Method for optimizing aircraft support system based on model axiomatization and aircraft support system

Abstract

The present application relates to the technical field of aircraft support, in particular to an aircraft support system optimization method based on model axiomatization and an aircraft support system, which comprises: S1, determining aircraft support system model elements required by a model axiomatization method according to the characteristics of the aircraft support system; S2, analyzing aircraft support system requirements and aircraft support system functions based on model axiomatization, constructing a white box model of the aircraft support system using a system modeling language SysML, and obtaining a model axiomatized aircraft support system; S3, using a specification algorithm and an independent axiom to perform rationality verification on a first-level model of the aircraft support system; and S4, using a design structure matrix of the aircraft support system to complete optimization design of the aircraft support system. The aircraft support system optimization method proposed by the present application can support forward development work of the aircraft support system, and can solve the problems of unreasonable resource function planning and large-scale support of the aircraft support system compared with an experience-based design and development method.

Description

Technical Field

[0001] This invention belongs to the field of aircraft support technology, and specifically relates to an aircraft support system optimization method and aircraft support system based on model axioms. Background Technology

[0002] Model-Based System Design (MBSD) belongs to the field of Model-Based Systems Engineering (MBSE) and mainly includes requirements analysis, functional analysis, and design synthesis. In MBSE, "model-based" can be seen as the transformation of systems engineering from a document- and natural language-centric approach to a model-centric approach.

[0003] Functional analysis is a system-oriented functional design process that further defines system functional requirements based on the top-level system requirements determined by requirements analysis. It typically employs methods such as system use case diagrams, black-box activity diagrams, sequence diagrams, and state machine construction.

[0004] Design synthesis is a system-oriented architectural analysis and design process. For different product levels of the system, this design determines the system's functional architecture, logical architecture, physical architecture, and solutions. Design synthesis typically employs methods such as white-box activity diagrams, sequence diagrams, and state machine construction.

[0005] Axiomatic Design (AD) is a systematic design decision theory that, since its introduction in 1990, has gradually become a design principle in the industrial field, playing a particularly novel role in innovative design and design improvement. This theory introduces three concepts: design domain, hierarchy, and inflectional mapping, as well as two design axioms. A domain is a collection of corresponding design elements at different design stages, serving as the boundary distinguishing different design activities. The entire design process is composed of four main domains: Customer Domain, Functional Domain, Physical Domain, and Process Domain. The contents of these four domains respectively include: Customer Needs, Functional Requirements, Design Parameters, and Process Variables.

[0006] The axiomatic design process, driven by customer needs, involves iteratively mapping through four domains from front to back according to the hierarchical structure of axiomatic design. This process yields design solutions comprised of different levels of functional requirements, design characteristics, and process parameters. The solutions are then optimized using the independence axiom and the information axiom. Specifically: the independence axiom maintains the relative independence of functional requirements for functional design; the information axiom selects the design with less information content, used when multiple alternative design parameters can achieve the same functional requirement, to choose the optimal design solution.

[0007] This invention primarily considers the design of aircraft support systems, and the classification of support resource types based on functional requirements has a significant impact on the final determined types and scale of support resources. For example, support activity diagram analysis can determine the functional requirements for support equipment, but determining the number of support equipment types needed to achieve these functions, and how to classify these functional requirements, is a crucial issue. There are typically dozens or even hundreds of support equipment types; an unscientific classification can lead to a significant increase in the scale of support, thereby affecting equipment support efficiency. Therefore, employing a scientific and rational design method for the forward design of aircraft support systems is both urgent and necessary. Summary of the Invention

[0008] To address the shortcomings of existing technologies, this invention provides an aircraft support system optimization method and system based on model axiomatization. By integrating axiomatic design and model-based system design theory, it changes the previous experience-based design and development approach, resulting in more objective and accurate results and providing a foundation for the forward design of aircraft support systems. This invention solves many problems of previous experience-based development methods and addresses the issues of unreasonable functional planning of aircraft support resources and large support scale through reduction algorithms and coupling judgments.

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

[0010] An optimization method for aircraft support systems based on model axioms, comprising:

[0011] S1: Based on the characteristics of the aircraft support system, determine the aircraft support system model elements required for the model axiomatic method;

[0012] Using the system modeling language SysML, relationships between the aircraft support system requirement sub-model, functional sub-model, and structural sub-model are constructed in an 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 these parameters are interconnected by m relationships (Map). The set M of parameters for the aircraft support system model based on the model axiomatization method is then constructed. A-M for:

[0013]

[0014] Among them, M A-M For aircraft support system parameter set; CR i FR is the i-th design requirement parameter for the aircraft support system. k DP is the k-th functional requirement parameter of the aircraft support system. k For the k-th structural design parameter of the aircraft support system; Map m Let represent the m-th association; K represent the design level of the aircraft support system; n represent the number of user requirements (CRs) for the aircraft support system; i represent the design requirement number of the aircraft support system; j represent the design iteration number of the aircraft support system; m represent the total number of design iterations for the aircraft support system; k represent the number of functional requirements and design parameters; L represent the number of layers in the aircraft support system; ∪ represents the union operator.

[0015] S2: Analyze the requirements and functions of the aircraft support system based on the model axiom, and use the system modeling language SysML to construct a white-box model of the aircraft support system to obtain the model axiomized aircraft support system.

[0016] Based on the existing aircraft support system data model, design parameters are generated from functional requirements to complete the first-level model of the aircraft support system. The functional structure mapping process is determined according to the set of aircraft support system model parameters from step S1, and the design equations for the aircraft support system are constructed as follows:

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

[0018]

[0019] Where FR is the functional requirement vector of the aircraft support system; FR k It is its k-th element; A is the design structure matrix of the aircraft support system; A jk DP is the design element in the j-th row and k-th column; DP is the design parameter vector of the aircraft support system; DP k Let it be its k-th element;

[0020] S3: Use the reduction algorithm and independence axiom to verify the rationality of 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 eliminate the independent functions of the aircraft support system and simplify the aircraft support system design structure matrix A;

[0022] S32: Use the independence axiom to determine the coupling of the aircraft support system design. Based on 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, thus realizing the coupling judgment of the aircraft support system design.

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

[0024] Through the analysis in step S32 above, the functional requirements FR of the aircraft support system that lead to functional coupling are determined. k Design parameters DP of aircraft support systems k By redesigning the design parameters DP of the aircraft support system k The resource optimization design of the aircraft support system was completed, and the secondary model of the aircraft support system was obtained.

[0025] Preferably, the model axiomatization method in step S1 is used as a top-down model design iterative process for aircraft support systems. Each iteration includes three stages: requirements 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 axiomatized design theory, respectively.

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

[0027] S21: Analysis of aircraft support system requirements:

[0028] S211: Analyze flight mission requirements. Based on the mission and positioning of the aircraft being analyzed, analyze and decompose the specific flight missions it needs to undertake to obtain a set of flight missions.

[0029] S212: Analyze the aircraft support mission requirements. Based on the set of aircraft flight missions analyzed and determined in step S211, analyze and decompose the support missions to be undertaken in the entire life cycle stage to determine the set of aircraft support missions, including: operation support missions and maintenance support missions.

[0030] S213: Analyze aircraft support requirements, construct support scenarios for each support task, and decompose the support activities and support nodes included in them;

[0031] S214: Analyze 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 obtain itemized user requirements.

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

[0033] S221: Based on the aircraft support system capability requirements determined by the requirements analysis, a black box model of the support system is constructed using the system modeling language SysML, namely the functional sub-model of the aircraft support system, 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 system needs to perform, as well as 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: the aircraft support system structural sub-model, including a white-box activity diagram and a white-box sequence diagram; the white-box model is based on the black-box model, in which each activity is assigned to a different swimlane, and each swimlane represents a design parameter, so that different functional requirements are undertaken by different design parameters.

[0036] Preferably, in step S2, the functional requirement vector FR 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, which is a function-to-physical process matrix; the design element A in the design structure matrix jk The meaning is constructed using the first auxiliary design element a1 and the second auxiliary design element a2; the first auxiliary design element a1 indicates that there is a relationship between the corresponding row and column elements; the second auxiliary design element a2 indicates that there is no relationship.

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

[0038] S311: Identify the functional requirements FR of the aircraft support system in the aircraft support system design structure matrix where all rows except the diagonal elements are the second auxiliary design element a2. k And the design parameters DP of the aircraft support system, where all columns are second auxiliary design element a2. k The matrix transformation is performed on the row and column elements of the design structure matrix to obtain the functional requirements of these aircraft support systems. k Placed in the upper left corner of the design structure matrix, the design parameters DP of the aircraft support system k Place it in the bottom right corner of the design structure matrix;

[0039] S312: Functional requirements for aircraft support systems where all rows except diagonal elements are second auxiliary design elements a2. k And the design parameters DP of the aircraft support system, where all columns are second auxiliary design element a2. k This means eliminating factors that will not lead to any functional coupling, resulting in a simplified design structure matrix; the functional requirements FR of these eliminated aircraft support systems k Design parameters DP of aircraft support systems k It possesses relative independence, guiding and ensuring system design, and proceeding to the next design iteration;

[0040] S313: The simplified aircraft support system design structure matrix is ​​analyzed again using steps S311 and S312 until it cannot be eliminated.

[0041] Preferably, in step S32, it is determined whether the current aircraft support system design structure matrix A satisfies the independence axiom, which is specifically handled in three cases.

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

[0043]

[0044] Let A = diag(a1, a1, ..., a1), indicating that the physical composition of different guarantee resources built for functional requirements is a decoupled design, and the next design iteration is carried out directly based on the correspondence between functional requirements and design parameters;

[0045] The second scenario: 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 element a2, specifically:

[0046] or

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

[0048] The third scenario: 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 scheme of the support resources, change the influence relationship of the design parameters on the functional requirements, and judge again whether the independence axiom is satisfied, so that the aircraft support system design structure matrix A is transformed into the diagonal matrix of the first scenario or the triangular matrix of the second scenario.

[0049] Preferably, in step S4, functional coupling is a key factor affecting the efficiency of support resource design in the aircraft support system. Using the independence axiom of axiomatic design theory as the criterion for judging whether the system design is coupled can effectively make design scheme decisions.

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

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

[0052] The user requirement analysis module performs user requirement capture and obtains itemized user requirements.

[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 support system; it generates preliminary design parameters based on functional requirements and analyzes them to obtain the preliminary design parameters of the support system; it constructs a design structure matrix and establishes a mapping relationship between functional requirements and design parameters.

[0055] The system rationality verification module can use a reduction algorithm to simplify the design structure matrix, which facilitates the next step of coupling judgment; the system rationality verification module can use the independence axiom to determine whether there is coupling between functional requirements and design parameters.

[0056] The support system optimization design module is used to redesign design parameters that do not conform to the independent axiom, thereby completing 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 in this invention integrates axiomatization design and model-based system design theory, which changes the previous experience-based design and development method. The results obtained are more objective and accurate, providing a foundation for the forward design of aircraft support systems.

[0059] (2) The aircraft support system optimization method based on model axioms designed in this invention takes user needs as the guide, establishes the mapping relationship between functional requirements and design parameters at each level of the support system, and realizes forward design.

[0060] (3) The aircraft support system optimization method based on model axioms designed in this invention solves many problems of the previous experience-based development method. Through reduction algorithm and coupling judgment, it solves problems such as the large number of support resources, complex functions, and mutual coupling between functions in the previous support system, resulting in redundancy or missing functions. It also solves the problems of unreasonable functional planning of aircraft support resources and large support scale. Attached Figure Description

[0061] Figure 1 This is a flowchart of the aircraft support system optimization method based on model axioms of the present invention;

[0062] Figure 2 This is a flowchart illustrating the design of the aircraft support system of the present invention. Detailed Implementation

[0063] Exemplary embodiments, features, and aspects of the present invention will now be described in detail with reference to the accompanying drawings. The same reference numerals in the drawings denote elements that have the same or similar functions. Although various aspects of the embodiments are shown in the drawings, they are not necessarily drawn to scale unless specifically indicated otherwise.

[0064] Taking the development of a certain type of helicopter as an example, this invention provides an aircraft support system optimization method and an aircraft support system based on model axioms, such as... Figure 1 As shown, considering the characteristics of aircraft support systems, the model elements required for the axiomatic approach to aircraft support systems are determined; the requirements and functions of aircraft support systems based on the axiomatic approach are analyzed; a white-box model of the aircraft support system is constructed using the system modeling language SysML, resulting in the axiomatic aircraft support system; the rationality of the first-level model of the aircraft support system is verified using the reduction algorithm and the independence axiom; and the optimization design of the aircraft support system is completed using the aircraft support system design structure matrix; this includes:

[0065] Step S1: Based on the characteristics of the aircraft support system, determine the aircraft support system model elements required for the model axiomatic method.

[0066] The system modeling language SysML is used to construct the relationships 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 axiomatic modeling method is a top-down iterative process for model design of aircraft support systems. Each iteration includes three stages: requirements analysis, functional analysis, and system design. Each stage corresponds to the user domain, functional domain, and structural domain in axiomatic design theory, respectively.

[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 these parameters are related by m relationships (Map). The set M of parameters for the aircraft support system model is derived from the model axiomatization method. A-M for:

[0069]

[0070] Among them, M A-M For aircraft support system parameter set; CR i FR is the i-th design requirement parameter for the aircraft support system. k DP is the k-th functional requirement parameter of the aircraft support system. k For the k-th structural design parameter of the aircraft support system; Map m Let m be the m-th association; K be the design level of the aircraft support system; n be the number of user requirements (CRs) of the aircraft support system; i be the design requirement number of the aircraft support system; j be the design iteration number of the aircraft support system; m be the total number of design iterations of the aircraft support system; k be the number of functional requirements and design parameters; L be the number of layers of the aircraft support system; and U be the union operator.

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

[0072] The analysis of aircraft support system requirements and functions based on model axioms is as follows:

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

[0074] Step S211: Analyze flight mission requirements. Based on the mission and positioning of the aircraft being analyzed, analyze and decompose the specific flight missions it needs to undertake to obtain a set of flight missions.

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

[0076] Step S213: Analyze aircraft support requirements, construct support scenarios for each support task, and decompose the support activities and support nodes included in them.

[0077] Step S214: Analyze 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.

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

[0079] Step S221: Based on the capability requirements of the aircraft support system determined by the requirements analysis, construct a black box model of the support system using the system modeling language SysML, namely the functional sub-model of the aircraft support system, including use case diagrams, black box activity diagrams and black box sequence diagrams.

[0080] Step S222: Based on the constructed black box model, analyze the main activities that the system needs to perform, as well as 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 structural sub-model of the aircraft support system, including the white-box activity diagram and the white-box sequence diagram; the white-box model is based on the black-box model, which divides each activity into different swimlanes, with each swimlane representing a design parameter, and different design parameters are used to implement different functional requirements.

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

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

[0084]

[0085] Where FR is the functional requirement vector of the aircraft support system; FR k It is its k-th element; A is the design structure matrix of the aircraft support system; A jk DP is the design element in the j-th row and k-th column; DP is the design parameter vector of the aircraft support system; DP k It is its k-th element.

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

[0087] Step S3: Use the reduction algorithm and independence axiom to verify the rationality of 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, eliminate the independent functions of the aircraft support system and simplify the aircraft support system design structure matrix A, specifically as follows:

[0089] Step S311: Identify the functional requirements FR of the aircraft support system in the aircraft support system design structure matrix where all rows except the diagonal elements are the second auxiliary design element a2. k And the design parameters DP of the aircraft support system, where all columns are second auxiliary design element a2. k The matrix transformation is performed on the row and column elements of the design structure matrix to obtain the functional requirements of these aircraft support systems. k Placed in the upper left corner of the design structure matrix, the design parameters DP of the aircraft support system k Place it in the bottom right corner of the design structure matrix.

[0090] Step S312: FR of the aircraft support system where all rows except the diagonal elements are second auxiliary design elements a2. k And the design parameters DP of the aircraft support system, where all columns are second auxiliary design element a2. k This means eliminating factors that will not lead to any functional coupling, resulting in a simplified design structure matrix; the functional requirements FR of these eliminated aircraft support systems k Design parameters DP of aircraft support systems k It has relative independence, guides and ensures system design, and moves on to the next design iteration.

[0091] Step S313: The simplified aircraft support system design structure matrix is ​​analyzed again using steps S311 and S312 until it cannot be eliminated.

[0092] Step S32: Use the independence axiom to determine the coupling of the aircraft support system design. Based on 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 judgment of the aircraft support system design.

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

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

[0095]

[0096] Let A = diag(a1, a1, ..., a1), indicating that the physical composition of different guarantee resources built for functional requirements is a decoupled design, and the next design iteration is carried out directly based on the correspondence between functional requirements and design parameters.

[0097] The second scenario: 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 element a2, specifically:

[0098] or

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

[0100] The third scenario: 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 scheme of the support resources, change the influence relationship of the design parameters on the functional requirements, and judge again whether the independence axiom is satisfied, so that the aircraft support system design structure matrix A is transformed into the diagonal matrix of the first scenario or the triangular matrix of the second scenario.

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

[0102] Through the analysis in step S32 above, the functional requirements FR of the aircraft support system that lead to functional coupling are determined. k Design parameters DP of aircraft support systems k By redesigning the design parameters DP of the aircraft support system k The resource optimization design of the aircraft support system was completed, and the secondary model of the aircraft support system was obtained.

[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 system design is coupled can effectively make design decisions.

[0104] like Figure 2 The method of this invention includes three steps: determining the axiomatic framework of the model, constructing the "requirements-functions-structures" design decomposition process of the aircraft support system, and applying the reduction algorithm of the aircraft support system design structure matrix, which ultimately realizes the design of the aircraft support system.

[0105] The second aspect of this invention proposes an aircraft support system optimization method based on model axioms, comprising: a support system model element construction module, a user requirement analysis module, a functional 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 combines model-based system design and axiomatic design theory. The user requirement analysis module captures user requirements to obtain itemized user requirements. The functional analysis module constructs a black-box model to obtain itemized functional requirements. The structural system design module constructs a white-box model to complete the preliminary design of the support system; it generates preliminary design parameters from functional requirements and analyzes them to obtain preliminary design parameters of the support system; it constructs a design structure matrix to establish a mapping relationship between functional requirements and design parameters. The support system rationality verification module uses a reduction algorithm to simplify the design structure matrix, facilitating subsequent coupling judgment; it also uses the independence axiom to determine whether there is coupling between functional requirements and design parameters. The support system optimization design module is used to redesign design parameters that do not conform to the independence axiom, thus completing the optimization of the aircraft support system.

[0106] The beneficial effects of this invention are as follows: This invention provides an aircraft support system optimization method based on model axioms. By integrating axiomatic design and model-based system design theory, it changes the previous experience-based design and development approach, resulting in more objective and accurate results, and providing a foundation for forward design of aircraft support systems. This invention takes the helicopter as a specific analysis object and user needs as the driving force, establishing a mapping relationship between functional requirements and design parameters at each level of the support system to achieve forward design. It solves many problems of previous experience-based development methods and, through reduction algorithms and coupling judgments, addresses issues such as the large number and complexity of support resources at each level of the previous support system, and the redundancy or missing functions caused by inter-functional coupling. It also solves the problems of unreasonable functional planning of aircraft support resources and large support scale.

[0107] The embodiments described above are merely preferred embodiments of the present invention and are not intended to limit the scope of the present invention. Various modifications and improvements made by those skilled in the art to the technical solutions of the present invention without departing from the spirit of the present invention should fall within the protection scope defined by the claims of the present invention.

Claims

1. An optimization method for aircraft support systems based on model axioms, characterized in that, It includes: S1: Based on the characteristics of the aircraft support system, determine the aircraft support system model elements required for the model axiomatic method; The system modeling language SysML is used to construct the relationships between the aircraft support system requirement sub-model, aircraft support system functional sub-model, and aircraft support system structural sub-model in the aircraft support system model based on model axiomatization. In the aircraft support system In each design level, there are Functional requirement parameters and structural design parameters At the same time, these parameters have Relationships The set of parameters M for the aircraft support system model based on the model axiomatization method A-M for: ； Among them, M A-M A set of parameters for aircraft support systems; For aircraft support systems One design requirement parameter; For aircraft support systems Each functional requirement parameter; For aircraft support systems One structural design parameter; For the first One relationship; Design hierarchy of aircraft support systems; For the needs of aircraft support system users Quantity; Number the design requirements for the aircraft support system; Number the number of design iterations for the aircraft support system; The total number of design iterations for the aircraft support system; The number of functional requirements and design parameters; The number of layers in the aircraft support system; U is the union operator; S2: Analyze the requirements and functions of the aircraft support system based on the model axiom, and use the system modeling language SysML to construct a white-box model of the aircraft support system to obtain the model axiomized aircraft support system. Based on the existing aircraft support system data model, design parameters are generated from functional requirements to complete the first-level model of the aircraft support system. The functional structure mapping process is determined according to the set of aircraft support system model parameters from step S1, and the design equations for the aircraft support system are constructed as follows: ； ； in, Functional requirements vector for aircraft support systems; For its first One element; Design a structural matrix for aircraft support systems; For its first Line 1 Column design elements; For the design parameter vector of the aircraft support system; For its first One element; S3: Use the reduction algorithm and independence axiom to verify the rationality of the first-level model of the aircraft support system in step S2; S31: Using a reduction algorithm for the aircraft support system design structure matrix, the independent functions of the aircraft support system are eliminated, thus simplifying the aircraft support system design structure matrix. ; S32: Use the independence axiom to determine the coupling of the aircraft support system design, based on the aircraft support system design structure matrix obtained in step S2. Determine the current aircraft support system design structure matrix Whether the independence axiom is satisfied enables the determination of coupling in the design of aircraft support systems; S4: Use the aircraft support system design structure matrix to complete the optimized design of the aircraft support system; The analysis in step S32 determines the functional requirements of the aircraft support system that lead to functional coupling. Design parameters of aircraft support systems By redesigning the design parameters of the aircraft support system The resource optimization design of the aircraft support system was completed, and the secondary model of the aircraft support system was obtained.

2. The aircraft support system optimization method based on model axioms as described in claim 1, characterized in that: The model axiomatization method in step S1 is a top-down iterative process for model design of aircraft support systems. Each iteration includes three stages: requirements 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 axiomatized design theory, respectively.

3. The aircraft support system optimization method based on model axioms as described in claim 1, characterized in that: The analysis in step S2 is based on the axiomatic requirements and functions of the aircraft support system, specifically: S21: Analysis of aircraft support system requirements: S211: Analyze flight mission requirements. Based on the mission and positioning of the aircraft being analyzed, analyze and decompose the specific flight missions it needs to undertake to obtain a set of flight missions. S212: Analyze the aircraft support mission requirements. Based on the set of aircraft flight missions analyzed and determined in step S211, analyze and decompose the support missions to be undertaken in the entire life cycle stage to determine the set of aircraft support missions, including: operation support missions and maintenance support missions. S213: Analyze aircraft support requirements, construct support scenarios for each support task, and decompose the support activities and support nodes included in them; S214: Analyze 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 obtain itemized user requirements. S22: Analyze the functions of the aircraft support system; S221: Based on the aircraft support system capability requirements determined by the requirements analysis, a black box model of the support system is constructed using the system modeling language SysML, namely the functional sub-model of the aircraft support system, 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 system needs to perform, as well as the functions required to perform these activities, and sort out the itemized functional requirements.

4. The aircraft support system optimization method based on model axioms as described in claim 1, characterized in that: The white-box model of the aircraft support system in step S2 is specifically: the structural sub-model of the aircraft support system, including the white-box activity diagram and the white-box sequence diagram; the white-box model is based on the black-box model, which divides each activity into different swimlanes, with each swimlane representing a design parameter, and different design parameters fulfilling different functional requirements.

5. The aircraft support system optimization method based on model axioms as described in claim 1, characterized in that: Functional requirements vector of aircraft support system in step S2 Design parameter vectors for aircraft support systems The design structure matrix of the aircraft support system needs to be derived from the function to the physical process. To associate and represent; design elements in the design structure matrix The meaning is constructed using the first auxiliary design element a1 and the second auxiliary design element a2; the first auxiliary design element a1 indicates that there is a relationship between the corresponding row and column elements; the second auxiliary design element a2 indicates that there is no relationship.

6. The aircraft support system optimization method based on model axioms as described in claim 1, characterized in that: Step S31 uses a reduction algorithm for the aircraft support system design structure matrix to eliminate independent functions of the aircraft support system and simplify the aircraft support system design structure matrix. Specifically: S311: Identify the functional requirements of an aircraft support system in the aircraft support system design structure matrix where all rows except the diagonal elements contain the second auxiliary design element a2. And the design parameters of the aircraft support system whose entire column is the second auxiliary design element a2. The matrix transformation is performed on the row and column elements of the design structure matrix to obtain the functional requirements of these aircraft support systems. Placed in the upper left corner of the design structure matrix, the design parameters of the aircraft support system. Place it in the bottom right corner of the design structure matrix; S312: Functional requirements for an aircraft support system where all rows except diagonal elements are second auxiliary design elements a2. And the design parameters of the aircraft support system whose entire column is the second auxiliary design element a2. This means eliminating factors that will not cause any functional coupling, resulting in a simplified design structure matrix; the functional requirements of these eliminated aircraft support systems Design parameters of aircraft support systems It possesses relative independence, guiding and ensuring system design, and proceeding to the next design iteration; S313: The simplified aircraft support system design structure matrix is ​​analyzed again using steps S311 and S312 until it cannot be eliminated.

7. The aircraft support system optimization method based on model axioms as described in claim 1, characterized in that: In step S32, the current aircraft support system design structure matrix is ​​determined. Whether the independence axiom is satisfied is handled in three specific cases. The first scenario: When the aircraft support system design structure matrix... When the matrix is ​​diagonal, all elements except the diagonal elements are the second auxiliary design element a2, specifically: ； This is denoted as A=diag(a1, a1, ..., a1), indicating that the physical composition of different guarantee resources built for functional requirements is a decoupled design, and the next design iteration is carried out directly based on the correspondence between functional requirements and design parameters. The second scenario: when the aircraft support system design structure matrix When it is a triangular matrix, all elements below or above the main diagonal are the second auxiliary design element a2, specifically: or ; The design is described as a quasi-coupled / decoupled design, which requires matrix transformation to convert it into a triangular matrix, thereby making the functional requirements relatively independent. The third scenario: When the aircraft support system is designed with a structural matrix When the matrix is ​​full, the functional requirements do not satisfy the independence axiom and are coupled with each other. Therefore, it is necessary to reselect the design parameters, i.e., the specific physical product design scheme for the support resources, change the influence of the design parameters on the functional requirements, and then re-evaluate whether the independence axiom is satisfied, thus ensuring the aircraft support system design structure matrix is ​​complete. Convert it into a diagonal matrix for the first case or a triangular matrix for the second case.

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

9. An aircraft support system obtained by the aircraft support system optimization method based on model axioms according to claim 1, characterized in that, It includes: The system includes a model element construction module, a user requirements analysis module, a functional analysis module, a structural system design module, a system rationality verification module, and a system optimization design module. The protection system model element construction module adopts a combination of model-based system design and axiomatic design theory; The user requirement analysis module performs user requirement capture and obtains itemized user requirements. The functional analysis module constructs a black-box model to obtain itemized functional requirements. The structural system design module constructs a white-box model to complete the preliminary design of the protection system. The initial design parameters are generated based on the functional requirements, and the preliminary design parameters of the system are obtained through analysis. Construct a design structure matrix to establish the mapping relationship between functional requirements and design parameters; The system rationality verification module can use a reduction algorithm to simplify the design structure matrix, which facilitates the next step of coupling judgment; the system rationality verification module can use the independence axiom to determine whether there is coupling between functional requirements and design parameters. The support system optimization design module is used to redesign design parameters that do not conform to the independent axiom, thereby completing the optimization of the aircraft support system.

Images