Aviation technology standard representation modeling method based on directed topological graph

Abstract

The invention belongs to the technical field of aircraft equipment standardization, and particularly relates to an aviation technology standard characterization modeling method based on a directed topological graph, which comprises the following steps of: S1, determining standard structure elements, relations among the standard structure elements and standard correlation elements of aircraft product standardization; s2, determining a standard input element and a standard input association relationship of the aviation technology standard action process; s3, determining a standard output element and a standard output association relationship of the aviation technology standard action process; s4, performing node modeling in the aviation technology standard action process; s5, relation modeling of the aviation technology standard action process is carried out, and aviation technology standard action process modeling is completed. According to the method, an aviation technology standard action process model is represented based on a directed topological graph, formalization and dominant representation of a standard enabling process are realized, and the formalized model is adopted to quantitatively evaluate the efficiency exerted in the formation and execution processes of an aircraft product standard and a standard system.

Description

Technical Field

[0001] The invention belongs to the technical field of aircraft equipment standardization evaluation, and in particular relates to an aviation technical standard representation modeling method based on a directed topological graph. Background Art

[0002] In the process of evaluating the implementation effect of standards, a comprehensive evaluation method is usually used to make a global and holistic evaluation. However, since the implementation effect of standards is difficult to quantify, there are still few widely recognized evaluation systems and methods for the implementation effect of standards. Therefore, the evaluation of the implementation effect of standards has always been a shortcoming of standardization work and a research hotspot in standardization work.

[0003] The existing standard implementation effect evaluation technologies are limited to expert evaluation methods based on fuzzy comprehensive evaluation methods, which are applicable to the standard implementation effect evaluation at the industry and national levels. It is a comprehensive evaluation with qualitative and quantitative descriptions, which requires the establishment of a reasonable evaluation index system and a certain sample size. The evaluation methods are mostly based on the analytic hierarchy process, combined with questionnaire surveys, expert evaluations and other methods to determine the weights of the evaluation index system, and then obtain the scores of the evaluation targets through expert scoring and judgment. In this process, only the effects produced after the implementation of the standard are scored and judged by experts, without considering the effect process of the entire life cycle of the standard. The subjective factors such as the composition of the index system, the selection of experts, the design of the questionnaire, and the survey method have too much influence on the evaluation results.

[0004] Under the general background of digital transformation of standards, on the basis of initial realization of digitalization, the evaluation of the implementation effect of standards should develop towards modeling. The present invention provides a modeling representation method that formalizes and makes explicit the action process of standards, opens the black box model of the action of standards, and clearly reflects the relationship between standard elements and elements. In the evaluation of standard effects, the present invention can reduce the reliance on fuzzy evaluation, and make the evaluation process more scientific, accurate, and traceable through the specific action process between elements. At the same time, the present invention can promote better embedded application of standards in research and production. Summary of the invention

[0005] In view of the shortcomings of the prior art, the present invention provides an aviation technical standard representation modeling method based on a directed topological graph. Through the form of a directed topological graph, the node set model is used to clarify the influencing factors such as standard factors, technical factors, quality factors, etc. in the implementation process of product standards. The edge set model is used to clarify the role and influence chain transmission process between the factors. The relevant implicit role process and standardization benefits are explicitly expressed through the modeling process, realizing the formalization and explicit expression of the entire process, and solving the problems of the current expert evaluation scoring method, such as the excessive influence of subjective factors on the evaluation results, the lack of traceability of the evaluation basis, and the insufficient quantification of the evaluation process.

[0006] To achieve the above-mentioned purpose, the present invention discloses the following technical solution: a method for representing and modeling aviation technical standards based on a directed topological graph, comprising:

[0007] S1: Determine the standard structural elements, the relationship between standard structural elements, and standard related elements of aircraft product standards;

[0008] S2: Determine the standard input elements and standard input associations in the aviation technical standard process;

[0009] S21: Determine the standard input elements of the aviation technical standard process; the standard input elements are determined based on the technical principles, data or material technical input carrier knowledge that form the standard, including product technical requirements, product verification methods, data models, program drawings and data report input elements of aircraft products;

[0010] S22: Determine the standard input correlation relationship of the aviation technology standard process, and use the standard input elements in step S21 to determine the technology maturity coefficient C TRL , Manufacturing Maturity Factor C MRL , Technical performance evaluation coefficient C TPM and standard constraint coefficient C SDC , the standard input association relationship C of the aircraft product is obtained as follows:

[0011] C=C TRL ·C MRL ·C TPM ·C SDC

[0012] Among them, C is the standard input association relationship of aircraft products;

[0013] S3: Determine the standard output elements and standard output correlation relationships of the aviation technical standards process;

[0014] S31: Determine the standard output elements of the aviation technical standard action process; the standard output element x is characterized by the quality characteristics of the aircraft function and the aircraft product;

[0015] S32: Determine the standard output correlation relationship of the aviation technical standard action process; the standard output correlation relationship refers to the degree of action of the standard body and its subsidiary characteristics supporting the output elements. The method for determining the standard output correlation relationship is to calculate the correlation coefficient r of a single standard correlation element and a single quality element one by one:

[0016]

[0017] Where r is the correlation coefficient of the standard output correlation relationship; χ i is the observed value of the standard output element; is the average value of the standard output elements; y i is the observed value of the quality output factor; is the average value of the quality output factors;

[0018] S33: Conduct regression analysis of standard output factors, take a single quality output factor as the dependent variable, and construct a regression analysis model:

[0019] b=(X y X) -1 X T Y

[0020] Among them, b is the weight coefficient vector of the standard output elements with high correlation; Y is the observation value vector of the quality elements; X is the observation value matrix of the standard output elements;

[0021] S4: Node modeling of the aviation technical standards action process;

[0022] S41: When modeling the main node and sub-node of the aircraft product standard, the main node element of the standard action process model is determined according to the aircraft product standard's ontology and structural elements; the main node refers to the aircraft product standard's ontology model, and one aircraft product standard forms one main node; the sub-node is a graph model constructed based on the aircraft product standard's ontology content and attributes, including an input basis node, a background and reference node, a technical requirement node, an implementation method and process node, and an applicable scope node;

[0023] S42: Modeling the subsidiary nodes of the aircraft product standard; determining the subsidiary nodes of the standard action process model according to the standard associated elements of the aircraft product standard in step S1; the subsidiary nodes refer to the graph model constructed based on the efficiency attributes of the standard, and the subsidiary nodes can characterize the efficiency attributes of a main node or N main nodes and the sub-nodes in step S41; the subsidiary nodes include technical content attribute nodes, influence attribute nodes and product implementation attribute nodes;

[0024] S43: Modeling the standard input elements and standard output elements of the aviation technical standard action process; determining the standard input nodes and standard output nodes in the action process model according to the standard input elements in step S2 and the standard output elements in step S3;

[0025] S5: Relationship modeling of the aviation technical standards process, complete the modeling of the aviation technical standards process;

[0026] S51: ontology association relationship modeling of aircraft product standards; based on the main node of the standard action process model in step S41, the action relationship of each sub-node is determined according to the relationship between the standard structural elements in step S1 to obtain the association relationship model of the standard ontology;

[0027] S52: Modeling the internal action process relationship of aircraft product standards; on the basis of the aircraft product standard ontology association relationship in step S51, according to the specific technical details of the standard structural elements in step S1, and the standards adopted in the technology and product realization process, the corresponding relationship between each standard structural element and the standard associated element is constructed, and the traceability action relationship of the standard associated element to the standard structural element is expressed, and the internal action process relationship model of the standard is obtained;

[0028] S53: Modeling the input and output correlation relationship of the aviation technical standard process; according to the technical maturity coefficient C of the technology or product corresponding to the standard structural element in step S22 TRL , Manufacturing Maturity Factor C MRL , Technical performance evaluation coefficient C TPM and standard constraint coefficient C SDC , express the effect of the technical elements of the input layer on the standard structural elements, and construct a standard input association relationship model; according to the correlation coefficient r of the standard output association relationship determined in step S32, according to the weight coefficient b of the standard output element with high correlation determined in step S33, express the effect of the standard structural elements on the quality elements of the output layer, and obtain an aviation technical standard effect process model based on a directed topological graph.

[0029] Preferably, the standard structural elements, the relationships between the standard structural elements, and the standard associated elements of the aircraft product standard are determined in step S1, specifically:

[0030] The standard structural elements refer to the model nodes determined by the standard text content and attributes, including input basis nodes, background and reference nodes, technical requirements nodes, implementation methods and process nodes, and scope of application nodes.

[0031] The relationship between the standard structural elements is based on the reference, realization, condition, composition, and applicable action relationship to realize the action relationship between the source node and the target node.

[0032] The standard-related elements refer to some subsidiary attributes related to the final use scenarios of the standard, including technical content attributes, influence attributes and product implementation attributes.

[0033] The relationship between structural elements and associated elements is defined as non-strict correlation, and its relationship is realized through a rule-based expert system. This relationship also gives the traceability relationship between structural elements and associated elements in the evaluation process. Representation.

[0034] Preferably, the technology maturity coefficient C in step S22 is TRL , Manufacturing Maturity Factor C MRL , Technical performance evaluation coefficient C TPM and standard constraint coefficient CSDC , specifically:

[0035] The technology maturity coefficient C TRL The relevant standards for the development of new technologies characterize the completeness of the application of the technology and the adequacy of verification in the process of technology development to product transformation; the technology maturity coefficient is determined by the technology maturity level L of the product or technology. T It is concluded that:

[0036]

[0037] Among them, C TRL is the technology maturity coefficient; L T is the technology maturity level;

[0038] The manufacturing maturity factor C MRL Mainly for the standards related to mass production of products, characterize the degree of standardization of product production and mass production capacity of itinerary standards; the manufacturing maturity coefficient is:

[0039]

[0040] Among them, C TRL is the manufacturing maturity factor; L M For manufacturing maturity level;

[0041] The technical performance evaluation coefficient C TPM The degree of strictness of the specified value of the key parameter that characterizes the content of the standard to the target value is determined by the ratio of the threshold value in the specified value of the key parameter to the realization of the target value; the types of key parameters are divided into extreme value type and interval type, specifically:

[0042] For extreme value key parameters, the first technical performance evaluation coefficient is:

[0043]

[0044] Among them, C TPM1 is the first technical performance evaluation coefficient; T is the first technical performance evaluation parameter; S is the first technical performance evaluation parameter;

[0045] For interval-type key parameters, the second technical performance evaluation coefficient is:

[0046]

[0047] Among them, C TPM2 is the second technical performance evaluation coefficient; L T is the third technical performance evaluation parameter; L S is the fourth technical performance evaluation parameter;

[0048] The standard constraint coefficient C SDC Characterizes the degree to which the content of the standard ontology constrains the technology it regulates.

[0049] Preferably, the weight coefficient vector of the standard output element with high correlation, the observation value vector of the quality element and the observation value matrix of the standard output element in step S33 are specifically:

[0050] The weight coefficient vector b of the standard output elements with high correlation is:

[0051]

[0052] Among them, b i is the weight coefficient of the i-th standard output element with high correlation; k is the total number of standard output elements with high correlation; i is the number of the standard output element with high correlation;

[0053] The observed value vector Y of the quality factor is:

[0054]

[0055] Among them, y j is the jth observation value of the quality factor; n is the total number of quality factors; j is the quality factor number;

[0056] The observation matrix X of the standard output elements is:

[0057]

[0058] Among them, x ij is the jth observation value of the i-th standard element.

[0059] Preferably, the standard input node and the standard output node in step S43 are specifically:

[0060] The standard input node is a graph model constructed based on the technology or product attributes specified by the standard, and is divided into product technical requirements, product verification methods, data models, solution drawings, and data report nodes;

[0061] The standard output node is a graph model constructed based on the objective quality level achieved by functions and products after the implementation of the standard, and is divided into two types of nodes: development quality and usage quality.

[0062] Preferably, the node modeling of the aviation technical standard action process in step S4 can use the main node, sub-node and subsidiary node and the association relationship to model the elements and associated characteristics of the standard, and can clearly express the evaluation dimensions and characteristics of the aircraft product standards and technology, and the quality effect.

[0063] Preferably, the node modeling of the aviation technical standard action process in step S4 should be based on a directed topological graph to model the action process of the standard, so as to achieve the formalization and explicit representation of the aircraft product standard empowerment process.

[0064] Preferably, the standard input elements in step S2 and the standard output elements in step S3 use formal models to model and characterize the input of aircraft product standards and the output of the effects of standards, which can provide a model basis for quantitatively evaluating the effects of aircraft product standards and standard systems.

[0065] Preferably, the standard structural elements, the relationships between standard structural elements, the standard associated elements in step S1, the standard inputs and input associated elements in step S2, and the standard outputs and output associated relationship elements in step S3 are expressed in a structured manner, which can provide a basis for the embedded application of various computing software in the aircraft product development process of each standardized element.

[0066] Compared with the prior art, the present invention has the following beneficial effects:

[0067] (1) The present invention models and represents the process of aircraft product standardization based on a directed topological graph, which can realize the formalization and explicit representation of the aircraft product standardization empowerment process. Compared with the qualitative conclusions given by the existing evaluation methods, the present invention has traceability and plays a significant role in solving the problems of the current expert evaluation scoring method, such as the excessive influence of subjective factors on the evaluation results, the lack of traceability of the evaluation basis, and the lack of quantification of the evaluation process.

[0068] (2) The present invention uses main nodes, sub-nodes, subsidiary nodes and associated relationships to model the elements and associated characteristics of aircraft product standardization, which can clearly express the dimensions and characteristics of the performance evaluation of aircraft product standardization.

[0069] (3) The present invention adopts a formal model to model and characterize the input of aircraft product standardization and the output of standard effect, which can provide a model basis for quantitatively evaluating the effect of aircraft product standardization and standard system.

[0070] (4) The present invention, through the structured expression of the elements related to aircraft product standardization, can provide a basis for the embedded application of various computing software of each element in the product development process. With the application and promotion of standard digitalization and intelligent technology, the present invention will play a more significant application effect. BRIEF DESCRIPTION OF THE DRAWINGS

[0071] Figure 1 A control block diagram of the aviation technical standard representation modeling method based on a directed topological graph of the present invention;

[0072] Figure 2A schematic diagram of modeling the main node and sub-nodes of the present invention;

[0073] Figure 3 A schematic diagram of modeling the auxiliary nodes of the present invention;

[0074] Figure 4 Modeling schematic diagrams for input and output elements of the present invention;

[0075] Figure 5 A schematic diagram of modeling the standard ontology association relationship of the present invention;

[0076] Figure 6 A schematic diagram of the modeling of the standard internal action process relationship of the present invention;

[0077] Figure 7 A case structure diagram for modeling the standard input association relationship of the present invention;

[0078] Figure 8 This is a case structure diagram of the standard output association relationship modeling of the present invention. DETAILED DESCRIPTION

[0079] 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.

[0080] The present invention provides a technical standard representation modeling method based on a directed topological graph, specifically, an aviation technical standard representation modeling method based on a directed topological graph. Figure 1 As shown, determine the standard structural elements, the relationship between standard structural elements, and the standard associated elements of aircraft product standardization; determine the standard input elements and standard input associated relationships of the aviation technical standard action process; determine the standard output elements and standard output associated relationships of the aviation technical standard action process; model the nodes of the aviation technical standard action process; complete the modeling of the aviation technical standard action process; which includes:

[0081] Step S1: Determine the standard structural elements, the relationships between the standard structural elements, and the standard associated elements of the aircraft product standard.

[0082] The standard structural element types are determined according to Table 1.

[0083] Table 1 Classification of standard structural elements

[0084]

[0085]

[0086]

[0087] The relationships between the standard structural elements are divided into five types: reference, implementation, condition, composition, and use, as shown in Table 2.

[0088] Table 2 Standard structural element relationship table

[0089]

[0090] The type of the standard association element is determined according to 3.

[0091] Table 3 Standard related elements and their descriptions

[0092]

[0093]

[0094] The relationship between structural elements and associated elements is defined as non-strict correlation, and its relationship is realized through a rule-based expert system. This relationship also gives the traceability relationship between structural elements and associated elements in the evaluation process. Representation.

[0095] Step S2: Determine the standard input elements and standard input association relationships of the aviation technical standard action process.

[0096] Step S21: Determine the standard input elements of the aviation technical standard process; the standard input elements are determined based on the technical principles, data or material technical input carrier knowledge that form the standard, including product technical requirements, product verification methods, data models, program drawings and data report input elements of aircraft products;

[0097] Table 4 Standard input elements

[0098]

[0099]

[0100]

[0101] Step S22: Determine the standard input correlation relationship of the aviation technology standard process, and use the standard input elements in step S21 to determine the technology maturity coefficient C TRL , Manufacturing Maturity Factor C MRL , Technical performance evaluation coefficient C TPM and standard constraint coefficient C SDC , as shown in Table 5; further calculations yield the standard input association relationship C for aircraft products:

[0102] C=C TRL ·C MRL ·C TPM ·CSDC ;

[0103] Among them, C is the standard input association relationship of aircraft products.

[0104] Table 5 Standard input association table

[0105]

[0106]

[0107] Step S3: Determine the standard output elements and standard output association relationships of the aviation technical standard action process.

[0108] Step S31: Determine the standard output element of the aviation technical standard action process; the standard output element x is characterized by the quality characteristics of the aircraft function and the aircraft product.

[0109] Table 6 Standard output elements table

[0110]

[0111] Step S32: Determine the standard output correlation relationship of the aviation technical standard action process; the standard output correlation relationship refers to the degree of action of the standard body and the auxiliary characteristics supporting the output elements. The method for determining the standard output correlation relationship is to calculate the correlation coefficient r of a single standard correlation element and a single quality element one by one:

[0112]

[0113] Where r is the correlation coefficient of the standard output correlation relationship; χ i is the observed value of the standard output element; is the average value of the standard output elements; y i is the observed value of the quality output factor; is the average value of the quality output elements.

[0114] Step S33: Perform regression analysis on the standard output factors, take a single quality output factor as the dependent variable, and construct a regression analysis model as follows:

[0115] b=(X T X) -1 X T Y;

[0116] Among them, b is the weight coefficient vector of the standard output factors with high correlation; Y is the observation value vector of the quality factors; and X is the observation value matrix of the standard output factors.

[0117] Step S4: Node modeling of the aviation technical standards action process.

[0118] Step S41: When modeling the main nodes and sub-nodes of the aircraft product standard, the main node elements of the standard action process model are determined according to the ontology and structural elements of the aircraft product standard; the main node refers to the ontology model of the aircraft product standard, and one aircraft product standardization forms a main node; the sub-node is a graph model constructed based on the content and attributes of the aircraft product standard ontology, including input basis nodes, background and reference nodes, technical requirements nodes, implementation methods and process nodes, and scope of application nodes.

[0119] like Figure 2 The figure shows a schematic diagram of the main node and sub-node modeling of the present invention; the main node elements of the model are determined according to the standard ontology and structural elements, and the sub-node model is constructed based on the standard ontology content and attributes.

[0120] like Figure 2 As shown, the main nodes include main node 1, main node 2, main node 3 and main node 4, and it is shown that the main node 1 includes multiple sub-nodes, and these sub-nodes include technical requirements 1-technical requirements 16, implementation methods 4-6, standard field 1 and object 1, etc.

[0121] According to the performance requirements of aircraft cockpit warning equipment and the corresponding inspection methods, the main body and structural elements include multiple main nodes and sub-nodes, including 5 main nodes and 38 sub-nodes. The 5 main nodes are 1-General specifications for aircraft cockpit warning equipment, 2-General requirements for aircraft lighting color and signal color, 3-Basic technical requirements and test methods for aircraft cockpit lighting, 4-Aircraft interior lighting compatible with night vision imaging systems, 5-General specifications for aircraft interior and exterior lighting equipment. Sub-nodes 2-5 lead to other standards and are not expanded in this model.

[0122] Main node 1 includes 17 sub-nodes of technical requirements, including technical requirements 1-3.1.1 Alarm form, technical requirements 2-3.1.2 Real-time performance, technical requirements 3-3.1.3 Signal display, technical requirements 4-3.1.3.1 Brightness, technical requirements 5-3.1.3.2 Chroma, technical requirements 6-3.1.3.3 Contrast, technical requirements 7-3.1.3.4 Readability in sunlight, technical requirements 8-3.1.3.5 Flicker rate, technical requirements 9-3.1.3.6 Compatibility with Night Market Imaging System (NVIS) Capacitance, technical requirement 10-3.1.4 Insulation dielectric strength, technical requirement 11-3.1.5 Insulation resistance, technical requirement 12-3.1.3.1.1 Warning light brightness, technical requirement 13-3.1.3.1.2 Light guide plate brightness, technical requirement 14-3.1.3.1.3 Brightness of buttons and knobs with built-in light sources, technical requirement 15-3.1.3.2.1 Warning light chromaticity, technical requirement 16-3.1.3.2.2 Light guide plate chromaticity, technical requirement 17-3.1.3.2.3 Chromaticity of buttons and knobs with built-in light sources.

[0123] The main node 1 also includes 11 implementation method sub-nodes, including implementation method 1-4.5.6.1 alarm form, implementation method 2-4.5.6.2 real-time, implementation method 3-4.5.6.3 signal display, implementation method 4-4.5.6.3.1 brightness, implementation method 5-4.5.6.3.2 chromaticity, implementation method 6-4.5.6.3.3 contrast, implementation method 7-4.5.6.3.4 readability in sunlight, implementation method 8-4.5.6.3.5 flicker rate, implementation method 9-4.5.6.3.6 compatibility with night vision imaging system (NVIS), implementation method 10-4.5.6.5 insulation dielectric strength, implementation method 11-4.5.6.4 insulation resistance.

[0124] The main node 1 also includes 10 sub-nodes of application scope, object 1-cockpit warning equipment, standard field 1-design, standard field 2-test, standard level 1-requirements, standard level 2-methods, product level 1-equipment, aircraft type 1-general, technical field 1-avionics / mission system, standard level 1-national military standard, stage 1-general. Each sub-node is composed of specific standard content, as shown in Table 7 below, and the mapping relationship between sub-nodes and content is realized by computer.

[0125] Table 7 Node content mapping table

[0126]

[0127] Step S42: Modeling the subsidiary nodes of the aircraft product standard; determining the subsidiary nodes of the standard action process model according to the standard association elements of the aircraft product standard in step S1; the subsidiary nodes refer to the graph model constructed based on the efficiency attributes of the standard, and the subsidiary nodes can characterize the efficiency attributes of a main node or N main nodes and the child nodes in step S41; the subsidiary nodes include technical content attribute nodes, influence attribute nodes and product implementation attribute nodes;

[0128] like Figure 3 The figure shows a schematic diagram of the subsidiary node modeling of the present invention; according to the correlation and tracing relationship between the main node and sub-node of the aircraft cockpit warning equipment and various elements of the subsidiary node, the subsidiary node model includes 4 technical content attribute class nodes and 2 product implementation attribute class nodes, including technological advancement, content applicability, system coordination, ease of use of standardization, standard parts universalization coefficient, and interface universalization coefficient.

[0129] Step S43: Modeling the standard input elements and standard output elements of the aviation technical standard process; according to the standard input elements in step S2 and the standard output elements in step S3, determine the standard input nodes and standard output nodes in the process model, specifically: the standard input node is a graph model built based on the technology or product attributes specified by the standard, and is divided into product technical requirements, product verification methods, data models, scheme drawings, and data report nodes. The standard output node is a graph model built based on the objective quality level of functions and products after the implementation of the standard, and is divided into two types of nodes: development quality and use quality.

[0130] The node modeling of the aviation technical standard action process can use the main node, sub-node, subsidiary node and associated relationship to model the elements and associated characteristics of the standard, and can clearly express the evaluation dimensions and characteristics of the effect of aircraft product standards and technology and quality characteristics. The node modeling of the aviation technical standard action process should be based on a directed topological graph to model the action process of the standard, and can realize the formalization and explicit representation of the aircraft product standard empowerment process.

[0131] like Figure 4 The schematic diagram of the input and output element modeling of the present invention is shown; the input model is constructed based on the technology specified by the standard or the product's own attributes, and according to the technical requirements specified in the technical protocol of a certain type of aircraft sound and light warning control box and the state identification function performance test outline, the input elements related to the main node and sub-node elements of the product include function 1-sound warning function, function 2-light warning function, performance 1-cockpit lighting, and identification test 1-sound warning function, identification test 2-light warning function, identification test 3-cockpit lighting. Each input element is composed of the product technical requirements of a specific type of aircraft sound and light warning control box, as shown in Table 8 below, and the mapping relationship between the input elements and the product technical requirements can be realized by a computer. The output elements currently available for the product include micro-quality 1-test pass rate, micro-quality 2-number of quality problems per year, and micro-quality 3-average failure interval time.

[0132] Table 8 Mapping table of input factors and product technical requirements

[0133]

[0134]

[0135] Step S5: Relationship modeling of the aviation technical standards action process, completing the aviation technical standards action process modeling.

[0136] Step S51: ontology association relationship modeling of aircraft product standards; based on the main node of the standard action process model in step S41, the action relationship of each sub-node is determined according to the relationship between the standard structural elements in step S1 to obtain the association relationship model of the standard ontology.

[0137] In this case, the sub-node Technical Requirement 3-3.1.3 Signal Display is composed of Technical Requirement 4-3.1.3.1 Brightness, Technical Requirement 5-3.1.3.2 Chroma, Technical Requirement 6-3.1.3.3 Contrast, Technical Requirement 7-3.1.3.4 Sunlight Readability, Technical Requirement 8-3.1.3.5 Flicker Rate, and Technical Requirement 9-3.1.3.6 Compatibility with Night Market Imaging System (NVIS). The sub-node Technical Requirement 4-3.1.3.1 Brightness is composed of Technical Requirement 12-3.1.3.1.1 Warning Light Brightness, Technical Requirement 13-3.1.3.1.2 Light Guide Brightness, and Technical Requirement 14-3.1.3.1.3 Brightness of Buttons and Knobs with Internal Light Sources. Technical requirement 5-3.1.3.2 Chromaticity is composed of technical requirement 15-3.1.3.2.1 Warning light chromaticity, technical requirement 16-3.1.3.2.2 Light guide plate chromaticity, and technical requirement 17-3.1.3.2.3 Button and knob chromaticity with internal light source; sub-node implementation method 3-4.5.6.3 Signal display is composed of implementation method 4-4.5.6.3.1 Brightness, implementation method 5-4.5.6.3.2 Chromaticity, implementation method 6-4.5.6.3.3 Contrast, implementation method 7-4.5.6.3.4 Sunlight readability, implementation method 8-4.5.6.3.5 Flicker rate, and implementation method 9-4.5.6.3.6 Compatibility with Night Vision Imaging System (NVIS).

[0138] In this case, sub-node technical requirement 1-3.1.1 Alarm form is implemented by implementation method 1-4.5.6.1 Alarm form, sub-node technical requirement 2-3.1.2 Real-time is implemented by implementation method 2-4.5.6.2 Real-time, sub-node technical requirement 3-3.1.3 Signal display is implemented by implementation method 3-4.5.6.3 Signal display, sub-node technical requirement 4-3.1.3.1 Brightness, technical requirement 12-3.1.3.1.1 Alarm Light brightness, Technical Requirements 13-3.1.3.1.2 Light guide plate brightness, Technical Requirements 14-3.1.3.1.3 The brightness of buttons and knobs with built-in light sources is implemented by implementation method 4-4.5.6.3.1 Brightness, sub-node Technical Requirements 5-3.1.3.2 Chroma, Technical Requirements 15-3.1.3.2.1 Warning light chroma, Technical Requirements 16-3.1.3.2.2 Light guide plate chroma, Technical Requirements 17-3.1.3.2.3 Built-in light The chromaticity of the buttons and knobs of the source is implemented by implementation method 5-4.5.6.3.2 Chromaticity, sub-node technical requirement 6-3.1.3.3 Contrast is implemented by implementation method 6-4.5.6.3.3 Contrast, sub-node technical requirement 7-3.1.3.4 Sunlight readability is implemented by implementation method 7-4.5.6.3.4 Sunlight readability, sub-node technical requirement 8-3.1.3.5 Flicker rate is implemented by implementation method 8-4.5.6.3.5 Flicker rate, sub-node technical requirement 9-3.1.3.6 Compatibility with Night Vision Imaging System (NVIS) is implemented by implementation method 9-4.5.6.3.6 Compatibility with Night Vision Imaging System (NVIS), sub-node technical requirement 10-3.1.4 Insulation dielectric strength is implemented by implementation method 10-4.5.6.5 Insulation dielectric strength, sub-node technical requirement 11-3.1.5 Insulation resistance is implemented by implementation method 11-4.5.6.4 Insulation resistance.

[0139] In this case, sub-node technical requirement 15-3.1.3.2.1 warning light chromaticity references main node 2, sub-node technical requirement 16-3.1.3.2.2 light guide plate chromaticity references main node 2 and main node 3, sub-node technical requirement 9-3.1.3.6 compatibility with night vision imaging system (NVIS) references main node 4, sub-node implementation method 4-4.5.6.3.1 brightness, implementation method 5-4.5.6.3.2 chromaticity, implementation method 6-4.5.6.3.3 contrast references main node 3, sub-node implementation method 7-4.5.6.3.4 readability in sunlight, implementation method 9-4.5.6.3.6 compatibility with night vision imaging system (NVIS) references main node 5.

[0140] In this case, the subnodes Object 1-Cockpit Warning Equipment, Standard Field 1-Design, Standard Field 2-Test, Standard Level 1-Requirement, Standard Level 2-Method, Product Level 1-Equipment, Aircraft Type 1-General, Technical Field 1-Avionics / Mission System, Standard Level 1-National Military Standard, and Phase 1-General are applicable to the main node 1. Figure 5 Shown is a schematic diagram of the standard ontology association relationship modeling of the present invention; a model constructed according to the above standard ontology association relationship.

[0141] Step S52: Modeling the internal action process relationship of aircraft product standards; on the basis of the aircraft product standard ontology association relationship in step S51, according to the specific technical details of the standard structure elements in step S1, and the standards adopted in the technology and product realization process, construct the corresponding relationship between each standard structure element and the standard association element, express the traceability relationship of the standard association element to the standard structure element, and obtain the standard internal action process relationship model.

[0142] In this case standard, the alarm form, output signal response time and delay requirements, night vision compatibility requirements for lighting display components, auditory alarm requirements and other related requirements reflect the technological advancement of the standard, and construct the traceability relationship between the sub-nodes Technical Requirements 1-3.1.1 Alarm Form, Technical Requirements 2-3.1.2 Real-time, and Technical Requirements 9-3.1.3.6 Compatibility with Night Market Imaging System (NVIS) and Technological Advancement 1. Corresponding inspection methods are given for the functional performance index requirements, reflecting the ease of implementation of the standard, and construct the traceability relationship between 11 sub-nodes such as sub-node implementation method 4-4.5.6.3.1 Brightness, implementation method 5-4.5.6.3.2 Chroma, and implementation method 6-4.5.6.3.3 Contrast and the applicability of implementation 1. Figure 6 Shown is a schematic diagram of the standard internal action process relationship modeling of the present invention, a model constructed according to the above standard internal action process relationship.

[0143] Step S53: Modeling the input and output relationship of the aviation technical standard process; according to the technical maturity coefficient C of the technology or product corresponding to the standard structural element in step S22 TRL , Manufacturing Maturity Factor C MRL , Technical performance evaluation coefficient C TPM and standard constraint coefficient C SDC , express the effect of the technical elements of the input layer on the standard structural elements, and construct a standard input association relationship model; according to the correlation coefficient r of the standard output association relationship determined in step S32, according to the weight coefficient b of the standard output element with high correlation determined in step S33, express the effect of the standard structural elements on the quality elements of the output layer, and obtain an aviation technical standard effect process model based on a directed topological graph.

[0144] In this case, function 1-sound alarm function and function 2-light alarm function act on the sub-nodes Technical Requirements 1-3.1.1 Alarm Form and Technical Requirements 2-3.1.2 Real-time. For Technical Requirement 1, this case uses the newly developed model identification product as the object, and the functional indicators do not involve technical performance evaluation, so the action coefficient adopts two indicators: technology maturity and standard energy conversion. According to the model identification stage of the case object product, the relevant technology has completed the use environment verification with the actual product as the carrier, the technology maturity is level 8, the technology maturity coefficient CTRL is determined to be 0.9, and the standard energy conversion coefficient is determined to be 0.73. Similarly, for Technical Requirement 2, the action coefficient adopts the two indicators of technology maturity and standard energy conversion, and adds a technical performance evaluation coefficient of 0.75 to table the effect of real-time performance.

[0145] Similarly, in this case, Performance 1-Cockpit Lighting acts on sub-nodes Technical Requirements 12-3.1.3.1.1 Warning Light Brightness, Technical Requirements 13-3.1.3.1.2 Light Guide Plate Brightness, Technical Requirements 15-3.1.3.2.1 Warning Light Chroma, Technical Requirements 16-3.1.3.2.2 Light Guide Plate Chroma, Technical Requirements 6-3.1.3.3 Contrast, and the action coefficients use three coefficients: technology maturity 0.9, technical performance evaluation 0.75, and standard energy conversion 0.75. Identification test 1-sound warning function, identification test 2-light warning function acts on the warning form of implementation method 1-4.5.6.1, and the action coefficient adopts two coefficients, such as technology maturity 0.9 and standard energy conversion 0.6. Identification test 3-cockpit lighting acts on implementation method 4-4.5.6.3.1 brightness, implementation method 5-4.5.6.3.2 chromaticity, implementation method 6-4.5.6.3.3 contrast, and the action coefficient adopts two coefficients, such as technology maturity 0.9 and standard energy conversion 0.68. Figure 7 Shown is a structural diagram of a standard input association relationship modeling case of the present invention; a model constructed according to the above standard input association relationship.

[0146] In this case, the weight coefficients of standard-related factors and quality factors are determined according to S42. It is assumed that there is a correlation between technological advancement 1 and micro-quality 1-test pass rate, micro-quality 2-number of quality problems per year, and micro-quality 3-average failure interval, with correlation coefficients of 0.8, 0.85, and 0.9, and there is a correlation between ease of use 1 and micro-quality 1-test pass rate, micro-quality 2-number of quality problems per year, and micro-quality 3-average failure interval, with correlation coefficients of 0.7, 0.8, and 0.9. Figure 8 Shown is a structural diagram of a standard output association relationship modeling case of the present invention; a model constructed according to the above standard input association relationship.

[0147] The beneficial effects of the embodiments of the present invention are as follows: the embodiments of the present invention model and characterize the action process of aircraft product standardization based on a directed topological graph, thereby realizing the formalization and explicit characterization of the standard empowerment process; the elements and associated characteristics of aircraft product standardization are modeled using main nodes, sub-nodes, subsidiary nodes and association relationships, which can clearly express the dimensions and characteristics of the performance evaluation of the standard; the input of aircraft product standardization and the output of the standard action are modeled and characterized using a formal model, which can provide a model basis for quantitatively evaluating the effectiveness of standards and standard systems; the structured expression of the elements related to aircraft product standardization can provide a basis for the embedded application of various computing software for each element during the product development process.

[0148] 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. A modeling method for representing aviation technical standards based on a directed topological graph, characterized by: It includes: S1: Determine the standard structural elements, the relationship between standard structural elements, and standard related elements of aircraft product standards; S2: Determine the standard input elements and standard input associations in the aviation technical standard process; S21: Determine the standard input elements of the aviation technical standard process; the standard input elements are determined based on the technical principles, data or material technical input carrier knowledge that form the standard, including product technical requirements, product verification methods, data models, program drawings and data report input elements of aircraft products; S22: Determine the standard input correlation relationship of the aviation technology standard process, and use the standard input elements in step S21 to determine the technology maturity coefficient C TRL , Manufacturing Maturity Factor C MRL , Technical performance evaluation coefficient C TPM and standard constraint coefficient C SDC ; The standard input association relationship C of the aircraft product is obtained as follows: C=C TRL ·C MRL ·C TPM ·C SDC Among them, C is the standard input association relationship of aircraft products; S3: Determine the standard output elements and standard output correlation relationships of the aviation technical standards process; S31: Determine the standard output elements of the aviation technical standard action process; the standard output element x is characterized by the quality characteristics of the aircraft function and the aircraft product; S32: Determine the standard output correlation relationship of the aviation technical standard action process; the standard output correlation relationship refers to the degree of action of the standard body and its subsidiary characteristics supporting the output elements. The method for determining the standard output correlation relationship is to calculate the correlation coefficient r of a single standard correlation element and a single quality element one by one: Among them, r is the correlation coefficient of the standard output correlation relationship; x i is the observed value of the standard output element; is the average value of the standard output element; i is the observed value of the quality output factor; is the average value of the quality output factors; S33: Conduct regression analysis of standard output factors, take a single quality output factor as the dependent variable, and construct a regression analysis model: b=(X T X) -1 X T Y Among them, b is the weight coefficient vector of the standard output elements with high correlation; Y is the observation value vector of the quality elements; X is the observation value matrix of the standard output elements; S4: Node modeling of the aviation technical standards action process; S41: When modeling the main node and sub-node of the aircraft product standard, the main node element of the standard action process model is determined according to the aircraft product standard's ontology and structural elements; the main node refers to the aircraft product standard's ontology model, and one aircraft product standard forms one main node; the sub-node is a graph model constructed based on the aircraft product standard's ontology content and attributes, including an input basis node, a background and reference node, a technical requirement node, an implementation method and process node, and an applicable scope node; S42: Modeling the subsidiary nodes of the aircraft product standard; determining the subsidiary nodes of the standard action process model according to the standard associated elements of the aircraft product standard in step S1; the subsidiary nodes refer to the graph model constructed based on the efficiency attributes of the standard, and the subsidiary nodes can characterize the efficiency attributes of a main node or N main nodes and the sub-nodes in step S41; the subsidiary nodes include technical content attribute nodes, influence attribute nodes and product implementation attribute nodes; S43: Modeling the standard input elements and standard output elements of the aviation technical standard action process; determining the standard input nodes and standard output nodes in the action process model according to the standard input elements in step S2 and the standard output elements in step S3; S5: Relationship modeling of the aviation technical standards process, complete the modeling of the aviation technical standards process; S51: Modeling the association relationship of the ontology of aircraft product standards; based on the main node of the standard action process model in step S41, the action relationship of each sub-node is determined according to the relationship between the standard structural elements in step S1, and the association relationship model of the standard ontology is obtained; S52: Modeling the internal action process relationship of aircraft product standards; on the basis of the aircraft product standard ontology association relationship in step S51, according to the specific technical details of the standard structural elements in step S1, and the standards adopted in the technology and product realization process, the corresponding relationship between each standard structural element and the standard associated element is constructed, and the traceability action relationship of the standard associated element to the standard structural element is expressed, and the internal action process relationship model of the standard is obtained; S53: Modeling the relationship between aircraft product standardization input and output; according to the technology maturity coefficient C of the technology or product corresponding to the standard structural element in step S22 TRL , Manufacturing Maturity Factor C MRL , Technical performance evaluation coefficient C TPM and standard constraint coefficient C SDC , express the effect of the technical elements of the input layer on the standard structural elements, and construct a standard input association relationship model; according to the correlation coefficient r of the standard output association relationship determined in step S32, according to the weight coefficient b of the standard output element with high correlation determined in step S33, express the effect of the standard structural elements on the quality elements of the output layer, and obtain an aviation technical standard effect process model based on a directed topological graph.

2. The aviation technical standard representation modeling method based on directed topological graph according to claim 1 is characterized in that: In step S1, the standard structural elements, the relationships between the standard structural elements, and the standard associated elements of the aircraft product standard are determined, specifically: The standard structural elements refer to the model nodes determined by the content and attributes of the standard text, including input basis nodes, background and reference nodes, technical requirements nodes, implementation methods and process nodes, and scope of application nodes; The relationship between the standard structural elements is based on the reference, realization, condition, composition, and applicable action relationship to realize the action relationship between the source node and the target node; The standard-related elements refer to some subsidiary attributes related to the final use scenarios of the standard, including technical content attributes, influence attributes and product implementation attributes.

3. The aviation technical standard representation modeling method based on directed topological graph according to claim 1 is characterized in that: The technology maturity coefficient C in step S22 TRL , Manufacturing Maturity Factor C MRL , Technical performance evaluation coefficient C TPM and standard constraint coefficient C SDC , specifically: The technology maturity coefficient C TRL The relevant standards for the development of new technologies characterize the completeness of the application of the technology and the adequacy of verification in the process of technology development to product transformation; the technology maturity coefficient is determined by the technology maturity level L of the product or technology. T It is concluded that: Among them, C TRL is the technology maturity coefficient; L T is the technology maturity level; The manufacturing maturity factor C MRL Mainly for the standards related to mass production of products, characterize the degree of standardization of product production and mass production capacity of itinerary standards; the manufacturing maturity coefficient is: Among them, C TRL is the manufacturing maturity factor; L M is the manufacturing maturity level; The technical performance evaluation coefficient C TPM The degree of strictness of the specified value of the key parameter that characterizes the content of the standard to the target value is determined by the ratio of the threshold value in the specified value of the key parameter to the realization of the target value; the types of key parameters are divided into extreme value type and interval type, specifically: For extreme value key parameters, the first technical performance evaluation coefficient is: Among them, C TPM1 is the first technical performance evaluation coefficient; T is the first technical performance evaluation parameter; S is the first technical performance evaluation parameter; For interval-type key parameters, the second technical performance evaluation coefficient is: Among them, C TPM2 is the second technical performance evaluation coefficient; L T is the third technical performance evaluation parameter; L S is the fourth technical performance evaluation parameter; The standard constraint coefficient C SDC Characterizes the degree to which the content of the standard ontology constrains the technology it regulates.

4. The aviation technical standard representation modeling method based on directed topological graph according to claim 1 is characterized in that: The weight coefficient vector of the standard output element with high correlation, the observation value vector of the quality element and the observation value matrix of the standard output element in step S33 are specifically: The weight coefficient vector b of the standard output elements with high correlation is: Among them, b i is the weight coefficient of the i-th standard output element with high correlation; k is the total number of standard output elements with high correlation; i is the number of the standard output element with high correlation; The observed value vector y of the quality factor is: Among them, y j is the jth observation value of the quality factor; n is the total number of quality factors; j is the quality factor number; The observation matrix X of the standard output elements is: Among them, x ij is the jth observation value of the i-th standard feature.

5. The aviation technical standard representation modeling method based on directed topological graph according to claim 1 is characterized in that: The standard input node and the standard output node in step S43 are specifically: The standard input node is a graph model constructed based on the technology or product attributes specified by the standard, and is divided into product technical requirements, product verification methods, data models, solution drawings and data report nodes; The standard output node is a graph model constructed based on the objective quality level achieved by functions and products after the implementation of the standard, and is divided into two types of nodes: development quality and usage quality.

6. The aviation technical standard representation modeling method based on directed topological graph according to claim 1 is characterized in that: The node modeling of the aviation technical standard action process in step S4 can use the main node, child node, subsidiary node and associated relationship to model the elements and associated characteristics of the standard, and can express the evaluation dimensions and characteristics of the aircraft product standards and technology, and the quality effect.

7. The aviation technical standard representation modeling method based on directed topological graph according to claim 1 is characterized in that: The node modeling of the aviation technical standard action process in step S4 should be based on a directed topological graph to model the standard action process and realize the formalization and explicit representation of the aircraft product standard empowerment process.

8. The aviation technical standard representation modeling method based on directed topological graph according to claim 1 is characterized in that: The standard input elements in step S2 and the standard output elements in step S3 use formal models to model and characterize the input of aircraft product standards and the output of the effects of standards, providing a model basis for quantitatively evaluating the effects of aircraft product standards and standard systems.

9. The aviation technical standard representation modeling method based on directed topological graph according to claim 1 is characterized in that: The standard structural elements, the relationships between standard structural elements and the standard associated elements in step S1, the standard inputs and input associated elements in step S2, and the standard outputs and output associated relationship elements in step S3 are expressed in a structured manner, providing a basis for the embedded application of various computing software in the aircraft product development process for each standardized element.

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