MBSE-based aircraft metrological modeling method and computer equipment

Abstract

The invention discloses an MBSE-based aircraft metrological modeling method and computer equipment. The method comprises the following steps: constructing a metrological meta-model by taking detection equipment or calibration equipment of a detected object as a minimum element; the whole aircraft is divided into sub-modules, demand analysis is carried out for metering objects corresponding to the sub-modules, and a metering demand model is formed; taking the output of the metrological demand model as the input, obtaining a functional architecture of the metering system through demand analysis, constructing a logical architecture of the system based on the functional architecture of the system, forming a metrological design model, and obtaining a recommendation list of the detection equipment or the calibration equipment; and determining a model selection scheme of the detection equipment or the calibration equipment from the recommendation list according to a trade-off strategy by taking the output of the metrological design model as the input, and outputting an aircraft traceability demand summary sheet. The overall measurability of the aircraft can be improved, the traceability work of the aircraft in the whole life cycle is achieved, and the development and subsequent maintenance cost of the aircraft is reduced.

Description

Technical Field

[0001] The present invention belongs to the field of measurability and system engineering methods, and in particular relates to an aircraft measurability modeling method and computer equipment based on MBSE. Background Art

[0002] Aircraft development is a complex system engineering project. Modern aircraft design often adopts the Model-Based Systems Engineering (MBSE) method. This method is superior to the traditional document-based and code-centric design methods. It uses a model-driven process and a graphical modeling language to describe, analyze, and design the requirements, structure, and behavior of complex systems in a non-dual manner, thereby avoiding inconsistencies when associating traceability information, reducing contradictions between system information elements, improving the collaborative efficiency of overall and separate designs, and eliminating system development problems caused by ambiguity in understanding. Moreover, the model-based system engineering method covers the entire design life cycle, and can quickly iterate and test the simulation design, greatly improving the progress of system development.

[0003] However, in the current domestic aircraft R&D process, the metrological traceability issues in the equipment manufacturing, use and maintenance process are often ignored. This gap between design and use increases the difficulty of subsequent traceability and increases the cost of actual aircraft manufacturing and subsequent maintenance. Therefore, it is very necessary to propose metrology in the aircraft R&D and design process. Summary of the invention

[0004] The purpose of the present invention is to provide an aircraft measurability modeling method, computer equipment, computer-readable storage medium and computer program product based on MBSE to address the problem of lack of measurability in the existing aircraft design process based on MBSE, which can improve the overall measurability of the aircraft, realize the traceability of the aircraft throughout its life cycle, and reduce the cost of aircraft development and subsequent maintenance.

[0005] In order to achieve the above object, one aspect of the present invention provides an aircraft metrology modeling method based on MBSE, comprising the following steps: Constructing a metrology metamodel, using a testing device or a calibration device of the object to be measured as a minimum element to construct the metrology metamodel, wherein the metrology metamodel is divided into a testing device metamodel and a calibration device metamodel according to a traceability path of the object to be measured; Construct a metrological demand model, divide the aircraft into several submodules, and conduct demand analysis on the metrological objects corresponding to each submodule based on the needs of stakeholders in each submodule to form a metrological demand model; Construct a metrological design model, take the output of the metrological demand model as input, obtain the functional architecture of the metrological system through demand analysis, build the logical architecture of the system based on the functional architecture of the system, conduct metrological indicator analysis, form a metrological design model, and obtain a recommended list of testing equipment or calibration equipment; Construct a metrological indicator trade-off analysis model, take the output of the metrological design model as input, determine the trade-off strategy according to the metrological object, determine the selection scheme of the testing equipment or calibration equipment from the recommended list according to the trade-off strategy, and output the summary table of aircraft traceability requirements.

[0006] Preferably, the steps of constructing a quantitative demand model include: Divide the aircraft into several submodules, obtain the requirements of various stakeholders in each submodule, and summarize the requirements of various stakeholders to form a system requirements table; Functionally group submodules into functional blocks, identify the control flow between functional blocks, clarify the interaction between functional blocks, and complete functional behavior analysis; Allocate the overall indicators of aircraft design to the functional blocks of each submodule, determine the relationship between the overall indicators and each sub-indicator, and complete the indicator analysis; From the perspective of measurability, the measurable requirements are obtained by analyzing the functions and indicators of the measurement object. Among them, the functional requirements are obtained by analyzing the functions of the measurement object, and the non-functional requirements are obtained by analyzing the indicators of the measurement object. Establish the traceability relationship of measurement demand and obtain the measurement demand model.

[0007] Preferably, the entire aircraft is divided into several sub-modules according to aircraft systems, usage scenarios, users or aircraft structures.

[0008] Preferably, the step of constructing a quantitative design model includes: System requirements analysis, including functional requirements analysis and non-functional requirements analysis. The functional architecture of the measurement system is obtained through functional requirements analysis, and the selection of testing equipment or calibration equipment is obtained through non-functional requirements analysis; System architecture analysis: building the system's logical architecture based on the system's functional architecture to obtain the system composition of the detection or calibration solution; System behavior analysis: detailed analysis of system functions, describing the logical relationship and data interaction of system functions; System indicator analysis, decomposition of system indicators, and clear performance of the measurement object to the outside world; Testing or calibration analysis, based on the results of system indicator analysis, obtain a recommended list of testing equipment or calibration equipment that meets the requirements.

[0009] Preferably, functional requirements analysis is performed through use case capture, and quantitative activities are obtained by describing quantitative requirements; non-functional requirements analysis is performed through indicator analysis, and quantitative indicators are obtained through simulation in the form of parameters and instances.

[0010] Preferably, the logical architecture of the system includes a logical component definition, a logical component structure tree definition, a logical component interaction relationship diagram, a logical port definition, and a definition of data, material, and energy interactions between logical ports.

[0011] Preferably, the inspection time, inspection distance, and in-situ or off-situ measurement of the measurement object are used as a trade-off strategy.

[0012] Another aspect of the present invention provides a computer device, including a memory, a processor, and a computer program stored in the memory, wherein the processor executes the computer program to implement the steps of the above method.

[0013] Another aspect of the present invention provides a computer-readable storage medium having a computer program stored thereon, which implements the steps of the above method when executed by a processor.

[0014] Another aspect of the present invention provides a computer program product, comprising a computer program, which implements the steps of the above method when executed by a processor.

[0015] According to the MBSE-based aircraft measurability modeling method, computer device, computer-readable storage medium and computer program product of the above aspects of the present invention, by introducing the concept of measurability into MBSE-based aircraft design, it is possible to improve the overall measurability of the aircraft, achieve traceability throughout the aircraft life cycle, and reduce the cost of aircraft development and subsequent maintenance. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] In order to more clearly illustrate the technical solution of the present invention, the following briefly introduces the drawings used in the description of the embodiments of the present invention. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative work: Figure 1 is a flow chart of an aircraft metrology modeling method based on MBSE according to an embodiment of the present invention; Figure 2 is a schematic diagram of use case capture of an embodiment of the present invention; Figure 3 is a schematic diagram of an activity diagram of an embodiment of the present invention; Figure 4 It is a structural diagram of a computer device according to an embodiment of the present invention. DETAILED DESCRIPTION

[0017] In order to make the purpose, technical solution and advantages of the present invention clearer, the technical solution of the present invention will be clearly and completely described below in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0018] An embodiment of the present invention provides an aircraft metrology modeling method based on MBSE. Figure 1 FIG. 1 is a flow chart of an aircraft metrology modeling method based on MBSE according to an embodiment of the present invention. Figure 1 As shown, the MBSE-based aircraft metrology modeling method of the embodiment of the present invention includes step 1: constructing a metrology meta-model, step 2: constructing a metrology requirement model, step 3: constructing a metrology design model, and step 4: constructing a metrology indicator trade-off analysis model. Each step is described in detail below.

[0019] Step 1: Construct a metrological metamodel. Based on the characteristics of the traditional aircraft system field and metrological analysis methods, define the detection equipment and calibration equipment of the measured object as minimized elements, and simplify the relationship between subsequent elements. The metamodel is defined as follows: Definition 1: Like the common settings, the metamodel is expressed in SysML language, which mainly includes metaclasses, stereotypes and customizations.

[0020] Metaclass is the key element in building a measurement metamodel. It is the most basic model predefined using the SysML language, the parent class of all custom metamodels, and all metamodel elements are generalized to the metaclass.

[0021] The stereotype is an important element in building a quantitative metamodel. Users model specific objects and can quickly build custom stereotypes by dragging and dropping to customize specific quantitative modeling objects.

[0022] Customization is an auxiliary element for building a measurement metamodel, which is used to assist in building a stereotype element model. Customization can customize the usage scenarios of the constructed stereotype elements. The customized content includes but is not limited to the target, owner, etc.

[0023] Metamodels are usually represented by internal module diagrams, and metamodels can interact and connect with each other. However, metamodels do not define the main usage scenarios, which is different from ordinary metamodel definitions.

[0024] Definition 2: The metrology metamodel takes the test equipment and calibration equipment of the measured object as the minimum elements. When defining the metrology metamodel, the use location, usage scenario and association relationship of the measured object are not considered. The metrology metamodel can be divided into the test equipment metamodel and the calibration equipment metamodel according to the traceability path of the measured object.

[0025] Example: Take the measurability design of the communication system of an aircraft's onboard system as an example. The aircraft's communication system is used for communication between the aircraft and the ground or other aircraft, and the transmission and reception of its communication signals are both achieved through antennas. Therefore, the antenna is an important device for the measurability design of the communication system. Taking the antenna as the object to be measured, the device completes the traceability through detection according to the traceability path of the antenna, and the corresponding metamodel is the detection device metamodel. The antennas of an aircraft are generally distributed in the fuselage, wings, tail, top and other parts. Due to the different types and functions of the antennas, their technical indicators are also different. By defining the metaclass of the antenna detection device metamodel, the structural type is customized according to different antenna types or the needs of different stakeholders, and then customized according to different application scenarios in different locations. Different targets or owners.

[0026] Step 2: Construct a measurable demand model. Take the requirements of stakeholders in aircraft design as input, use measurability as a perspective, describe the demand scenario, capture the requirements, build a model framework, perform behavioral analysis and indicator analysis on the model, and finally define the demand model. Use SysML language to express the measurable demand model and build the relationship between aircraft design and measurability.

[0027] The logic of step 2 is: divide the aircraft as a whole into several sub-modules, and form a measurable demand model based on the needs of the stakeholders of each sub-module from the perspective of measurability. The whole process includes conducting demand analysis for the metering objects corresponding to the sub-modules, and then completing the capture action through demand capture, use case capture, and use case analysis of the metering objects. Based on the demand capture function, a complete expression of the metering object input requirements is carried out, and based on the use case capture function, a complete coverage of the functional requirements or metering object application scenarios in the metering requirements is carried out, and based on the use case analysis function, the participants in the use case scenario and the functions that the participants should have to complete the use case scenario are displayed. Among them, demand capture is divided into functional requirements and non-functional requirements.

[0028] The specific steps are as follows: Step 2.1: Divide the aircraft as a whole into n sub-modules according to the aircraft system, usage scenario, user, aircraft structure, etc.

[0029] Example: Aircraft systems can be classified into external fuselage and wing structure systems, hydraulic systems, flight control systems, landing gear systems, cabin environment control systems, fuel systems, fire protection systems, etc.

[0030] According to the classification of aircraft usage scenarios, it can be divided into stationary phase, taxiing phase, take-off phase, climbing phase, cruising phase, descent phase, landing phase, taxi-in phase, maintenance phase, and repair phase, etc.

[0031] Based on the classification of aircraft users, they can be divided into pilots, flight attendants, cargo hold loading team, ground tower team, aircraft support team, aircraft maintenance team, aircraft development team, etc.

[0032] Based on the aircraft structure, it can be classified into main structure, power system, landing gear, onboard system, interior and protective structure.

[0033] Step 2.2: The aircraft is divided into n submodules, each of which corresponds to a corresponding requirement. The stakeholders of each requirement can come from users, relevant standards or policies, technical specifications, etc. The stakeholder requirements must include the overall technical indicator requirements for aircraft development.

[0034] Example: Taking the GPS antenna of an aircraft as an example, in the communication system, the stakeholders of the antenna can be the design department S1, the development department S2, the user department S3, the measurement department S4 and the maintenance and support department S5, where S1 to S5 are the corresponding department codes, which are convenient for subsequent design calls or references. The design department S1 proposed the requirements for antenna weight control, the user department S3 proposed the requirements for gain, standing wave ratio, and frequency band, and the measurement department S4 proposed the requirements for measurement traceability rate, measurement equipment universality rate, and important level classification of detection equipment. The details are shown in Table 1.

[0035]

[0036] Step 2.3: Requirements analysis First, we need to identify the stakeholders of the submodules, and then analyze the requirements proposed by the stakeholders to form a system requirements table, as shown in Table 1. The input of the stakeholder requirements table can come from the modeling tool input that comes with MBSE, or it can be imported from the ReqIF file exported by the IBM Rational DOORS requirements management tool or an Excel table. The language used is SysML, which can be a diagram, computer language, etc.

[0037] Step 2.4: Architecture analysis, first of all, group functions into functional blocks and define logical components. Then design the logical architecture and carry out interface feature design. Finally, through continuous iteration, a highly secure system logic architecture solution is formed.

[0038] Example: GPS antenna consists of three functional blocks: passive antenna, low noise amplifier module, and connector.

[0039] Step 2.5: Functional behavior analysis, first establish a behavior analysis activity diagram, identify the control flow between functional blocks, sort them according to the sub-function coupling relationship, and identify and analyze other possible functional paths. Then clarify the interface interaction relationship between functional blocks and form a functional interface block diagram. Finally, based on the functional control flow in the functional flow diagram, clarify the interaction content between functional blocks, form a functional interface block diagram and functional interface file, and complete the functional behavior analysis.

[0040] Example: After the use case capture of the GPS antenna, a series of behavior use cases will be captured, the most important of which is to achieve the transmission or reception of communication signals. Taking the realization of communication signal reception as an example, the main components closely related to this process are passive antennas, low noise amplifier modules, and connectors. Figure 2 shown.

[0041] After capturing the use case, the activities associated with it should be expressed in the form of an activity diagram, such as Figure 3 As shown, the entire activity process is: the executor turns on the power, the passive antenna receives the RF signal in the space, the RF signal is amplified and filtered by the low-noise amplifier module to obtain a resolvable RF signal, and the RF signal is transmitted to the corresponding analysis equipment through the connector.

[0042] Step 2.6: Index analysis First, the overall indicators of aircraft design are inherited, decomposed, and allocated to the functional blocks (equipment or subsystems) of each submodule, and the relationship between the overall indicators and each sub-indicator is described by value attribute and parameter diagram. By creating a new module instance, the system indicators are simulated and analyzed to obtain the parameters and indicators decomposed and allocated to the equipment or subsystem.

[0043] Example: GPS antenna is divided into passive antenna, low noise amplifier module, and connector, where the value attributes of GPS antenna are weight, gain, standing wave ratio, and frequency band. The value attributes of GPS antenna will be decomposed or allocated to passive antenna, low noise amplifier module, and connector. The value attributes of passive antenna are weight, the value attributes of low noise amplifier module are weight, gain, standing wave ratio, and frequency band, and the value attributes of connector are weight and frequency band.

[0044] Step 2.7: Requirements capture is mainly obtained through the analysis of the functions and indicators of the measurement object. Requirements capture is divided into functional requirements and non-functional requirements, that is, stakeholder requirements are divided into functional and non-functional, and requirements are defined from the perspective of measurability. Functional requirements are captured through use case analysis for behavioral use cases, and non-functional requirements are analyzed using indicators.

[0045] Example: Taking the GPS antenna as an example, after completing the architecture, behavior and indicator analysis, the quantitative requirements are captured. The weight requirements of the GPS antenna are distributed to the passive antenna, low-noise amplifier module, and connector, and the weights of the three parts are mutually constrained. The gain requirements and standing wave ratio requirements of the GPS antenna are decomposed into the low-noise amplifier module, which is constrained by the components of the module. The frequency band requirements of the GPS antenna are decomposed into the low-noise amplifier module and the connector. The components and connectors that make up the module all constrain the bandwidth limit of the RF signal transmission. Therefore, the quantitative requirements of the GPS antenna are decomposed into Table 2.

[0046]

[0047] Step 2.8: Requirements capture is done through modeling tools, using system context to capture requirements and establish traceability relationships including the analysis source of requirements and the impact of requirement changes.

[0048] Example: Because the weight of the GPS antenna is composed of the weight of the passive antenna, the low-noise amplifier module, and the connector, if the weight of the passive antenna increases, the weight of the low-noise amplifier module and the connector will decrease. After establishing a traceability relationship, the impact of the weight adjustment can be more intuitively seen.

[0049] Step 3: Construct a metrological design model, using the output of the aircraft metrological requirement model as input, obtain a metrological architecture design through requirement analysis, analyze the system logical architecture, and carry out functional performance indicator decomposition, perform simulation verification on key metrological indicators, and form a metrological design model.

[0050] Metrological design can be divided into two parts: detection scheme design and calibration scheme design. The process is: system requirements analysis, system architecture analysis, system behavior analysis, system indicator analysis, detection or calibration analysis. The specific steps are as follows: Step 3.1: System requirements analysis includes functional requirements analysis and non-functional requirements analysis. Functional requirements analysis is conducted using the use case capture method during the modeling process. The analysis process is mainly based on behaviors and activities, and quantitative activities are obtained by describing quantitative requirements. Non-functional requirements analysis is conducted through indicator analysis during the modeling process. The analysis process is mainly in the form of parameters and instances, and quantitative indicators are obtained through simulation. The requirements analysis of the quantitative design model comes from the quantitative requirements model.

[0051] Among them, the structural composition of the measurement system is obtained through functional requirements analysis, and the selection of testing equipment or calibration equipment is obtained through non-functional analysis.

[0052] Example: Taking GPS antenna as an example, Table 2 above is the quantitative demand output of GPS antenna, and is also the demand analysis input of quantitative design of GPS antenna.

[0053] Step 3.2: System architecture analysis is based on the functional architecture, clearly defines the technical solution or traceability path to be adopted, and forms a logical solution for the system, including the definition of logical components, the definition of the logical component structure tree, the block diagram of the logical component interaction relationship, the definition of logical ports, and the definition of data, material, and energy interaction between logical ports. By building a logical architecture, the composition of the detection or calibration solution system is sorted out, and the required detection or calibration equipment is determined based on its functional and non-functional requirements.

[0054] Example: It is known that the GPS antenna is composed of a passive antenna, a low-noise amplifier module, and a connector. Its traceability path is to trace it back to the national standard parameters through detection. Therefore, the system architecture of the GPS antenna detection metrology design model is a passive antenna, a low-noise amplifier module, and a connector.

[0055] Step 3.3: System behavior analysis is to conduct detailed analysis of functions based on the system functions obtained from the requirements analysis. The behavior analysis process is a more detailed analysis process for system functions with a smaller granularity, mainly describing the logical relationship and data interaction to complete the current system functions.

[0056] Example: It is known that the main function of a GPS antenna is to receive radio frequency signals. Further analysis shows that whether the antenna can receive radio frequency signals is a key function, and the quality of the radio frequency signals received by the antenna is another key function.

[0057] Step 3.4: System indicator analysis is to describe the degree of capability displayed by the measurement object. Its performance can be presented to the outside world through a black box, or analyzed and judged through a white box (known algorithms or correlations).

[0058] Example: The main functions of the GPS antenna can be to measure whether the gain of the RF signal output by the low noise amplifier module reaches 4.5dBiC, whether the standing wave ratio measurement value is less than 1.5, and whether the bandwidth measurement value meets the requirements of 20MHz to 600MHz.

[0059] Step 3.5: Testing or calibration analysis: Based on the results of the system indicator analysis, a recommended list of testing equipment or calibration equipment that meets the requirements is obtained, and the selection is made based on the recommended list.

[0060] Example: The gain of the RF signal must meet 4.5dBiC, the VSWR measurement value must be less than 1.5, and the bandwidth measurement value range must meet 20MHz to 600MHz. List the gain, VSWR, and bandwidth devices that can be measured. Select the matching device based on the listed device list.

[0061] Step 4: Through quantitative index analysis and multi-solution trade-off analysis, a complete summary table of aircraft traceability requirements is finally output. The specific steps are as follows: Step 4.1: Quantitative indicator trade-off analysis, by defining multiple alternatives for the system components obtained from the quantitative design analysis, to form different trade-off solutions.

[0062] Example: Use the inspection time, inspection distance, and on-site or off-site measurement of the aircraft measurement object as the basis for the trade-off strategy. Set the following rules: The inspection time is divided into three levels according to completion within 5 days, within 5-10 days, and more than 10 days, and are assigned values ​​of 10, 5, and 1 respectively; the inspection distance is divided into three levels according to round trip within 2 days, round trip within 2-5 days, and more than 5 days, and are assigned values ​​of 10, 5, and 1 respectively; the on-site measurement is assigned a value of 8, and the off-site measurement is assigned a value of 0.

[0063] The solution scores of the measurement object are calculated according to the above algorithm, and the solution with the highest score is selected.

[0064] Step 4.2: Perform trade-off analysis through simulation according to the trade-off solution definition. The analysis results can also be reconfirmed through on-site expert review. Based on the simulation analysis results or review demonstration, the appropriate selection solution is obtained.

[0065] Example: According to the algorithm in step 4.1, obtain the total score of each scheme of the measurement object through simulation, and select the scheme with the highest score.

[0066] Alternatively, according to the algorithm in step 4.1, the total score of each scheme of the measurement object can be obtained through simulation, and the schemes with the highest scores can be reviewed and verified to select the most suitable scheme.

[0067] Step 4.3: Finally, selectively add selection constraints to the trade-off solution definition, and obtain the selection results intuitively through simulation. The results can also be reviewed and verified.

[0068] Finally, a summary table of aircraft traceability requirements is obtained.

[0069] In summary, the MBSE-based aircraft metrology modeling method of the embodiment of the present invention forms a metrology modeling process standard by constructing a metrology metamodel, a metrology requirement model, a metrology design model, a metrology indicator analysis and a multi-scheme trade-off analysis, and finally outputs a complete aircraft traceability requirement summary table, thereby improving the overall measurability of the aircraft, making it easy to measure the aircraft from research and development, manufacturing to subsequent use and maintenance, and ensuring the accuracy of the overall measurement value of the aircraft.

[0070] The MBSE-based aircraft measurability modeling method of the embodiment of the present invention introduces the concept of measurability into MBSE-based aircraft design and integrates the measurability requirement model into the MBSE application, thereby facilitating the traceability of the entire life cycle of the aircraft, reducing the cost of aircraft development and subsequent maintenance, filling the gap in this field, and will have a beneficial impact on the research and development, manufacturing, use and subsequent maintenance of aircraft equipment.

[0071] An embodiment of the present invention further provides a computer device, which may be a server, and its internal structure diagram may be as shown in FIG. Figure 4 As shown. The computer device includes a processor, a memory and a network interface connected through a system bus. Among them, the processor of the computer device is used to provide computing and control capabilities. The memory of the computer device includes a non-volatile storage medium and an internal memory. The non-volatile storage medium stores an operating system, a computer program and a database. The internal memory provides an environment for the operation of the operating system and the computer program in the non-volatile storage medium. The database of the computer device is used to store operating parameter data of each framework. The network interface of the computer device is used to communicate with an external terminal through a network connection. When the computer program is executed by the processor, the steps of the method of the embodiment of the present invention are implemented.

[0072] Those skilled in the art will understand that Figure 4 The structure shown in the figure is only a block diagram of a part of the structure related to the solution of the present application, and does not constitute a limitation on the computer device to which the solution of the present application is applied. The specific computer device may include more or fewer components than those shown in the figure, or combine certain components, or have a different arrangement of components.

[0073] An embodiment of the present invention further provides a computer-readable storage medium having a computer program stored thereon, and when the computer program is executed by a processor, the steps of the method of the embodiment of the present invention are implemented.

[0074] An embodiment of the present invention further provides a computer program product, including a computer program, which implements the steps of the method of the embodiment of the present invention when executed by a processor.

[0075] The above description is only by way of illustration of certain exemplary embodiments of the present invention. It is undoubted that those skilled in the art can modify the described embodiments in various ways without departing from the spirit and scope of the present invention. Therefore, the above drawings and descriptions are illustrative in nature and should not be construed as limiting the scope of protection of the claims of the present invention.

Claims

1. An aircraft quantitative modeling method based on MBSE, characterized in that: The following steps are involved: Constructing a metrology metamodel, using a testing device or a calibration device of the object to be measured as a minimum element to construct the metrology metamodel, wherein the metrology metamodel is divided into a testing device metamodel and a calibration device metamodel according to a traceability path of the object to be measured; Construct a metrological demand model, divide the aircraft into several submodules, and conduct demand analysis on the metrological objects corresponding to each submodule based on the needs of stakeholders in each submodule to form a metrological demand model; Construct a metrological design model, take the output of the metrological demand model as input, obtain the functional architecture of the metrological system through demand analysis, build the logical architecture of the system based on the functional architecture of the system, conduct metrological indicator analysis, form a metrological design model, and obtain a recommended list of testing equipment or calibration equipment; Construct a metrological indicator trade-off analysis model, take the output of the metrological design model as input, determine the trade-off strategy according to the metrological object, determine the selection scheme of the testing equipment or calibration equipment from the recommended list according to the trade-off strategy, and output the summary table of aircraft traceability requirements.

2. The method according to claim 1, characterized in that The steps to construct a quantitative demand model include: Divide the aircraft into several submodules, obtain the requirements of various stakeholders in each submodule, and summarize the requirements of various stakeholders to form a system requirements table; Functionally group submodules into functional blocks, identify the control flow between functional blocks, clarify the interaction between functional blocks, and complete functional behavior analysis; Allocate the overall indicators of aircraft design to the functional blocks of each submodule, determine the relationship between the overall indicators and each sub-indicator, and complete the indicator analysis; From the perspective of measurability, the measurable requirements are obtained by analyzing the functions and indicators of the measurement object. Among them, the functional requirements are obtained by analyzing the functions of the measurement object, and the non-functional requirements are obtained by analyzing the indicators of the measurement object. Establish the traceability relationship of measurement demand and obtain the measurement demand model.

3. The method according to claim 2, characterized in that The aircraft as a whole is divided into several sub-modules according to the aircraft system, usage scenario, user or aircraft structure.

4. The method according to any one of claims 1 to 3, characterized in that The steps to construct a quantitative design model include: System requirements analysis, including functional requirements analysis and non-functional requirements analysis. The functional architecture of the measurement system is obtained through functional requirements analysis, and the selection of testing equipment or calibration equipment is obtained through non-functional requirements analysis; System architecture analysis: building the system's logical architecture based on the system's functional architecture to obtain the system composition of the detection or calibration solution; System behavior analysis: detailed analysis of system functions, describing the logical relationship and data interaction of system functions; System indicator analysis, decomposition of system indicators, and clear performance of the measurement object to the outside world; Testing or calibration analysis, based on the results of system indicator analysis, obtain a recommended list of testing equipment or calibration equipment that meets the requirements.

5. The method according to claim 4, characterized in that Functional requirement analysis is carried out through use case capture, and quantitative activities are obtained by describing quantitative requirements; non-functional requirement analysis is carried out through indicator analysis, and quantitative indicators are obtained through simulation in the form of parameters and instances.

6. The method according to claim 5, characterized in that The logical architecture of the system includes the definition of logical components, the definition of the logical component structure tree, the block diagram of the interaction relationship between logical components, the definition of logical ports, and the definition of data, material, and energy interactions between logical ports.

7. The method according to any one of claims 1 to 3, characterized in that The trade-off strategy is based on the inspection time, inspection distance, and on-site or off-site measurement of the measured object.

8. A computer device comprising a memory, a processor and a computer program stored in the memory, characterized in that: The processor executes the computer program to implement the steps of the method according to any one of claims 1 to 7.

9. A computer-readable storage medium having a computer program stored thereon, characterized in that: When the computer program is executed by a processor, the steps of the method according to any one of claims 1 to 7 are implemented.

10. A computer program product, comprising a computer program, characterized in that When the computer program is executed by a processor, the steps of the method according to any one of claims 1 to 7 are implemented.

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