CN104820892A - Aviation power generation system quantitative hazardness analysis method based on data transmission - Google Patents

Aviation power generation system quantitative hazardness analysis method based on data transmission Download PDF

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CN104820892A
CN104820892A CN201510217129.2A CN201510217129A CN104820892A CN 104820892 A CN104820892 A CN 104820892A CN 201510217129 A CN201510217129 A CN 201510217129A CN 104820892 A CN104820892 A CN 104820892A
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fault
fault mode
generation system
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indenture level
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CN104820892B (en
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赵广燕
王昕�
陈新
孙宇锋
胡薇薇
李亚球
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INST OF AVIATION EQUIPMENT ACADEMY OF AIRFORCE EQUIPMENT PLA
Beihang University
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INST OF AVIATION EQUIPMENT ACADEMY OF AIRFORCE EQUIPMENT PLA
Beihang University
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Abstract

The invention provides an aviation power generation system quantitative hazardness analysis method based on data transmission, and belongs to the technical field of reliability engineering. The method comprises the steps that conventional layers of an aviation power generation system are divided; FMECA analysis is performed on electronic parts and components or mechanical parts and components on the lowest conventional layer; FMECA analysis is performed on all functional units on the functional unit level conventional layer; FMECA analysis is performed on components on the conventional layers above the functional unit level from the bottom to the top; final influence, severe degree level and fault influence probability of all the components on all the conventional layers are obtained via analysis from the top to the bottom; mode hazardous degree and product hazardous degree are calculated; and a hazardness matrix graph is drafted. Quantitative data are acquired to perform accurate quantitative CA analysis, and an inverted V-shaped FMECA analysis flow is provided so that analysis results are more accurate.

Description

A kind of quantitative HAZAN method of aviation electricity generation system transmitted based on data
Technical field
The invention provides a kind of quantitative HAZAN method of aviation electricity generation system, for carrying out quantitative HAZAN to the electromechanical hybrid system containing inconsistent fail data information, belonging to reliability engineering technique field.
Background technology
Along with developing rapidly of modern high technology and industrial construction, the complexity of aviation electricity generation system improves constantly, also more and more higher to the requirement of its reliability.Aviation electricity generation system is generally made up of the part such as controller and generator, is a typical electromechanical hybrid system.Execute the task in process at aircraft, electricity generation system is responsible for aircraft full safety and powers, once it breaks down, certainly will cause significant impact to aircraft, and serious also may cause fatal crass.
Failure mode effect and HAZAN (Failure Mode, Effects and Criticality Analysis, FMECA) method are one of failure prevention analysis methods generally adopted in reliability design analysis.FMECA is made up of Failure Mode Effective Analysis FMEA and HAZAN CA two parts.CA is supplementing and expansion FMEA, the risky priority number method of common method and harmfulness matrix method.Harmfulness matrix method is generally adopted in military domain such as Aeronautics and Astronautics.Harmfulness matrix method is divided into again qualitative analysis and quantitative test two kinds of methods.Quantitative analysis method result is more accurate, but can only adopt analytical approach qualitatively when obtaining failure-rate data.Current engineering only accurately can obtain failure rate and the fault mode frequency ratio of electronic devices and components, and mostly rely on experience to provide related data for circuit more than module level, and it is less for engineering goods fault data information, engineering empirically carries out qualitative analysis mostly, therefore cannot carry out more accurately quantitatively HAZAN to electronic product entirety.Also do not report for work for the consideration product bug transitive relation of aviation electricity generation system and the inconsistent investigation and application of the quantitative CA method affected that waits of data message at present both at home and abroad.
Summary of the invention
The object of the invention is for the deficiencies in the prior art, a kind of quantitative HAZAN method of aviation electricity generation system transmitted based on data is provided.Method provided by the invention a kind ofly considers the quantitative HAZAN method of the situations such as Data Source is inconsistent based on fault effects transitive relation, can provide a kind of for the more objective HAZAN implementation method of aviation electricity generation system for design analysis personnel, simultaneously also for the design improvement of aviation electricity generation system provides foundation.
A kind of quantitative HAZAN method of aviation electricity generation system transmitted based on data provided by the invention, its concrete steps are as follows:
Step 1: the indenture level dividing aviation electricity generation system.
1) the structure composition of aviation electricity generation system is determined;
2) form according to the structure of product, product is divided into several indenture levels from top to bottom, wherein independently functional unit is an indenture level, the component of machine that minimum indenture level is electronic devices and components or can not be split.
Step 2: carry out FMECA analysis to the electronic devices and components on minimum indenture level or component of machine, obtains fault mode, fault effects and quantitative data; Wherein quantitative data comprises fault mode frequency ratio and crash rate;
For electronic devices and components, estimate to search handbook GJB299C-2006 to obtain fault mode and fault mode frequency ratio from reliability of electronic equipment, adopt Stress Analysis Method to obtain failure rate;
For component of machine, according to outfield statistics or like product data acquisition fault mode and fault mode frequency ratio, THE PRINCIPAL FACTOR ANALYSIS method and probabilistic reliability method for designing is utilized to obtain failure rate;
Described THE PRINCIPAL FACTOR ANALYSIS method refers to the core position of determining to cause component of machine chife failure models to occur, and replaces the failure rate of component of machine by the failure rate at core position;
Described probabilistic reliability method for designing is: according to the Q-percentile life of the duty determination analytic target of analytic target, then determines the life-span distribution of analytic target, determines the crash rate of analytic target according to life-span distribution;
For each failure mode analysis (FMA) its to the fault effects of same layer and upper-layer functionality unit.
Step 3: carry out FMECA analysis to each functional unit on functional unit level indenture level, obtains the fault mode of functional unit, failure cause, fault effects and quantitative data etc.;
According to the FMECA result of each electronic devices and components on minimum indenture level, conclude the fault mode obtaining functional unit; To the failure cause of fault mode as this fault mode of functional unit of the whole minimum indenture level of a certain fault mode of functional unit be caused, obtain whole failure causes of each fault mode; For each fault mode, analyze its fault effects to same layer and upper strata product.
If certain functional unit is made up of n electronic devices and components or component of machine, λ pibe the failure rate of i-th electronic devices and components or component of machine, then the failure rate λ of this functional unit pfor:
The frequency ratio acquisition methods of a certain fault mode k of this functional unit is: first, determines the failure rate λ of a jth fault mode of i-th electronic devices and components or component of machine on minimum indenture level mijfor: λ mij=λ piα ij, α ijit is the frequency ratio of a jth fault mode of i-th electronic devices and components or component of machine; Secondly, the failure rate sum of whole failure causes of fault mode k is determined, as the recursion failure rate λ ' of fault mode k mk; Then, the recursion frequency ratio of fault mode k is obtained finally, carry out the normalized of fault mode frequency ratio, obtain the frequency ratio of physical fault pattern k wherein l represents the fault mode number of this functional unit.
Step 4: bottom-uply carry out FMECA analysis to the parts on the above indenture level of functional unit level, according to the method for step 3, obtains the fault mode of each parts on whole indenture level, failure cause, fault effects and quantitative data;
Step 5: from up to down analyze the final impact of each parts on the whole indenture level of acquisition, severity grade and fault effects probability;
For lower one deck of initial indenture level, analyze and finally affect, and severity grade, and provide the fault effects probability causing this fault effects; According to transitive relation, from initial indenture level to minimum indenture level recursion, obtain final impact and the severity grade of all indenture levels;
Obtain the fault effects probability of each indenture level of below initial indenture level, concrete grammar is:
If a jth fault mode FM of a certain indenture level i-th parts ijone of failure cause occurred is g fault mode FM of h parts on its next indenture level hg, then the process obtaining fault effects probability is:
A. FM is analyzed hgto FM ijfault effects probability β ';
B. FM is obtained hgfault effects probability β hg: β hg=β ijβ '; β ijfault mode FM ijfault effects probability.
Step 6: calculate density of infection, comprise pattern density of infection and product density of infection, specific implementation step is as follows:
Step 6.1: the working time t determining aviation electricity generation system and each building block;
Step 6.2: the density of infection determining each fault mode;
If certain component working time is t, the frequency ratio of certain fault mode of these parts is α, failure rate is λ p, fault effects probability is β, then the density of infection C of this fault mode m(h)=α β λ pt, wherein, h represents severity grade, and setting h has four grades, C mh () represents the number of stoppages that h grade occurs with a certain fault mode in t between these parts operationally;
Step 6.3: the density of infection determining aviation electricity generation system; If C rh () represents that the severity grade produced in t between aviation electricity generation system is operationally the number of stoppages of h, if N represents the fault mode sum of aviation electricity generation system under severity grade is h, then C r ( h ) = Σ i N C m ( h ) .
Step 7: draw harmfulness matrix diagram, the comprehensive impact analyzed aviation electricity generation system or each building block severity grade and density of infection or pattern density of infection and cause, compares the harmfulness size of fault mode and building block, provides harmfulness sequence.
Relative to prior art, the inventive method tool has the following advantages and good effect:
(1) the Data Source analytical approach of all kinds of components and parts and parts in electricity generation system is given, the quantitative data information such as failure rate, fault mode frequency ratio of different object is obtained, for quantitative CA analysis provides data basis accurately respectively by Stress Analysis Method and THE PRINCIPAL FACTOR ANALYSIS method, probabilistic reliability method for designing.
(2) give the quantitative calculation method based on bottom data and the functional unit of fault effects transitive relation and the data such as failure rate, fault mode frequency ratio of above level product, comparing provides related data based on experience, has more accuracy.
(3) reverse V-shaped FMECA analysis process is given, i.e. bottom-up parse high-rise fault effects, fault mode, the final impact of from up to down backtracking and severity grade.Compare in GJB 1391 the bottom-up analytic process provided, analysis result has more accuracy, is convenient to designer and analyzes.Because if indenture level is greater than 3 grades, when product bottom, designer is difficult to Direct Analysis and obtains the fault effects of bottom components and parts to initial indenture levels such as aircrafts, and analysis result more easily deviation occurs.
Accompanying drawing explanation
Fig. 1 is aviation electricity generation system of the present invention quantitative HAZAN method flow block diagram;
Fig. 2 is table 1 electricity generation system product composition structure complete list;
Fig. 3 is the schematic diagram in the embodiment of the present invention, electricity generation system being divided into 5 indenture levels;
Fig. 4 is table 2 processor monitoring module FMECA analytical table;
Fig. 5 is table 3 frequency detection circuit FMECA analytical table;
Fig. 6 is table 4 generator FMECA analytical table;
Fig. 7 is table 5 processor module FMECA analytical table;
Fig. 8 is table 6 controller FMECA analytical table;
Fig. 9 is table 7 electricity generation system FMECA analytical table;
Figure 10 is the table 8 controller FMECA analytical table obtained through step 4;
Figure 11 is the table 9 processor module FMECA analytical table obtained through step 4;
Figure 12 is the table 10 processor monitoring module FMECA analytical table obtained through step 4;
Figure 13 is the table 11 frequency detection circuit FMECA analytical table obtained through step 4;
Figure 14 is the table 12 generator FMECA analytical table obtained through step 4;
Figure 15 is controller harmfulness matrix diagram;
Figure 16 is generator failure pattern harmfulness matrix diagram.
Embodiment
Below in conjunction with drawings and Examples, the present invention is described in further detail.
The quantitative HAZAN method of aviation electricity generation system transmitted based on data provided by the invention, that based on GJB299C, the quantitative data information such as failure rate, fault mode frequency ratio is determined to the electronic component portions in electricity generation system, based on main factor defining method and mechanical probabilistic reliability method for designing, the data such as its failure rate are determined to non-electrical part, on this basis, based on the transitive relation between fault mode, reason and impact, accurate calculating product density of infection Cr at different levels, the CA completing aviation electricity generation system entirety analyzes.The quantitative HAZAN method of aviation electricity generation system of the present invention, supplements existing HAZAN method and assists, making analysis result more accurate.
Following examples carry out implementing according to flow process as shown in Figure 1, mainly comprises parts such as dividing aviation electricity generation system indenture level, minimum indenture level object FMECA analysis, functional unit and above level object FMECA analysis, the calculating of product density of infection.The present embodiment analytic target is certain aviation electricity generation system, for simplifying the analysis, and the selective analysis electronic section of controller and the non-electrical part of generator.Aviation electricity generation system mainly comprises the LRU such as controller and generator, specifically contain again the internal field replaceable unitses such as processor module, discrete magnitude collection and output module, a main stator module, a main rotor assembly, and components and parts and the parts such as the functional unit such as frequency detection circuit, surge restraint circuit circuit and capacitor, resistor, diode, iron core, winding, O-ring seal.
Step 1: carry out indenture level division to aviation electricity generation system, determines the hierarchical relationship of analytic target.The structure composition of aviation electricity generation system and numbering thereof are as shown in the table 1 of Fig. 2, and indenture level as shown in Figure 3.Give the composition structure of portioned product in electricity generation system in table 1, such as, under generator, comprise 101 bleeder resistances, 102 wave filters etc.
In the embodiment of the present invention, according to electricity generation system function and design feature, aviation electricity generation system is carried out indenture level division from top to bottom, the assembly that minimum indenture level is electronic devices and components or can not be split, independently functional unit is an indenture level.As shown in Figure 3, aviation electricity generation system is divided into 5 indenture levels.
1) initial indenture level, is analytic system itself: electricity generation system;
2) the second indenture level, is LRU level, comprises: generator, controller, influenza device;
3) the 3rd indenture level, is internal field replaceable units level, comprises: main stator module, air release, processor module, power module etc.;
4) the 4th indenture level, is functional unit level, comprises: processor monitoring module, freq converting circuit, surge restraint circuit, voltage voting circuit etc.;
5) minimum indenture level is electronic devices and components and can not be split component of machine, comprising: resistance, electric capacity, diode, iron core, winding, valve, O-ring seal etc.
For a certain product, it is positioned at product on an indenture level or assembly, and its all components or product are positioned at below on indenture level.Such as, the generator on the second indenture level in Fig. 3, the assembly on the minimum indenture level of generator is positioned at the components and parts that on the 3rd indenture level, each assembly of generator comprises and the component of machine that can not be split.For controller, on minimum indenture level is the electronic devices and components that each functional module of controller on the 4th indenture level comprises.
Step 2: minimum indenture level FMECA analyzes.For dissimilar minimum indenture level object, carry out FMECA respectively and analyze, specifically comprise the content such as acquisition of fault mode, fault effects, quantitative data, detailed process is as follows:
1) to form the minimum indenture level object-electronic devices and components of the controller of electricity generation system, carry out FMECA work, detailed process has:
A) according to the composition in table 1, fault mode, the fault mode frequency ratio of handbook GJB299C-2006, searching electronic devices and components is estimated from reliability of electronic equipment.As: 2101012 class ceramic capacitor C1, search GJB299C-2006 reliability of electronic equipment and estimate handbook, obtain fault mode and have three kinds: open circuit, short circuit and parameter drift, fault mode frequency ratio α is respectively 16%, 73%, 11%.Fault mode frequency is also referred to as fault mode number percent.
B) according to circuit design, utilize Stress Analysis Method to calculate the crash rate of electronic devices and components, the failure rate obtaining 2101012 class ceramic capacitor C1 is 1.376E-8 (/h).Failure rate also claims crash rate.
2) to form the minimum indenture level object-component of machine of the generator of electricity generation system, carry out FMECA work, detailed process has:
A) form according to table 1, for component of machine, according to outfield statistics or like product data, obtain fault mode and the fault mode frequency ratio of non-electric parts.Outfield statistics refers to the statistics to the fault data that product occurs in the process of the test of outfield; Like product data refer to the fault data verified through internal field verification experimental verification or field trial that the product similar to aviation electricity generation system to be analyzed has, and wherein like product refers to the product in function, structure, material, technique etc. with aviation electricity generation system to be analyzed with more than 90% similarity.In statistics, the information such as the direct record trouble pattern of big city, time of origin, occurrence condition, directly therefrom can obtain fault mode; Add up the ratio of number of times that a certain assembly or component failure pattern occur and this assembly or component failure generation total degree on this basis, then can draw fault mode frequency ratio information.
B) type of the non-electric parts of labor and feature, choose diverse ways determination crash rate.
I. THE PRINCIPAL FACTOR ANALYSIS method: composition and the chife failure models of analyzing non-electrical component of machine, determines the core position that causing trouble pattern occurs and factor, replaces the crash rate of non-electrical assembly by the crash rate at core position.Send out the object such as stator module, a main rotor assembly for main, adopt the method.Main stator module of sending out is primarily of iron core and winding composition, shown by product performance analysis and a large amount of history field data, main stator module fault of sending out mainly occurs on winding, therefore the crash rate of winding is equivalent to the main crash rate sending out stator module, calculates the crash rate of winding with reference to GJB299C-2006 relevant data.
Ii. probabilistic reliability method for designing: according to the duty of analytic target, using degree theory waits and calculates its Q-percentile life; Then according to the difference of analytic target feature, determine that its life-span distributes; The crash rate of analytic target is determined again according to life-span distribution.For the part such as elastic shaft, main bearing, adopt the method.Physical dimension according to elastic shaft designs, and using degree design theory calculates the reliability coefficient U of elastic shaft r=8.9, it is 0.99990 that its fiduciary level requires.Due to elastic shaft life-span Normal Distribution, can derive its crash rate formula, can be calculated its crash rate for people is 3E-18 (/h).
3) combination product analyzes the fault effects of each fault mode of minimum indenture level to same layer and upper-layer functionality unit.Table 2 as shown in Fig. 4 ~ Fig. 6 ~ table 4.Fault mode coding, fault mode, failure cause, fault effects etc. is given in table.
Step 3: carry out FMECA analysis to each functional unit on functional unit level indenture level, obtains the fault mode of functional unit, failure cause, fault effects and quantitative data etc.
Main contents comprise:
1) according to the FMECA analysis result of minimum indenture level, the fault mode gathering and obtain functional unit is concluded.Conclude from minimum indenture level FMECA analysis result and gather high-rise impact, merge the item of similar impact, and remove " without impact ", remain different fault effectses, as the fault mode of functional unit, front 5 row of table 5, record fault mode coding, fault mode, failure cause, fault effects etc. as shown in Figure 7;
2) will the failure cause of fault mode as this fault mode of functional unit of the whole minimum indenture level of a certain fault mode of functional unit be caused, and obtain whole failure causes of fault mode by that analogy;
3) analyze the fault effects of each fault mode to same layer and upper strata product, the 8th, 9 row of chart 5, describe local influence and upper strata impact;
Based on the failure rate of electronic devices and components on minimum indenture level, according to the division of product indenture level, obtain whole electronic devices and components or the non-electrical component of machine of composition function unit, suppose that certain functional unit is made up of n electronic devices and components or component of machine, the failure rate of i-th electronic devices and components or component of machine is λ pi, then the failure rate λ of this functional unit pfor:
λ p = Σ i = 1 n λ pi - - - ( 1 )
Based on the quantitative data of the electronic devices and components on minimum indenture level or component of machine, utilize fault effects transitive relation, calculate the fault mode frequency ratio α obtaining each functional unit, detailed process is as follows:
(1) the failure rate λ of certain fault mode mfor fault mode frequency ratio α and cell failure rate λ plong-pending, calculate the mode fault rate λ of a jth fault mode of i-th electronic devices and components or component of machine on minimum indenture level mij, be shown below:
λ mij＝λ pi·α ij(2)
Wherein, α ijit is the frequency ratio of a jth fault mode of i-th electronic devices and components or component of machine.
(2) the mode fault rate sum of whole failure causes of computing function unit a certain fault mode k, as the recursion mode fault rate λ ' of this fault mode mk.
(3) by recursion mode fault rate λ ' mkdivided by the failure rate λ of this functional unit p, obtain the recursion fault mode number percent α ' of this fault mode k, as follows:
α k ′ = λ mk ′ λ p - - - ( 3 )
(4) due to " without impact " pattern may be there is, therefore need the normalized of carrying out fault mode number percent, obtain actual fault mode number percent α k, as follows:
α k = α k ′ Σ k = 1 l α k ′ - - - ( 4 )
In formula, l represents the fault mode number of this functional unit.
In the embodiment of the present invention, using formula (1), calculates the failure rate λ of each functional unit p, as shown in the 13rd row of table 5.As: processor monitoring module comprises 70 capacitors and 1 piece of printed board and 1 solder joint set, totally 72 functional units altogether, the failure rate solution procedure of processor monitoring module is:
λ p = Σ i = 1 72 λ pi = 1.376 × 10 - 8 + . . . = 2.0058 × 10 - 6
Utilize fault effects transitive relation, using formula (2) ~ formula (4), calculates the fault mode frequency ratio α of each functional unit, as shown in the 14th row of table 5." watchdog function is abnormal " fault mode as: processor monitoring module is caused by the open circuit of C1, short trouble, the therefore recursion mode fault rate λ ' of " watchdog function is abnormal " this fault mode m1for:
λ′ m1＝∑λ pi·α ij＝1.376×10 -8×16％+1.376×10 -8×73％＝1.225×10 -8
In above formula, ask for the mode fault rate sum of this fault mode whole failure cause on minimum indenture level, in the embodiment of the present invention, in table 5, have two failure causes.
The frequency ratio α ' of this fault mode 1computation process be:
α 1 ′ = λ m 1 ′ λ p = 1.225 × 10 - 8 2.0058 × 10 - 6 = 0.6 %
In table 5, processor monitoring module has 3 fault modes, so the normalization computation process of the frequency ratio of " watchdog function is abnormal " this fault mode is:
α 1 = α 1 ′ Σ k = 1 3 α k ′ = 0.6 0.6 + 51.6 + 35.8 = 0.7 %
The like, calculate the quantitative data of other functional unit indenture levels of electricity generation system, and result inserted in the FMECA table of functional unit circuit, end product is as shown in table 5.
Step 4: according to the method for step 3, bottom-uply carries out FMECA to the parts on the above indenture level of functional unit level, obtains the fault mode of whole indenture level, failure cause, fault effects and quantitative data.
Reference function cell level FMECA analytical approach, analyze based on the FMECA of each parts in each functional module and minimum indenture level, same method carries out FMECA analysis to each parts on a upper indenture level successively, complete the acquisition of the fault mode of each parts on whole indenture level, failure cause, high-rise impact and the quantitative data such as failure rate, fault mode number percent, the such as table 6 shown in Fig. 8 and 9 and table 7.
The FMECA result of each electronic devices and components on known d indenture level, conclude the fault mode of each parts on acquisition d-1 indenture level, adopt step 3 method, for certain parts on d-1 indenture level, to the failure cause of fault mode as this this fault mode of parts of whole d indenture levels of a certain fault mode of these parts be caused, the like obtain whole failure causes of this parts each fault modes.For each fault mode, analyze its fault effects to same layer and upper strata product.Formula (1) ~ (4) can be utilized equally, obtain the failure rate of d-1 indenture level upper-part, the frequency ratio of each fault mode and failure rate.
Step 5: from up to down analyze the final impact of each parts on the whole indenture level of acquisition, severity grade and fault effects probability.
1) for lower one deck of initial indenture level, analyze and finally affect, and severity grade, and provide the fault effects probability β causing this fault effects, in the respective column in the middle of table 7;
2) according to transitive relation, from initial indenture level to minimum indenture level recursion, final impact and the severity grade of all indenture levels is obtained, in the respective column in table 8 ~ table 12;
3) calculate the fault effects probability β of each indenture level, in the respective column in table 8 ~ table 12, the β in the embodiment of the present invention is 1;
In the present invention, if the jth of an a certain indenture level i-th parts fault mode FM ijone of failure cause occurred is g fault mode FM of h parts on its next indenture level hg, then the process obtaining fault effects probability is:
A. FM is analyzed hgto FM ijfault effects probability β ';
B. FM is obtained hgfault effects probability β hg: β hg=β ijβ ';
Wherein, β ' is arranged as the case may be, is all set to 1 in the embodiment of the present invention.β ijfault mode FM ijfault effects probability.
4) supplement other related contents of each layer FMECA form, obtain the table 7 ~ table 12 as shown in Fig. 9 ~ Figure 14.
Step 6: density of infection calculates.Main contents comprise the calculating of pattern density of infection and product density of infection.The implementation procedure of concrete steps 5 is as follows:
Step 6.1: the working time t determining electricity generation system and each building block, in the embodiment of the present invention, t is 2.5h;
Step 6.2: the density of infection C calculating each fault mode m(h), as follows:
C m(h)＝α·β·λ p·t,h＝Ⅰ、Ⅱ、Ⅲ、Ⅳ (5)
If certain component working time is t, the frequency ratio of certain fault mode of these parts is α, failure rate is λ p, fault effects probability is β, then the density of infection of this fault mode is such as formula shown in (5).H represents severity grade, and setting h in the embodiment of the present invention has four grades.C mh () represents the number of stoppages that h grade occurs with a certain fault mode in t between these parts operationally.
Step 6.3: the density of infection determining aviation electricity generation system; If C rh () represents that the severity grade produced in t between aviation electricity generation system is operationally is the number of stoppages of h, if N represents the fault mode sum of aviation electricity generation system under severity grade is h, then:
C r ( h ) = Σ i N C m ( h ) - - - ( 6 )
Using formula (5) and formula (6), insert in the FMECA form of above each layer by the result calculated, in two row after table 7 ~ table 12.
Step 7: draw harmfulness matrix diagram, the comprehensive impact analyzed aviation electricity generation system or each building block severity grade and density of infection or pattern density of infection and cause, compares the harmfulness size of fault mode and building block, provides harmfulness sequence.
With severity grade for horizontal ordinate, density of infection and product density of infection are ordinate in mode respectively, draw the harmfulness matrix diagram of different indenture level object.For controller, its product harmfulness matrix diagram as shown in figure 15.
Can find out, to controller harmfulness size according to density of infection C according to Figure 15 controller harmfulness matrix diagram rorder is from big to small: 21 (processor module) >23 (analogue collection module) >22 (discrete magnitude collection and output module) >24 (internal electric source module) >25 (voltage regulating module) >27 (front panel) >26 (bus bar plate).
For generator, its fault mode harmfulness matrix as shown in figure 16.
Generator failure pattern to harm to the system according to order is from big to small: M101 (generator output voltage pulsation strengthens) >M104 (generator does not have voltage signal to export) >M102 (generator output voltage pulsating quantity does not meet the demands) >M103 (output information of generator reduces).
The present invention establishes based on fault effects transitive relation and considers the quantitative HAZAN method of the situations such as Data Source is inconsistent.Utilize the method, design analysis personnel can carry out more objective HAZAN implementation method to for aviation electricity generation system, also for the design improvement of aviation electricity generation system provides foundation, thus improve the reliability of product.

Claims (2)

1., based on the quantitative HAZAN method of aviation electricity generation system that data are transmitted, it is characterized in that, performing step is as follows:
Step 1: the indenture level dividing aviation electricity generation system;
According to the structure of aviation electricity generation system, aviation electricity generation system is carried out indenture level division from top to bottom; Wherein independently functional unit is an indenture level; The component of machine that minimum indenture level is electronic devices and components or can not be split;
Step 2: carry out failure mode effect and HAZAN (FMECA) to each electronic devices and components on minimum indenture level or component of machine, obtains fault mode, fault effects and quantitative data; Quantitative data comprises frequency ratio and the failure rate of fault mode;
For electronic devices and components, estimate to search handbook GJB299C-2006 to obtain fault mode and fault mode frequency ratio from reliability of electronic equipment, adopt Stress Analysis Method to obtain failure rate;
For component of machine, according to outfield statistics or like product data acquisition fault mode and fault mode frequency ratio, THE PRINCIPAL FACTOR ANALYSIS method and probabilistic reliability method for designing is utilized to obtain failure rate;
THE PRINCIPAL FACTOR ANALYSIS method refers to the core position of determining to cause component of machine chife failure models to occur, and replaces the failure rate of component of machine by the failure rate at core position;
Probabilistic reliability method for designing refers to: according to the Q-percentile life of the duty determination analytic target of analytic target, then determines the life-span distribution of analytic target, determines the crash rate of analytic target according to life-span distribution;
For each failure mode analysis (FMA) its to the fault effects of same layer and upper-layer functionality unit;
Step 3: carry out FMECA to each functional unit on functional unit level indenture level, obtains fault mode, failure cause, fault effects and quantitative data;
According to the FMECA result of each electronic devices and components on minimum indenture level, conclude the fault mode obtaining functional unit; To the failure cause of fault mode as this fault mode of functional unit of the whole minimum indenture level of a certain fault mode of functional unit be caused, obtain whole failure causes of each fault mode; For each fault mode, analyze its fault effects to same layer and upper strata product;
If certain functional unit is made up of n electronic devices and components or component of machine, λ pibe the failure rate of i-th electronic devices and components or component of machine, then the failure rate λ of this functional unit pfor:
The frequency ratio acquisition methods of a certain fault mode k of this functional unit is: first, determines the failure rate λ of a jth fault mode of i-th electronic devices and components or component of machine on minimum indenture level mijfor: λ mij=λ piα ij, α ijit is the frequency ratio of a jth fault mode of i-th electronic devices and components or component of machine; Secondly, the failure rate sum of whole failure causes of fault mode k is determined, as the recursion failure rate λ ' of fault mode k mk; Then, the recursion frequency ratio of fault mode k is obtained finally, carry out the normalized of fault mode frequency ratio, obtain the frequency ratio of physical fault pattern k wherein l represents the fault mode number of this functional unit;
Step 4: bottom-uply carry out FMECA to the parts on the above indenture level of functional unit level, obtains the fault mode of each parts, failure cause, fault effects and quantitative data;
Step 5: from up to down analyze the final impact of the whole indenture level of acquisition, severity grade and fault effects probability data;
For each parts on lower one deck of initial indenture level, determine final impact and severity grade, and provide the fault effects probability causing this fault effects; It initial indenture level is aviation electricity generation system; According to transitive relation, from initial indenture level to minimum indenture level recursion, obtain the final impact on each indenture level, severity grade and fault effects probability;
Obtain the fault effects probability of each indenture level of below initial indenture level, concrete grammar is:
If a jth fault mode FM of i-th parts on a certain indenture level ijone of failure cause occurred is g fault mode FM of h parts on next indenture level of these parts hg, then the process obtaining fault effects probability is:
A. FM is analyzed hgto FM ijfault effects probability β ';
B. FM is obtained hgfault effects probability β hg: β hg=β ijβ '; β ijfault mode FM ijfault effects probability;
Step 6: calculate density of infection, comprise pattern density of infection and product density of infection, specific as follows:
Step 6.1: the working time determining aviation electricity generation system and each building block;
Step 6.2: the density of infection determining each fault mode;
If certain component working time is t, the frequency ratio of certain fault mode of these parts is α, failure rate is λ p, fault effects probability is β, then the density of infection C of this fault mode m(h)=α β λ pt, wherein, h represents severity grade, C mthe number of stoppages that h () represents is h with a certain fault mode generation severity grade in t between these parts operationally;
Step 6.3: the density of infection determining aviation electricity generation system; If C rh () represents that the severity grade produced in t between aviation electricity generation system is operationally the number of stoppages of h, if N represents the fault mode sum of aviation electricity generation system under severity grade is h, then C r ( h ) = Σ i N C m ( h ) ;
Step 7: draw harmfulness matrix diagram, the comprehensive impact analyzed aviation electricity generation system or each building block severity grade and density of infection or pattern density of infection and cause, compares the harmfulness size of fault mode and building block, provides harmfulness sequence.
2. the quantitative HAZAN method of aviation electricity generation system according to claim 1, is characterized in that, in described step 1, aviation electricity generation system is divided into 5 indenture levels:
1) initial indenture level, comprises aviation electricity generation system itself;
2) the second indenture level, is LRU level, comprises: generator, controller, influenza device;
3) the 3rd indenture level, is internal field replaceable units level, comprises: main stator module, air release, processor module, power module;
4) the 4th indenture level, is functional unit level, comprises: processor monitoring module, freq converting circuit, surge restraint circuit, voltage voting circuit;
5) minimum indenture level, comprises electronic devices and components and can not be split component of machine.
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