Aircraft support system optimization method based on model publication and aircraft support system

Abstract

The invention relates to the technical field of aircraft support, in particular to an aircraft support system optimization method based on model publication and an aircraft support system.The aircraft support system optimization method comprises the steps that S1, aircraft support system model elements needed by a model publication method are determined according to the characteristics of the aircraft support system; s2, analyzing aircraft support system requirements and aircraft support system functions based on model publication, and constructing a white box model of the aircraft support system by using a system modeling language SysML to obtain the aircraft support system of the model publication; s3, performing rationality verification on the primary model of the aircraft support system by using a protocol algorithm and an independent axiom; and S4, completing the optimization design of the aircraft support system by using the aircraft support system design structure matrix. The aircraft support system optimization method provided by the invention can support the aircraft support system to carry out forward development work, and can solve the problems of unreasonable resource function planning and large support scale of the aircraft support system compared with an experience-based design and development mode.

Description

Technical Field

[0001] The invention belongs to the technical field of aircraft support, and in particular relates to an aircraft support system optimization method based on model axiomatization and an aircraft support system. Background Art

[0002] Model-based system design (MBSD) belongs to the technical field of model-based system engineering (MBSE), which mainly includes requirements analysis, functional analysis, design synthesis, etc. In MBSE, "model-based" can be seen as the transformation process of system engineering from the original expression method centered on documents and natural language to the expression method centered on models.

[0003] Functional analysis is a system-oriented functional design. It is based on the top-level system requirements determined by the requirements analysis to further complete the definition of system functional requirements. It is usually carried out using methods such as system use case diagrams, black box activity diagrams, sequence diagrams, and state machine construction.

[0004] Design synthesis is a system-oriented architecture analysis and architecture design. For different product levels of the system, the functional architecture, logical architecture, physical architecture and scheme of the system are determined through this design. Design synthesis is usually carried out using methods such as white box activity diagrams, sequence diagrams, and state machine construction.

[0005] Axiomatic Design (AD) is a systematic design decision theory. Since it was proposed in 1990, it has gradually become a design criterion in the industrial field, especially in innovative design or design improvement. This theory provides three concepts: design domain, hierarchy and zigzag mapping, as well as two design axioms. Domain is a collection of corresponding design elements in different design stages, and is the boundary that distinguishes different design activities. The entire design process is composed of four main domains in series, including: customer domain, functional domain, physical domain and process domain. The contents of the four domains include: customer needs, functional requirements, design parameters and process variables.

[0006] The axiomatic design process is driven by customer needs. According to the hierarchical structure of axiomatic design, the design scheme consisting of functional requirements, design characteristics and process parameters at different levels is obtained in the process of iterative mapping in four domains from front to back, and then the scheme is optimized through the independence axiom and information axiom. Among them: the independence axiom refers to keeping the functional requirements relatively independent, which is used for functional design; the information axiom refers to selecting a design with less information content in the design, which is used to select the optimal design scheme when there are multiple optional design parameters that can achieve the same functional requirement.

[0007] The present invention mainly considers the design of the aircraft support system, and the division of support resource types based on the functional requirements of support resources has a very important impact on the type of support resources and the scale of support that are finally determined. For example, the functional requirements for support equipment can be determined through support activity diagram analysis, but how many types of support equipment are ultimately used to achieve these functions and how to divide the above functional requirements is a very important issue. For support equipment, there are usually dozens or hundreds of types. If the division is not scientific, it will often cause a substantial increase in the scale of support, thereby affecting the support efficiency of the equipment. Therefore, it is very urgent and necessary to adopt a scientific and reasonable design method to carry out the forward design of the aircraft support system. Summary of the invention

[0008] In view of the deficiencies in the prior art, the present invention provides an aircraft support system optimization method and an aircraft support system based on model axiomatization, which integrates axiomatic design and model-based system design theory, changes the previous experience-based design and development method, and obtains more objective and accurate results, providing a basis for the forward design of the aircraft support system; the present invention solves many problems of the previous experience-based development method, and solves the problems of unreasonable aircraft support resource function planning and large support scale through reduction algorithms and coupling judgments.

[0009] To achieve the above object, the present invention discloses the following technical solution:

[0010] An aircraft support system optimization method based on model axiomatization includes:

[0011] S1: According to the characteristics of the aircraft support system, determine the aircraft support system model elements required by the model axiomatic method;

[0012] The system modeling language SysML is used to construct the relationship between the aircraft support system requirement sub-model, aircraft support system function sub-model, and aircraft support system structure sub-model in the aircraft support system model based on model axiomatization; in the j-th design level of the aircraft support system, there are k functional requirement parameters FR and structural design parameters DP, and there are m association relationships Map between these parameters; the aircraft support system model parameter composition set M based on the model axiomatization method A-M for:

[0013]

[0014] Among them, M A-M It is a set of aircraft support system parameters; CR i is the i-th design requirement parameter of the aircraft support system; FR k is the kth functional requirement parameter of the aircraft support system; DP k is the kth structural design parameter of the aircraft support system; Map m is the mth association relationship; K is the design level of the aircraft support system; n is the number of aircraft support system user requirements CR; i is the aircraft support system design requirement number; j is the aircraft support system design iteration number; m is the total number of aircraft support system design iterations; k is the number of functional requirements and design parameters; L is the number of layers of the aircraft support system; ∪ is the union operator symbol;

[0015] S2: Analyze the requirements and functions of the aircraft support system based on model axiomatization, use the system modeling language SysML to build a white box model of the aircraft support system, and obtain the aircraft support system with model axiomatization;

[0016] Based on the data model of the existing aircraft support system, the design parameters are generated from the functional requirements to complete the first-level model of the aircraft support system; the demand function structure mapping process is determined according to the aircraft support system model parameter composition set in step S1, and the aircraft support system design equation is constructed as follows:

[0017] {FR}=[A]{DP};

[0018]

[0019] Among them, FR is the functional requirement vector of the aircraft support system; FR k is its kth element; A is the aircraft support system design structure matrix; A jk is the design element of its jth row and kth column; DP is the design parameter vector of the aircraft support system; DP k is its kth element;

[0020] S3: Use the reduction algorithm and the independence axiom to perform a rationality check on the first-level model of the aircraft support system in step S2;

[0021] S31: Use the reduction algorithm of the aircraft support system design structure matrix to exclude the independent functions of the aircraft support system and simplify the aircraft support system design structure matrix A;

[0022] S32: using the independence axiom to judge the coupling of the aircraft support system design, judging whether the current aircraft support system design structure matrix A satisfies the independence axiom according to the aircraft support system design structure matrix A obtained in step S2, thereby realizing the coupling judgment of the aircraft support system design;

[0023] S4: Use the aircraft support system design structure matrix to complete the aircraft support system optimization design;

[0024] Through the analysis of step S32 above, the functional requirements FR of the aircraft support system that cause functional coupling are determined. k and the design parameters DP of the aircraft support system k , by redesigning the design parameters DP of the aircraft support system k , complete the resource optimization design of the aircraft support system and obtain the secondary model of the aircraft support system.

[0025] Preferably, the model axiomatic method in step S1 is a top-down model design iterative process for the aircraft support system, and each iteration includes three stages: requirement analysis, functional analysis and system design of the aircraft support system, and each stage corresponds to the user domain, functional domain and structural domain in the axiomatic design theory.

[0026] Preferably, the analysis in step S2 is based on the model axiomatized aircraft support system requirements and aircraft support system functions, specifically:

[0027] S21: Analyze aircraft support system requirements:

[0028] S211: Analyze flight mission requirements, analyze and decompose specific flight missions to be undertaken by the aircraft according to its mission and positioning, and obtain a flight mission set;

[0029] S212: analyzing the aircraft support mission requirements, based on the aircraft flight mission set analyzed and determined in step S211, analyzing and decomposing the support missions to be undertaken in the entire life cycle stage, and determining the aircraft support mission set, including: operation support missions and maintenance support missions;

[0030] S213: Analyze aircraft support requirements, build support scenarios for each support task, and decompose the support activities and support nodes it contains;

[0031] S214: Analyze the aircraft support capability requirements. Capability requirement analysis refers to analyzing the support capabilities that the aircraft support system needs to have for each support activity and support node in order to complete the support mission, and obtaining itemized user requirements;

[0032] S22: Analyze the functions of aircraft support systems;

[0033] S221: Based on the aircraft support system capability requirements determined by the requirements analysis, the system modeling language SysML is used to construct the support system black box model, i.e., the aircraft support system functional sub-model, including use case diagrams, black box activity diagrams, and black box sequence diagrams;

[0034] S222: Based on the constructed black box model, analyze the main activities that the security system needs to perform and the functions required to perform these activities, and sort out the itemized functional requirements.

[0035] Preferably, the white box model of the aircraft support system in step S2 is specifically: an aircraft support system structural sub-model, including a white box activity diagram and a white box sequence diagram; the white box model divides each activity into different lanes based on the black box model, one lane is a design parameter, and different functional requirements are undertaken by different design parameters.

[0036] Preferably, the functional requirement vector FR of the aircraft support system and the design parameter vector DP of the aircraft support system in step S2 need to be associated and represented by the aircraft support system design structure matrix A of the function-to-physical process; the design element A in the design structure matrix jk The meaning of is constructed by the first auxiliary design element a1 and the second auxiliary design element a2; the first auxiliary design element a1 indicates that there is an association relationship between the corresponding row and column elements; the second auxiliary design element a2 indicates that there is no association relationship.

[0037] Preferably, in step S31, a reduction algorithm of the aircraft support system design structure matrix is ​​used to exclude the independent functions of the aircraft support system and simplify the aircraft support system design structure matrix A, specifically:

[0038] S311: Find the functional requirements FR of the aircraft support system in which all rows except the diagonal elements in the aircraft support system design structure matrix are the second auxiliary design elements a2 k And the design parameters DP of the aircraft support system whose columns are all the second auxiliary design elements a2 k , transform the row and column elements of the design structure matrix, and transform the functional requirements FR of these aircraft support systems k Placed in the upper left corner of the design structure matrix, the design parameter DP of the aircraft support system k Place it in the lower right corner of the design structure matrix;

[0039] S312: The functional requirements FR of the aircraft support system whose rows except the diagonal elements are all the second auxiliary design elements a2 k And the design parameters DP of the aircraft support system whose columns are all the second auxiliary design elements a2 k , that is, factors that will not lead to any functional coupling are eliminated, and a streamlined design structure matrix is ​​obtained; the functional requirements FR of these eliminated aircraft support systems k and the design parameters DP of the aircraft support system k It has relative independence, guides the design of the security system, and enters the next design iteration;

[0040] S313: The simplified aircraft support system design structure matrix is ​​analyzed again using steps S311 and S312 until no more elements can be eliminated.

[0041] Preferably, in step S32, it is determined whether the current aircraft support system design structure matrix A satisfies the independence axiom, and three cases are specifically processed;

[0042] The first case: When the aircraft support system design structure matrix A is a diagonal matrix, that is, except for the diagonal elements, the remaining elements are the second auxiliary design elements a2, specifically:

[0043]

[0044] It is recorded as A=d iag(a1, a1, ..., a1), which means that the physical composition design of different security resources built according to the functional requirements is a non-coupling design, and the next design iteration is carried out directly according to the corresponding relationship between the functional requirements and the design parameters;

[0045] The second case: When the aircraft support system design structure matrix A is a triangular matrix, that is, all elements below or above the main diagonal are the second auxiliary design elements a2, specifically:

[0046] or

[0047] This indicates that the design is a quasi-coupled design / decoupled design, which needs to be converted into a triangular matrix through matrix transformation to make the functional requirements relatively independent;

[0048] The third case: When the aircraft support system design structure matrix A is a full matrix, the functional requirements do not satisfy the independence axiom, and there is coupling between them. It is necessary to reselect the design parameters, that is, the specific physical product design plan of the support resources, change the influence of the design parameters on the functional requirements, and once again judge whether the independence axiom is satisfied, so that the aircraft support system design structure matrix A is converted into a diagonal matrix in the first case or a triangular matrix in the second case.

[0049] Preferably, the functional coupling in step S4 is a key factor affecting the design efficiency of support resources in the aircraft support system, and using the independence axiom of axiomatic design theory as a criterion for judging whether the system design is coupled can effectively make design decision-making.

[0050] The second aspect of the present invention proposes an aircraft support system obtained by an aircraft support system optimization method based on model axiomatization, which includes: a support system model element construction module, a user demand analysis module, a function analysis module, a structural system design module, a support system rationality verification module and a support system optimization design module;

[0051] The support system model element building module adopts a combination of model-based system design and axiomatic design theory;

[0052] The user demand analysis module captures user demands and obtains itemized user demands;

[0053] The functional analysis module constructs a black box model to obtain itemized functional requirements;

[0054] The structural system design module constructs a white box model to complete the preliminary design of the guarantee system; completes the preliminary generation of design parameters based on functional requirements, and obtains the preliminary design parameters of the guarantee system through analysis; constructs a design structure matrix to establish a mapping relationship between functional requirements and design parameters;

[0055] The rationality check module of the security system can use the reduction algorithm to simplify the design structure matrix to facilitate the next step of coupling judgment; the rationality check module of the security system can use the independence axiom to judge whether there is coupling between functional requirements and design parameters;

[0056] The support system optimization design module is used to redesign the design parameters that do not meet the independence axiom to complete the optimization of the aircraft support system.

[0057] Compared with the prior art, the present invention has the following beneficial effects:

[0058] (1) The aircraft support system optimization method based on model axiomatization designed by the present invention integrates axiomatic design and model-based system design theory, changes the previous experience-based design and development method, and obtains more objective and accurate results, providing a basis for the forward design of the aircraft support system.

[0059] (2) The aircraft support system optimization method based on model axiomatization designed by the present invention is driven by user needs, establishes a mapping relationship between the functional requirements of each level of the support system and the design parameters, and realizes forward design.

[0060] (3) The aircraft support system optimization method based on model axiomatization designed by the present invention solves many problems of the previous experience-based development method, and through the reduction algorithm and coupling judgment, solves the problems of various levels of the previous support system, such as the large number of support resources, complex functions, mutual coupling between functions, resulting in redundancy or loss, and solves the problems of unreasonable functional planning of aircraft support resources and large support scale. BRIEF DESCRIPTION OF THE DRAWINGS

[0061] Figure 1 A flowchart of the aircraft support system optimization method based on model axiomization of the present invention;

[0062] Figure 2 It is a design flow chart of the aircraft support system of the present invention. DETAILED DESCRIPTION

[0063] The exemplary embodiments, features and aspects of the present invention will be described in detail below with reference to the accompanying drawings. The same reference numerals in the accompanying drawings represent elements with the same or similar functions. Although various aspects of the embodiments are shown in the accompanying drawings, the drawings are not necessarily drawn to scale unless otherwise specified.

[0064] The embodiment of the present invention takes the development of a certain type of helicopter as an example, and provides an aircraft support system optimization method and an aircraft support system based on model axiomization, such as Figure 1 As shown in the figure, according to the characteristics of the aircraft support system, the model elements of the aircraft support system required by the model axiomatization method are determined; the aircraft support system requirements and aircraft support system functions based on the model axiomatization are analyzed, and the white box model of the aircraft support system is constructed using the system modeling language SysML to obtain the model axiomatized aircraft support system; the rationality of the first-level model of the aircraft support system is checked using the specification algorithm and the independent axiom; the aircraft support system design structure matrix is ​​used to complete the aircraft support system optimization design; which includes:

[0065] Step S1: According to the characteristics of the aircraft support system, determine the aircraft support system model elements required by the model axiomatic method.

[0066] The system modeling language SysML is used to construct the relationship between the aircraft support system requirement sub-model, aircraft support system function sub-model, and aircraft support system structure sub-model in the aircraft support system model based on model axioms.

[0067] The model axiomatic method is a top-down iterative model design process for aircraft support systems. Each iteration includes three stages: requirement analysis, functional analysis, and system design of the aircraft support system. Each stage corresponds to the user domain, functional domain, and structural domain in the axiomatic design theory.

[0068] In the j-th design level of the aircraft support system, there are k functional requirement parameters FR and structural design parameters DP, and there are m association relationships Map between these parameters; the aircraft support system model parameter composition set M based on the model axiom method A-M for:

[0069]

[0070] Among them, M A-M It is a set of aircraft support system parameters; CR i is the i-th design requirement parameter of the aircraft support system; FR k is the kth functional requirement parameter of the aircraft support system; DP k is the kth structural design parameter of the aircraft support system; Map m is the mth association relationship; K is the design level of the aircraft support system; n is the number of user requirements CR of the aircraft support system; i is the design requirement number of the aircraft support system; j is the design iteration number of the aircraft support system; m is the total number of design iterations of the aircraft support system; k is the number of functional requirements and design parameters; L is the number of layers of the aircraft support system; U is the union operation symbol.

[0071] Step S2: Analyze the aircraft support system requirements and aircraft support system functions based on model axiomatization, use the system modeling language SysML to build a white box model of the aircraft support system, and obtain the aircraft support system with model axiomatization.

[0072] Analyze the aircraft support system requirements and aircraft support system functions based on model axiomatization, specifically:

[0073] Step S21: Analyze aircraft support system requirements.

[0074] Step S211: Analyze the flight mission requirements, analyze and decompose the specific flight missions to be undertaken by the aircraft according to the mission and positioning of the aircraft to be analyzed, and obtain a flight mission set.

[0075] Step S212: Analyze the aircraft support mission requirements. Based on the aircraft flight mission set analyzed and determined in step S211, analyze and decompose the support tasks to be undertaken during its entire life cycle, and determine the aircraft support mission set, including: operation support missions and maintenance support missions.

[0076] Step S213: Analyze the aircraft support requirements, construct a support scenario for each support task, and decompose the support activities and support nodes it contains.

[0077] Step S214: analyzing the aircraft support capability requirements. Capability requirement analysis refers to analyzing the support capabilities that the aircraft support system needs to have for each support activity and support node in order to complete the support task, and obtaining itemized user requirements.

[0078] Step S22: Analyze the aircraft support system function.

[0079] Step S221: Based on the aircraft support system capability requirements determined by the requirements analysis, a support system black box model, i.e., an aircraft support system functional sub-model, is constructed using the system modeling language SysML, including a use case diagram, a black box activity diagram, and a black box sequence diagram.

[0080] Step S222: Based on the constructed black box model, analyze the main activities that the security system needs to perform and the functions required to perform these activities, and sort out the itemized functional requirements.

[0081] The white box model of the aircraft support system is specifically: the aircraft support system structural sub-model, including the white box activity diagram and the white box sequence diagram; the white box model divides each activity into different lanes based on the black box model, and one lane is a design parameter. Different functional requirements are undertaken by different design parameters.

[0082] Step S23: Based on the data model of the existing aircraft support system, the design parameters are generated from the functional requirements to complete the first-level model of the aircraft support system; the requirement function structure mapping process is determined according to the aircraft support system model parameter composition set in step S1, and the aircraft support system design equation is constructed as follows:

[0083] {FR}=[A]{DP};

[0084]

[0085] Among them, FR is the functional requirement vector of the aircraft support system; FR k is its kth element; A is the aircraft support system design structure matrix; A jk is the design element of its jth row and kth column; DP is the design parameter vector of the aircraft support system; DP k is its kth element.

[0086] The functional requirement vector FR of the aircraft support system and the design parameter vector DP of the aircraft support system need to be associated and represented through the aircraft support system design structure matrix A of the function-to-physical process; the design element A in the design structure matrix jk The meaning of is constructed by the first auxiliary design element a1 and the second auxiliary design element a2; the first auxiliary design element a1 indicates that there is an association relationship between the corresponding row and column elements; the second auxiliary design element a2 indicates that there is no association relationship.

[0087] Step S3: Use the reduction algorithm and the independence axiom to perform a rationality check on the first-level model of the aircraft support system in step S2.

[0088] Step S31: using the reduction algorithm of the aircraft support system design structure matrix, excluding the independent functions of the aircraft support system, and simplifying the aircraft support system design structure matrix A, specifically:

[0089] Step S311: Find the functional requirements FR of the aircraft support system in which all rows except the diagonal elements in the aircraft support system design structure matrix are the second auxiliary design elements a2 k And the design parameters DP of the aircraft support system whose columns are all the second auxiliary design elements a2 k , transform the row and column elements of the design structure matrix, and transform the functional requirements FR of these aircraft support systems k Placed in the upper left corner of the design structure matrix, the design parameter DP of the aircraft support system k Place it in the lower right corner of the design structure matrix.

[0090] Step S312: The functional requirements FR of the aircraft support system whose rows except the diagonal elements are all the second auxiliary design elements a2 k And the design parameters DP of the aircraft support system whose columns are all the second auxiliary design elements a2 k , that is, factors that will not lead to any functional coupling are eliminated, and a streamlined design structure matrix is ​​obtained; the functional requirements FR of these eliminated aircraft support systems k and the design parameters DP of the aircraft support system k It has relative independence, guides and ensures system design, and enters the next design iteration.

[0091] Step S313: The simplified aircraft support system design structure matrix is ​​analyzed again using steps S311 and S312 until no more elements can be eliminated.

[0092] Step S32: Use the independence axiom to determine the coupling of the aircraft support system design. According to the aircraft support system design structure matrix A obtained in step S2, determine whether the current aircraft support system design structure matrix A satisfies the independence axiom, thereby realizing the coupling determination of the aircraft support system design.

[0093] To determine whether the current aircraft support system design structure matrix A satisfies the independence axiom, three specific cases are dealt with.

[0094] The first case: When the aircraft support system design structure matrix A is a diagonal matrix, that is, except for the diagonal elements, the remaining elements are the second auxiliary design elements a2, specifically:

[0095]

[0096] It is denoted as A=d iag(a1, a1, ..., a1), which means that the physical structure design of different security resources constructed according to functional requirements is a non-coupling design, and the next design iteration is carried out directly according to the correspondence between functional requirements and design parameters.

[0097] The second case: When the aircraft support system design structure matrix A is a triangular matrix, that is, all elements below or above the main diagonal are the second auxiliary design elements a2, specifically:

[0098] or

[0099] This indicates that the design is a quasi-coupled design / decoupled design, which needs to be converted into a triangular matrix through matrix transformation to make the functional requirements relatively independent.

[0100] The third case: When the aircraft support system design structure matrix A is a full matrix, the functional requirements do not satisfy the independence axiom, and there is coupling between them. It is necessary to reselect the design parameters, that is, the specific physical product design plan of the support resources, change the influence of the design parameters on the functional requirements, and once again judge whether the independence axiom is satisfied, so that the aircraft support system design structure matrix A is converted into a diagonal matrix in the first case or a triangular matrix in the second case.

[0101] Step S4: Use the aircraft support system design structure matrix to complete the aircraft support system optimization design.

[0102] Through the analysis of step S32 above, the functional requirements FR of the aircraft support system that cause functional coupling are determined. k and the design parameters DP of the aircraft support system k , by redesigning the design parameters DP of the aircraft support system k , complete the resource optimization design of the aircraft support system and obtain the secondary model of the aircraft support system.

[0103] Functional coupling is a key factor affecting the efficiency of support resource design in aircraft support systems. Using the independence axiom of axiomatic design theory as a criterion for judging whether the system design is coupled can effectively make design decisions.

[0104] like Figure 2 As shown, the method of the present invention includes three steps: determining the model axiomatic method framework, constructing the "demand-function-structure" design decomposition process of the aircraft support system, and applying the reduction algorithm of the aircraft support system design structure matrix, and finally realizing the design of the aircraft support system.

[0105] The second aspect of the embodiment of the present invention proposes an aircraft support system obtained by an aircraft support system optimization method based on model axiomatization, which includes: a support system model element construction module, a user demand analysis module, a function analysis module, a structural system design module, a support system rationality verification module and a support system optimization design module. The support system model element construction module adopts a combination of model-based system design and axiomatic design theory. The user demand analysis module carries out user demand capture to obtain itemized user demand. The function analysis module constructs a black box model to obtain itemized function requirements. The structural system design module constructs a white box model to complete the preliminary design of the support system; the functional requirements complete the preliminary generation of design parameters, and the preliminary design parameters of the support system are obtained by analysis; the design structure matrix is ​​constructed to establish a mapping relationship between the function requirements and the design parameters. The support system rationality verification module can use the specification algorithm to simplify the design structure matrix to facilitate the next step of coupling judgment; the support system rationality verification module can use the independence axiom to judge whether there is coupling between the function requirements and the design parameters. The support system optimization design module is used to redesign the design parameters that do not meet the independence axiom to complete the optimization of the aircraft support system.

[0106] The beneficial effects of the present invention are as follows: the embodiment of the present invention provides an aircraft support system optimization method based on model axiomatization, which is integrated through axiomatic design and model-based system design theory, changes the previous experience-based design and development method, and obtains more objective and accurate results, providing a basis for the forward design of the aircraft support system. The embodiment of the present invention takes helicopters as the specific analysis object, takes user needs as the driving force, establishes a mapping relationship between the functional requirements and design parameters of each level of the support system, and realizes forward design; solves many problems of the previous experience-based development method, and solves the problems of the previous support system levels such as the large number of support resources, complex functions, mutual coupling between functions, redundancy or missing, etc. through the specification algorithm and coupling judgment, and solves the problems of unreasonable functional planning of aircraft support resources and large support scale.

[0107] The embodiments described above are only descriptions of the preferred implementation modes of the present invention, and are not intended to limit the scope of the present invention. Without departing from the design spirit of the present invention, various modifications and improvements made to the technical solutions of the present invention by ordinary technicians in this field should all fall within the protection scope determined by the claims of the present invention.

Claims

1. An aircraft support system optimization method based on model axiomatization, characterized in that: It includes: S1: According to the characteristics of the aircraft support system, determine the aircraft support system model elements required by the model axiomatic method; Use the system modeling language SysML to construct the relationship between the aircraft support system requirement sub-model, aircraft support system function sub-model, and aircraft support system structure sub-model in the aircraft support system model based on model axioms; In the j-th design level of the aircraft support system, there are k functional requirement parameters FR and structural design parameters DP, and there are m association relationships Map between these parameters; the aircraft support system model parameter composition set M based on the model axiom method A-M for: Among them, M A-M It is a set of aircraft support system parameters; CR i is the i-th design requirement parameter of the aircraft support system; FR k is the kth functional requirement parameter of the aircraft support system; DP k is the kth structural design parameter of the aircraft support system; Map m is the mth association relationship; K is the design level of the aircraft support system; n is the number of aircraft support system user requirements CR; i is the aircraft support system design requirement number; j is the aircraft support system design iteration number; m is the total number of aircraft support system design iterations; k is the number of functional requirements and design parameters; L is the number of layers of the aircraft support system; U is the union operator symbol; S2: Analyze the requirements and functions of the aircraft support system based on model axiomatization, use the system modeling language SysML to build a white box model of the aircraft support system, and obtain the aircraft support system with model axiomatization; Based on the data model of the existing aircraft support system, the design parameters are generated from the functional requirements to complete the first-level model of the aircraft support system; the demand function structure mapping process is determined according to the aircraft support system model parameter composition set in step S1, and the aircraft support system design equation is constructed as follows: {FR}=[A]{DP} Among them, FR is the functional requirement vector of the aircraft support system; FR k is its kth element; A is the aircraft support system design structure matrix; A jk is the design element of its jth row and kth column; DP is the design parameter vector of the aircraft support system; DP k is its kth element; S3: Use the reduction algorithm and the independence axiom to perform a rationality check on the first-level model of the aircraft support system in step S2; S31: Use the reduction algorithm of the aircraft support system design structure matrix to exclude the independent functions of the aircraft support system and simplify the aircraft support system design structure matrix A; S32: using the independence axiom to judge the coupling of the aircraft support system design, judging whether the current aircraft support system design structure matrix A satisfies the independence axiom according to the aircraft support system design structure matrix A obtained in step S2, thereby realizing the coupling judgment of the aircraft support system design; S4: Use the aircraft support system design structure matrix to complete the aircraft support system optimization design; Through the analysis in step S32, the functional requirements FR of the aircraft support system that cause functional coupling are determined k and the design parameters DP of the aircraft support system k , by redesigning the design parameters DP of the aircraft support system k , complete the resource optimization design of the aircraft support system and obtain the secondary model of the aircraft support system.

2. The aircraft support system optimization method based on model axiomatization according to claim 1 is characterized by: The model axiomatic method in step S1 is a top-down model design iterative process for the aircraft support system. Each iteration includes three stages: requirement analysis, functional analysis, and system design of the aircraft support system. Each stage corresponds to the user domain, functional domain, and structural domain in the axiomatic design theory.

3. The aircraft support system optimization method based on model axiomatization according to claim 1, characterized in that: The analysis in step S2 is based on the model axiomatized aircraft support system requirements and aircraft support system functions, specifically: S21: Analyze aircraft support system requirements: S211: Analyze flight mission requirements, analyze and decompose specific flight missions to be undertaken by the aircraft according to its mission and positioning, and obtain a flight mission set; S212: analyzing the aircraft support mission requirements, based on the aircraft flight mission set analyzed and determined in step S211, analyzing and decomposing the support missions to be undertaken in the entire life cycle stage, and determining the aircraft support mission set, including: operation support missions and maintenance support missions; S213: Analyze aircraft support requirements, build support scenarios for each support task, and decompose the support activities and support nodes it contains; S214: Analyze the aircraft support capability requirements. Capability requirement analysis refers to analyzing the support capabilities that the aircraft support system needs to have for each support activity and support node in order to complete the support mission, and obtaining itemized user requirements; S22: Analyze the functions of aircraft support systems; S221: Based on the aircraft support system capability requirements determined by the requirements analysis, the system modeling language SysML is used to construct the support system black box model, i.e., the aircraft support system functional sub-model, including use case diagrams, black box activity diagrams, and black box sequence diagrams; S222: Based on the constructed black box model, analyze the main activities that the security system needs to perform and the functions required to perform these activities, and sort out the itemized functional requirements.

4. The aircraft support system optimization method based on model axiomatization according to claim 1, characterized in that: The white box model of the aircraft support system in step S2 is specifically: an aircraft support system structural sub-model, including a white box activity diagram and a white box sequence diagram; the white box model divides each activity into different lanes based on the black box model, and one lane is a design parameter, and different functional requirements are undertaken by different design parameters.

5. The aircraft support system optimization method based on model axiomatization according to claim 1, characterized in that: In step S2, the functional requirement vector FR of the aircraft support system and the design parameter vector DP of the aircraft support system need to be associated and represented by the aircraft support system design structure matrix A of the function-to-physical process; the design element A in the design structure matrix jk The meaning of is constructed by the first auxiliary design element a1 and the second auxiliary design element a2; the first auxiliary design element a1 indicates that there is an association relationship between the corresponding row and column elements; the second auxiliary design element a2 indicates that there is no association relationship.

6. The aircraft support system optimization method based on model axiomatization according to claim 1, characterized in that: In step S31, the aircraft support system design structure matrix reduction algorithm is used to exclude the independent functions of the aircraft support system and simplify the aircraft support system design structure matrix A, specifically: S311: Find the functional requirements FR of the aircraft support system in which all rows except the diagonal elements in the aircraft support system design structure matrix are the second auxiliary design elements a2 k And the design parameters DP of the aircraft support system whose columns are all the second auxiliary design elements a2 k , transform the row and column elements of the design structure matrix, and transform the functional requirements FR of these aircraft support systems k Placed in the upper left corner of the design structure matrix, the design parameter DP of the aircraft support system k Place it in the lower right corner of the design structure matrix; S312: The functional requirements FR of the aircraft support system whose rows except the diagonal elements are all the second auxiliary design elements a2 k And the design parameters DP of the aircraft support system whose columns are all the second auxiliary design elements a2 k , that is, factors that will not lead to any functional coupling are eliminated, and a streamlined design structure matrix is ​​obtained; the functional requirements FR of these eliminated aircraft support systems k and the design parameters DP of the aircraft support system k It has relative independence, guides the design of the security system, and enters the next design iteration; S313: The simplified aircraft support system design structure matrix is ​​analyzed again using steps S311 and S312 until no more elements can be eliminated.

7. The aircraft support system optimization method based on model axiomatization according to claim 1 is characterized in that: In step S32, it is determined whether the current aircraft support system design structure matrix A satisfies the independence axiom, and three specific cases are processed; The first case: When the aircraft support system design structure matrix A is a diagonal matrix, that is, except for the diagonal elements, the remaining elements are the second auxiliary design elements a2, specifically: It is recorded as A=diag(a1, a1, …, a1), which means that the physical composition design of different security resources built according to the functional requirements is a non-coupling design, and the next design iteration is carried out directly according to the correspondence between the functional requirements and the design parameters; The second case: When the aircraft support system design structure matrix A is a triangular matrix, that is, all elements below or above the main diagonal are the second auxiliary design elements a2, specifically: or The design is a quasi-coupled design / decoupled design, which needs to be converted into a triangular matrix through matrix transformation, so that the functional requirements are relatively independent; The third case: When the aircraft support system design structure matrix A is a full matrix, the functional requirements do not satisfy the independence axiom and are coupled with each other. It is necessary to reselect the design parameters, that is, the specific physical product design plan of the support resources, change the influence of the design parameters on the functional requirements, and once again judge whether the independence axiom is satisfied, so that the aircraft support system design structure matrix A is converted into a diagonal matrix in the first case or a triangular matrix in the second case.

8. The aircraft support system optimization method based on model axiomatization according to claim 1, characterized in that: Functional coupling in step S4 is a key factor affecting the efficiency of support resource design in the aircraft support system. The independence axiom of axiomatic design theory is used as a criterion for judging whether the system design is coupled.

9. An aircraft support system obtained by an aircraft support system optimization method based on model axiomatization, characterized in that: It includes: Support system model element construction module, user demand analysis module, function analysis module, structural system design module, support system rationality verification module and support system optimization design module; The support system model element building module adopts a combination of model-based system design and axiomatic design theory; The user demand analysis module captures user demands and obtains itemized user demands; The functional analysis module constructs a black box model to obtain itemized functional requirements; The structural system design module builds a white box model to complete the preliminary design of the support system; The design parameters are initially generated based on the functional requirements, and the preliminary design parameters of the guarantee system are obtained through analysis; Construct a design structure matrix to establish the mapping relationship between functional requirements and design parameters; The rationality check module of the security system can use the reduction algorithm to simplify the design structure matrix to facilitate the next step of coupling judgment; the rationality check module of the security system can use the independence axiom to judge whether there is coupling between functional requirements and design parameters; The support system optimization design module is used to redesign the design parameters that do not meet the independence axiom to complete the optimization of the aircraft support system.

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