CN104820892B - A kind of aviation electricity generation system based on data transfer quantifies HAZAN method - Google Patents
A kind of aviation electricity generation system based on data transfer quantifies HAZAN method Download PDFInfo
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Abstract
The present invention provides a kind of aviation electricity generation systems based on data transfer to quantify HAZAN method, belongs to reliability engineering technique field.This method includes：Divide the indenture level of aviation electricity generation system；FMECA analyses are carried out to the electronic component on minimum indenture level or component of machine；FMECA analyses are carried out to each functional unit on functional unit grade indenture level；The bottom-up component on functional unit grade more than indenture level carries out FMECA analyses；Final influence, severity grade and the failure of each component influence probability on the whole indenture levels of analysis acquisition from up to down；Calculating pattern density of infection and product density of infection；Draw harmfulness matrix diagram.The present invention accurately quantify CA analyses, gives reverse V-shaped FMECA analysis process, analysis result has more accuracy by obtaining quantitative data.
Description
Technical field
The present invention provides a kind of aviation electricity generation system and quantifies HAZAN method, for containing inconsistent fail data
The electromechanical hybrid system of information carries out quantitative HAZAN, belongs to reliability engineering technique field.
Background technology
With the rapid development of modern high technology and industrial construction, the complexity of aviation electricity generation system is continuously improved,
Requirement to its reliability is also higher and higher.Aviation electricity generation system is generally made of the part such as controller and generator, is one
Typical electromechanical hybrid system.In aircraft performs task process, electricity generation system is responsible for the power supply of aircraft full safety, once its
It breaks down, significant impact certainly will be caused to aircraft, it is serious to be also possible to lead to fatal crass.
Failure mode effect and HAZAN (Failure Mode, Effects and Criticality
Analysis, FMECA) method is one of failure prevention analysis method generally used in reliability design analysis.FMECA is by event
Hinder mode influences analysis FMEA and HAZAN CA two parts are formed.CA is the supplement and extension to FMEA, and common method has
Risk priority number method and harmfulness matrix method.Harmfulness matrix method is generally used in military domains such as Aeronautics and Astronautics.Harmfulness square
The tactical deployment of troops is divided into as two methods of qualitative analysis and quantitative analysis.Quantitative analysis method result is more accurate, but can not obtain event
Qualitatively analysis method can only be used during barrier rate data.Only can accurately be obtained in engineering at present electronic component failure rate and
Fault mode frequency ratio, and experience is depended on greatly for circuit more than module level and provides related data, and for engineering goods
Fault data information is less, and qualitative analysis is empirically carried out, therefore electronic product integrally can not be carried out more mostly in engineering
Accurately quantify HAZAN.At present both at home and abroad not yet be directed to aviation electricity generation system the considerations of product failure transitive relation and
The research and application of the quantitative CA methods of the inconsistent grade influences of data information are reported for work.
Invention content
In view of the deficiencies of the prior art, it is an object of the present invention to provide a kind of aviation electricity generation systems based on data transfer to determine
Measure HAZAN method.Method provided by the invention is that a kind of failure that is based on influences transitive relation and considers that data source differs
The quantitative HAZAN method of situations such as cause can provide a kind of more objective for aviation electricity generation system for design analysis personnel
The HAZAN implementation of sight, while also foundation is provided for the design of aviation electricity generation system improvement.
A kind of aviation electricity generation system based on data transfer provided by the invention quantifies HAZAN method, specific to walk
It is rapid as follows：
Step 1：Divide the indenture level of aviation electricity generation system.
1) structure composition of aviation electricity generation system is determined；
2) according to the structure composition of product, product is divided into several indenture levels from top to bottom, wherein independent work(
Energy unit is an indenture level, and minimum indenture level is electronic component or the component of machine that can not be split.
Step 2：FMECA analyses are carried out to the electronic component on minimum indenture level or component of machine, obtain failure
Pattern, failure influences and quantitative data；Wherein quantitative data includes fault mode frequency ratio and crash rate；
For electronic component, searched from the estimated handbook GJB299C-2006 of reliability of electronic equipment and obtain fault mode
With fault mode frequency ratio, failure rate is obtained using Stress Analysis Method；
For component of machine, according to outfield statistical data or like product data acquisition fault mode and fault mode frequency
Number ratio obtains failure rate using THE PRINCIPAL FACTOR ANALYSIS method and probabilistic reliability design method；
The THE PRINCIPAL FACTOR ANALYSIS method refers to the core position for determining that component of machine chife failure models is caused to occur, and uses
The failure rate at core position replaces the failure rate of component of machine；
The probabilistic reliability design method is：Working condition according to analysis object determines the reliable longevity of analysis object
Life, then determine the service life distribution of analysis object, the crash rate for determining analysis object is distributed according to the service life；
For each failure mode analysis (FMA), its failure on same layer and upper-layer functionality unit influences.
Step 3：FMECA analyses are carried out to each functional unit on functional unit grade indenture level, obtain functional unit
Fault mode, failure cause, failure influence and quantitative data etc.；
According to the FMECA of each electronic component on minimum indenture level as a result, concluding the failure mould of acquisition functional unit
Formula；It will lead to the fault mode of the minimum indenture level of whole of a certain fault mode of functional unit as the functional unit failure mould
The failure cause of formula obtains whole failure causes of each fault mode；For each fault mode, analyze its to same layer and
The failure of upper strata product influences.
If some functional unit is made of n electronic component or component of machine, λpiFor i-th of electronic component or machine
The failure rate λ of the failure rate of tool parts, the then functional unitpFor：
The frequency ratio acquisition methods of a certain fault mode k of the functional unit are：First, it determines on minimum indenture level
The failure rate λ of j-th of fault mode of i electronic component or component of machinemijFor：λmij=λpi·αij, αijIt is i-th
The frequency ratio of j-th of fault mode of electronic component or component of machine；Secondly, determine that whole failures of fault mode k are former
The sum of failure rate of cause, the recursion failure rate λ ' as fault mode kmk；Then, the recursion frequency ratio of fault mode k is obtainedFinally, the normalized of fault mode frequency ratio is carried out, obtains the frequency ratio of physical fault pattern kWherein l represents the fault mode number of the functional unit.
Step 4：The bottom-up component on functional unit grade more than indenture level carries out FMECA analyses, according to step 3
Method, obtain that the fault mode of each component on whole indenture levels, failure cause, failure influences and quantitative data；
Step 5：Final influence, severity grade and the event for obtaining each component on whole indenture levels are analyzed from up to down
Barrier influences probability；
For next layer of initial indenture level, final influence and severity grade are analyzed, and provide and cause the failure
The failure of influence influences probability；According to transitive relation, from initial indenture level to minimum indenture level recursion, acquisition is had an agreement
The final of level influences and severity grade；
Obtaining the failure of each indenture level below initial indenture level influences probability, and specific method is：
If j-th of fault mode FM of a certain i-th of component of indenture levelijOne of failure cause of generation is next about for its
G-th of fault mode FM of upper h-th of the component of given layer timehg, then obtain failure influence probability process be：
A. FM is analyzedhgTo FMijFailure influence probability β '；
B. FM is obtainedhgFailure influence probability βhg：βhg=βij·β′；βijIt is fault mode FMijFailure influence probability.
Step 6：Density of infection is calculated, including pattern density of infection and product density of infection, specific implementation step is as follows：
Step 6.1：Determine the working time t of aviation electricity generation system and each building block；
Step 6.2：Determine the density of infection of each fault mode；
If certain component working time is t, the frequency ratio of some fault mode of the component is α, failure rate λp, failure shadow
Ring the density of infection C that probability is β, the then fault modem(h)=α β λpT, wherein, h represents severity grade, and setting h has
Four grades, Cm(h) number of stoppages of h grades occurs between representing the component at work in t with a certain fault mode；
Step 7：Draw harmfulness matrix diagram, comprehensive analysis aviation electricity generation system or each building block severity grade and danger
The harmfulness size of fault mode and building block is compared in influence caused by evil degree or pattern density of infection, provides harmfulness sequence.
Relative to the prior art, the method for the present invention has the following advantages that and good effect：
(1) the data source analysis method of all kinds of components and parts in electricity generation system is given, passes through stress respectively
Analytic approach and THE PRINCIPAL FACTOR ANALYSIS method, probabilistic reliability design method obtain failure rate, the fault mode frequency of different object
Than etc. quantitative datas information, for accurately quantify CA analysis provide data basis.
(2) give influences the functional unit of transitive relation and the failure of more than level product based on bottom data and failure
The quantitative calculation method of the data such as rate, fault mode frequency ratio, compares for providing related data based on experience, with more standard
True property.
(3) reverse V-shaped FMECA analysis process, the i.e. influence of bottom-up parse high level failure, fault mode are given, from
Upper backtracking downwards finally influences and severity grade.Compared to the bottom-up analytic process provided in GJB 1391, analysis knot
Fruit has more accuracy, is analyzed convenient for designer.Because if indenture level is more than 3 grades, in product bottom, designer
It is difficult to directly analyze and obtains the failure influence of bottom component initial indenture level on aircraft etc., analysis result is easier to occur inclined
Difference.
Description of the drawings
The aviation electricity generation system that Fig. 1 is the present invention quantifies HAZAN method flow block diagram；
Fig. 2 is 1 electricity generation system product form structure list of table；
Fig. 3 is the schematic diagram that electricity generation system is divided into 5 indenture levels in the embodiment of the present invention；
Fig. 4 is 2 processor monitoring module FMECA analytical tables of table；
Fig. 5 is 3 frequency detection circuit FMECA analytical tables of table；
Fig. 6 is 4 generator FMECA analytical tables of table；
Fig. 7 is 5 processor module FMECA analytical tables of table；
Fig. 8 is 6 controller FMECA analytical tables of table；
Fig. 9 is 7 electricity generation system FMECA analytical tables of table；
Figure 10 is the 8 controller FMECA analytical tables of table obtained through step 4；
Figure 11 is the 9 processor module FMECA analytical tables of table obtained through step 4；
Figure 12 is the 10 processor monitoring module FMECA analytical tables of table obtained through step 4；
Figure 13 is the 11 frequency detection circuit FMECA analytical tables of table obtained through step 4；
Figure 14 is the 12 generator FMECA analytical tables of table obtained through step 4；
Figure 15 device harmfulness matrix diagram in order to control；
Figure 16 is generator failure pattern harmfulness matrix diagram.
Specific embodiment
Below in conjunction with drawings and examples, the present invention is described in further detail.
Aviation electricity generation system provided by the invention based on data transfer quantifies HAZAN method, is to electricity generation system
In electronic component portions the quantitative datas information such as failure rate, fault mode frequency ratio are determined based on GJB299C, to non-electrical part
It determines that method and mechanical probabilistic reliability design method determine the data such as its failure rate based on main factor, on this basis, is based on
Transitive relation between fault mode, reason and influence, accurately calculates product density of infection Cr at different levels, and it is whole to complete aviation electricity generation system
The CA analyses of body.The aviation electricity generation system of the present invention quantifies HAZAN method, and existing HAZAN method is carried out
Supplement and auxiliary so that analysis result is more accurate.
Following embodiment is implemented according to flow as shown in Figure 1, main to include dividing aviation electricity generation system about
Given layer time, minimum indenture level object FMECA analyses, functional unit and more than level object FMECA analyses, product density of infection meter
The parts such as calculation.The present embodiment analysis object is certain aviation electricity generation system, for simplifying the analysis, the selective analysis electricity of controller
The non-electrical part of subdivision and generator.Aviation electricity generation system mainly includes the Field Replaceable Unit such as controller and generator,
Specifically containing the internal fields such as processor module, discrete magnitude acquisition and output module, main hair stator module, main hair rotor assembly again can
Replace the functional units such as unit and frequency detection circuit, surge restraint circuit circuit and capacitor, resistor, diode,
The components such as iron core, winding, sealing ring and parts.
Step 1：Indenture level division is carried out to aviation electricity generation system, determines the hierarchical relationship of analysis object.Aviation generates electricity
For the structure composition and its number of system as shown in the table 1 of Fig. 2, indenture level is as shown in Figure 3.It is given in electricity generation system in table 1
The composition structure of portioned product, for example, including 101 bleeder resistances, 102 wave filters etc. under generator.
In the embodiment of the present invention, according to electricity generation system function and design feature, aviation electricity generation system is carried out from top to bottom
Indenture level divides, and minimum indenture level is electronic component or the component that can not be split, independent functional unit for one about
Given layer time.As shown in figure 3, aviation electricity generation system is divided into 5 indenture levels.
1) initial indenture level, be analysis system in itself：Electricity generation system；
2) the second indenture level is Field Replaceable Unit grade, including：Generator, controller, influenza device；
3) third indenture level is internal field replaceable units grade, including：Main hair stator module, vent valve, processor die
Block, power module etc.；
4) the 4th indenture level is functional unit grade, including：Processor monitoring module, freq converting circuit, Surge suppression
Circuit, voltage voting circuit etc.；
5) minimum indenture level is electronic component and can not be split component of machine, including：Resistance, capacitance, two poles
Pipe, iron core, winding, valve, sealing ring etc..
For a certain product, the product or component being located on a upper indenture level, all components or product are located at
Below on indenture level.For example, the generator on the second indenture level in Fig. 3, the group on the minimum indenture level of generator
Part is to be located at the component that each component of generator is included on third indenture level and the component of machine that can not be split.For control
Device processed, on minimum indenture level is the electronic component that is included of each function module of controller on the 4th indenture level.
Step 2：Minimum indenture level FMECA analyses.For the minimum indenture level object of different type, carry out respectively
FMECA is analyzed, and it is as follows to specifically include contents, the detailed process such as fault mode, failure influence, the acquisition of quantitative data：
1) for forming minimum indenture level object-electronic component of controller of electricity generation system, carry out FMECA
Work, detailed process have：
A) composition in table 1 searches electronics member device from the estimated handbook GJB299C-2006 of reliability of electronic equipment
The fault mode of part, fault mode frequency ratio.Such as：2101012 class ceramic capacitor C1 search GJB299C-2006 electronic equipments
Reliability prediction handbook, obtain fault mode altogether there are three types of：Open circuit, short circuit and parameter drift, fault mode frequency ratio α are respectively
16%th, 73%, 11%.Fault mode frequency is also referred to as fault mode percentage.
B) according to circuit design, the crash rate of electronic component is calculated using Stress Analysis Method, obtains 2101012 class porcelain dielectrics
The failure rate of container C1 is 1.376E-8 (/h).Failure rate is also referred to as crash rate.
2) for forming minimum indenture level object-component of machine of generator of electricity generation system, carry out FMECA
Work, detailed process have：
A) it is formed according to table 1, for component of machine, according to outfield statistical data or like product data, obtains non-electrical
The fault mode of parts and fault mode frequency ratio.Outfield statistical data refers to what product was occurred during field trial
The statistics of fault data；Like product data refer to possessed by the product similar to aviation electricity generation system to be analyzed by interior
Field verification experimental verification or the fault data of field trial verification, wherein like product refer to aviation electricity generation system to be analyzed in work(
Energy, structure, material, technique etc. have the product of more than 90% similarity.Big city directly records failure in statistical data
The information such as pattern, time of origin, occurrence condition directly can therefrom obtain fault mode；Count on this basis a certain component or
With the component or component failure the ratio between total degree occurs for the number that component failure pattern occurs, then can obtain fault mode frequency
Number compares information.
B) type and feature of the non-electric parts of detailed analysis chooses different methods and determines crash rate.
I. THE PRINCIPAL FACTOR ANALYSIS method：The composition and chife failure models of non-electrical component of machine are analyzed, determines to lead to failure mould
The core position and factor that formula occurs replace the crash rate of non-electrical component with the crash rate at core position.For main hair stator pack
The objects such as part, main hair rotor assembly, using this method.Main hair stator module is mainly made of iron core and winding, passes through product spy
Property analysis and a large amount of history field datas show that main hair stator module failure is occurred mainly on winding, therefore by the mistake of winding
The crash rate of stator module is sent out based on efficiency is equivalent, the crash rate of winding is calculated with reference to the related data of GJB299C-2006.
Ii. probabilistic reliability design method：According to the working condition of analysis object, it is reliable to calculate it using strength theory etc.
Service life；Then according to the difference of analysis features of the object, determine that its service life is distributed；The mistake for determining analysis object is distributed further according to the service life
Efficiency.For parts such as elastic shaft, base bearings, using this method.It is designed according to the structure size of elastic shaft, utilizes Intensity Design
Theory, calculate elastic shaft coefficient of reliability UR=8.9, reliability requirement is 0.99990.Since the elastic shaft service life obeys
Normal distribution can derive its crash rate formula, its crash rate is can be calculated as 3E-18 (/h) for people.
3) combination product analyzes failure shadow of minimum each fault mode of indenture level to same layer and upper-layer functionality unit
It rings.Such as Fig. 4~2~table of table shown in fig. 64.Fault mode coding, fault mode, failure cause, failure are given in table to be influenced
Etc..
Step 3：FMECA analyses are carried out to each functional unit on functional unit grade indenture level, obtain functional unit
Fault mode, failure cause, failure influences and quantitative data etc..
Main contents include：
1) according to the FMECA analysis results of minimum indenture level, the fault mode for summarizing and obtaining functional unit is concluded.From most
It is concluded in low indenture level FMECA analysis results and summarizes high-rise influence, merge the item of similar influence, and remove " no to influence " one
, remaining different failure influences, and as the fault mode of functional unit, preceding 5 row of table 5 as shown in Figure 7 record fault mode
Coding, fault mode, failure cause, failure influence etc.；
2) fault mode of the minimum indenture level of whole of a certain fault mode of functional unit will be caused as functional unit
The failure cause of the fault mode, and so on obtain fault mode whole failure causes；
3) analyzing each fault mode influences the failure of same layer and upper strata product, and the 8th, 9 row of chart 5 describe
Local influence and upper strata influence；
Based on the failure rate of electronic component on minimum indenture level, according to the division of product indenture level, formed
Whole electronic components of functional unit or non-electrical component of machine, it is assumed that some functional unit is by n electronic component or machine
Tool parts form, and the failure rate of i-th of electronic component or component of machine is λpi, then the failure rate λ of the functional unitp
For：
Based on the electronic component or the quantitative data of component of machine on minimum indenture level, influence to transmit using failure
Relationship, calculates the fault mode frequency ratio α for obtaining each functional unit, and detailed process is as follows：
(1) the failure rate λ of some fault modemFor fault mode frequency ratio α and cell failure rate λpProduct, calculate it is minimum
The mode fault rate λ of j-th of fault mode of i-th of electronic component or component of machine on indenture levelmij, such as following formula institute
Show：
λmij=λpi·αij (2)
Wherein, αijFrequency ratio for i-th of electronic component or j-th of fault mode of component of machine.
(2) the sum of mode fault rate of whole failure causes of a certain fault mode k of computing function unit, as the failure
The recursion mode fault rate λ ' of patternmk。
(3) by recursion mode fault rate λ 'mkDivided by the failure rate λ of the functional unitp, obtain the recursion event of the fault mode
Barrier pattern percentage α 'k, it is as follows：
(4) since there may be " no to influence " patterns, it is therefore desirable to carry out the normalized of fault mode percentage, obtain
Obtain practical fault mode percentage αk, it is as follows：
In formula, l represents the fault mode number of the functional unit.
In the embodiment of the present invention, formula (1) calculates the failure rate λ of each functional unitp, such as the 13rd row institute of table 5
Show.Such as：Processor monitoring module includes 70 capacitors and 1 piece of printed board and 1 solder joint set altogether, totally 72 function lists
Member, the failure rate solution procedure of processor monitoring module are：
Transitive relation is influenced using failure, formula (2)~formula (4) calculates the fault mode of each functional unit
Frequency ratio α, as shown in the 14th row of table 5.Such as：" watchdog function is abnormal " fault mode of processor monitoring module is opened by C1's
Road, short trouble cause, therefore the recursion mode fault rate λ ' of " watchdog function is abnormal " this fault modem1For：
λ′m1=∑ λpi·αij=1.376 × 10-8× 16%+1.376 × 10-8× 73%=1.225 × 10-8
In above formula, the fault mode the sum of mode fault rate of whole failure causes on minimum indenture level is asked for, this
There are two failure causes in table 5 in inventive embodiments.
The frequency ratio α ' of the fault mode1Calculating process be：
Processor monitoring module shares 3 fault modes in table 5, so " watchdog function is abnormal " this fault mode
The normalization calculating process of frequency ratio is：
And so on, the quantitative data of other functional unit indenture levels of electricity generation system is calculated, and result is inserted into work(
In the FMECA tables of energy element circuit, final result is as shown in table 5.
Step 4：According to the method for step 3, the bottom-up component on functional unit grade more than indenture level carries out
FMECA obtains fault mode, failure cause, failure influence and the quantitative data of whole indenture levels.
With reference to functional unit grade FMECA analysis methods, based on each component in each function module and minimum indenture level
FMECA is analyzed, and same method carries out FMECA analyses to component each on a upper indenture level successively, is completed on whole indenture levels
The fault mode of each component, failure cause, it is high-rise influence and the acquisition of the quantitative datas such as failure rate, fault mode percentage, example
Table 6 and table 7 as shown in FIG. 8 and 9.
The FMECA of each electronic component on known d indenture levels is obtained on d-1 indenture levels respectively as a result, concluding
The fault mode of component using step 3 method, for certain component on d-1 indenture levels, will lead to a certain failure mould of the component
Failure cause of the fault mode of all d indenture levels of formula as the component fault mode, and so on obtain the portion
Whole failure causes of each fault mode of part.For each fault mode, its failure to same layer and upper strata product is analyzed
It influences.Equally using formula (1)~(4), the failure rate of d-1 indenture level upper-parts, the frequency of each fault mode are obtained
Than and failure rate.
Step 5：Final influence, severity grade and the event for obtaining each component on whole indenture levels are analyzed from up to down
Barrier influences probability.
1) for next layer of initial indenture level, final influence and severity grade are analyzed, and provide and cause the event
The failure that barrier influences influences probability β, the respective column being shown in Table in 7；
2) according to transitive relation, from initial indenture level to minimum indenture level recursion, all indenture levels are obtained most
It is influenced eventually with severity grade, the respective column being shown in Table in 8~table 12；
3) calculating the failure of each indenture level influences probability β, the respective column being shown in Table in 8~table 12, the embodiment of the present invention
In β be 1；
In the present invention, if j-th of fault mode FM of i-th of component of a certain indenture levelijOne of failure cause of generation
G-th of fault mode FM for h-th of component on its next indenture levelhg, then obtain failure influence probability process be：
A. FM is analyzedhgTo FMijFailure influence probability β '；
B. FM is obtainedhgFailure influence probability βhg：βhg=βij·β′；
Wherein, β ' is set as the case may be, and 1 is disposed as in the embodiment of the present invention.βijIt is fault mode FMij's
Failure influences probability.
4) other related contents of each layer FMECA tables are supplemented, obtain 7~table of table 12 as shown in Fig. 9~Figure 14.
Step 6：Density of infection calculates.Main contents include the calculating of pattern density of infection and product density of infection.Specific steps 5
Realization process is as follows：
Step 6.1：Determine the working time t of electricity generation system and each building block, t is 2.5h in the embodiment of the present invention；
Step 6.2：Calculate the density of infection C of each fault modem(h), it is as follows：
Cm(h)=α β λpT, h=I, II, III, IV (5)
If certain component working time is t, the frequency ratio of some fault mode of the component is α, failure rate λp, failure shadow
It is β to ring probability, then shown in the density of infection of the fault mode such as formula (5).H represents severity grade, and h is set in the embodiment of the present invention
There are four grades.Cm(h) number of stoppages of h grades occurs between representing the component at work in t with a certain fault mode.
Step 6.3：Determine the density of infection of aviation electricity generation system；If Cr(h) between representing aviation electricity generation system at work in t
The severity grade of generation is the number of stoppages of h, if N represents fault mode of the aviation electricity generation system in the case where severity grade is h
Sum, then：
Formula (5) and formula (6), by the result calculated insert more than each layer FMECA tables in, be shown in Table 7~
12 next two columns of table.
Step 7：Draw harmfulness matrix diagram, comprehensive analysis aviation electricity generation system or each building block severity grade and danger
The harmfulness size of fault mode and building block is compared in influence caused by evil degree or pattern density of infection, provides harmfulness sequence.
Using severity grade as abscissa, density of infection and product density of infection are ordinate in mode respectively, and drafting is different about
The harmfulness matrix diagram of given layer time object.By taking controller as an example, product harmfulness matrix diagram is as shown in figure 15.
It can be seen that according to Figure 15 controller harmfulness matrix diagram to controller harmfulness size according to density of infection CrFrom big
It is to small sequence：21 (processor modules)>23 (analogue collection modules)>22 (discrete magnitude acquires and output modules)>24 is (interior
Portion's power module)>25 (voltage regulating modules)>27 (front panels)>26 (bus bar plates).
By taking generator as an example, fault mode harmfulness matrix is as shown in figure 16.
Generator failure pattern is according to sequence from big to small to harm to the system：M101 (generator output voltage arteries and veins
It is dynamic to increase)>M104 (generator does not have voltage signal output)>M102 (generator output voltage pulsating quantity is unsatisfactory for requiring)>
M103 (output information of generator is reduced).
The present invention establishes the quantitative harm for influencing transitive relation based on failure and considering situations such as data source is inconsistent
Property analysis method.Using this method, design analysis personnel can carry out more objective harmfulness to being directed to aviation electricity generation system
Implementation is analyzed, also foundation is provided for the design of aviation electricity generation system improvement, so as to improve the reliability of product.
Claims (2)
1. a kind of aviation electricity generation system based on data transfer quantifies HAZAN method, which is characterized in that realizes step such as
Under：
Step 1：Divide the indenture level of aviation electricity generation system；
According to the structure of aviation electricity generation system, aviation electricity generation system is subjected to indenture level division from top to bottom；It is wherein independent
Functional unit is an indenture level；Minimum indenture level is electronic component or the component of machine that can not be split；
Step 2：Failure mode effect and harm are carried out to each electronic component on minimum indenture level or component of machine
Property analysis FMECA, obtain fault mode, failure influence and quantitative data；Quantitative data includes frequency ratio and the event of fault mode
Barrier rate；
For electronic component, searched from the estimated handbook GJB299C-2006 of reliability of electronic equipment and obtain fault mode and event
Hinder pattern frequency ratio, failure rate is obtained using Stress Analysis Method；
For component of machine, according to outfield statistical data or like product data acquisition fault mode and fault mode frequency
Than obtaining failure rate using THE PRINCIPAL FACTOR ANALYSIS method and probabilistic reliability design method；
THE PRINCIPAL FACTOR ANALYSIS method refers to the core position for determining that component of machine chife failure models is caused to occur, with core position
Failure rate replaces the failure rate of component of machine；
Probabilistic reliability design method refers to：Working condition according to analysis object determines the Q-percentile life of analysis object, then really
The service life distribution of setting analysis object, the crash rate for determining analysis object is distributed according to the service life；
For each failure mode analysis (FMA), its failure on same layer and upper-layer functionality unit influences；
Step 3：FMECA is carried out to each functional unit on functional unit grade indenture level, it is former to obtain fault mode, failure
Cause, failure influences and quantitative data；
According to the FMECA of each electronic component on minimum indenture level as a result, concluding the fault mode of acquisition functional unit；It will
Lead to the fault mode of the minimum indenture level of whole of a certain fault mode of functional unit as the functional unit fault mode
Failure cause obtains whole failure causes of each fault mode；For each fault mode, it is analyzed to same layer and upper strata
The failure of product influences；
If some functional unit is made of n electronic component or component of machine, λpiFor i-th of electronic component or machinery zero
The failure rate λ of the failure rate of component, the then functional unitpFor：
The frequency ratio acquisition methods of a certain fault mode k of the functional unit are：First, it determines on minimum indenture level i-th
The failure rate λ of j-th of fault mode of electronic component or component of machinemijFor：λmij=λpi·αij, αijFor i-th of electronics
The frequency ratio of j-th of fault mode of component or component of machine；Secondly, whole failure causes of fault mode k are determined
The sum of failure rate, the recursion failure rate λ ' as fault mode kmk；Then, the recursion frequency ratio of fault mode k is obtainedFinally, the normalized of fault mode frequency ratio is carried out, obtains the frequency ratio of physical fault pattern kWherein l represents the fault mode number of the functional unit；
Step 4：The bottom-up component on functional unit grade more than indenture level carries out FMECA, obtains the failure of each component
Pattern, failure cause, failure influences and quantitative data；
Step 5：Final influence, severity grade and the failure of the whole indenture levels of analysis acquisition influence probability number from up to down
According to；
For each component on next layer of initial indenture level, final influence and severity grade are determined, and provide and cause this
The failure that failure influences influences probability；It is aviation electricity generation system on initial indenture level；According to transitive relation, from initially about given layer
It is secondary to minimum indenture level recursion, obtain on each indenture level it is final influence, severity grade and failure influence probability；
Obtaining the failure of each indenture level below initial indenture level influences probability, and specific method is：
If j-th of fault mode FM of i-th of component on a certain indenture levelijOne of failure cause of generation is one under the component
G-th of fault mode FM of h-th of component on indenture levelhg, then obtain failure influence probability process be：
A. FM is analyzedhgTo FMijFailure influence probability β '；
B. FM is obtainedhgFailure influence probability βhg：βhg=βij·β’；βijIt is fault mode FMijFailure influence probability；
Step 6：Density of infection is calculated, it is specific as follows including pattern density of infection and product density of infection：
Step 6.1：Determine the working time of aviation electricity generation system and each building block；
Step 6.2：Determine the density of infection of each fault mode；
If certain component working time is t, the frequency ratio of some fault mode of the component is α, failure rate λp, failure influence it is general
Rate is β, then the density of infection C of the fault modem(h)=α β λpT, wherein, h represents severity grade, Cm(h) representing should
Component at work between the number of stoppages of the severity grade as h is occurred using a certain fault mode in t；
Step 6.3：Determine the density of infection of aviation electricity generation system；If Cr(h) it is generated in t between representing aviation electricity generation system at work
Severity grade be h the number of stoppages, if it in severity grade is the fault mode sum under h that N, which represents aviation electricity generation system,
Then
Step 7：Draw harmfulness matrix diagram, comprehensive analysis aviation electricity generation system or each building block severity grade and density of infection
Or influence caused by pattern density of infection, compare the harmfulness size of fault mode and building block, provide harmfulness sequence.
2. aviation electricity generation system according to claim 1 quantifies HAZAN method, which is characterized in that the step
In 1, aviation electricity generation system is divided into 5 indenture levels：
1) initial indenture level, including aviation electricity generation system in itself；
2) the second indenture level is Field Replaceable Unit grade, including：Generator, controller, influenza device；
3) third indenture level is internal field replaceable units grade, including：It is main to generate stator module, vent valve, processor module, electricity
Source module；
4) the 4th indenture level is functional unit grade, including：Processor monitoring module, freq converting circuit, Surge suppression electricity
Road, voltage voting circuit；
5) minimum indenture level including electronic component and can not be split component of machine.
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| CN105260519B (en) * | 2015-09-25 | 2019-06-28 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of unmanned plane FMECA analysis method |
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| CN110135029B (en) * | 2019-04-29 | 2020-11-03 | 中国电子科技集团公司第二十九研究所 | Failure mode auxiliary identification method |
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| 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 |
| CN111140356B (en) * | 2019-12-25 | 2021-07-27 | 中国人民解放军陆军航空兵学院陆军航空兵研究所 | Fault assessment method and device for helicopter engine fuel system |
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| CN112215377B (en) * | 2020-11-05 | 2024-04-09 | 中国航空工业集团公司西安航空计算技术研究所 | Hardware FMEA method of IMA platform |
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Citations (1)
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Non-Patent Citations (2)
| Title |
|---|
| B737NG航线维护故障模式影响及危害性分析;丰世林;《中国民航飞行学院学报》;20110915;第22卷(第5期);第19-21 * |
| Risk assessment modeling in aviation safety management;WK Lee;《Journal of Air Transport Management》;20061231;第12卷(第5期);第267-273页 * |
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