / tools category, design elements include comprehensive support equipment and tools. Support equipment and tools with independent functions are divided into separate modules, such as emergency power installation frame module and canopy support rod module.

[0045] (6) Technical data category: Design elements include technical data. Based on the composition of the technical data, a document is divided into modules, such as the working unit code manual module or the instruction manual module for a certain type of aircraft.

[0046] Step S2 is used for configuration item selection, which is the "vertical" classification of configuration items. Configuration items should be selected from products whose functional and physical characteristics can be managed separately and which help to achieve the overall end-use requirements. The principle is based on PBS (Plan-Based Service), expanding step by step from project level, aircraft level, system level, subsystem level, and sub-system level as technical status items; it should reflect serialization and generalization design requirements, and be achieved by constructing three types of technical status item resource trees: general configuration, optional items, and customized items.

[0047] Step S3 is used for configuration item division. Based on the selection of higher-level technical status items, the top-level technical status items are divided for the prototype manufacturing, flight testing, and subsequent development stages. This division forms smaller-granular modules, which are the lower-level module technical status items. The division activity generally begins in the detailed preliminary design stage, is basically finalized at the end of the detailed design, and is gradually improved, modified, and confirmed in subsequent development stages.

[0048] In some alternative implementations, in step S3, when performing configuration item segmentation, the selected items include:

[0049] Projects that are outsourced for manufacturing, projects delivered separately, projects installed separately, projects involving the docking and assembly of modules and system filling during sub-assembly (installation of equipment, conduits and cables), projects involving the installation of modules of the system and the installation of equipment, conduits and wiring harnesses throughout the machine during final assembly, projects with selections, optional installations and multiple options specified in the overall plan, projects that are installed in conjunction with selected projects, projects that are replaced during the installation of optional projects, projects that involve individual changes to control components or parts, projects that involve multi-configuration serialization and modular design, projects with specified high-risk characteristics and backup projects that replace projects with such high-risk characteristics, projects with interfaces with other projects of specified complexity, projects with specified support and maintenance conditions, projects related to testing and modification, independently managed drawings (schematic diagrams, wiring harness diagrams, etc.), finished equipment installation models, drawings and software configuration items, and interface control documents.

[0050] In some alternative implementations, the specified partitioning principles in step S3 include:

[0051] For manufacturing purposes, select units whose functional and physical characteristics can be managed separately as configuration items.

[0052] This embodiment facilitates change control and management during subsequent development phases.

[0053] In alternative implementations, the division principles also include control over the division objects and granularity. Regarding the division objects, technical status items should be selected based on the business scope and resource allocation, focusing on system functions, design definitions, and product structure. In terms of granularity, the quality and effectiveness of configuration management should be ensured, meeting the unitized management requirements of technical status items in terms of functional and physical characteristics, and ensuring effective configuration of the product structure in the product data management system. Furthermore, the manufacturing plant's development model should be considered, accurately defining the delivery status of technical status items manufactured by each supplier; the system's functional composition characteristics and design separation surfaces should be reflected, achieved through modular design and module finalization; the process assembly areas and process separation surfaces should be reflected, achieved through design occupancy and process areas of each model; components and equipment / finished products should be appropriately selected based on their independent special functional characteristics.

[0054] In some alternative implementations, step S3 further includes:

[0055] (1) According to the design of each component structure, process separation surface and assembly sequence, the composition of each component is divided into configuration items; for example, the front fuselage: frame, floor, wall panel, mounting frame and front landing gear bay, etc. are disassembled, sub-assembly process, process frame setting, assembly inside and outside the frame and installation of components after removal from the frame.

[0056] (2) Structural components based on process frame are expressed through the first variable configuration item (VCI) and are divided into configuration items as a sub-item of configuration item; for example, an assembly VCI should be set to express the components of structural assembly connection, such as: plate, corner box, connector, joint and standard parts.

[0057] (3) The connecting parts that connect the variable configuration items (VCI) of the fuselage are expressed through the second variable configuration item (VCI) and are divided into configuration items as a sub-item of the configuration item; in addition to the connection and docking of each VCI structure, it also includes the docking of structural sections, such as the front fuselage and the middle fuselage. A connecting VCI should be set to express the components connected by the VCI, docking strips, machined stringer joints and standard parts.

[0058] (4) The supporting components of the moving structure are expressed through the third variable configuration item VCI and divided into configuration items as a sub-item of the configuration item; for example, structural hinge support components should be set as VCI, such as: hinge supports of the cover, door frame, fairing, as well as struts and locking mechanisms, etc.

[0059] (5) Components with interchangeability requirements are expressed through the fourth variable configuration item (VCI) and divided into configuration items as a sub-item of the configuration item; for example, cockpit canopy, landing gear door, etc.

[0060] (6) The components used to strengthen the body structure are expressed through the fifth variable configuration item (VCI) and divided as a sub-item of the configuration item; for example, the reinforcement design of each cover and door frame, the added wall panels, reinforcing beams and other components should be set as a VCI.

[0061] (7) The connecting members and joints that bear and transmit the specified loads are expressed through the sixth variable configuration item VCI and are divided into configuration items as a sub-item of the configuration item.

[0062] (8) The structure of the multi-scheme (including primary and backup schemes) design is expressed through multiple seventh variable configuration items (VCIs), and the configuration items are divided as multiple sub-items of the configuration item.

[0063] (9) The molding method of composite materials is expressed through the eighth variable configuration item (VCI) and is divided into configuration items as a sub-item of the configuration item. In composite material structures, technical status items should be set according to the characteristics and requirements of integral molding, co-curing and bonding of composite materials. Among them, the electrical lap joint components in composite material structures should be set as a VCI.

[0064] When naming each VCI, automatically add and adjust the naming suffixes according to technical personnel, adding words such as installation, docking (connection), assembly, and component as suffixes to indicate whether it includes the connecting parts used during installation, docking (connection), and assembly. The cover name should include the cover's maintenance code. The design of finished products and equipment installation fasteners and structural components should be managed as separate VCIs.

[0065] In some optional implementations, step S3, when expressing the second variable configuration item VCI and the third variable configuration item VCI, includes further decomposing the second variable configuration item VCI and the third variable configuration item VCI according to the process steps and design tasks. Such VCIs also follow assembly-oriented technology requirements.

[0066] Finally, configuration item adjustment management is carried out in step S4. By defining the configuration item adjustment management business process, a set of technical status item change business processes is constructed, which are initiated by designers and approved by configuration and related personnel. The management requirements, business processes and work instructions of this business are clarified. The management method of configuration item adjustment is realized by improving the digital tools to achieve the construction of means.

[0067] like Figure 2 As shown, the top-level product structure, after being confirmed by the overall team and each system, is uniformly submitted to the technical management team for system construction and maintenance. The configuration layer is designed, established, and maintained by the respective professional supervisors, with the division method as described in the previous steps. The creation and adjustment of the configuration layer should be approved by the system before taking effect. In some optional implementations, in step S4, different approval processes and divisions of responsibilities are used in different stages, namely the detailed design stage and the engineering change stage, and the nodes are controlled according to project nodes. The creation and adjustment of the configuration layer should distinguish whether the specification validity is configured before the initial release of the model, and define different subsequent processes; for models that have not configured specification validity before the initial data release, the specification validity configuration process should be automatically initiated after the creation and adjustment of the configuration layer; specification configuration is not allowed during the change process of all released data.

[0068] In some optional implementations, step S4, when making engineering changes to the connector expressed by the second variable configuration item VCI, further includes assessing the scope of the change's impact based on a dynamic impact propagation model, wherein the formula for calculating the impact degree E of the model is:

[0069] ;

[0070] Where k is the number of associated VCIs directly or indirectly affected by the change. Let the keyness weight of the j-th associated VCI be... To demonstrate the strength of the dependency between the j-th VCI and the currently modified VCI, Let j be the total number of dependencies for the j-th VCI. To influence the number of hops required to propagate to the j-th VCI;

[0071] If E > 0.8, it is considered a major change, and a high-level review in the tiered approval process is initiated; if E ≤ 0.3, it is authorized for fast-track approval.

[0072] For example, an engineering change (ECR) was proposed: to optimize the second variable configuration item (VCI) connecting the fuselage and the wing, namely the main docking joint, by replacing its material from the original high-strength aluminum alloy with a more advanced composite material to reduce weight by 15%.

[0073] This change to the connector affects the following 5 VCIs:

[0074] (1) The main body of the wing, the joint is the foundation for the installation of the wing, the connection interface and load path need to be re-verified, the criticality weight of the main body of the wing is 0.9, the dependence strength ratio is 0.13, and the propagation hop count is 1;

[0075] (2) The structure of the fuselage main body and the joint connection area needs to be redesigned and analyzed. The criticality weight of the fuselage main body is 0.9, the dependency strength ratio is 0.10, and the propagation hop count is 1;

[0076] (3) The flap system's control cable routing is affected by minor adjustments to the shape of the wing docking area. The criticality weight of the flap system is 0.7, the dependence strength ratio is 0.125, and the propagation hop count is 2.

[0077] (4) Wing harness: The length of the harness passing near the connector and the fixing clamps may need adjustment. The criticality weight of the wing harness is 0.5, the dependence strength ratio is 0.10, and the propagation hop count is 2;

[0078] (5) Maintenance manual: The inspection and repair procedures for composite materials are completely different from those for metal parts, and the manual needs to be updated. The criticality weight of the maintenance manual is 0.6, the dependence strength ratio is 1.0, and the propagation hop count is 3.

[0079] Substituting into the above formula, we can calculate E=1.13. E>0.8 is considered a major change.

[0080] In this embodiment, triggering a high-level review means that the change must be submitted to configuration control senior management for a high-level review, focusing on assessing its comprehensive impact on cost, project schedule, aircraft weight indicators, airworthiness compliance (composite material structures have stricter certification requirements), etc.

[0081] In this embodiment, the propagation hop count describes the "distance" an engineering change travels through the configuration item (VCI) dependency network. It quantifies the dependency steps required for the impact of a change to propagate from its origin to an affected item. Specifically, in this example, from the change to the "wing-fuselage connector" to each VCI, for the wing and fuselage, the connector's material, size, and mounting interface directly determine the corresponding design parameters of the connected wing and fuselage structures—this is a direct dependency with a propagation hop count of 1. For the flap system and cabling, local changes to the wing structure may affect the routing and anchoring points of the cabling passing through it; changes to the fuselage structure may affect the installation of connected components such as the flap system—this is an indirect dependency with a propagation hop count of 2. For the manual, all the aforementioned physical configuration changes (connectors, wings, fuselage, flaps, wiring harnesses) ultimately converge and are reflected in the maintenance procedures, diagrams, and instructions. The maintenance manual must be updated based on all these final physical states. This is a further indirect dependency with a propagation hop count of 3.

[0082] This application, using the modular simplified configuration management method as its core control point, achieves the rational division and strict management of configuration items for modular military aircraft products through standardized business logic and workflows. This reduces the cost and difficulty of technical status control, standardizes and rationalizes the product definition process, and improves engineering development efficiency. The results of this project can be extended to the technical status management of all models, providing a clear approach and methodology for the technical status control of newly developed models.

[0083] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. An aircraft product configuration item partitioning adjustment management method, characterized in that, Includes the following steps: Step S1: Classify the configuration items according to the design data type, dividing them into body structure, supporting products, pipelines, wiring harnesses, support equipment, and technical data. Step S2: Based on the aircraft product decomposition structure, configuration item selection is carried out step by step, forming three types of resource trees: general configuration, optional items, and customized items from the project level, aircraft level, system level, subsystem level, and subsystem level. Step S3: Initiate configuration item division during the detailed preliminary design phase, including dividing each configuration item according to the specified division principles; Step S4: During the detailed design and engineering change phases, a tiered review and approval process is used to adjust the content of each configuration item.

2. The aircraft product configuration item partition adjustment management method of claim 1, wherein, In step S3, when dividing the configuration items, the selected items include: Projects that are outsourced for manufacturing, projects delivered separately, projects installed separately, projects involving the docking and assembly of modules and system filling during sub-assembly, projects involving the installation of modules of the system and the installation of equipment, conduits and wiring harnesses throughout the machine during final assembly, projects with selections, optional installations and multiple options specified in the overall plan, projects that are installed in conjunction with selected projects, projects that are replaced during the installation of optional projects, projects that involve separate changes to control components or parts, projects that involve multi-configuration serialization and modular design, projects with specified high-risk characteristics and backup projects that replace projects with such high-risk characteristics, projects with specified complexity interfaces with other projects, projects with specified support and maintenance conditions, projects related to testing and modification, independently managed drawings, finished equipment installation models, drawings and software configuration items, and interface control documents.

3. The aircraft product configuration item partition adjustment management method of claim 1, wherein, In step S3, the specified partitioning principles include: For manufacturing purposes, select units whose functional and physical characteristics can be managed separately as configuration items.

4. The method for managing the classification and adjustment of aircraft product configuration items according to claim 1, characterized in that, Step S3 further includes: The components are divided into configuration items according to their structural design, process separation surfaces, and assembly sequence. Structural components based on process frame are expressed through the first variable configuration item (VCI) and are divided into configuration items as a sub-item of the configuration item; The connectors that connect the variable configuration item (VCI) structure of the body are expressed through the second variable configuration item (VCI) and are divided into configuration items as a sub-item of the configuration item; The supporting components that support the moving structure are expressed through the third variable configuration item (VCI) and are divided into configuration items as a sub-item of the configuration item. Components with interchangeability requirements are expressed through the fourth variable configuration item (VCI) and are divided into configuration items as a sub-item of the configuration item. The components used to strengthen the body structure are expressed through the fifth variable configuration item (VCI) and are divided into configuration items as a sub-item of the configuration item. The connecting components and joints that bear and transmit specified loads are expressed through the sixth variable configuration item (VCI) and are divided into configuration items as a sub-item of the configuration item; The structure of the multi-scheme design is expressed through multiple seventh variable configuration items (VCIs), which are used as multiple sub-items of the configuration item for configuration item division; The molding method of composite materials is expressed through the eighth variable configuration term (VCI) and is divided into configuration terms as a sub-term of the configuration term.

5. The aircraft product configuration item partition adjustment management method of claim 4, wherein, In step S3, when expressing the second variable configuration item VCI and the third variable configuration item VCI, the second variable configuration item VCI and the third variable configuration item VCI are further decomposed according to the process steps and design tasks.

6. The aircraft product configuration item partition adjustment management method of claim 1, wherein, In step S4, different approval processes and division of responsibilities are used in the detailed design phase and the engineering change phase.

7. The aircraft product configuration item partition adjustment management method of claim 4, wherein, In step S4, when making engineering changes to the connectors expressed through the second variable configuration item VCI, the process further includes assessing the scope of the changes based on a dynamic impact propagation model. The formula for calculating the impact degree E of the model is as follows: ； Where k is the number of associated VCIs directly or indirectly affected by the change. Let the keyness weight of the j-th associated VCI be... To demonstrate the strength of the dependency between the j-th VCI and the currently modified VCI, Let j be the total number of dependencies for the j-th VCI. To influence the number of hops required to propagate to the j-th VCI; If E > 0.8, it is considered a major change, and a high-level review in the tiered approval process is initiated; if E ≤ 0.3, it is authorized for fast-track approval.

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