CN109033564A - A kind of aircraft airborne equipment testability demonstration index evaluating method - Google Patents
A kind of aircraft airborne equipment testability demonstration index evaluating method Download PDFInfo
- Publication number
- CN109033564A CN109033564A CN201810734123.6A CN201810734123A CN109033564A CN 109033564 A CN109033564 A CN 109033564A CN 201810734123 A CN201810734123 A CN 201810734123A CN 109033564 A CN109033564 A CN 109033564A
- Authority
- CN
- China
- Prior art keywords
- fault mode
- physics
- injection
- fault
- product
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Classifications
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/15—Vehicle, aircraft or watercraft design
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06Q—INFORMATION AND COMMUNICATION TECHNOLOGY [ICT] SPECIALLY ADAPTED FOR ADMINISTRATIVE, COMMERCIAL, FINANCIAL, MANAGERIAL OR SUPERVISORY PURPOSES; SYSTEMS OR METHODS SPECIALLY ADAPTED FOR ADMINISTRATIVE, COMMERCIAL, FINANCIAL, MANAGERIAL OR SUPERVISORY PURPOSES, NOT OTHERWISE PROVIDED FOR
- G06Q10/00—Administration; Management
- G06Q10/06—Resources, workflows, human or project management; Enterprise or organisation planning; Enterprise or organisation modelling
- G06Q10/063—Operations research, analysis or management
- G06Q10/0639—Performance analysis of employees; Performance analysis of enterprise or organisation operations
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Business, Economics & Management (AREA)
- Human Resources & Organizations (AREA)
- Theoretical Computer Science (AREA)
- Geometry (AREA)
- General Physics & Mathematics (AREA)
- Strategic Management (AREA)
- Development Economics (AREA)
- Entrepreneurship & Innovation (AREA)
- Economics (AREA)
- Educational Administration (AREA)
- Mathematical Analysis (AREA)
- Pure & Applied Mathematics (AREA)
- Computational Mathematics (AREA)
- General Engineering & Computer Science (AREA)
- Evolutionary Computation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Computer Hardware Design (AREA)
- Mathematical Optimization (AREA)
- Game Theory and Decision Science (AREA)
- Automation & Control Theory (AREA)
- Marketing (AREA)
- Operations Research (AREA)
- Quality & Reliability (AREA)
- Tourism & Hospitality (AREA)
- General Business, Economics & Management (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
A kind of aircraft airborne equipment testability demonstration index evaluating method, it is reported first according to the FMEA of product, determine the fault mode collection F of product, all fault modes in the fault mode collection F of product are analyzed again, determine laboratory can physics injection fault mode collection and can not physics injection fault mode collection, determining fault mode be all can physics inject fault mode collection, then formulate testing program, carry out testability demonstration test, completes testability assessment；Determining fault mode exist can not physics injection fault mode, then product failure set of patterns F is split, redefines the fault mode collection of product after splitting, and carried out corresponding analysis and assess；By carrying out aggregative weighted to testability demonstration, multi-panel information is merged, to guarantee the integrality and adequacy in experimental data source, effectively improves the accuracy of product test assessment.
Description
Technical field
The present invention relates to aircraft test and analysis technology field more particularly to a kind of aircraft airborne equipment testability demonstration indexs
Appraisal procedure.
Background technique
Aircraft airborne equipment testability validation & evaluation method is mainly statistical method at present, including based on bi-distribution and
The testability appraisal procedure of normal distribution, the standard that can refer to mainly have GJB2072, GJB1770, GJB5080, GB4087 etc..
However current aircraft airborne equipment testability demonstration test, all fault modes of product cannot be injected, to lead
The sample space in test is caused not have adequacy.
Summary of the invention
Technical problem solved by the invention is to provide a kind of aircraft airborne equipment testability demonstration index evaluating method,
To solve the disadvantage in above-mentioned background technique.
Technical problem solved by the invention is realized using following technical scheme:
A kind of aircraft airborne equipment testability demonstration index evaluating method, the specific steps are as follows:
1) it is reported first according to the FMEA of product, determines the fault mode collection F of product；
2) all fault modes in the fault mode collection F of product are analyzed, determine laboratory can physics injection
Fault mode collection and can not physics injection fault mode collection；
3) according to step 2) determine fault mode be all can physics inject fault mode collection, then formulate test side
Case carries out testability demonstration test, completes testability assessment；
4) according to step 2) determine fault mode exist can not physics injection fault mode, then by product failure mode
Collection F is split, and the fault mode collection of product after splitting is redefined, and carries out corresponding analysis assessment；
5) combining step 4) in analysis assessment, provide testability validation & evaluation conclusion.
In the present invention, in step 4), redefine split after product fault mode collection, by it is all can physics injection
Fault mode be defined as can physics injection fault mode collection, it is all can not the fault mode of physics injection be defined as can not physics
The fault mode collection of injection.
In the present invention, in step 4), according to meet after fractionation can physics injection fault mode collection, to product index into
Row is converted, and is obtained the index of physics injection examination, is then developed programs, implements physical fault injection, and is carried out based on physics event
Hinder the assessment of injection.
In the present invention, in step 4), according to meet after fractionation can not physics injection fault mode concentration belong to nature
The fault mode of generation executes the simulated failure based on emulation and injects analysis.
In the present invention, analyze each fault mode can physics injection the case where and natural failure a situation arises, determine therefore
Barrier mode 1 ..., T are that physical fault injection can be achieved；Fault mode T+1 ..., q be can not physics injection but belong to naturally-occurring
Failure；Fault mode q+1 ..., N be can not physics injection and be not belonging to naturally-occurring failure, it is true by testability simulation analysis
It is fixed:
Specific assessment formula is as follows:
In formula (1)~(2), FDRLThe confidence lower limit value for being β for airborne equipment confidence level；FDRTLIt is set for physical fault injection
Reliability is the confidence lower limit value of β, FDRqLThe confidence lower limit value for being β for naturally-occurring failure confidence level；CiFor i-th of fault mode
Opposite occurrence frequency；KLFor the reduced value of airborne equipment confidence lower limit；DiFor the event that can be detected in testability simulation analysis
Hinder pattern count.
The utility model has the advantages that the present invention merges multi-panel information, to guarantee to test by carrying out aggregative weighted to testability demonstration
The integrality and adequacy of data source, and then the fault mode that makes up the deficiency of existing Test Information and will can not be injected in test
The phenomenon that same object as analysis and assessment, effectively improves the accuracy of product test assessment.
Specific embodiment
In order to be easy to understand the technical means, the creative features, the aims and the efficiencies achieved by the present invention, tie below
Specific embodiment is closed, the present invention is further explained.
A kind of aircraft airborne equipment testability demonstration index evaluating method, the specific steps are as follows:
1) it is reported according to the FMEA of product, determines the fault mode collection F of product；
2) all fault modes in the fault mode collection F of product are analyzed, determine laboratory can physics injection
Fault mode collection and can not physics injection fault mode collection；
3) according to step 2) determine fault mode be all can physics inject fault mode collection, then formulate test side
Case carries out testability demonstration test, completes testability assessment；
4) according to step 2) determine fault mode exist can not physics injection fault mode, then by product failure mode
Collection F split, by it is all can physics injection fault mode be defined as can physics injection fault mode collection, it is all can not object
Reason injection fault mode be defined as can not physics injection fault mode collection；
5) according to step 4) split after can physics injection fault mode collection, product index is converted, object is obtained
The index of reason injection examination, and develop programs, implement physical fault injection, and carry out the assessment injected based on physical fault；
6) according to step 4) split after can not physics injection fault mode concentration belong to abiogenous fault mode,
It executes the simulated failure based on emulation and injects analysis, i.e. testability simulation analysis；
7) assessment of step 5)~step 6) is integrated with analysis, provides testability validation & evaluation conclusion.
In the present embodiment, analyze each fault mode can physics injection the case where and natural failure a situation arises, determine
Fault mode 1 ..., T are that physical fault injection can be achieved；Fault mode T+1 ..., q be can not physics injection but belong to nature hair
Raw failure；Fault mode q+1 ..., N be can not physics injection and be not belonging to naturally-occurring failure, pass through testability simulation analysis
It determines:
Specific assessment formula is as follows:
In formula (1)~(2), FDRLThe confidence lower limit value for being β for airborne equipment confidence level；FDRTLIt is set for physical fault injection
Reliability is the confidence lower limit value of β, FDRqLThe confidence lower limit value for being β for naturally-occurring failure confidence level；CiFor i-th of fault mode
Opposite occurrence frequency；KLFor the reduced value of airborne equipment confidence lower limit；DiFor the event that can be detected in testability simulation analysis
Hinder pattern count.
The above shows and describes the basic principles and main features of the present invention and the advantages of the present invention.The technology of the industry
Personnel are it should be appreciated that the present invention is not limited to the above embodiments, and the above embodiments and description only describe this
The principle of invention, without departing from the spirit and scope of the present invention, various changes and improvements may be made to the invention, these changes
Change and improvement all fall within the protetion scope of the claimed invention.The claimed scope of the invention by appended claims and its
Equivalent thereof.
Claims (5)
1. a kind of aircraft airborne equipment testability demonstration index evaluating method, which is characterized in that specific step is as follows:
1) it is reported first according to the FMEA of product, determines the fault mode collection F of product；
2) all fault modes in the fault mode collection F of product are analyzed, determine laboratory can physics injection failure
Set of patterns and can not physics injection fault mode collection；
3) according to step 2) determine fault mode be all can physics inject fault mode collection, then formulate testing program, open
Testability demonstration test is opened up, testability assessment is completed；
4) according to step 2) determine fault mode exist can not physics injection fault mode, then by product failure set of patterns F
It is split, redefines the fault mode collection of product after splitting, and carry out corresponding analysis assessment；
5) combining step 4) in analysis assessment, provide testability validation & evaluation conclusion.
2. a kind of aircraft airborne equipment testability demonstration index evaluating method according to claim 1, which is characterized in that step
It is rapid 4) in, redefine the fault mode collection of product after splitting, by it is all can the fault mode of physics injection be defined as can physics
The fault mode collection of injection, it is all can not physics injection fault mode be defined as can not physics injection fault mode collection.
3. a kind of aircraft airborne equipment testability demonstration index evaluating method according to claim 2, which is characterized in that root
According to meet after fractionation can physics injection fault mode collection, product index is converted, obtain physics injection examination index,
It then develops programs, implements physical fault injection, and carry out the assessment injected based on physical fault.
4. a kind of aircraft airborne equipment testability demonstration index evaluating method according to claim 2, which is characterized in that root
According to meet after fractionation can not the fault mode concentration of physics injection belong to abiogenous fault mode, execute the mould based on emulation
Quasi- direct fault location analysis.
5. a kind of aircraft airborne equipment testability demonstration index evaluating method according to claim 1, which is characterized in that point
Analyse each fault mode can physics injection the case where and natural failure a situation arises, determine fault mode 1 ..., T is physical fault
Injection can be achieved；Fault mode T+1 ..., q be can not physics injection but belong to naturally-occurring failure；Fault mode q+1 ..., N
It is that physics injection and naturally-occurring failure can not be not belonging to, passes through testability simulation analysis and determine:
Specific assessment formula is as follows:
In formula (1)~(2), FDRLThe confidence lower limit value for being β for airborne equipment confidence level；FDRTLConfidence level is injected for physical fault
For the confidence lower limit value of β, FDRqLThe confidence lower limit value for being β for naturally-occurring failure confidence level；CiFor the phase of i-th of fault mode
To occurrence frequency；KLFor the reduced value of airborne equipment confidence lower limit；DiFor the failure mould that can be detected in testability simulation analysis
Formula number.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810734123.6A CN109033564A (en) | 2018-07-06 | 2018-07-06 | A kind of aircraft airborne equipment testability demonstration index evaluating method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810734123.6A CN109033564A (en) | 2018-07-06 | 2018-07-06 | A kind of aircraft airborne equipment testability demonstration index evaluating method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109033564A true CN109033564A (en) | 2018-12-18 |
Family
ID=64641183
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810734123.6A Pending CN109033564A (en) | 2018-07-06 | 2018-07-06 | A kind of aircraft airborne equipment testability demonstration index evaluating method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109033564A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110942227A (en) * | 2019-10-25 | 2020-03-31 | 中国飞行试验研究院 | Verification method and device for ground support equipment of civil aircraft |
| CN114036450A (en) * | 2021-10-25 | 2022-02-11 | 中国电子科技集团公司第二十九研究所 | Method for quickly assessing testability indexes of electronic information equipment and storage medium |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20050194590A1 (en) * | 2004-03-03 | 2005-09-08 | Hiroshi Matsushita | System and method for controlling manufacturing apparatuses |
| CN105067933A (en) * | 2015-08-31 | 2015-11-18 | 中国人民解放军63908部队 | Universal system for electronic equipment testability validation and evaluation and testing method |
| CN105574333A (en) * | 2015-12-13 | 2016-05-11 | 中国航空工业集团公司西安飞机设计研究所 | Determination method for fault sample quantity in testability experiment of airborne equipment |
| CN106742058A (en) * | 2016-12-26 | 2017-05-31 | 中国航空工业集团公司西安飞机设计研究所 | A kind of testability laboratory test fault population determines method |
-
2018
- 2018-07-06 CN CN201810734123.6A patent/CN109033564A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20050194590A1 (en) * | 2004-03-03 | 2005-09-08 | Hiroshi Matsushita | System and method for controlling manufacturing apparatuses |
| CN105067933A (en) * | 2015-08-31 | 2015-11-18 | 中国人民解放军63908部队 | Universal system for electronic equipment testability validation and evaluation and testing method |
| CN105574333A (en) * | 2015-12-13 | 2016-05-11 | 中国航空工业集团公司西安飞机设计研究所 | Determination method for fault sample quantity in testability experiment of airborne equipment |
| CN106742058A (en) * | 2016-12-26 | 2017-05-31 | 中国航空工业集团公司西安飞机设计研究所 | A kind of testability laboratory test fault population determines method |
Non-Patent Citations (1)
| Title |
|---|
| 张艺琼 等: "测试性验证试验中的综合评估方法", 《测控技术》 * |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110942227A (en) * | 2019-10-25 | 2020-03-31 | 中国飞行试验研究院 | Verification method and device for ground support equipment of civil aircraft |
| CN114036450A (en) * | 2021-10-25 | 2022-02-11 | 中国电子科技集团公司第二十九研究所 | Method for quickly assessing testability indexes of electronic information equipment and storage medium |
| CN114036450B (en) * | 2021-10-25 | 2023-06-06 | 中国电子科技集团公司第二十九研究所 | Method for quickly checking testability index of electronic information equipment and storage medium |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN107545349A (en) | A kind of Data Quality Analysis evaluation model towards electric power big data | |
| CN102508780B (en) | Crossed dynamic software testing method and device | |
| CN102799822B (en) | Software running security measurement and estimation method based on network environment | |
| CN104317681B (en) | For the behavioral abnormal automatic detection method and detecting system of computer system | |
| CN106934208B (en) | A kind of dam thundering observed data automatic identifying method | |
| CN109470946B (en) | Power generation equipment fault detection method and system | |
| CN102270253A (en) | Built-in test modeling simulation method based on state diagram | |
| CN111290955B (en) | Non-invasive automatic test system for subway signal system test software | |
| CN106682432A (en) | Dynamic monitoring system and method for quantitative detection and intelligent auditing | |
| CN109033564A (en) | A kind of aircraft airborne equipment testability demonstration index evaluating method | |
| CN107391370A (en) | A kind of software defect estimated number method based on data oversampling and integrated study | |
| CN105159827A (en) | Reliability accelerated testing method for GUI software | |
| CN105930900A (en) | Method and system for predicting hybrid wind power generation | |
| CN106383303A (en) | Observation point and concurrence based fault injection simulation method and device | |
| CN106647650A (en) | Distributed industrial process monitoring method based variable weighting PCA (Principal Component Analysis) model | |
| CN109272190A (en) | A kind of power cable state evaluation method based on momentum BP neural network | |
| CN103678529B (en) | Integration method of wafer test data of multiple times | |
| CN112800540B (en) | Aircraft engine load spectrum task segment modeling method based on Gaussian process regression | |
| CN110210171A (en) | A kind of mathematical model tests die worker's tool | |
| CN108710568A (en) | Detection method, computer equipment and the storage medium of static code defect | |
| Roccetti et al. | A paradox in ML design: less data for a smarter water metering cognification experience | |
| CN106356994A (en) | Grid stability judging method based on grid PMU big data | |
| CN105843736A (en) | Test method for power system state estimation software | |
| CN113723871B (en) | Multi-source information-based current situation flood consistency processing method and system | |
| CN113033845B (en) | Construction method and device for power transmission resource co-construction and sharing |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20181218 |