CN105574271A - Active fault tolerant design method of FADS (flush air data sensing) system - Google Patents

Active fault tolerant design method of FADS (flush air data sensing) system Download PDF

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CN105574271A
CN105574271A CN201510947301.XA CN201510947301A CN105574271A CN 105574271 A CN105574271 A CN 105574271A CN 201510947301 A CN201510947301 A CN 201510947301A CN 105574271 A CN105574271 A CN 105574271A
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pressure
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meridian
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fault
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CN105574271B (en
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陈广强
周伟江
杨云军
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China Academy of Aerospace Aerodynamics CAAA
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    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • G06F30/20—Design optimisation, verification or simulation
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F2117/00—Details relating to the type or aim of the circuit design
    • G06F2117/02—Fault tolerance, e.g. for transient fault suppression

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Abstract

The invention relates to an active fault tolerant design method of an FADS (flush air data sensing) system and belongs to the technical field of FADS. According to the active fault tolerant design method, a hierarchical diagnosis strategy is adopted, a pressure sensing point array is mounted on an aircraft to measure pressure at pressure sensing points, then whether faults occur to a meridian is judged according to a similarity relation matrix, a pressure filed fault diagnosis model is used for diagnosing a specific faulted point on the meridian, and whether a reference model or a reconstruction model is called for atmospheric parameter calculation is determined according to the fault condition. The method is accurate in diagnosis, high in efficiency, high in fault tolerant capacity and high in reliability.

Description

A kind of Flush Airdata Sensing System Active Fault Tolerant method for designing
Technical field
The present invention relates to flush airdata sensing system algorithm design, particularly relate to Flush Airdata Sensing System Active Fault Tolerant method for designing, belong to flush airdata sensing system technical field.
Background technology
Flush airdata sensing system (FlushAirDataSensing, FADS) system, rely on array of pressure sensors to measure the pressure distribution of aircraft surface, indirectly obtained the flight atmosphere data such as static pressure, Mach number, the angle of attack, yaw angle by special algorithm.FADS system is that supersonic aircraft obtains the main path of flight atmosphere data as flight control inputs, and the supersonic aircraft particularly for air suction type is particularly important.But pressure measurement point pressure tap very little (usual 1mm ~ 2mm), therefore easily breaks down, as blocking, sensor failure etc.The fundamental purpose of FADS system solution algorithm fault-tolerant design improves the reliability of atmosphere parameter measurement, ensures the safety that flight controls.Algorithm fault-tolerant design refers to that algorithm designs the tolerance of the FADS system failure, namely to refer in running order FADS system one or more pressure tap break down or mistake time, algorithm can automatic Detection and diagnosis, and can take appropriate measures and ensure FADS its specifying measurement precision of system held or maintain its error technology within the acceptable range.According to the difference of fault-tolerant design, Passive fault-tolerant control can be divided into design and Active Fault Tolerant design.The starting point of Passive fault-tolerant control design reduces algorithm to the dependence of single pressure tap ruuning situation, even if when breaking down and without corrective action, and system endure.First Active Fault Tolerant design is wanted automatically to detect in good time and is diagnosed out the fault of pressure tap, then take the strategy of control to fault or process, therefore Active Fault Tolerant design comprises the Configuration design fault diagnosis of system and FADS being resolved to model under normal circumstances.Current FADS algorithm design mainly adopts Active Fault Tolerant layout strategy.First can diagnose quickly and accurately the pressure tap in FADS system, and carry out trouble spot isolation, then adopt corresponding reconstruction model to ensure systems stay, stable, safe operation.And carry out fast to trouble spot, judge it is FADS algorithm fault-tolerant design key issue to be solved accurately.
Current Active Fault Tolerant FADS algorithm mainly adopts the redundancy contrast organizing calculation result to judge more, low to targeted diagnostics efficiency, easily occurs that the fault judged by accident, diagnose is counted less, and only has the pressure of spot pressure and larger could the diagnosis of normal value deviation to be out of order.
Summary of the invention
Technology of the present invention is dealt with problems and is: overcome the deficiency that existing fault-tolerant networks relies on redundancy contrast judgment technology, provide a kind of and diagnose the Flush Airdata Sensing System Active Fault Tolerant method for designing accurate, efficiency is high, fault-tolerant ability is strong, reliability is high.
Technical solution of the present invention is: adopt layering Diagnostic Strategy, the pressure of each pressure tap of pressure tap array measurement is first installed on board the aircraft, then applications similar maxim of relation judges whether meridian exist fault, re-use concrete trouble spot on pressure field fault diagnosis model diagnosis meridian, determine to call benchmark model or reconstruction model according to failure condition and carry out atmospheric parameter and resolve.Specifically comprise the following steps:
Vehicle nose's shell is installed counts as the pressure tap array of N, N is odd number, and N=1+4 × M, M is the integer of >=2, pressure tap array is installed as follows: with Vehicle nose's shell summit for three-dimensional coordinate initial point, aircraft is axisymmetric body, rotational symmetry face is XY coordinate plane, it is X-axis positive dirction along Vehicle nose to bottom direction, Y-axis is perpendicular to X-axis, it is Y-axis positive dirction above aircraft, the vertical XY coordinate plane of Z axis, meet screw law, pressure tap point three cross sections in X-axis positive dirction are installed, first cross section was the plane that initial point is vertical with X-direction, 1 pressure tap is installed, second cross section and the 3rd cross section all with the first cross-section parallel, second cross section and initial point keep a segment distance to make its equivalent diameter be not less than 50mm, i.e. d >=50mm, d is the equivalent diameter of aircraft skin on the second cross section, 2 × M pressure tap installed by the aircraft skin in the second cross section, 3rd cross section is positioned at the aircraft xsect of distance the second cross section >=1 × d, this cross section is also installed 2 × M pressure tap, and the pressure tap of the 3rd arbitrary pressure tap in cross section and the second relevant position, cross section and 3, Vehicle nose's shell summit are point-blank, form meridian, have 2 × M meridian,
The installation of 2 × M the pressure tap in the second cross section and the 3rd cross section can take the following two kinds mode to install according to the difference of the concrete shape of aircraft:
When aircraft be conical wait symmetric body up and down time the second cross section and 2 × M the pressure tap in the 3rd cross section all along the symmetrical installation of Z axis: the positive negative direction of Z axis respectively installs 1 point, and the direction shell of positive and negative Y-axis respectively installs M-1 point, M-1 Ge Dian uniform layout.
When aircraft upper and lower asymmetric, can according to 2 × M the pressure tap in actual conditions second cross section and the 3rd cross section along the asymmetric installation of Z axis: positive Y-direction installs 1 point, the positive negative direction of Z axis respectively installs 1 point, and remaining 2 × M-3 Ge Dian uniform layout bears on two quadrant shells in Y-direction.
(2) the pressure P of each pressure tap in Vehicle nose's pressure array is gathered i, i=1 ~ N;
(3) judge each pressure tap pressure in pressure array whether in pressure transducer range ability, if not in pressure transducer range ability, then judge that this point is as trouble spot, rejects this point; If there is >=4 × M-5 pressure measurement to count pressure not in pressure transducer range ability, then this fault-tolerant processing terminates, otherwise, proceed to next step;
(4) judge whether according to similarity relation criterion model the meridian having trouble spot, if there is not out of order meridian, then call benchmark and resolve Models computed flight atmosphere data, if there is out of order meridian more than half, then fault-tolerant processing terminates, otherwise, proceed to next step.
The pressure values of the pressure tap in any two meridian chosen by described similarity relation criterion model: P j, P k, P l, P m, P jand P lbe respectively a two some pressure meridian being positioned at the second cross section and the 3rd cross section, P kand P mbe respectively two the some pressure another meridian being positioned at the second cross section and the 3rd cross section, calculate: F i=(P j/ P k)/(P l/ P m), wherein c is permutation and combination, judges F ivalue with 1 Error Absolute Value whether in pre-determined threshold, if in pre-determined threshold, then think this F itwo involved meridian do not have fault, if not in thresholding, then think this F itwo involved meridian have fault, calculate all F ivalue, obtain likely out of order meridian, then according to the F in scope iget rid of and wherein do not have out of order meridian, final diagnosis which meridian concrete breaks down.
(5) adopt pressure field fault diagnosis model to find out the trouble spot existed in fault meridian, then call reconstruct and resolve model solution acquisition flight atmosphere data.
The disposal route of described pressure field fault diagnosis model is: first get rid of pressure tap in all fault meridians, sets up other pressure and possible trouble spot pressure P ifuntcional relationship, obtain the pressure tap predicted value P that wherein may break down a little xi, this point with by diagnostic points measured value P irelatively should meet following condition:
(P i-P xi)/P xi≤b i
In formula:
I is the pressure tap numbering in fault meridian;
P ifor by the measured value of pressure tap pressure;
P xifor the predicted value of pressure tap pressure;
Bi represents the deviation threshold that requirement differentiates out;
If P xiwith P icompare and do not meet above-mentioned condition, then can judge p ibreak down, otherwise, p inon-fault.
Benchmark model is that the FADS that application 1+4 × M pressure tap is set up resolves model.
Reconstruction model is then diagnosis be out of order a little to be rejected, and the FADS applying the foundation of remaining pressure tap resolves model.
The present invention compared with prior art beneficial effect is:
(1) the present invention is more accurate than the diagnosis of existing redundancy contrast judgment technology, efficiency is high.
(2) the diagnosable fault of the present invention is counted many, can reach at most 4 × M-5, adopts existing redundancy to contrast judgment technology algorithm complicated, owing to being subject to time restriction, generally can only diagnose 2 ~ 3 trouble spots.
(3) fault tolerant of the present invention is counted many, and can reach at most the fault-tolerant ability of 4 × M-6 trouble spot, reliability is high.
Accompanying drawing explanation
Fig. 1 is 9 FADS pressure tap array of figure (M=2, symmetrical installation) in the embodiment of the present invention 1;
Fig. 2 is 13 FADS pressure tap array of figure (M=3, asymmetric installation) in the embodiment of the present invention 2;
Fig. 3 is Flush Airdata Sensing System Active Fault Tolerant method for designing process flow diagram of the present invention;
Fig. 4 is p in the embodiment of the present invention 1 2pressure tap measured deviation is to F 2affect analogous diagram;
Fig. 5 is p in the embodiment of the present invention 1 2pressure tap measured deviation is to F 3affect analogous diagram;
Fig. 6 is p in the embodiment of the present invention 1 2pressure tap measured deviation is to F 5affect analogous diagram;
Fig. 7 is different deviation p in the embodiment of the present invention 1 1the testing result of pressure tap;
Fig. 8 is different deviation p in the embodiment of the present invention 1 2the testing result of pressure tap.
Embodiment
Below in conjunction with the drawings and specific embodiments, the present invention is described in further detail:
Embodiment 1
The present embodiment describes specific implementation process of the present invention in detail for 9 pressure tap layouts (i.e. M=2): (1) installs 9 pressure taps in Vehicle nose, 9 pressure tap layouts as shown in Figure 1, with Vehicle nose's shell summit for three-dimensional coordinate initial point, aircraft is axisymmetric body, axis of symmetry is Y-axis, with its rotational symmetry face for XY coordinate plane, is X-axis positive dirction perpendicular to Y-axis along aircraft center line direction, the vertical XY coordinate plane of Z axis, and meets screw law.1 pressure tap p is arranged on Vehicle nose's shell summit 1, the aircraft skin of the xsect (the equivalent diameter d of this xsect is 100mm) of distance aircraft summit 300mm is evenly arranged 4 pressure tap (p 2, p 3, p 4, p 5), these 4 pressure taps lay respectively on 0 °, 90 °, 180 °, 270 ° directions, as shown in Figure 1.This mounting means belongs to full symmetric and is uniformly distributed, and being particularly suitable for aircraft is the conical situation waiting symmetric body up and down, and the aircraft skin of the xsect of distance aircraft summit 500mm is evenly arranged 4 pressure tap (p 6, p 7, p 8, p 9), p 1, p 3and p 7point-blank, a meridian (137 meridian) is formed, p 1, p 2, p 6form another meridian (126 meridian), p 1, p 4and p 8form a meridian (148 meridian), p 1, p 5and p 9form a meridian (159 meridian), have 4 meridian.
(2) as shown in Figure 3, pressure P1 ~ the P9 of each pressure tap of Real-time Collection, judge 9 pressure tap pressure in pressure array successively whether in pressure transducer range ability, if not in pressure transducer range ability, then judge that this point is as trouble spot, this point is rejected, continue to judge whether remaining point exceedes range ability, judge that a little the rear pressure tap to exceeding range ability is added up, if there are 3 pressure measurement to count pressure not in range ability, exit fault-tolerant processing process, now, need to detect all pressure tap sensors whether normally work or whether normally connect, the pressure transducer of timely replacing pressure tap ensures that whole test macro normally works, otherwise, proceed to next step,
(3) feature being rotational symmetry profile according to Vehicle nose sets up pressure tap force value similarity relation as criterion, and diagnosis exists the meridian of fault.For 9 pressure tap layouts (i.e. M=2), profile as shown in Figure 1, because the second cross section is vertical with X-axis and parallel with the 3rd cross section, the difference of the second cross section pressure tap pressure in each any two meridian and the pressure tap pressure ratio in the 3rd cross section is very little, can approximately equal, therefore, for 9 pressure tap arrays, definable F 1=(P5/P3)/(P9/P7), F 2=(P4/P2)/(P8/P6), F 3=(P2/P5)/(P6/P9), F 4=(P4/P8)/(P5/P9), F 5=(P3/P2)/(P7/P6), F 6=(P3/P4)/(P7/P8), judges F ivalue with 1 Error Absolute Value whether in pre-determined threshold, if in pre-determined threshold, then think this F itwo involved meridian do not have fault, if not in thresholding, then think this F itwo involved meridian have fault, calculate all F ifault meridian comprehensive diagnos which meridian concrete that value is determined or got rid of breaks down.Choosing of this pre-determined threshold has relation with the fault that will detect, the general fault that will detect and actual value deviation less, the threshold value preset is less, but thresholding can not lower than the measurement noises scope of pressure, lower than the easy noise interference of pressure measurement noise, true fault point cannot be judged.The present embodiment chooses 10% as threshold value, lists pressure tap p respectively in Fig. 4 ~ Fig. 6 2load 0 and 25% deviation time F 2, F 3and F 5value, horizontal ordinate is catalogue number(Cat.No.), and sample frequency is 100Hz, and ordinate is F ivalue, P in figure i_ error is the error loaded.Can draw as pressure tap p from figure 2when loading 0 deviation, F 2, F 3and F 5value near 1, and F after loading the deviation of 25% 2, F 3and F 5value>=1.15 or≤0.85, with 1 absolute value of the bias beyond 10% threshold range, and other does not comprise p 2f 1, F 4and F 6value and 1 absolute value of the bias within 10%.Assuming that p 2the meridian at place breaks down, F 2, F 3and F 5value display overrun, determine that 4 meridian all may have fault, and F 1in scope, infer 159 meridians and 137 meridian non-fault, F 4in scope, infer 148 meridians and 159 meridian non-fault, F 6in scope, infer 137 meridians and 148 meridian non-fault, comprehensive analysis can get rid of 159,148,137 meridians, determines that 126 meridians exist fault.
By F idefinition known, F irelevant to the pressure tap in any two meridian, have nothing to do, due to F with the pressure tap in other meridians ibe the result that in all meridians, optional two meridian calculate, so when some pressure taps break down, this point only can have influence on associated F ithe F that other meridian had no truck with calculates can not be had influence on i, therefore this method accuracy of judgement, is not easy to cause erroneous judgement.
(4) then according to breaking down a meridian line position, reject the spot pressure build-up pressure field model that fault meridian relates to, then applying pressure field model diagnoses concrete position of failure point on this fault meridian.In previous step, diagnose out 126 meridians to break down in this enforcement in example, get rid of the spot pressure p on this meridian 1, p 2and p 6, choose remaining p 3, p 4, p 5, p 7, p 8, p 9the pressure field model of pressure by setting up based on the Nonlinear Mapping relation of BP neural net method, this model obtains P respectively 1, P 2and P 6predicted value: P x1, P x2and P x6, these three pressure tap pressure predicted values compared with measured value, just can judge which point has fault, concrete decision method is: suppose that bi represents the required deviation differentiated out, i.e. P ip is then thought more than bi with exact value deviation ibreak down and need p idetect.This point with by diagnostic points measured value P irelatively should meet following condition:
(P i-P xi)/P xi≤ b i(1) in formula:
I is the pressure tap numbering in all fault meridians;
P ifor by the measured value of pressure tap pressure;
P xifor the predicted value of pressure tap pressure;
Bi represents the deviation threshold that requirement differentiates out;
If P xiwith P icompare and do not meet above-mentioned condition, then can judge P ibreak down, otherwise, P inon-fault.
Still for 9 pressure tap arrays, setting bi represents in 20%, Fig. 7 to work as p 1diagnostic result of the present invention when pressure tap pressure and actual value deviation are-20% ,-15% ,-10%, 20%, 30%, 40%, represents in Fig. 8 and works as p 2diagnostic result of the present invention when pressure tap pressure and actual value deviation are-30% ,-25% ,-20%, 15%, 25%, 30%, horizontal ordinate in figure is the pressure tap time history of test, the value of ordinate flag is failure identification, equal 1 and be diagnosed as fault, equal 0 and be diagnosed as non-fault, P1* is p 1the input pressure values of pressure tap, as can be seen from the figure p 1point diagnosis deviation for lower than-20% or higher than 40% time can free from errors be diagnosed, p 2~ p 9point diagnosis deviation for lower than-30% or higher than 30% time can free from errors be diagnosed, work as p 1the diagnosis deviation of point is-15% or 30%, p 2~ p 9can be diagnosed to greater probability when the diagnosis deviation of point is-25% or 20%.
According to Flush Airdata Sensing System Active Fault Tolerant method for designing provided by the present invention, judge that there is not out of order meridian then calls benchmark model and resolve according to similarity relation criterion model, otherwise resolve by calling reconstruction model after the localization of faults of pressure field model again, as shown in Figure 3.Benchmark model is that the FADS that the N number of pressure tap of application is set up resolves model, and reconstruction model is then be out of order in diagnosis a little to be rejected, and the FADS applying the foundation of remaining pressure tap resolves model.
The present invention all rejects out of order pressure tap in the diagnosis algorithm of each level, the pressure measurement value of out of order pressure tap can not have an impact to new model, having broken traditional fault-tolerant design adopts redundancy contrast easily to occur the technical bottleneck of mistaken diagnosis, efficiency is high and diagnosis deviation is little, and being finally used for setting up the pressure tap that FADS resolves model is all non-fault point, and calculation accuracy is high.
Embodiment 2
This gives the pressure tap array (i.e. M=3) of 13 pressure tap layouts, in Vehicle nose, 13 pressure taps are installed, as shown in Figure 2, three-dimensional coordinate definition is consistent with embodiment 1, and 1 pressure tap p is arranged on Vehicle nose's shell summit for 13 pressure tap layouts 1, the aircraft skin of the xsect of distance aircraft summit 300mm is evenly arranged 6 pressure tap (p 2, p 3, p 4, p 5, p 6, p 7), these 6 pressure taps adopt along the asymmetric installation of Z axis, p 3be installed on 90 ° of directions, p 2, p 7, p 6, p 5, p 4be installed on 0 ° ,-45 ° ,-90 ° ,-135 ° ,-180 ° directions, the aircraft skin of the xsect of distance aircraft summit 500mm is evenly arranged 6 pressure tap (p again 8, p 9, p 10, p 11, p 12, p 13), the mounting means of each pressure tap is identical with the second cross section, and the pressure tap of the 3rd each pressure tap in cross section and the second relevant position, cross section and 3, Vehicle nose's shell summit are in straight line, form meridian, as shown in Figure 2,6 meridian such as 139,128 are formed altogether.Asymmetric mounting means shown in Fig. 2 is more suitable for the irregular aircraft of profile, and pressure tap layout is more reasonable, and pressure measurement is more accurate, and fault diagnosis is accurate, and the mode of the vertical mirror of the mounting means shown in Fig. 2 still can be adopted to install.
13 pressure tap arrays are more than 9 pressure measurement dot matrix pressure tap numbers, and diagnosable fault is counted many, and counting of fault tolerant is more, and resolve available pressure measurement and count many, system reliability is high, and final flight parameter calculation accuracy is high.
The unspecified part of the present invention belongs to general knowledge as well known to those skilled in the art.

Claims (5)

1. a Flush Airdata Sensing System Active Fault Tolerant method for designing, is characterized in that the method adopts Stratified Strategy, comprises the following steps:
(1) on Vehicle nose's shell, installation is counted as the pressure tap array of N, N is odd number, and N=1+4 × M, M is the integer of >=2, pressure tap array is installed as follows: with Vehicle nose's shell summit for three-dimensional coordinate initial point, aircraft is axisymmetric body, rotational symmetry face is XY coordinate plane, it is X-axis positive dirction along Vehicle nose to bottom direction, Y-axis is perpendicular to X-axis, it is Y-axis positive dirction above aircraft, the vertical XY coordinate plane of Z axis, meet screw law, pressure tap point three cross sections in X-axis positive dirction are installed, first cross section was the plane that initial point is vertical with X-direction, 1 pressure tap is installed, second cross section and the 3rd cross section all with the first cross-section parallel, second cross section and initial point keep a segment distance to make its equivalent diameter be not less than 50mm, i.e. d >=50mm, d is the equivalent diameter of aircraft skin on the second cross section, 2 × M pressure tap installed by the aircraft skin in the second cross section, 3rd cross section is positioned at the aircraft xsect of distance the second cross section >=1 × d, this cross section is also installed 2 × M pressure tap, and the pressure tap of the 3rd arbitrary pressure tap in cross section and the second relevant position, cross section and 3, Vehicle nose's shell summit are point-blank, form meridian, have 2 × M meridian,
(2) the pressure Pi of each pressure tap in Vehicle nose's pressure array is gathered, i=1 ~ N;
(3) judge each pressure tap pressure in pressure array whether in pressure transducer range ability, if not in pressure transducer range ability, then judge that this point is as trouble spot, rejects this point; If there is >=4 × M-5 pressure measurement to count pressure not in pressure transducer range ability, then this fault-tolerant processing terminates, otherwise, proceed to next step;
(4) judge whether according to similarity relation criterion model the meridian having trouble spot, if there is not out of order meridian, then call benchmark and resolve Models computed flight atmosphere data, if there is out of order meridian more than half, then fault-tolerant processing terminates, otherwise, proceed to next step;
(5) adopt pressure field fault diagnosis model to find out the trouble spot existed in fault meridian, then call reconstruct and resolve model solution acquisition flight atmosphere data.
2. a kind of Flush Airdata Sensing System Active Fault Tolerant method for designing according to claim 1, it is characterized in that 2 × M the pressure tap in described second cross section and the 3rd cross section is all installed along Z axis symmetry: the positive negative direction of Z axis respectively installs 1 point, the direction shell of positive and negative Y-axis respectively installs M-1 point, M-1 Ge Dian uniform layout.
3. a kind of Flush Airdata Sensing System Active Fault Tolerant method for designing according to claim 1, it is characterized in that 2 × M the pressure tap in described second cross section and the 3rd cross section is along the asymmetric installation of Z axis: positive Y-direction installs 1 point, the positive negative direction of Z axis respectively installs 1 point, and remaining 2 × M-3 Ge Dian uniform layout bears on two quadrant shells in Y-direction.
4. a kind of Flush Airdata Sensing System Active Fault Tolerant method for designing according to claim 1, is characterized in that: the pressure values of the pressure tap in any two meridian chosen by described similarity relation criterion model: P j, P k, P l, P m, P jand P lbe respectively a two some pressure meridian being positioned at the second cross section and the 3rd cross section, P kand P mbe respectively two the some pressure another meridian being positioned at the second cross section and the 3rd cross section, calculate: F i=(P j/ P k)/(P l/ P m), wherein c is permutation and combination, judges F ivalue with 1 Error Absolute Value whether in pre-determined threshold, if in pre-determined threshold, then think this F itwo involved meridian do not have fault, if not in thresholding, then think this F itwo involved meridian have fault, calculate all F ivalue, obtain likely out of order meridian, then according to the F in scope iget rid of and wherein do not have out of order meridian, final diagnosis which meridian concrete breaks down.
5. a kind of Flush Airdata Sensing System Active Fault Tolerant method for designing according to claim 1, it is characterized in that: the disposal route of described pressure field fault diagnosis model is: first get rid of pressure tap in all fault meridians, set up other pressure and possible trouble spot pressure P ifuntcional relationship, obtain the pressure tap predicted value P that wherein may break down a little xi, this point with by diagnostic points measured value P irelatively should meet following condition:
(P i-P xi)/P xi≤b i
In formula:
I is the pressure tap numbering in fault meridian;
P ifor the measured value of pressure tap pressure;
P xifor the predicted value of pressure tap pressure;
Bi represents the deviation threshold that requirement differentiates out;
If P xiwith P icompare and do not meet above-mentioned condition, then can judge p ibreak down, otherwise, p inon-fault.
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