CN104021248B - A kind of airborne machinery product FMECA analysis methods - Google Patents
A kind of airborne machinery product FMECA analysis methods Download PDFInfo
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- CN104021248B CN104021248B CN201410246845.9A CN201410246845A CN104021248B CN 104021248 B CN104021248 B CN 104021248B CN 201410246845 A CN201410246845 A CN 201410246845A CN 104021248 B CN104021248 B CN 104021248B
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Abstract
The present invention relates to a kind of airborne machinery product FMECA analysis methods, the detailed process is：Step a, sets up Typical Components failure mode data storehouse；Step b, sets up FMECA databases；Step c, carries out the preparation before FMECA analyses；Step d, completes the design and FMECA information inputs of single parts；Step e, FMECA information Store and next parts are designed and FMECA information input, storage, until whole product design complete；Step f, FMECA analyses are carried out to product；Step g, FMECA analysis report are exported.The present invention can realize FMECA information, the hierarchical relationship clearly between reactor product parts of the combining closely of product design and product F MECA analyses, the management of system each parts.
Description
Technical field
The present invention relates to field of flight vehicle design, more particularly to a kind of airborne machinery product FMECA analysis methods.
Background technology
Failure Mode Effective Analysis are a kind of analysis method for determining potential failure mode and its reason, fault mode
And impact analysis (FMEA) and HAZAN (CA) are collectively referred to as FMECA.It is to sum up to come in engineering practice, with failure mould
Based on formula, the analytical technology with fault impact or consequence as target.It passes through to analyze the different faults of each part one by one
Influence to system work, weak link and key project during identification is designed comprehensively, and to evaluate and improving system design
Reliability provides essential information.At present, in many important engineering fields, FMEA receives the height weight of administration of research activities personnel
Depending on, and it is expressly stated the technology that must be grasped for design studies personnel.It is that designer and contractor must be complete to implement FMEA
Into task.FMECA data is also defined as indispensable design document, be the data that must pay attention in criterion design review it
One.
Emerge many softwares that FMEA analyses are carried out to product both at home and abroad at present, but due to airborne machinery product
Complexity, particularity, still carry out the special method of FMECA analyses for airborne engineering goods at present.To aviation machine
Carrying machinery product and carrying out the problem that FMECA presently, there are has：(1) FMECA is inadequate with the conjugation of product design；(2) zero
It is not comprehensive enough that part failure mode considers；(3) transitive relation between parts, finished product and system between fault mode is difficult to manage
Clearly.
In view of drawbacks described above, creator of the present invention passes through prolonged research and practice obtains this creation finally.
The content of the invention
It is an object of the invention to provide a kind of airborne machinery product FMECA analysis methods, it is used to overcome above-mentioned
Technological deficiency.
To achieve the above object, the present invention provides a kind of airborne machinery product FMECA analysis methods,
Comprise the following steps：
Step a, sets up Typical Components failure mode data storehouse；
Step b, sets up FMECA databases；
Step c, carries out the preparation before FMECA analyses；
Step d, completes the design and FMECA information inputs of single parts；
Step e, FMECA information Store and next parts are designed and FMECA information input, storage, directly
Completed to whole product design；
Step f, FMECA analyses are carried out to product；
Step g, FMECA analysis report are exported；
In above-mentioned steps d, the design of single parts is with the detailed process of FMECA information inputs：
Step d1, carries out the configuration design of product in CATIA；
Step d2, carries out FMECA information inputs, and Typical Components failure mode data storehouse is retrieved first, judges whether
Retrieved successfully in database, if do not retrieved successfully, perform step d3, if retrieved successfully, perform step d4；
Step d3, input fault pattern, and failure criterion information, and store to Typical Components failure mode data storehouse
In, for using later；
Step d4, reads related data；
Step d5, is input into other FMEA information；
Step d6, is input into the CA information of parts；
Step d7, fills in the relation of the parts and other parts, for setting up reliability block diagram.
Further, in above-mentioned steps a, the Typical Components failure mode data storehouse is used to store Typical Components
Failure mode, failure cause and failure criterion information.
Further, in above-mentioned steps b, the FMECA databases are used for the FMECA information of design Storage process input；
It includes herein below：Indenture level definition, severity definition, the definition of fault mode probability levels, the FMECA of each parts
Information include fault mode, failure cause, fault impact, severity, fault detection method, failure criterion, using indemnifying measure,
Design improved method, fault detection method, probability of malfunction grade and harmfulness information.
Further,
In above-mentioned steps d6, the detailed process for being input into the CA information of parts is：
HAZAN method, difinite quality and quantitative two kinds of analysis methods are selected first, if selection quantitative analysis, holds
Row step d61, if carrying out qualitative analysis, performs step d69；
Step d61, selects severity classification and task phase；
Then perform step d62, the fault mode to the parts counts, have n, make i=1, i.e., from this zero
First fault mode of part proceeds by input；
Step d63, is input into the fault mode frequency ratio of i-th fault mode of the parts；
Step d64, is input into the failure mode effect probability of i-th fault mode of the parts；
Step d65, is input into fault rate and time of the parts in task phase；
Step d66, calculates the fault mode density of infection of the fault mode, judges that whether n, less than i, if being less than i, is performed
Step d67, if being not less than i, performs step d68；
Step d67, is circulated the information for being input into next fault mode；
Step d68, calculates density of infection of the parts in given severity classification and task phase；
Step d69, input fault model probabilities grade.
Further, in above-mentioned steps f, it is to the detailed process that finished product carries out FMECA analyses：
Step f1, carries out system definition, including functional task analysis and analysis of Influential Factors；
Perform step f2, failure mode analysis (FMA)；
Perform step f3, failure reason analysis；
Step f4 is performed, failure effect analysis (FEA), including the influence of local influence, a level high and final influence is carried out；
Step f5 is performed, severity analysis is carried out；
Perform step f6, fault detection method analysis；
Step f7 is performed, failure symptom analysis is carried out；
Step f8 is performed, corrective measure is designed and is analyzed using indemnifying measure；
Step f9 is performed, HAZAN is carried out.
Further, in above-mentioned steps g, the detailed process of FMECA analysis reports output is：
The indenture level of output report is wanted in step g1, selection；
Step g2, sets relevant parameter；
Step g3, the analysis result output FMECA analysis reports according to a upper module.
Compared with prior art the beneficial effects of the present invention are：The present invention is realized in product design and reliability point
That analyses combines closely.The huge FMECA information dispersions of airborne machinery product are completed to the design process of each parts,
Avoid the confusion of information, can take into full account the failure mode of each parts using database, the management of system each zero
The FMECA information of part.The reliability information of correlation can be just input into during parts design is carried out using CATIA,
And the FMECA information of parts is shown in the characteristics tree of CATIA, is easily modified, checked, and characteristics tree can be very clear
Hierarchical relationship between clear reactor product parts, is well adapted for the analysis needs of FMECA, while being easy to implement each about
The inspection of given layer time parts.
Realize the FMECA letters of the combining closely of product design and product F MECA analysis, the management of system each parts
Hierarchical relationship between breath, clearly reactor product parts.
Brief description of the drawings
Fig. 1 is the flow chart of airborne machinery product FMECA analysis methods of the present invention；
Fig. 2 is the flow chart of the design with FMECA information inputs of single parts of the invention；
Fig. 3 is the flow chart of the CA information of present invention input parts；
Fig. 4 is the flow chart of FMECA analyses of the present invention；
Fig. 5 is the flow chart of report output of the present invention.
Specific embodiment
Below in conjunction with accompanying drawing, the technical characteristic above-mentioned and other to the present invention and advantage are described in more detail.
Airborne machinery product FMECA analysis methods of the present invention include product design part, database and FMECA point
Analysis part, wherein, product design part carries out product design, carries out the related letter of the input preparation before FMECA analyses, FMECA
Breath input；Database is used for FMECA information retrievals and storage FMECA information；FMECA analysis parts, for according to database
In information the arrangement of FMECA relevant informations and analysis are carried out to product.
Refer to shown in Fig. 1, it is the flow chart of airborne machinery product FMECA analysis methods of the present invention, including
Following steps：
Step a, sets up Typical Components failure mode data storehouse；
The database is used to store the information such as failure mode, failure cause, the failure criterion of Typical Components；Designing
Journey, retrieves the failure mode of parts from the database, can well solve what failure mode considered by the database
Infull problem.
Step b, sets up FMECA databases；
The database is used for the FMECA information of design Storage process input.The database includes herein below：Indenture level
Definition, severity definition, the definition of fault mode probability levels, the FMECA information of each parts include that fault mode, failure are former
Cause, fault impact, severity, fault detection method, failure criterion, use indemnifying measure, design improved method, fault detect side
Method, probability of malfunction grade and harmfulness information.
Step c, carries out the preparation before FMECA analyses；
The step is used for Analysis on Selecting method, determines table format, defines indenture level, failure definition model probabilities etc.
Level, definition severity, clear failure sign determine principle and collect information material etc..
Step d, completes the design and FMECA information inputs of single parts；
CATIA is designed to single parts, then carries out FMECA inputs, and the FMECA information for filling in correlation includes event
Barrier pattern, failure cause, fault impact, severity, fault detection method, failure criterion, use indemnifying measure, design improvement side
Method, fault detection method and harmfulness information.
The failure mode of the parts is retrieved in Typical Components failure mode data storehouse first, if there is then direct
Read, in the absence of then need add the parts failure mode, be then input into the parts other FMECA information and this zero
Relation between part and other parts.
Step e, FMECA information Store and next parts are designed and FMECA information input, storage, directly
Completed to whole product design；
The step is used for the FMECA information of the parts of design Storage process input, and the information Store of the step is in FMECA
In database.
The connection in the FMECA information and dates storehouse in characteristics tree is realized by program, the synchronization of information is realized；Subsequently into
The design of next parts and the input of FMECA information, storage, until whole product design is completed.
Step f, FMECA analyses are carried out to finished product；
The step carries out FMECA analyses to finished product, according to the information of each indenture level parts in FMECA databases,
Implement FMECA analyses, completion system definition carries out failure mode analysis (FMA), failure reason analysis, failure effect analysis (FEA), severity
Analysis, fault detection method analysis, failure symptom analysis, design are improved and use indemnifying measure analysis and HAZAN.
Step g, FMECA analysis report are exported；
The step is used for report output, and the indenture level of output report, and other parameters are wanted in setting, according to above-mentioned steps
The analysis result output FMECA reports of f.
Refer to shown in Fig. 2, it is the design and the flow chart of FMECA information inputs of single parts of the invention, that is, go up
State in step d, the design of single parts is with the detailed process of FMECA information inputs：
Step d1, carries out the configuration design of product in CATIA；
Step d2, carries out FMECA information inputs, and Typical Components failure mode data storehouse is retrieved first, judges whether
Retrieved successfully in database, if do not retrieved successfully, perform step d3, if retrieved successfully, perform step d4；
Step d3, input fault pattern, and failure criterion information, and store to Typical Components failure mode data storehouse
In, for using later；
Step d4, reads related data；
Then step d5 is performed, other FMEA information are input into；
Step d6 is performed, the CA information of parts part is input into；
Then step d7 is performed, the relation of the parts and other parts is filled in, for setting up reliability block diagram etc..
Refer to shown in Fig. 3, it is the flow chart of the CA information of present invention input parts, the detailed process is：
HAZAN method, difinite quality and quantitative two kinds of analysis methods are selected first,
If selection quantitative analysis, performs step d61, if carrying out qualitative analysis, step d69 is performed；
Step d61, selects severity classification and task phase；
Then perform step d62, the fault mode to the parts counts, have n, make i=1, i.e., from this zero
First fault mode of part proceeds by input；
Step d63, is input into the fault mode frequency ratio of i-th fault mode of the parts；
Step d64, is input into the failure mode effect probability of i-th fault mode of the parts；
Step d65, is input into fault rate and time of the parts in task phase；
Step d66, calculates the fault mode density of infection of the fault mode, judges that whether n, less than i, if being less than i, is performed
Step d67, if being not less than i, performs step d68；
Step d67, is circulated the information for being input into next fault mode；
Step d68, calculates density of infection of the parts in given severity classification and task phase；
Step d69, input fault model probabilities grade.
Refer to shown in Fig. 4, it is the flow chart of FMECA analyses of the present invention, the detailed process is：
Step f1, carries out system definition, including functional task analysis and analysis of Influential Factors；
Perform step f2, failure mode analysis (FMA)；
Perform step f3, failure reason analysis；
Step f4 is performed, failure effect analysis (FEA), including the influence of local influence, a level high and final influence is carried out；
Step f5 is performed, severity analysis is carried out；
Perform step f6, fault detection method analysis；
Step f7 is performed, failure symptom analysis is carried out；
Step f8 is performed, corrective measure is designed and is analyzed using indemnifying measure；
Step f9 is performed, HAZAN is carried out.
Refer to shown in Fig. 5, it is the flow chart of report output of the present invention, the detailed process is：
The indenture level of output report is wanted in step g1, selection；
Step g2 is performed, relevant parameter, such as form etc. are set；
Step g3 is performed, FMECA analysis reports are exported according to last point of analysis result.
The present invention realizes combining closely in product design and fail-safe analysis.Airborne machinery product is huge
FMECA information dispersions are completed to the design process of each parts, it is to avoid the confusion of information, using database can be abundant
Consider the failure mode of each parts, the FMECA information for managing each parts of system.Zero is being carried out using CATIA
Part can just be input into the reliability information of correlation during designing, and show parts in the characteristics tree of CATIA
FMECA information, is easily modified, checks, and characteristics tree can with the hierarchical relationship between gem-pure reactor product parts,
The analysis needs of FMECA are well adapted for, while being easy to implement the inspection of each indenture level parts.
Presently preferred embodiments of the present invention is the foregoing is only, is merely illustrative for invention, and it is nonrestrictive.
Those skilled in the art understanding, can carry out many changes in the spirit and scope that invention claim is limited to it, change,
It is even equivalent, but fall within protection scope of the present invention.
Claims (6)
1. a kind of airborne machinery product FMECA analysis methods, it is characterised in that comprise the following steps：
Step a, sets up Typical Components failure mode data storehouse；
Step b, sets up FMECA databases；
Step c, carries out the preparation before FMECA analyses；
Step d, completes the design and FMECA information inputs of single parts；
Step e, FMECA information Store and next parts are designed and FMECA information input, storage, until whole
Individual product design is completed；
Step f, FMECA analyses are carried out to product；
Step g, FMECA analysis report are exported；
In above-mentioned steps d, the design of single parts is with the detailed process of FMECA information inputs：
Step d1, carries out the configuration design of product in CATIA；
Step d2, carries out FMECA information inputs, and Typical Components failure mode data storehouse is retrieved first, judges whether in data
Retrieved successfully in storehouse, if do not retrieved successfully, perform step d3, if retrieved successfully, perform step d4；
Step d3, input fault pattern, and failure criterion information, and store in Typical Components failure mode data storehouse,
For using later；
Step d4, reads related data；
Step d5, is input into other FMEA information；
Step d6, is input into the CA information of parts；
Step d7, fills in the relation of the parts and other parts, for setting up reliability block diagram.
2. airborne machinery product FMECA analysis methods according to claim 1, it is characterised in that in above-mentioned step
In rapid a, the Typical Components failure mode data storehouse is used to store failure mode, failure cause and the failure of Typical Components
Criterion information.
3. airborne machinery product FMECA analysis methods according to claim 2, it is characterised in that in above-mentioned step
In rapid b, the FMECA databases are used for the FMECA information of design Storage process input；It includes herein below：Indenture level
Definition, severity definition, the definition of fault mode probability levels, the FMECA information of each parts include that fault mode, failure are former
Cause, fault impact, severity, fault detection method, failure criterion, use indemnifying measure, design improved method, fault detect side
Method, probability of malfunction grade and harmfulness information.
4. airborne machinery product FMECA analysis methods according to claim 1, it is characterised in that above-mentioned steps
In d6, the detailed process for being input into the CA information of parts is：
HAZAN method, difinite quality and quantitative two kinds of analysis methods are selected first, if selection quantitative analysis, performs step
Rapid d61, if carrying out qualitative analysis, performs step d69；
Step d61, selects severity classification and task phase；
Then step d62 is performed, the fault mode to the parts is counted, has n, make i=1, i.e., from the parts
First fault mode proceed by input；
Step d63, is input into the fault mode frequency ratio of i-th fault mode of the parts；
Step d64, is input into the failure mode effect probability of i-th fault mode of the parts；
Step d65, is input into fault rate and time of the parts in task phase；
Step d66, calculates the fault mode density of infection of the fault mode, judges that whether n, less than i, if being less than i, performs step
D67, if being not less than i, performs step d68；
Step d67, is circulated the information for being input into next fault mode；
Step d68, calculates density of infection of the parts in given severity classification and task phase；
Step d69, input fault model probabilities grade.
5. airborne machinery product FMECA analysis methods according to claim 1, it is characterised in that above-mentioned steps f
In, it is to the detailed process that finished product carries out FMECA analyses：
Step f1, carries out system definition, including functional task analysis and analysis of Influential Factors；
Perform step f2, failure mode analysis (FMA)；
Perform step f3, failure reason analysis；
Step f4 is performed, failure effect analysis (FEA), including the influence of local influence, a level high and final influence is carried out；
Step f5 is performed, severity analysis is carried out；
Perform step f6, fault detection method analysis；
Step f7 is performed, failure symptom analysis is carried out；
Step f8 is performed, corrective measure is designed and is analyzed using indemnifying measure；
Step f9 is performed, HAZAN is carried out.
6. airborne machinery product FMECA analysis methods according to claim 1, it is characterised in that above-mentioned steps g
In, the detailed process of FMECA analysis reports output is：
The indenture level of output report is wanted in step g1, selection；
Step g2, sets relevant parameter；
Step g3, the analysis result output FMECA analysis reports according to a upper module.
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Families Citing this family (10)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN107590576A (en) * | 2016-07-07 | 2018-01-16 | 中芯国际集成电路制造(上海)有限公司 | FMEA Database Systems |
| CN108999890B (en) * | 2018-08-31 | 2019-08-30 | 西北工业大学 | A kind of splined builtup sequential selection method and splined member improving the spline service life |
| CN109543466B (en) * | 2018-10-31 | 2021-06-18 | 北京航空航天大学 | Hardware Trojan threat analysis method based on functional characteristic expansion |
| CN110348148B (en) * | 2019-07-16 | 2021-02-19 | 北京航空航天大学 | Key test process identification method based on process FMEA |
| CN110531608B (en) * | 2019-07-29 | 2022-04-01 | 华东计算技术研究所（中国电子科技集团公司第三十二研究所） | High-reliability electronic equipment quantitative FMECA analysis method and system based on redundancy design |
| CN110807605A (en) * | 2019-11-14 | 2020-02-18 | 北京京航计算通讯研究所 | Key inspection characteristic defect rate statistical method |
| CN113076619B (en) * | 2020-01-03 | 2023-06-23 | 中国航发商用航空发动机有限责任公司 | Aeroengine fault simulator, aeroengine fault simulation method and computer readable storage medium |
| CN112711851A (en) * | 2020-12-29 | 2021-04-27 | 中国航空工业集团公司西安飞机设计研究所 | Fault diagnosis demand data model construction method |
| CN115509795B (en) * | 2022-10-26 | 2024-02-02 | 聪脉（上海）信息技术有限公司 | FMECA report generation method and system |
| CN115630043B (en) * | 2022-10-28 | 2023-08-22 | 中国航发沈阳发动机研究所 | Model-driven aeroengine multi-reliability database system design method |
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| CN103760886A (en) * | 2013-12-02 | 2014-04-30 | 北京航空航天大学 | Newly-developed aviation electronic product hardware comprehensive FMECA method |
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| US8645019B2 (en) * | 2010-12-09 | 2014-02-04 | GM Global Technology Operations LLC | Graph matching system for comparing and merging fault models |
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| CN103760886A (en) * | 2013-12-02 | 2014-04-30 | 北京航空航天大学 | Newly-developed aviation electronic product hardware comprehensive FMECA method |
Non-Patent Citations (1)
| Title |
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| FMECA方法在无人机燃油系统中的应用;王俊祥;《中国优秀硕士学位论文全文数据库 工程科技Ⅱ辑》;20111215(第12期);正文第三章 * |
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