CN103018027B - Method for exciting faults of airplane brake valve - Google Patents
Method for exciting faults of airplane brake valve Download PDFInfo
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- CN103018027B CN103018027B CN201210521578.2A CN201210521578A CN103018027B CN 103018027 B CN103018027 B CN 103018027B CN 201210521578 A CN201210521578 A CN 201210521578A CN 103018027 B CN103018027 B CN 103018027B
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Abstract
Disclosed is a durability development test accelerating method of an airplane brake valve. A test section is formulated for excitation of hidden wear-out fault dangers of the brake valve, an acceleration effect of exciting hidden fault danger within a short time is achieved, and a performance critical value of the airplane brake valve under the combined action of a stepping environmental condition and a working condition through actual measurement is included in the test requirement and taken as an evidence for determining accelerated durability development test conditions. According to the method, hidden dangers related to high and low temperatures are excited through enlarging assessment force under high temperature and low temperature environments, hidden dangers related to the frequency are excited through accelerating the working efficiency, and hidden dangers related to temperature changes are excited through accelerating temperature change rates; whether the hidden wear-out fault dangers exist in the brake valve is diagnosed through tests, improving suggestions are put forward according to excited hidden fault dangers to eliminate the hidden faults, so that the service life of the brake valve can reach the development requirement. The method has the advantages of being short in test time, low in energy consumption, saving in resources and low in labor costs.
Description
Technical field
The present invention relates to airplane brake system field, specifically a kind of method being excited aircraft brake valve fault by applying environmental stress and working stress.
Background technology
The long-life development of aircraft brake valve is exactly eliminate permanance weak link, improves the index of aging of aircraft brake valve.Long-life checking is the index of aging reached by physical method determination aircraft brake valve.
Current permanance development test object has following 2 points:
A) in Project R&D, completing the work exciting wear-out fault at the appointed time, reaching long-life object by improving consume weak link.Because the time limit, test condition allows to accelerate, and accelerated test method is personal from grinding;
B) when the durability Design of aircraft brake valve, manufacture process level are high, index of aging reaches 10000 constantly little by analysis, and the target of permanance development test is the work completing checking index of aging at short notice.
In prior art, the durability test method of aircraft brake valve does not accelerate, and tests by existing durability test method.When the index of aging of aircraft brake valve is 10000 constantly little, empirically coefficient is the convention of 1.5, and test period is: 10000 rise and fall × 1.5=15000 hour, are equivalent to for 1875 working days.Test period is oversize, is difficult to arrange in development.The long-life that this traditional durability test method can not effectively solve in current Project R&D develops and validation problem.
The endurancing feature of the hydraulic products such as external existing aircraft brake valve has:
A) do not accelerate in test, operating load is pressed test profile and is applied, and when the operating load of brake system is divided into ground turning, landing braking, take-off line to brake, various load is not cut out, and applies in proportion.Make test period identical with service time, consume the energy many, spended time is long, and accurately can not reflect the potential faults of aircraft brake valve.
B) test objective is by inspection, is not excite the potential faults affecting permanance;
C) endurancing is based on normal temperature, and high temperature and low temperature only carry out performance test, can not excite the potential faults of high temperature and low-temperature condition aircraft brake valve.
Summary of the invention
For overcoming the deficiency that can not excite potential faults and the test period length affecting aircraft brake valve existed in prior art, the present invention proposes a kind of accelerated durability development test method of aircraft brake valve.
Detailed process of the present invention is:
Step 1, the frequency of operation unstability value of testing airplane brake valve.Adopt the frequency of operation unstability value of step-by-step method testing airplane brake valve, this step has three test parameters.To the test of aircraft brake valve frequency of operation unstability value from 10 times/min, and increase progressively with the step-length of 2 times/min, the test duration in every step-length is 40min, until test proceeds to the frequency of operation broken down; Ratio between the brake pressure exported and the electric current of input is judged to fault when not meeting linear relationship;
Step 2, testing airplane brake valve is to the reaction of temperature variation.
During the reaction of testing airplane brake valve to temperature variation, the temperature range of setting is-55 ~ 70 DEG C; Specifically, after being placed in by aircraft brake valve of continuous repetition keeps 1h in-55 DEG C of low-temperature test chambers, be transferred in the high-temperature test chamber of 70 DEG C, when high-temperature test chamber temperature reaches 70 DEG C of temperature again, should be linear relationship between the brake pressure that test exports and the electric current of input, brake valve is qualified under this temperature variation condition; Otherwise then described brake valve is defective under this temperature variation condition, test terminates;
Aircraft brake valve testing table is 15min from the process shifted in high-temperature test chamber in low-temperature test chamber by described first time, and after this each process decrements 1 ~ 2min from shifting in high-temperature test chamber in low-temperature test chamber, until when described transfer process is decremented to 1min, test terminates;
When aircraft brake valve is transferred to after in high-temperature test chamber in low-temperature test chamber, whether the ratio between the brake pressure that test exports and the electric current of input is linear relationship, if the ratio between the brake pressure exported and the electric current of input is linear relationship, prove the designing requirement that this aircraft brake valve satisfied temperature changes; Otherwise then prove that this aircraft brake valve does not meet the designing requirement of temperature variation, need to carry out the improvement for improving temperature control, test terminates;
Step 3, determines the low temperature critical value of aircraft brake valve
The environmental qualification test low temperature of aircraft brake valve is-55 DEG C; In test, each temperature spot aircraft brake valve output pressure is tested respectively between-55 DEG C ~-65 DEG C, when pass between the electric current that control enclosure inputs to brake valve and aircraft brake valve output pressure is linear relationship, the output pressure of this aircraft brake valve is qualified, continues next step test; If when control enclosure is non-linear to the pass between the input current of brake valve and aircraft brake valve output pressure, then prove that the output pressure of this aircraft brake valve is defective, end of test.
Step 4, determines the high temperature critical value of aircraft brake valve
The initial temperature of the environmental qualification test of aircraft brake valve is 70 DEG C; In test, the output pressure of each temperature spot aircraft brake valve is tested respectively between 70 DEG C ~ 80 DEG C, be linear relationship when being input to the pass between the electric current of brake valve and aircraft brake valve output pressure from control enclosure, the output pressure of this aircraft brake valve is qualified, continues next step test; If the pass between input current and aircraft brake valve output pressure is nonlinear relationship, then the output pressure of this aircraft brake valve is defective, end of test.
Step 5, determines resonance frequency and the vibration value of aircraft brake valve
During testing airplane brake valve vibration value, aircraft brake valve is carried out to the swept-sine vibration test of 10Hz ~ 1000Hz.Specifically, under different vibration values, progressively swept-sine vibration test is carried out successively respectively; The frequency of described sine sweep is from 10Hz, until terminate during 1000Hz.In test, if the input current of aircraft brake valve and aircraft brake valve output pressure are linear relationship, then carry out the swept-sine vibration test of next vibration value, repeat described process, until described vibration value reaches actual vibration value 1.5 times; When the input current of aircraft brake valve and aircraft brake valve output pressure are nonlinear relationship, prove that this aircraft brake valve performance is defective, terminate test, this aircraft brake valve is improved.
Step 6, determines the operating load applied in process of the test
Operating load comprises control enclosure to the input current of brake valve and output pressure corresponding to brake valve
The working stress that aircraft brake valve in use bears comprises take-off line brake pressure, the differential brake pressure of landing antiskid brake pressure and ground.
Step 7, determines accelerated test condition
When determining accelerated test condition:
The first step, cryogenic temperature is-55 DEG C, duration 50min, and control enclosure is to the input current 20mA of brake valve, and brake valve exports brake pressure 10MPa, frequency of operation 16 times/min, work times: 50min × 16 time/min=800 time;
Second step, cryogenic temperature is-55 DEG C, duration 25min, and control enclosure, to the input current 40mA of brake valve, exports brake pressure 20MPa, frequency of operation 16 times/min, work times: 25min × 16 time/min=400 time;
3rd step, high-temperature temperature is 70 DEG C, duration 50min, and control enclosure is to the input current 20mA of brake valve, and brake valve exports brake pressure 10MPa, frequency of operation 16 times/min, work times: 50min × 16 time/min=800 time;
4th step, high-temperature temperature is 70 DEG C, duration 25min, and input electric stress 40mA, exports brake pressure 20MPa, frequency of operation 16 times/min, work times: 25min × 16 time/min=400 time;
5th step, room temperature condition, duration 25min, input electric stress 20mA, exports brake pressure 10MPa, frequency of operation 16 times/min, work times: 25min × 16 time/min=400 time;
6th step, room temperature condition, duration 13min, input electric stress 40mA, exports brake pressure 20MPa, frequency of operation 16 times/min, work times: 13min × 16 time/min=208 time;
Step 8, accelerated durability test
The first step: determine test period.
Second step: test.At the end of second section B interval, carry out temperature shock test to brake valve, occur stress-free fault to aircraft brake valve during brake valve input 40mA electric current, test stops.Carry out the supporting gap of guiding valve to exciting out of order brake valve to improve.
Step 9, again carries out temperature shock to the brake valve after improvement and excites fault test; Again accelerated durability test is carried out, to excite fault to the brake valve after improving.Described temperature shock of again carrying out excites fault test to be circulation step 7 and step 8 totally 15 times, the content of the test of the test profile defined that circulated each time;
Step 10, experimental data processing.
Take-off line brake pressure described in step 6 of the present invention and landing antiskid brake pressure are determined according to designing requirement, and wherein: when input current is 40mA, take-off line brake pressure is 20MPa; When input current is 20mA, landing antiskid brake pressure is 10MPa.
In step 5 of the present invention, the lowest vibration value of aircraft brake valve is 2.5G.
Brake valve to be transferred in low-temperature test chamber or in high-temperature test chamber time, described brake valve is arranged on hydraulic test bench, hydraulic test bench and brake valve is together transferred in low-temperature test chamber or in high-temperature test chamber.
The present invention is by strengthening high temperature, low temperature environment examination dynamics, and excite and low temperature, hidden danger that high temperature is relevant, whether access control box there will be fault at high temperature, low temperature; By accelerating frequency of operation, excite the hidden danger with frequency dependence; By accelerating rate temperature change, excite the hidden danger relevant with temperature variation.
The present invention forms accelerated durability development test method, is suitable for the application in new product development neutralization batch Production Life test.
The object of accelerated durability development test completes the object exciting fault at short notice, and complete the object of checking durability index at short notice.
The invention discloses a kind of accelerated durability development test method of aircraft brake valve, list the characteristic threshold value of actual measurement aircraft brake valve under stepping environmental baseline and condition of work combined action in testing requirements, as the foundation determining accelerated durability development test condition.
The present invention is carried out compared with the prior art from following aspect:
A) sensitivity of measuring technology performance, the comparison of critical value: the sensitivity of aircraft brake valve performance when existing endurancing technology does not require to determine changes in environmental conditions, but in use there is the environmental baselines such as fast temperature change;
B) comparison of environmental test condition: existing environmental test condition is undertaken by GJB150 " military equipment environmental test method ", only carry out the performance test under environmental baseline, do not carry out the endurancing under environmental baseline, the present invention is classified as endurancing at ambient conditions as main contents, excites wear-out fault at ambient conditions;
C) comparison of operating load: the operating load of prior art comprises the content of the test of ground turning differential movement, the output pressure of differential brake is about 3MPa, pressure value is on the low side, and not enough to the permanance examination effect of elasticity original paper, the present invention has cut out this part content of the test;
D) head of the comparison of test period: the prior art 10000h phase of turning at least takes out two covers each test 15000h, and test period adds up 30000h; Accelerated durability development test can complete content of the test in 100h;
E) comparison of test objective: the durability test of prior art is to verify technology stability, often criticizes to take out and a set ofly carries out durability test; And the object of permanance development test excites and correct wear-out fault, the index of aging of checking aircraft brake valve, when this technology is applied in batch durability test, can play the green effect saved time with resource;
F) comparison of difficulty is tested: prior art has become convention as you know; Accelerated durability development test needs to formulate special test profile, and test profile is determined according to measured data;
G) comparison of testing equipment: prior art will carry out the test routine of temperature return after carrying out high temperature, low-temperature test, and this way does not have the examination effect of temperature shock to brake valve; The accelerated durability development test of brake valve requires that low-temperature test carries out hot test after terminating immediately, realizes the temperature shock examination effect to brake valve.
Accelerated durability development test is for exciting the wear-out fault hidden danger of brake valve to formulate test profile, having the acceleration effect exciting potential faults at short notice.Propose the requirement carrying out permanance development test in brake valve development, propose recommendation on improvement by the result of this test, make product reach long-life, highly reliable technical requirement, reach the object of accelerated durability development test.
The present invention adopts the method for test to diagnose brake valve whether to there is wear-out fault hidden danger, and proposes recommendation on improvement according to inspired potential faults, to eliminate potential faults, makes the life-span of brake valve reach manufacture claim.Because the present invention has energy-saving and cost-reducing green effect, and by the accelerated life test thought of electronic product with reference to using in the present invention, thus the present invention is made to have the advantages that to shorten test period, economize energy, resource and manpower.
Accompanying drawing explanation
Fig. 1 is test profile of the present invention;
Fig. 2 is the vibrational spectra of vibration frequency sweep test;
Fig. 3 is FB(flow block) of the present invention.
Embodiment
The present embodiment carries out accelerated durability development test to the brake valve in certain civil transport brake system, environmental stress and the working stresses such as high temperature, low temperature, temperature shock, vibration is applied by pressing test profile, exciting the wear-out fault of aircraft brake valve, is the method that whether testing airplane brake valve performance is qualified in accelerated durability test.Described wear-out fault refers to that wear-out fault is the fault directly affecting life of product by the fault caused in the consume reasons such as wearing and tearing, aging, corrosion and fatigue.Described aircraft brake valve performance comprises:
A. exporting take-off line brake pressure is: 20MPa;
B. landing antiskid brake pressure 10MPa is exported;
C. export ground to turn differential brake pressure 3MPa.
In the process of the above-mentioned performance of test, apply environmental stress simultaneously, play the object verifying the brake valve life-span under environmental stress, working stress acting in conjunction, in the present invention, the unit in brake valve life-span is h, in the test life time of regulation, there is not wear-out fault, just reach life requirements by No. (1985) 1325, former Commission of Science, Technology and Industry for National Defence literary composition regulation; If there occurs wear-out fault, just propose recommendation on improvement for failure cause, the brake valve after improving is tested according to test profile, more again until reach the life requirements of regulation.
The index of aging of this aircraft brake valve is 10000h.Wear-out fault refers to: wearing and tearing, aging, tired, the fault that causes of corrosion.For brake valve, wear-out fault refers to:
A. spool move around in valve pocket produce wearing and tearing;
B. spool Repeated Compression spring causes spring fatigue;
C. non-metallic seal under the high temperature conditions is aging; The sclerosis of non-metallic seal under cryogenic;
D., under temperature variation condition, the clamping stagnation that expansion and systolic dyssynchrony due to spool, valve pocket produce also belongs to checking scope.
The test period plan of the present embodiment checking 10000h index of aging controls within 100h, the checking work of 15000h is completed by the test period less than 100h, the ratio that two kinds of test methods are taken time is: 15000/100=150, thus plays energy-saving and cost-reducing effect.The working time of test period finger to finger test equipment is exactly the index of aging checking work that testing equipment runs that 100h completes brake valve 10000h.
The aircraft brake valve carrying out accelerated durability development test in the present embodiment must through frequency of operation limit test, and in test process, output pressure is landing braking pressure.
The testing equipment that the present embodiment adopts is prior art, comprising: maximum temperature is the WG213 walk-in type high-temperature test chamber of 180 DEG C; Minimum temperature is the WD713 walk-in type low-temperature test chamber of-70 DEG C; Can carry out electric vibrating system that is sinusoidal and random vibration, thrust is 3 tons; Flow is 40 liters/min, and output pressure is the normal temperature hydraulic power source of 21MPa; The high/low temperature tensimeter of range 40MPa.
The concrete steps of the present embodiment are:
Step 1, the frequency of operation unstability value of testing airplane brake valve.Described frequency of operation unstability value is turned the frequency values of differential brake pressure in take-off line brake pressure, the landing antiskid brake pressure of output and the ground of output exported.
When the frequency of operation unstability value of testing airplane brake valve, adopt stepping method to test, test is carried out at normal temperatures.Detailed process is:
The first step: determine frequency test initial value, initial value is 10 times/min;
Second step: determine increasing progressively of frequency step, it is 2 times/min that step-length increases progressively;
3rd step: determine that the test period in every step-length is 40min.The frequency of operation unstability value of brake valve is tested after off-test; In every step-length time=stabilization time+test duration=30min+10min=40min.
4th step: determine failure criterion.Ratio between the brake pressure exported and the electric current of input is judged to fault when not meeting linear relationship; Failure criterion is: between the brake pressure exported and the electric current of input, do not meet linear relationship, and be judged to fault when dead band electric current exceeds 4 ± 2mA; As: when the dead band electric current of this brake valve is 4mA, if input current is less than 4mA, then output pressure is zero; If input current is greater than 4mA, then input current and output pressure are proportionate relationship, and exist when input current is 20mA, output pressure is 10MPa, and when input current is 40mA, output pressure is the proportionate relationship of 20MPa.
5th step: test: to the test of aircraft brake valve frequency of operation unstability value from 10 times/min, and increase progressively with the step-length of 2 times/min, namely second time test is 12 times/min, and third time test is 14 times/min, until test proceeds to the frequency of operation broken down.In the present embodiment, when test proceeds to 40 times/min, occurring obviously fluctuating, when test frequency is increased to 50 times/min, be nonlinear relationship between output pressure and input current, therefore the 50th time/min is unstability work fault working frequency.
Step 2, testing airplane brake valve is to the reaction of temperature variation.The reaction of described aircraft brake valve to temperature variation be export take-off line brake pressure, output the variation range of landing antiskid brake pressure following temperature whether overproof.
During the reaction of testing airplane brake valve to temperature variation, low at temperature aloft according to aircraft, high in surface temperature, be a temperature-rise period from high-altitude to ground, then carry out antiskid brake on ground, therefore temperature variation requires is the requirement that is rapidly heated.
Test procedure is:
The first step: the testing table being provided with aircraft brake valve is placed in after keeping 1h in-55 DEG C of low-temperature test chambers, is transferred in the high-temperature test chamber of 70 DEG C; When the temperature of high-temperature test chamber reaches 70 DEG C again, whether the ratio of testing immediately between the brake pressure of brake valve output and the electric current of input is linear relationship.If the brake pressure exported and the electric current of input are linear relationship, brake valve is qualified in the temperature test of-55 DEG C ~ 70 DEG C, continues next step test; Otherwise then prove that this aircraft brake valve does not meet the designing requirement of temperature variation, need the improvement of carrying out improving temperature control, test terminates.Described aircraft brake valve testing table is 15min from the process shifted in high-temperature test chamber in low-temperature test chamber, and the temperature of this chamber after transferring to high-temperature cabinet can decline, and when this chamber intensification reaches 70 DEG C again, just can carry out performance test.
Second step: after the testing table being provided with aircraft brake valve is kept 1h in-55 DEG C of low-temperature test chambers, be transferred in the high-temperature test chamber of 70 DEG C, when the temperature of low-temperature test chamber reaches 70 DEG C again, whether the ratio between the brake pressure that test exports and the electric current of input is linear relationship; If the ratio between the brake pressure exported and the electric current of input is linear relationship, carry out next step test; Otherwise then prove that this aircraft brake valve does not meet the designing requirement of temperature variation, need to carry out the improvement for improving temperature control, test terminates.Described aircraft brake valve testing table is 14min from the process shifted in high-temperature test chamber in low-temperature test chamber, and the temperature of this chamber after transferring to high-temperature cabinet can decline, and when this chamber intensification reaches 70 DEG C again, just can carry out performance test.
By that analogy, repeat aircraft brake valve testing table by being transferred in 70 DEG C of high-temperature test chambers in-55 DEG C of low-temperature test chambers, whether the ratio of simultaneously testing between the brake pressure of output and the electric current of input is linear relationship, and each from-55 DEG C of cryogenic boxes to the time shorten 1 ~ 2min of 70 DEG C of high-temperature cabinets.In test, if the ratio between the brake pressure exported and the electric current of input is nonlinear relationship, then prove that this aircraft brake valve does not meet the designing requirement of temperature variation, need to carry out the improvement for improving temperature control, test terminates.In the present embodiment, at every turn from-55 DEG C of cryogenic boxes to the time shorten 1min of 70 DEG C of high-temperature cabinets.
When from-55 DEG C of cryogenic boxes to the time shorten of 70 DEG C of high-temperature cabinets to 1min, test terminates.Rate temperature change between-55 DEG C of described cryogenic boxes and 70 DEG C of high-temperature cabinets reaches 125 DEG C/min.Whether the ratio of simultaneously testing between the brake pressure of output and the electric current of input is linear relationship, if the ratio between the brake pressure exported and the electric current of input is linear relationship, proves the designing requirement that this aircraft brake valve satisfied temperature changes; Otherwise then proving that this aircraft brake valve does not meet the designing requirement of temperature variation, needing to carry out the improvement for improving temperature control;
Step 3, determines the low temperature critical value of aircraft brake valve.The low temperature critical value of described aircraft brake valve be export take-off line brake pressure, output landing antiskid brake pressure when changing at low temperatures whether in the scope of technical manual.
The environmental qualification test low temperature requirements of aircraft brake valve is-55 DEG C, therefore the test starting point of low temperature critical value is defined as-55 DEG C, the method that the present embodiment surmounts environmental qualification test condition derives from GMW8287 standard, by stepping temperature test, find the low temperature potential faults of brake valve, propose recommendation on improvement; Testing procedure is:
The first step: the output pressure of testing airplane brake valve under-55 DEG C of conditions, when control enclosure is linear relationship to the pass between the input current of brake valve and the output pressure of aircraft brake valve, the output pressure of this aircraft brake valve is qualified, carries out next step test.If the pass between input current and aircraft brake valve output pressure is nonlinear relationship, then prove that the output pressure of this aircraft brake valve is defective, end of test, this aircraft brake valve is improved.When control enclosure is 40mA to the maximum current that brake valve exports, the quiet brake pressure that corresponding brake valve exports is 20MPa; When control enclosure is 20mA to the maximum current that brake valve exports, the antiskid brake pressure that corresponding brake valve exports is 10MPa.
Second step: the output pressure of testing airplane brake valve under-60 DEG C of conditions, when control enclosure is linear relationship to the pass between the input current of brake valve and aircraft brake valve output pressure, the output pressure of this aircraft brake valve is qualified, carries out next step test; If the pass between input current and aircraft brake valve output pressure is nonlinear relationship, then prove that the output pressure of this aircraft brake valve is defective, end of test, this aircraft brake valve is improved.When control enclosure is 40mA to the maximum current that brake valve exports, the quiet brake pressure that corresponding brake valve exports is 20MPa; When control enclosure is 20mA to the maximum current that brake valve exports, the antiskid brake pressure that corresponding brake valve exports is 10MPa.
3rd step: testing airplane brake valve output pressure under-65 DEG C of conditions, now, the low temperature critical value of aircraft brake valve has the safe margin of-10 DEG C from-55 ~-65, test terminates.Pass between its input current and aircraft brake valve output pressure is linear relationship, and aircraft brake valve have passed low temperature examination, does not need the design carried out for improving cryogenic property to improve; If the pass between input current and aircraft brake valve output pressure is nonlinear relationship, then prove that the output pressure of this aircraft brake valve is defective, this aircraft brake valve is improved.When control enclosure is 40mA to the maximum current that brake valve exports, the quiet brake pressure that corresponding brake valve exports is 20MPa; When control enclosure is 20mA to the maximum current that brake valve exports, the antiskid brake pressure that corresponding brake valve exports is 10MPa.
Step 4, determines the high temperature critical value of aircraft brake valve.The high temperature critical value of described aircraft brake valve is the take-off line brake pressure of output, whether the landing antiskid brake pressure of output is linear relationship when at high temperature changing.
The environmental qualification test high temperature requirement of aircraft brake valve is 70 DEG C, and therefore the test starting point of high temperature critical value is defined as 70 DEG C, and testing procedure is:
The first step: testing airplane brake valve output pressure under 70 DEG C of conditions, the pass between its input current and aircraft brake valve output pressure is linear relationship, and the output pressure of this aircraft brake valve is qualified, carries out next step test; If the pass between input current and aircraft brake valve output pressure is nonlinear relationship, then prove that the output pressure of this aircraft brake valve is defective, end of test, according to testing program regulation, this aircraft brake valve is improved.When control enclosure is 40mA to the maximum current that brake valve exports, the quiet brake pressure that corresponding brake valve exports is 20MPa; When control enclosure is 20mA to the maximum current that brake valve exports, the antiskid brake pressure that corresponding brake valve exports is 10MPa.
Second step: test under 75 DEG C of conditions, aircraft brake valve output pressure, the pass between its input current and aircraft brake valve output pressure is linear relationship, and the output pressure of this aircraft brake valve is qualified, carries out next step test; If the pass between input current and aircraft brake valve output pressure is nonlinear relationship, then prove that the output pressure of this aircraft brake valve is defective, end of test, this aircraft brake valve is improved.When control enclosure is 40mA to the maximum current that brake valve exports, the quiet brake pressure that corresponding brake valve exports is 20MPa; When control enclosure is 20mA to the maximum current that brake valve exports, the antiskid brake pressure that corresponding brake valve exports is 10Mpa.
3rd step: testing airplane brake valve output pressure under 80 DEG C of conditions, now, the low temperature critical value of aircraft brake valve has the safe margin of 10 DEG C from 70 ~ 80, test terminates.Pass between its input current and aircraft brake valve output pressure is linear relationship, and aircraft brake valve have passed low temperature examination, does not need the design carried out for improving high-temperature behavior to improve; If the pass between input current and aircraft brake valve output pressure is nonlinear relationship, then prove that the output pressure of this aircraft brake valve is defective, this aircraft brake valve is improved.When control enclosure is 40mA to the maximum current that brake valve exports, the quiet brake pressure that corresponding brake valve exports is 20MPa; When control enclosure is 20mA to the maximum current that brake valve exports, the antiskid brake pressure that corresponding brake valve exports is 10MPa.
80 DEG C is the temperature terminating point of high temperature test, higher than environmental appraisal 70 DEG C 10 DEG C.
Step 5, determines resonance frequency and the vibration value of aircraft brake valve.Whether the vibration value of described aircraft brake valve is take-off line brake pressure, the landing antiskid brake pressure of output and the ground of output exported differential brake pressure change under vibrating conditions of turning is linear relationship.The process of testing airplane brake valve vibration value comprises:
The first step, the resonance frequency of testing airplane brake valve.Aircraft brake valve is arranged in electric vibrating system and tests, vibration transducer is attached on aircraft brake valve, open shaking table, carry out the swept-sine vibration of 10Hz to 1000Hz, whether the performance of testing brake valve in frequency sweep vibration processes is qualified, finds the resonant frequency range larger on brake valve impact.In the present embodiment, the maximum thrust of electric vibrating system is 12 tons.
First test under vibration value is the condition of 2.5G, sine sweep is from 10Hz, until terminate during 1000Hz.In test, if the input current of aircraft brake valve and aircraft brake valve output pressure are linear relationship, then carry out next step test; When the input current of aircraft brake valve and aircraft brake valve output pressure are nonlinear relationship, prove that this aircraft brake valve performance is defective, terminate test, this aircraft brake valve is improved.
In next step test, vibration value is 5G, and sine sweep is from 10Hz, until terminate during 1000Hz.In test, if the input current of aircraft brake valve and aircraft brake valve output pressure are linear relationship, then carry out next step test; When the input current of aircraft brake valve and aircraft brake valve output pressure are nonlinear relationship, prove that this aircraft brake valve performance is defective, terminate test, this aircraft brake valve is improved.When control enclosure is 40mA to the maximum current that brake valve exports, the quiet brake pressure that corresponding brake valve exports is 20MPa; When control enclosure is 20mA to the maximum current that brake valve exports, the antiskid brake pressure that corresponding brake valve exports is 10MPa.
Repeat said process, vibration value is adjusted to 8G, sine sweep is from 10Hz, until terminate during 1000Hz.In test, if the input current of aircraft brake valve and aircraft brake valve output pressure are linear relationship, prove that this aircraft brake valve performance is qualified, terminate test.If the input current of aircraft brake valve and aircraft brake valve output pressure are nonlinear relationship, prove that this aircraft brake valve performance is defective, terminate test, this aircraft brake valve is improved.
In the present embodiment, when vibration value is 8G, when sine sweep is 150 ~ 160Hz, is nonlinear relationship between the output pressure of aircraft brake valve and input current, breaks down.Therefore, this aircraft brake valve is at low frequency range job insecurity.When the installation position resonance frequency of aircraft brake valve there will be hydraulic shock close to 150 ~ 160Hz, when installation position resonance frequency is 150 ~ 160Hz, aircraft brake valve there will be the fracture damage phenomenon of the part such as spring, resiliency supported, namely when vibrating value and being increased to 8G, aircraft brake valve there will be the damage that resonance causes, its vibration spectral pattern is shown in Fig. 1, must improve this aircraft brake valve.
Whether meeting design requirement after improvement for detecting the aircraft brake valve broken down, again the test of vibration value being carried out to this aircraft brake valve.The determination of described vibration value must be greater than actual vibration value 1.5 times by engineering experience, and in the present embodiment, vibration value is 19G, and sine sweep is from 10Hz, until terminate during 1000Hz.In test, resonance is there is when sine sweep is 180 ~ 190Hz, but due in reality use, the actual vibration value of aircraft brake valve is only about 10G, therefore the resonance produced to aircraft brake valve without harm, but install this aircraft brake valve time must avoid the frequency zones that sine sweep is 180 ~ 190Hz.
Step 6, determines the operating load applied in process of the test.Operating load comprises electric current that control enclosure inputs to brake valve and the pressure that corresponding brake valve exports.
The pressure that described corresponding brake valve exports is, the take-off line brake pressure of output, the landing antiskid brake pressure of output.
Test whether the change under the condition of vibration and different temperatures of the take-off line brake pressure of described output and the landing antiskid brake pressure of output is linear relationship.
The operating load that aircraft brake valve in use bears comprises take-off line brake pressure, the differential brake pressure of landing antiskid brake pressure and ground.Described take-off line brake pressure and landing antiskid brake pressure are determined according to designing requirement, wherein:
When input current is 40mA, take-off line brake pressure is 20MPa;
When input current is 20mA, landing antiskid brake pressure is 10MPa;
When input current is 6.6mA, the differential brake pressure in ground is 3MPa; .
The test parameters selection range testing the test parameters that obtains and determine according to described parameter is in table 1.
Table 1 tests the one group of parameter obtained and the test parameters selection range summary sheet formulated according to test parameter
In table 1, the parameter value of display is substance and the protection main points of the present embodiment, and test value scope is the concrete implementation data of the present embodiment, is the foundation formulating test condition.Institute fetches data and meets table 1 and just have acceleration effect, if the excessive brake valve that may damage that fetches data, if fetch data and too smallly there is no acceleration effect.
The operating load that the present embodiment is chosen is:
When input current is 40mA, take-off line brake pressure is 20MPa;
When input current is 20mA, landing antiskid brake pressure is 10MPa;
Step 7, determines accelerated test condition.Accelerated test condition comprises following content:
A) high-temperature temperature in a test profile and duration;
B) cryogenic temperature in a test profile and duration;
C) rate temperature change;
D) the normal temperature temperature in a test profile and duration;
E) frequency of operation of brake valve and amplitude;
When f) reaching the test period of life-span checking, the working time of testing equipment.
The life-span unification of brake valve represents with the working hours h of aircraft, the working hours of existing endurancing technology aircraft is equal with the hours run of testing equipment, after the test profile formulating rules employing accelerated durability development test technology of GJB899A, the hours run of testing equipment is less than the working hours of aircraft, shorten test period, serve accelerated test effect.
When determining accelerated test condition:
The first step, cryogenic temperature is-55 DEG C, duration 50min, to the input current 20mA of brake valve, the output brake pressure 10MPa of brake valve, frequency of operation 16 times/min, work times: 50min × 16 time/min=800 time, remove dark duty of skidding and often rise and fall maximum 4 times, 800 tasks are equivalent to 200 times and rise and fall, feeder liner is is often risen and fallen the 2h that about flies, and rises and falls for 200 times and is equivalent to 400h; See that Figure 1A is interval;
Second step, cryogenic temperature is-55 DEG C, duration 25min, to the input current 40mA of brake valve, the output brake pressure 20MPa of brake valve, frequency of operation 16 times/min, work times: 25min × 16 time/min=400 time, take-off line often rises and falls maximum 2 times through the duty of brake, and 400 tasks are equivalent to 200 times and rise and fall, feeder liner is is often risen and fallen the 2h that about flies, and rises and falls for 200 times and is equivalent to 400h; See that Figure 1B is interval;
3rd step, high-temperature temperature is 70 DEG C, duration 50min, to the input current 20mA of brake valve, the output brake pressure 10MPa of brake valve, frequency of operation 16 times/min, work times: 50min × 16 time/min=800 time, remove dark duty of skidding and often rise and fall maximum 4 times, 800 tasks are equivalent to 200 times and rise and fall, feeder liner is is often risen and fallen the 2h that about flies, and rises and falls for 200 times and is equivalent to 400h; See that Fig. 1 C is interval;
4th step, high-temperature temperature is 70 DEG C, duration 25min, input electric stress 40mA, exports brake pressure 20MPa, frequency of operation 16 times/min, work times: 25min × 16 time/min=400 time, take-off line often rises and falls maximum 2 times through the duty of brake, and 400 tasks are equivalent to 200 times and rise and fall, feeder liner is is often risen and fallen the 2h that about flies, and rises and falls for 200 times and is equivalent to 400h; See that Fig. 1 D is interval;
5th step, room temperature condition, duration 25min, input electric stress 20mA, exports brake pressure 10MPa, frequency of operation 16 times/min, work times: 25min × 16 time/min=400 time, remove dark duty of skidding and often rise and fall maximum 4 times, 400 tasks are equivalent to 100 times and rise and fall, feeder liner is is often risen and fallen the 2h that about flies, and rises and falls for 100 times and is equivalent to 200h;
6th step, room temperature condition, duration 13min, input electric stress 40mA, exports brake pressure 20MPa, frequency of operation 16 times/min, work times: 13min × 16 time/min=208 time, the duty of the quiet brake of take-off line is is often risen and fallen maximum 2 times, and 208 tasks are equivalent to 104 times and rise and fall, feeder liner is is often risen and fallen the 2h that about flies, and rises and falls for 104 times and is equivalent to 208h;
The test profile duration 188min of Fig. 1, removes dark skidding work and quiet brake work and is 500 and rises and falls/1000 working hours; 15000 working hours press Fig. 1 cyclic test 15 sections, and total testing time (testing equipment working time) is, and: 188min/ often circulates × 15 circulations=2820min=47h, reaches acceleration object.
Step 8, accelerated durability test.Technological improvement in accelerated durability test process is carried out for fault, and the fault of the present embodiment occurs in temperature variation, and the fault for temperature variation carries out technological improvement.
The first step: determine test period: when the life requirements of brake valve is 10000h, empirically coefficient is the convention of 1.5, test period is proving time in the life-span 15000h of brake valve, testing equipment working time is 47h, the accelerated test time is the 15000/47=0.0031 of conventional test time, saves time and the Be very effective of the energy.
Second step: test: be tested to 1400 working hours by Fig. 1, testing equipment runs 263min.At the end of second section B interval, temperature shock is carried out to brake valve, this brake valve is moved in the sweat box of-55 DEG C in 1min in the sweat box of 70 DEG C, occur that take-off line brakes stress-free phenomenon of the failure to during brake valve input 40mA electric current, its reason is that the guiding valve of aircraft brake valve inside occurs clamping stagnation under temperature variation condition, and test stops.
According to determined accelerated test scheme, carry out the supporting gap of guiding valve to exciting out of order brake valve and improve.
Step 9, again carries out the test of accelerated durability test, excites fault to the brake valve after improvement
Again carry out temperature shock to the brake valve after improvement and excite fault test, again carry out temperature shock and excite fault test to be repetition step 7 and step 8, its detailed process is:
A. cryogenic temperature is-55 DEG C, duration 50min, input electric stress 20mA, export brake pressure 10MPa, frequency of operation 16 times/min, work times: 50min × 16 time/min=800 time, remove dark duty of skidding often to rise and fall maximum 4 times, 800 tasks are equivalent to 200 times and rise and fall, and feeder liner is is often risen and fallen the 2h that about flies, and rises and falls for 200 times and is equivalent to 400h; See that Figure 1A is interval, do not break down in process of the test;
B. cryogenic temperature is-55 DEG C, duration 25min, input electric stress 40mA, export brake pressure 20MPa, frequency of operation 16 times/min, work times: 25min × 16 time/min=400 time, take-off line often rises and falls maximum 2 times through the duty of brake, 400 tasks are equivalent to 200 times and rise and fall, and feeder liner is is often risen and fallen the 2h that about flies, and rises and falls for 200 times and is equivalent to 400h; See that Figure 1B is interval, do not break down in process of the test;
C. high-temperature temperature is 70 DEG C, duration 50min, input electric stress 20mA, export brake pressure 10MPa, frequency of operation 16 times/min, work times: 50min × 16 time/min=800 time, remove dark duty of skidding often to rise and fall maximum 4 times, 800 tasks are equivalent to 200 times and rise and fall, and feeder liner is is often risen and fallen the 2h that about flies, and rises and falls for 200 times and is equivalent to 400h; See that Fig. 1 C is interval, do not break down in process of the test;
D. high-temperature temperature is 70 DEG C, duration 25min, input electric stress 40mA, export brake pressure 20MPa, frequency of operation 16 times/min, work times: 25min × 16 time/min=400 time, take-off line often rises and falls maximum 2 times through the duty of brake, 400 tasks are equivalent to 200 times and rise and fall, and feeder liner is is often risen and fallen the 2h that about flies, and rises and falls for 200 times and is equivalent to 400h; See that Fig. 1 D is interval, do not break down in process of the test;
E. room temperature condition, duration 25min, input electric stress 20mA, exports brake pressure 10MPa, frequency of operation 16 times/min, work times: 25min × 16 time/min=400 time, remove dark duty of skidding often to rise and fall maximum 4 times, 400 tasks are equivalent to 100 times and rise and fall, and feeder liner is is often risen and fallen the 2h that about flies, rise and fall for 100 times and be equivalent to 200h, do not break down in process of the test;
F. room temperature condition, duration 13min, input electric stress 40mA, exports brake pressure 20MPa, frequency of operation 16 times/min, work times: 13min × 16 time/min=208 time, the duty of the quiet brake of take-off line is is often risen and fallen maximum 2 times, and 208 tasks are equivalent to 104 times and rise and fall, and feeder liner is is often risen and fallen the 2h that about flies, rise and fall for 104 times and be equivalent to 208h, do not break down in process of the test;
In test, described process a ~ f is circulated altogether 15 times,
Circulated the circulation of a test profile each time, the present embodiment completes the test of 15 sections, testing equipment 47h working time, is equivalent to the accelerated durability development test that aircraft brake valve completes 15000h, and do not break down in process of the test, prove that it is effective for improving; Reach test objective.
Step 10, experimental data processing, adopts the engineering experience method in former Commission of Science, Technology and Industry for National Defence (1985) No. 1325 literary compositions to carry out data processing:
In process of the test, do not occur wear-out fault, calculate according to engineering experience method, experience factor is 1.5, and the life-span is: 15000/1.5=10000h, reaches the object of permanance development test.
Claims (4)
1. excite a method for aircraft brake valve fault, it is characterized in that, detailed process is:
Step 1, the frequency of operation unstability value of testing airplane brake valve; Described frequency of operation unstability value is turned the frequency values of differential brake pressure in take-off line brake pressure, the landing antiskid brake pressure of output and the ground of output exported; Adopt the frequency of operation unstability value of step-by-step method testing airplane brake valve, this step has three test parameters; To the test of aircraft brake valve frequency of operation unstability value from 10 times/min, and increase progressively with the step-length of 2 times/min, the test duration in every step-length is 40min, until test proceeds to the frequency of operation broken down; Ratio between the brake pressure exported and the electric current of input is judged to fault when not meeting linear relationship;
Step 2, testing airplane brake valve is to the reaction of temperature variation; The reaction of described aircraft brake valve to temperature variation be export take-off line brake pressure, output the variation range of landing antiskid brake pressure following temperature whether overproof; During the reaction of testing airplane brake valve to temperature variation, the temperature range of setting is-55 ~ 70 DEG C; Specifically, after being placed in by aircraft brake valve of continuous repetition keeps 1h in-55 DEG C of low-temperature test chambers, be transferred in the high-temperature test chamber of 70 DEG C, when high-temperature test chamber temperature reaches 70 DEG C of temperature again, be linear relationship between the brake pressure that test exports and the electric current of input, brake valve is qualified under this temperature variation condition; Otherwise then described brake valve is defective under this temperature variation condition, test terminates;
Aircraft brake valve testing table is 15min from the process shifted in high-temperature test chamber in low-temperature test chamber by described first time, and after this each process decrements 1 ~ 2min from shifting in high-temperature test chamber in low-temperature test chamber, until when described transfer process is decremented to 1min, test terminates;
When aircraft brake valve is transferred to after in high-temperature test chamber in low-temperature test chamber, whether the ratio between the brake pressure that test exports and the electric current of input is linear relationship, if the ratio between the brake pressure exported and the electric current of input is linear relationship, prove the designing requirement that this aircraft brake valve satisfied temperature changes; Otherwise then prove that this aircraft brake valve does not meet the designing requirement of temperature variation, need to carry out the improvement for improving temperature control, test terminates;
Step 3, determine the low temperature critical value of aircraft brake valve: the low temperature critical value of described aircraft brake valve be export take-off line brake pressure, output landing antiskid brake pressure when changing at low temperatures whether in the scope of technical manual; The environmental qualification test low temperature of aircraft brake valve is-55 DEG C; In test, each temperature spot aircraft brake valve output pressure is tested respectively between-55 DEG C ~-65 DEG C, when pass between the electric current that control enclosure inputs to brake valve and aircraft brake valve output pressure is linear relationship, the output pressure of this aircraft brake valve is qualified, continues next step test; If when control enclosure is non-linear to the pass between the input current of brake valve and aircraft brake valve output pressure, then prove that the output pressure of this aircraft brake valve is defective, end of test;
Step 4, determines the high temperature critical value of aircraft brake valve: the high temperature critical value of described aircraft brake valve is the take-off line brake pressure of output, whether the landing antiskid brake pressure of output is linear relationship when at high temperature changing;
The initial temperature of the environmental qualification test of aircraft brake valve is 70 DEG C; In test, the output pressure of each temperature spot aircraft brake valve is tested respectively between 70 DEG C ~ 80 DEG C, be linear relationship when being input to the pass between the electric current of brake valve and aircraft brake valve output pressure from control enclosure, the output pressure of this aircraft brake valve is qualified, continues next step test; If the pass between input current and aircraft brake valve output pressure is nonlinear relationship, then the output pressure of this aircraft brake valve is defective, end of test;
Step 5, determines resonance frequency and the vibration value of aircraft brake valve: whether the vibration value of described aircraft brake valve is take-off line brake pressure, the landing antiskid brake pressure of output and the ground of output exported differential brake pressure change under vibrating conditions of turning is linear relationship;
During testing airplane brake valve vibration value, aircraft brake valve is carried out to the swept-sine vibration test of 10Hz ~ 1000Hz; Specifically, under different vibration values, progressively swept-sine vibration test is carried out successively respectively; The frequency of described sine sweep is from 10Hz, until terminate during 1000Hz; In test, if the input current of aircraft brake valve and aircraft brake valve output pressure are linear relationship, then carry out the swept-sine vibration test of next vibration value, repeat described process, until described vibration value reaches actual vibration value 1.5 times; When the input current of aircraft brake valve and aircraft brake valve output pressure are nonlinear relationship, prove that this aircraft brake valve performance is defective, terminate test, this aircraft brake valve is improved;
Step 6, determines the operating load applied in process of the test
Operating load comprises control enclosure to the input current of brake valve and output pressure corresponding to brake valve
The working stress that aircraft brake valve in use bears comprises take-off line brake pressure, the differential brake pressure of landing antiskid brake pressure and ground;
Step 7, determines accelerated test condition
When determining accelerated test condition:
The first step, cryogenic temperature is-55 DEG C, duration 50min, and control enclosure is to the input current 20mA of brake valve, and brake valve exports brake pressure 10MPa, frequency of operation 16 times/min, work times: 50min × 16 time/min=800 time;
Second step, cryogenic temperature is-55 DEG C, duration 25min, and control enclosure, to the input current 40mA of brake valve, exports brake pressure 20MPa, frequency of operation 16 times/min, work times: 25min × 16 time/min=400 time;
3rd step, high-temperature temperature is 70 DEG C, duration 50min, and control enclosure is to the input current 20mA of brake valve, and brake valve exports brake pressure 10MPa, frequency of operation 16 times/min, work times: 50min × 16 time/min=800 time;
4th step, high-temperature temperature is 70 DEG C, duration 25min, and input electric stress 40mA, exports brake pressure 20MPa, frequency of operation 16 times/min, work times: 25min × 16 time/min=400 time;
5th step, room temperature condition, duration 25min, input electric stress 20mA, exports brake pressure 10MPa, frequency of operation 16 times/min, work times: 25min × 16 time/min=400 time;
6th step, room temperature condition, duration 13min, input electric stress 40mA, exports brake pressure 20MPa, frequency of operation 16 times/min, work times: 13min × 16 time/min=208 time;
Step 8, accelerated durability test
The first step: determine test period;
Second step: test; At the end of second section B interval, carry out temperature shock test to brake valve, occur stress-free fault to aircraft brake valve during brake valve input 40mA electric current, test stops; Carry out the supporting gap of guiding valve to exciting out of order brake valve to improve;
Step 9, again carries out temperature shock to the brake valve after improvement and excites fault test; Again accelerated durability test is carried out, to excite fault to the brake valve after improving; Described temperature shock of again carrying out excites fault test to be circulation step 7 and step 8 totally 15 times, the content of the test of the test profile defined that circulated each time;
Step 10, experimental data processing.
2. excite the method for aircraft brake valve fault as claimed in claim 1, it is characterized in that, the brake pressure of take-off line described in step 6 and landing antiskid brake pressure are determined according to designing requirement, wherein:
When input current is 40mA, take-off line brake pressure is 20MPa;
When input current is 20mA, landing antiskid brake pressure is 10MPa.
3. excite the method for aircraft brake valve fault as claimed in claim 1, it is characterized in that, in step 5, the lowest vibration value of aircraft brake valve is 2.5G.
4. excite the method for aircraft brake valve fault as claimed in claim 1, it is characterized in that, brake valve to be transferred in low-temperature test chamber or in high-temperature test chamber time, described brake valve is arranged on hydraulic test bench, hydraulic test bench and brake valve is together transferred in low-temperature test chamber or in high-temperature test chamber.
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| CN105547679B (en) * | 2016-01-08 | 2018-11-13 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of cooling turbine unit acceleration service life test method |
| CN105644543B (en) * | 2016-02-04 | 2018-06-01 | 西安航空制动科技有限公司 | A kind of brake system brake pressure bearing calibration |
| CN107515599B (en) * | 2017-06-26 | 2019-09-17 | 西安航空制动科技有限公司 | A kind of hot test method of airplane brake system |
| CN107515089A (en) * | 2017-07-26 | 2017-12-26 | 中国航空工业集团公司西安飞机设计研究所 | A kind of temperature stress efficiently excites the reliability development test method of failure |
| CN110116800B (en) * | 2019-05-14 | 2022-12-13 | 西安航空制动科技有限公司 | Brake control method of airplane antiskid brake system under antiskid fault |
| CN110501152B (en) * | 2019-08-27 | 2021-02-02 | 中国航空综合技术研究所 | Test method and test fixture for intermittent fault recurrence of connection type structural assembly |
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