CN109557286A - Helicopter electric heating windscreen Transparent Parts durability test and lifetime estimation method - Google Patents
Helicopter electric heating windscreen Transparent Parts durability test and lifetime estimation method Download PDFInfo
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- CN109557286A CN109557286A CN201811354752.2A CN201811354752A CN109557286A CN 109557286 A CN109557286 A CN 109557286A CN 201811354752 A CN201811354752 A CN 201811354752A CN 109557286 A CN109557286 A CN 109557286A
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- 238000012360 testing method Methods 0.000 title claims abstract description 146
- 238000000034 method Methods 0.000 title claims abstract description 48
- 238000005485 electric heating Methods 0.000 title claims abstract description 45
- 238000009434 installation Methods 0.000 claims abstract description 18
- 230000000694 effects Effects 0.000 claims abstract description 11
- 230000032683 aging Effects 0.000 claims abstract description 7
- 238000001816 cooling Methods 0.000 claims abstract description 6
- 238000010438 heat treatment Methods 0.000 claims description 18
- 238000004781 supercooling Methods 0.000 claims description 16
- 230000007613 environmental effect Effects 0.000 claims description 13
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 13
- 230000005611 electricity Effects 0.000 claims description 12
- 238000007689 inspection Methods 0.000 claims description 10
- 238000010998 test method Methods 0.000 claims description 10
- 125000004122 cyclic group Chemical group 0.000 claims description 8
- 239000007788 liquid Substances 0.000 claims description 8
- 239000002131 composite material Substances 0.000 claims description 7
- 238000012372 quality testing Methods 0.000 claims description 7
- 239000006185 dispersion Substances 0.000 claims description 6
- 239000007769 metal material Substances 0.000 claims description 6
- 239000010410 layer Substances 0.000 description 7
- 230000035939 shock Effects 0.000 description 5
- 230000000630 rising effect Effects 0.000 description 4
- LFQSCWFLJHTTHZ-UHFFFAOYSA-N Ethanol Chemical compound CCO LFQSCWFLJHTTHZ-UHFFFAOYSA-N 0.000 description 3
- 235000006508 Nelumbo nucifera Nutrition 0.000 description 3
- 240000002853 Nelumbo nucifera Species 0.000 description 3
- 235000006510 Nelumbo pentapetala Nutrition 0.000 description 3
- 238000013461 design Methods 0.000 description 3
- 238000011161 development Methods 0.000 description 3
- 230000018109 developmental process Effects 0.000 description 3
- 239000011521 glass Substances 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- 229920002635 polyurethane Polymers 0.000 description 3
- 239000004814 polyurethane Substances 0.000 description 3
- 239000000243 solution Substances 0.000 description 3
- 239000002775 capsule Substances 0.000 description 2
- 230000007547 defect Effects 0.000 description 2
- 238000002474 experimental method Methods 0.000 description 2
- 238000009738 saturating Methods 0.000 description 2
- 239000002904 solvent Substances 0.000 description 2
- 230000002411 adverse Effects 0.000 description 1
- 239000007864 aqueous solution Substances 0.000 description 1
- 230000009977 dual effect Effects 0.000 description 1
- 230000007774 longterm Effects 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 238000011084 recovery Methods 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
- 239000002356 single layer Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 230000003746 surface roughness Effects 0.000 description 1
- 238000010257 thawing Methods 0.000 description 1
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N33/00—Investigating or analysing materials by specific methods not covered by groups G01N1/00 - G01N31/00
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- G01N33/386—Glass
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N17/00—Investigating resistance of materials to the weather, to corrosion, or to light
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N17/00—Investigating resistance of materials to the weather, to corrosion, or to light
- G01N17/002—Test chambers
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N17/00—Investigating resistance of materials to the weather, to corrosion, or to light
- G01N17/004—Investigating resistance of materials to the weather, to corrosion, or to light to light
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Abstract
This application provides a kind of helicopter electric heating windscreen Transparent Parts durability tests and lifetime estimation method, comprising: S100: taking full-scale windscreen Transparent Parts as sample, hydrothermal aging test is first carried out to sample, photochemical effect test is carried out to test after room temperature is cooling, and room temperature is cooling；S200: treated sample is installed on test equipment according to the actual installation state on helicopter；S300: specimen test, specimen test include that the cold air of sample load determination, the hot weather type environment test of sample and sample waits type environment test；S400: the windscreen efficiency test time T under single use environment is determined1Or T2, and access time T1And T2Minimum value be windscreen efficiency test time T under two kinds of environmentte；The aerial flight life time of windscreen is obtained according to the windscreen efficiency test time.The application more really simulates actual working state, so that the result of appraisal are more reliable.
Description
Technical field
The application belongs to helicopter durability test technical field, in particular to a kind of helicopter is transparent with electric heating windscreen
Part durability test and lifetime estimation method.
Background technique
With the full territory of helicopter, the round-the-clock tight demand used, have anti-icing, defrosting function electric heating windscreen saturating
Application of the bright part in helicopter sharply increases.Electric heating windscreen Transparent Parts are usually sandwich composite, more traditional single layer
For windscreen Transparent Parts, material category is more, structure is more complicated, thus brings the factor influenced on windscreen durability of product
It increases significantly, causes the comprehensive assessment mode in electric heating windscreen Transparent Parts development process to be difficult to carry out, and can not obtain
Its test assessment service life.
During the examination of existing windscreen product, mini-test environment is usually carried out to windscreen according to design requirement and is examined
Core, such as high/low temperature, vibration, test process cannot embody multifactor reciprocation and bring；Long-term effect can not be examined simultaneously
Environmental factor caused by properties of product reduce influence to product use process；Process is actually used to windscreen in addition, lacking
In common adverse circumstances examination, cloud layer containing super-cooling waterdrop is entered when opening electricity heating function such as helicopter and is brought to windscreen low temperature
Shock effect.Since integrated environment durability test methods more for helicopter electric heating windshield are in blank rank at present
Section, therefore also the service life of windscreen product can not just be assessed by the method for test, cause taking in windscreen product
It cannot determine when fail during labour, use security presence larger hidden danger.
Summary of the invention
There is provided a kind of helicopter electric heating windscreen Transparent Parts durability tests and life appraisal for the purpose of the application
Method, it is any of the above-described to solve the problems, such as.
The technical solution of the application is: a kind of helicopter electric heating windscreen Transparent Parts durability test and life appraisal side
Method comprising:
S100: taking full-scale windscreen Transparent Parts as sample, first carries out hydrothermal aging test to sample, right after room temperature is cooling
Test carries out photochemical effect test, and room temperature is cooling；
S200: treated sample is installed on test equipment according to the actual installation state on helicopter；
S300: specimen test, specimen test include sample load determination, the hot weather type environment test of sample and sample
Cold air wait type environment test；
S400: the windscreen efficiency test time T under single use environment is determinedte, TteFor T1Or T2, access time T1And T2
Minimum value be windscreen efficiency test time T under two kinds of environmentte；
Then the aerial flight life time of windscreen isN is the inorganic non-metallic material fatigue coefficient of dispersion.
In this application, in step S100, the hydrothermal aging test method of sample includes: that sample is placed in air themperature 43
± 2 DEG C, 240h under the environment of humidity RH >=95%.
In this application, in step S100, the photochemical effect test method of sample includes: that sample is placed in air themperature
49 ± 2 DEG C, 240h in the environment of irradiation level 1120W/m2.
In this application, in step S300, sample load determination includes: S311: with single load cycle P1 → P2 → P3
→ P1 be simulate one flight rise and fall middle windscreen Transparent Parts gas pressure loads variation, one flight rise and fall the time be T1f, sample root
According to the maximum flying speed V of helicoptermax, cruising speed VcIt determines；S312: P1,3 load of load p keep first in three-level load
Predetermined time, load p 2 are kept for the second predetermined time, are scheduled load change rate, a complete load between load change
Lotus cycle time TtpTo be no less than 0.5min.
In this application, in step 311, load p 1=Vmax 2× η/1600, load p 2=Vc 2× η/1600, load p 3=
(0.8Vc)2× η/1600, η are height variation coefficient of wind pressure, and loading direction is directed toward inside, vertical windshield surface on the outside of windscreen.
In this application, in step 312, the first predetermined time was 2s~10s, and the second predetermined time was 2s~80s, was made a reservation for
Load change rate be 10Pa/s~400Pa/s, complete load cycle time Ttp be 0.5min~15min.
In this application, in step S300, the hot weather type environment test of sample includes:
S321: the test of hot weather environmental form is carried out using temperature-load Orthogonal Composite, with predetermined time interval Tg be every
Check the test inspection cycle requirement of windscreen Transparent Parts, i.e. global cycle number Tg/T in predetermined time interval Tg1fIt is secondary；Hot weather class
Temperature step is defined as 38 DEG C and accounts for the 95% of the implementation cycle, 52 DEG C accounting for the 5% of the implementation cycle in type, i.e. cycle-index is respectively
0.95*Tg/T1f、0.05*Tg/T1；
S322: it after sample installation, follows the steps below:
A) testing equipment analog temperature control out of my cabin analog temperature control in 38 ± 2 DEG C, cabin is carried at 4~32 DEG C
Lotus recycles (P1 → P2 → P3 → P1) 0.95*Tg/T1fIt is secondary；
B) analog temperature rises to 52 ± 2 DEG C to testing equipment out of my cabin, and temperature rate-of-rise is greater than 10 DEG C/min, simulates in cabin
Temperature is controlled at 4~32 DEG C, carries out load cycle, and load cycle number is 0.05*Tg/T1f；
C) every completion Tg/T1fThe circulation of secondary step a to step b takes out sample and carries out quality testing, failure mode such as occurs
Stop test, records test period；Continue to repeat step a to step b Ru without failure, until sample fails or reaches
To specified test period；
D) according to step a, step b, step c, sample efficiency test time T is obtained1。
In this application, in step S300, the cold air of sample waits type environment test and includes
S331: cold air is waited environmental form test and is equally carried out using temperature-load Orthogonal Composite, i.e., in certain temperature environment
Under the conditions of carry out a complete load cycle and be equivalent to simulating a flight and rising and falling, while defining predetermined time interval Tg and being
Check the test inspection cycle requirement of windscreen Transparent Parts, i.e. global cycle number Tg/T in predetermined time interval Tg1fIt is secondary；Cold air waits class
Temperature step is defined as 4 DEG C and accounts for the 45% of the implementation cycle, -4 DEG C of 25%, -32 DEG C for accounting for the implementation cycle accounting for the implementation cycle in type
25%, the 5% of the implementation cycle is accounted for for -55 DEG C, i.e. cycle-index is respectively 0.45*Tg/T1f、0.25*Tg/T1f、0.25*Tg/T1f、
0.05*Tg/T1f；
S332: it after sample installation, follows the steps below:
A) analog temperature control is arranged in 4 ± 2 DEG C, cabin at 4~32 DEG C in analog temperature to testing equipment out of my cabin, carries out load
Recycle 0.45*Tg/T1fIt is secondary；Electric heating function is opened by practical maximum service rating Pw when each load cycle starts, is completed
Load p 3 protects Tp3 when carrying and closes electricity heating function, is realized and is heated up to windscreen Transparent Parts by electric heating in a cyclic process
With recovery to environment temperature；Simultaneously when the electric heating time reaching Tp3-Tc, start to implement duration to windscreen Transparent Parts outer surface
For Tc super-cooling waterdrop impact, super-cooling waterdrop parameter be 0~-10 DEG C of temperature, 5~20um of drop diameter, Liquid water content 0.2~
10g/m3；
B) analog temperature drops to -4 ± 2 DEG C to testing equipment out of my cabin, and temperature fall off rate is greater than 10 DEG C/min, simulates in cabin
Temperature is controlled at 4~32 DEG C, carries out load cycle, 0.25*Tg/T1fIt is secondary；When each load cycle starts by practical maximum work
Rate of doing work Pw opens electric heating function, completes load p 3 and protects Tp3 closing electricity heating function when carrying, passes through in a cyclic process
Electric heating is realized heating to windscreen Transparent Parts and is restored to environment temperature；Simultaneously when the electric heating time reaching Tp3-Tc, start
The super-cooling waterdrop impact of a length of Tc when implementing to windscreen Transparent Parts outer surface, 0~-10 DEG C of super-cooling waterdrop parameters of temperature, water droplet are straight
5~20um of diameter, 0.2~10g/m3 of Liquid water content；
C) analog temperature drops to -32 ± 2 DEG C to testing equipment out of my cabin, and temperature fall off rate is greater than 10 DEG C/min, cabin internal model
Quasi- temperature control carries out load cycle 0.25*Tg/T at 4~32 DEG C1fIt is secondary；
D) analog temperature drops to -55 ± 2 DEG C to testing equipment out of my cabin, and temperature fall off rate is greater than 10 DEG C/min, cabin internal model
Quasi- temperature control carries out load cycle 0.05*Tg/T at 4~32 DEG C1fIt is secondary；
E) every completion Tg/T1fThe circulation of secondary step a, step b, step c, step d take out sample and carry out quality testing, such as
There is failure mode and stop test, records test period；Continue to repeat step a, step b, step Ru without failure
C, step d until sample failure or reaches specified test period；
F) step a, step b, step c, step d, step e are pressed, sample efficiency test time T is obtained2。
In this application, the predetermined time interval Tg is 100h.
In this application, in step S400, inorganic non-metallic material coefficient of dispersion n value is 4~6.
The test of the application and lifetime estimation method may be implemented electric heating windscreen Transparent Parts the development stage utmostly
Detect design, latent defect existing for technical process, guarantee that electric heating windscreen Transparent Parts can be with cost-benefit
Mode executes corrective action, ensures the first-fly safety of helicopter, and the windscreen Transparent Parts assessment service life of acquisition can be used for instructing wind
The line of Transparent Parts is kept off, raising product uses safe during one's term of military service.
Detailed description of the invention
In order to illustrate more clearly of technical solution provided by the present application, attached drawing will be briefly described below.It is aobvious and easy
Insight, drawings discussed below are only some embodiments of the present application.
Fig. 1 is the windscreen durability test and lifetime estimation method flow chart of steps of the application；
Fig. 2 is the testing equipment of an embodiment used by the present processes with reference to figure；
Fig. 3 is that the present processes compbined test composes block.
Specific embodiment
To keep the purposes, technical schemes and advantages of the application implementation clearer, below in conjunction in the embodiment of the present application
Attached drawing, technical solutions in the embodiments of the present application is further described in more detail.
In the description of the present application, term " center ", " longitudinal direction ", " transverse direction ", "front", "rear", "left", "right", "vertical",
The orientation or positional relationship of the instructions such as "horizontal", "top", "bottom", "inner", "outside" is that orientation based on the figure or position are closed
System is merely for convenience of description the application and simplifies description, rather than the device or element of indication or suggestion meaning must have
Specific orientation is constructed and operated in a specific orientation, therefore should not be understood as the limitation to the application protection scope.
The helicopter of the application electric heating windscreen Transparent Parts durability test and lifetime estimation method mainly include following
Step: sample (full-scale windscreen) pre-processes (damp and hot-ultraviolet), test specimen installation, test implementation and life appraisal judgement.Sample coupon
Number is determined according to the regional natural environment weather of helicopter military service: Service Environment Type division is that hot weather type and cold air wait class
Type such as uses in single environment climate type, carries out 1 corresponding amblent air temperature Type Test；Such as have in two kinds of environmental forms
It uses, two kinds of environment respectively carry out 1 test, and lifetime results take its low value.
The helicopter of the application electric heating windscreen Transparent Parts durability test and lifetime estimation method, referring to Fig. 1 to figure
3, specifically include:
S100, sample pretreatment
S101 chooses full-scale windscreen as sample, sample is placed in 43 ± 2 DEG C of air themperature, the ring of humidity RH >=95%
240h under border, hydrothermal aging are cooled to room temperature after the completion, take out sample；
Sample after humid heat treatment is placed in 49 ± 2 DEG C of air themperature, irradiation level 1120W/m by S1022In the environment of
240h, realizes damp and hot with reciprocation of the photochemical effect factor on test specimen, after the completion of photochemical effect, is cooled to room temperature and takes
Out；
S200, sample installation
Referring to fig. 2, pretreated sample will be completed according to the actual installation state on helicopter in test equipment
It is installed on (the skeleton outer dimension of analog capsule cabin should be consistent with background helicopter virtual condition), related connection standard is installed
Part, material, installation method etc. are consistent with virtual condition；
S300, test are implemented, and specimen test includes sample load determination, the hot weather type environment test of sample and sample
Cold air wait type environment test
S310 determines sample load parameter
S311, the single load cycle (P1 → P2 → P3 → P1) of test is risen and fallen for one flight of simulation, and (one is flown
Falling timing definition is T1f, the gas pressure loads variation of windscreen Transparent Parts, straight with specific reference to windscreen Transparent Parts application background in unit h)
The maximum flying speed V of the machine of litermax, cruising speed VcIt determines.Specifically, for defining three-level load ladder in single load cycle
Spend P1, P2, P3:P1 Vmax 2× η/1600, P2 Vc 2× η/1600, P3 are (0.8Vc)2× η/1600, η are the change of wind pressure height
Change coefficient, loading direction is directed toward inside, vertical windshield surface on the outside of windscreen；
S312, P1, P3 protect load-time and are better than 2S~10S in three-level load, and P2, which is protected, to be carried the time and be better than 2S~80S, load
Rate of change is better than 10Pa/s~400Pa/s, a complete load cycle time TtpBetter than 0.5min~15min；
S320, the test of hot weather environmental form
S321, the test of hot weather environmental form is carried out using temperature-load Orthogonal Composite, i.e., in certain temperature environmental condition
One complete load cycle of lower progress, which is equivalent to, to be simulated a flight and rises and falls, while defining 100h to check windscreen Transparent Parts
The requirement of test inspection cycle, i.e. global cycle number 100/T in 100h1fIt is secondary.Temperature step is defined as being 38 in hot weather type
DEG C (implementation cycle accounting 95%), 52 DEG C (implementation cycle accounting 5%), i.e., cycle-index is respectively 95/T1f、5/T1f。
It is checked comprehensively for raising test exploitativeness with simulating windscreen quality of 100h flight time progress, referring specifically to
Step S322.
S322 is followed the steps below after sample installation:
A) testing equipment analog temperature control out of my cabin analog temperature control in 38 ± 2 DEG C, cabin is carried at 4~32 DEG C
Lotus recycles (P1 → P2 → P3 → P1) 95/T1fIt is secondary；
B) analog temperature rises to 52 ± 2 DEG C to testing equipment out of my cabin, and temperature rate-of-rise is greater than 10 DEG C/min, simulates in cabin
Temperature is controlled at 4~32 DEG C, is carried out load cycle (P1 → P2 → P3 → P1), and load cycle number is 5/T1f；
C) every completion 100/T1f(analog temperature is declined the circulation of secondary step a to step b by 52 ± 2 DEG C out of my cabin for cyclic process
It is greater than 10 DEG C/min to 38 DEG C of rates), it takes out sample and carries out quality testing.Such as occur failure mode (electricity heating functional fault,
Internal and external layers of glass is cracked, is layered, and bubble etc. occurs in middle layer polyurethane pellicle) stop test, record test period；Such as
It is without failure to continue to repeat step a to b, until sample failure or reach specified test period；
D) according to step a), b), c), obtain sample efficiency test time T1。
S330, cold air wait Type Test
S331, cold air is waited environmental form test and is equally carried out using temperature-load Orthogonal Composite, i.e., in certain temperature environment
Under the conditions of carry out a complete load cycle and be equivalent to simulating a flight and rising and falling, while defining 100h is that inspection windscreen is saturating
The test inspection cycle of bright part requires, i.e. global cycle number 100/T in 100h1fIt is secondary.Temperature step is defined as in cold climate type
For 4 DEG C (implementation cycle accountings 45%), -4 DEG C (implementation cycle accounting 25%), -32 DEG C (implementation cycle accounting 25%), -55 DEG C
(implementation cycle accounting 5%), i.e., cycle-index is respectively 45/T1f、25/T1f、25/T1f、5/T1f。
S332 is followed the steps below after sample installation:
A) analog temperature control is arranged in 4 ± 2 DEG C, cabin at 4~32 DEG C in analog temperature to testing equipment out of my cabin, carries out load
Recycle (P1 → P2 → P3 → P1) 45/T1fIt is secondary.Electricity is opened by practical maximum service rating Pw when each load cycle starts to add
Heat function completes load p 3 and protects Tp3 closing electricity heating function when carrying, transparent to windscreen by electric heating in a cyclic process
Part is realized heating and is restored to environment temperature.Simultaneously when the electric heating time reaching Tp3-Tc (Tc be better than 1S~30S), start pair
The super-cooling waterdrop impact of windscreen Transparent Parts outer surface a length of Tc when implementing, super-cooling waterdrop (can contain to the asexual energy loss of windscreen Transparent Parts
Harmful solvents such as alcohol etc.) parameter be better than 0~-10 DEG C of temperature, 5~20um of drop diameter, 0.2~10g/m3 of Liquid water content；
B) analog temperature drops to -4 ± 2 DEG C to testing equipment out of my cabin, and temperature fall off rate is greater than 10 DEG C/min, simulates in cabin
Temperature is controlled at 4~32 DEG C, is carried out load cycle (P1 → P2 → P3 → P1), 25/T1fIt is secondary.When each load cycle starts by
Practical maximum service rating PwElectric heating function is opened, load p 3 is completed and protects T when carryingp3Electricity heating function is closed, is recycled at one
Heating is realized to windscreen Transparent Parts by electric heating in the process and is restored to environment temperature.Reach T in the electric heating time simultaneouslyp3-
When Tc (Tc is better than 1S~30S), the super-cooling waterdrop impact of a length of Tc, super-cooling waterdrop when starting to implement windscreen Transparent Parts outer surface
(solvents such as alcohol etc. to windscreen Transparent Parts without performance compromise can be contained) parameter better than 0~-10 DEG C of temperature, drop diameter 5~
20um, 0.2~10g/m of Liquid water content3；
C) analog temperature drops to -32 ± 2 DEG C to testing equipment out of my cabin, and temperature fall off rate is greater than 10 DEG C/min, cabin internal model
Quasi- temperature control carries out load cycle (P1 → P2 → P3 → P1) 25/T at 4~32 DEG C1fIt is secondary；
D) analog temperature drops to -55 ± 2 DEG C to testing equipment out of my cabin, and temperature fall off rate is greater than 10 DEG C/min, cabin internal model
Quasi- temperature control carries out load cycle (P1 → P2 → P3 → P1) 5/T at 4~32 DEG C1fIt is secondary；
E) every completion 100/T1fSecondary step a, step b, step c, step d circulation (cyclic process out of my cabin analog temperature by-
55 ± 2 DEG C of rates for rising to 4 ± 2 DEG C are greater than 10 DEG C/min), it takes out sample and carries out quality testing, failure mode (electricity such as occur
Heating function failure, internal and external layers of glass is cracked, is layered, and bubble etc. occurs in middle layer polyurethane pellicle) stop test, note
Record test period；Continue to repeat step a, step b, step c, step d Ru without failure, until sample fails or reaches
Specified test period；
F) step a, step b, step c, step d, step e are pressed, sample efficiency test time T is obtained2。
S400, life appraisal judgement, comprising:
S410 obtains the windscreen efficiency test time T that single environment type in above-mentioned steps usesteAs T1(or T2),
Choose the windscreen efficiency test time T that two kinds of environmental forms useteFor T1、T2In lower value；
S420 calculates windscreen Transparent Parts aerial flight life timeUnit is h, and wherein n is inorganic non-
The Metal Material Fatigue coefficient of dispersion recommends value 4~6.
To make present context and step have a better understanding and awareness, by certain type helicopter as example into
Row detailed description.
The helicopter of the application electric heating windscreen Transparent Parts durability test method, comprising the following steps:
S100, sample pretreatment:
1) it chooses full-scale windscreen as sample, sample is placed in 43 ± 2 DEG C, 240h under the environment of humidity RH >=95%, it is wet
It is cooled to room temperature after the completion of heat ageing, takes out sample；
2) sample after humid heat treatment is placed in 49 ± 2 DEG C of temperature, irradiation level 1120W/m2In the environment of 240h, photochemistry
After the completion of effect, it is cooled to room temperature taking-up；
S200, sample installation, comprising:
Pretreated sample will be completed according to the actual installation state on helicopter in test equipment (analog capsule cabin
Skeleton outer dimension should be consistent with background helicopter virtual condition) on install, install involved in connection standard component, material,
Installation method etc. is consistent with virtual condition；
S300, test are implemented, comprising:
S310 determines load parameter
S311, the maximum flying speed V of certain helicoptersmaxFor 260km/h, cruising speed VcFor 246km/h, wind pressure height
Degree variation coefficient η takes 1.23 by 20m terrain clearance, B class surface roughness, obtains three-level load gradient P1, P2, P3 and is respectively as follows:
4010Pa(P1),3590Pa(P2),2297Pa(P3)；
S312, load is 1 load cycle from P1 → P2 → P3 → P1 in test, and wherein P1, P3 protect load-time and take 3S,
P2 guarantor takes 6S the load time, and it is 1.342min that load change rate, which takes 50Pa/s, a complete load cycle time Tp,.
S320, it is assumed that helicopter waits type area in cold air and is on active service, and after sample installation, cold air is waited type environment test and carried out
Following steps:
S321, it is assumed that one flight time of rising and falling of helicopter is defined as 10min (1/6h), amounts in the inspection cycle of 100h
Recycle 100/T1fSecondary i.e. 400 times, 4 DEG C of each temperature step, -4 DEG C, -32 DEG C, -55 DEG C of cycle-index be respectively 270,150,
150、30。
S322 is followed the steps below after sample installation:
A) testing equipment analog temperature control out of my cabin analog temperature control in 4 ± 2 DEG C, cabin carries out load at 4~32 DEG C
Recycle (P1 → P2 → P3 → P1) 270 times.According in step 3.1.2,0~46.3S (T from each load cyclep3) during open
It opens by practical maximum service rating PwElectric heating function, at the same carry out in 40.3S for when 6S super-cooling waterdrop impact, subcooled water
Drop selection alcohol water blend (- 4 DEG C of temperature, drop diameter 10um, Liquid water content 1g/m3)。
B) testing equipment analog temperature control out of my cabin drops to -4 ± 2 DEG C, and temperature fall off rate is greater than 10 DEG C/min, in cabin
Analog temperature is controlled at 4~32 DEG C, is carried out load cycle (P1 → P2 → P3 → P1), 150 times.0 in each load cycle~
46.3S(Tp3) during open press practical maximum service rating PwElectric heating function, at the same carry out in 40.3S for when 6S supercooling
Water droplet impingement, super-cooling waterdrop select spirituosity aqueous solution (- 4 DEG C of temperature, drop diameter 10um, Liquid water content 1g/m3)。
C) testing equipment analog temperature control out of my cabin drops to -32 ± 2 DEG C, and temperature fall off rate is greater than 10 DEG C/min, cabin
Interior analog temperature control carries out load cycle (P1 → P2 → P3 → P1) 150 times at 4~32 DEG C.
D) testing equipment analog temperature control out of my cabin drops to -55 ± 2 DEG C, and temperature fall off rate is greater than 10 DEG C/min, cabin
Interior analog temperature control carries out load cycle (P1 → P2 → P3 → P1) 30 times at 4~32 DEG C；
After 600 step a of every completion, step b, step c, step d e) (cyclic process out of my cabin analog temperature by -55 ± 2 DEG C
Rise to 4 ± 2 DEG C of rate and be greater than 10 DEG C/min), it takes out sample and carries out quality testing, failure mode (electricity heating function such as occur
Energy failure, internal and external layers of glass is cracked, is layered, and bubble etc. occurs in middle layer polyurethane pellicle) stop test, record is tested
Time；Continue to repeat step a, step b, step c, step d Ru without failure, until sample failure or reaches specified examination
Test the time；
F) it is amounted to by step a, step b, step c, step d, step e and completes 10 complete cycles, is i.e. acquisition sample is effective
Test period T2For 1500h.
S400, service life judgement, comprising:
Taking inorganic non-metallic material fatigue coefficient of dispersion n is 4, windscreen Transparent Parts aerial flight life time TL=1500 ×
10/1.342/4=2794h.
This helicopter is had the advantages that with electric heating windscreen Transparent Parts durability test and lifetime estimation method
1) a kind of completely new electricity heating windscreen Transparent Parts durability test method and process are proposed, prior art sky is filled up
It is white, it can be achieved that the effect that existing method is unable to reach: utmostly detect design in the development stage, dive existing for technical process
In defect, windscreen Transparent Parts service life is obtained；
2) multiple environment examination factor bring reciprocations are considered, the reciprocation examination factor covers damp and hot, photochemical
Effect, load, temperature, temperature shock are learned, is different from existing conventional test methods using single factor test or the examination factor of dual factors
Incomplete wire examination method；
3) the temperature shock test method based on real working condition is devised, establishes and low temperature mistake is implemented by windscreen electric heating
Cold water drop realizes the test method and parameter of temperature shock；
4) aerodynamic loading and the temperature shock factor based on helicopter flight process are used, existing traditional experiment master is different from
Actual working state is more really simulated, the result of appraisal are more reliable using the examination factor proposed based on storage environment；
5) it uses based on predetermined time interval as the temperature of inspection cycle-load quadratic-orthogonal experiment implementation method, makes
Test period is more compact, obtains lower experimentation cost, higher feasibility.
More than, the only specific embodiment of the application, but the protection scope of the application is not limited thereto, and it is any to be familiar with
Within the technical scope of the present application, any changes or substitutions that can be easily thought of by those skilled in the art, should all cover
Within the scope of protection of this application.Therefore, the protection scope of the application should be subject to the protection scope in claims.
Claims (10)
1. a kind of helicopter electric heating windscreen Transparent Parts durability test and lifetime estimation method characterized by comprising
S100: taking full-scale windscreen Transparent Parts as sample, hydrothermal aging test is first carried out to sample, to test after room temperature is cooling
Photochemical effect test is carried out, and room temperature is cooling；
S200: treated sample is installed on test equipment according to the actual installation state on helicopter；
S300: specimen test, specimen test include the cold of sample load determination, the hot weather type environment test of sample and sample
Climate type environmental test；
S400: the windscreen efficiency test time T under single use environment is determinedte, TteFor T1Or T2, access time T1And T2Most
Small value is the windscreen efficiency test time T under two kinds of environmentte；
Then the aerial flight life time of windscreen isN is the inorganic non-metallic material fatigue coefficient of dispersion.
2. helicopter according to claim 1 electric heating windscreen Transparent Parts durability test and lifetime estimation method, feature
It is, in step S100, the hydrothermal aging test method of sample includes:
Sample is placed in 240h under 43 ± 2 DEG C of air themperature, the environment of humidity RH >=95%.
3. helicopter according to claim 2 electric heating windscreen Transparent Parts durability test and lifetime estimation method, feature
It is, in step S100, the photochemical effect test method of sample includes:
Sample is placed in 240h in the environment of 49 ± 2 DEG C of air themperature, irradiation level 1120W/m2.
4. helicopter as claimed in claim 3 is existed with electric heating windscreen Transparent Parts durability test and lifetime estimation method, feature
In in step S300, sample load determination includes:
S311: being to simulate a flight to rise and fall the gas pressure loads of middle windscreen Transparent Parts with single load cycle P1 → P2 → P3 → P1
Variation, a flight rise and fall the time as T1f, sample is according to the maximum flying speed V of helicoptermax, cruising speed VcIt determines；
S312: P1,3 load of load p are kept for the first predetermined time in three-level load, and load p 2 keeps the second predetermined time, load
It is scheduled load change rate, a complete load cycle time T between variationtpTo be no less than 0.5min.
5. helicopter as claimed in claim 4 is existed with electric heating windscreen Transparent Parts durability test and lifetime estimation method, feature
In, in step 311, load p 1=Vmax 2× η/1600, load p 2=Vc 2× η/1600, load p 3=(0.8Vc)2× η/1600,
η is height variation coefficient of wind pressure, and loading direction is directed toward inside, vertical windshield surface on the outside of windscreen.
6. helicopter according to claim 5 electric heating windscreen Transparent Parts durability test and lifetime estimation method, feature
It is, in step 312, the first predetermined time was 2s~10s, and the second predetermined time was 2s~80s, and scheduled load change rate is
10Pa/s~400Pa/s, complete load cycle time Ttp are 0.5min~15min.
7. helicopter as claimed in claim 6 is existed with electric heating windscreen Transparent Parts durability test and lifetime estimation method, feature
In in step S300, the hot weather type environment test of sample includes:
S321: the test of hot weather environmental form is carried out using temperature-load Orthogonal Composite, is every inspection with predetermined time interval Tg
The test inspection cycle of windscreen Transparent Parts requires, i.e. global cycle number Tg/T in predetermined time interval Tg1fIt is secondary；In hot weather type
Temperature step is defined as 38 DEG C and accounts for the 95% of the implementation cycle, 52 DEG C accounting for the 5% of the implementation cycle, i.e. cycle-index is respectively 0.95*
Tg/T1f、0.05*Tg/T1；
S322: it after sample installation, follows the steps below:
A) testing equipment analog temperature control out of my cabin analog temperature control in 38 ± 2 DEG C, cabin carries out load and follows at 4~32 DEG C
Ring (P1 → P2 → P3 → P1) 0.95*Tg/T1fIt is secondary；
B) analog temperature rises to 52 ± 2 DEG C to testing equipment out of my cabin, and temperature rate-of-rise is greater than 10 DEG C/min, analog temperature in cabin
Control carries out load cycle at 4~32 DEG C, and load cycle number is 0.05*Tg/T1f；
C) every completion Tg/T1fThe circulation of secondary step a to step b takes out sample and carries out quality testing, failure mode such as occurs and stop
It only tests, records test period；Continue to repeat step a to step b Ru without failure, until sample failure or reaches finger
Determine test period；
D) according to step a, step b, step c, sample efficiency test time T is obtained1。
8. helicopter as claimed in claim 7 is existed with electric heating windscreen Transparent Parts durability test and lifetime estimation method, feature
In in step S300, the cold air of sample waits type environment test and includes
S331: cold air is waited environmental form test and is equally carried out using temperature-load Orthogonal Composite, i.e., in certain temperature environmental condition
One complete load cycle of lower progress, which is equivalent to, to be simulated a flight and rises and falls, while defining predetermined time interval Tg to check
The test inspection cycle of windscreen Transparent Parts requires, i.e. global cycle number Tg/T in predetermined time interval Tg1fIt is secondary；In cold climate type
Temperature step is defined as 4 DEG C and accounts for the 45% of the implementation cycle, -4 DEG C of 25%, -32 DEG C for accounting for the implementation cycle accounting for the implementation cycle
25%, the 5% of the implementation cycle is accounted for for -55 DEG C, i.e. cycle-index is respectively 0.45*Tg/T1f、0.25*Tg/T1f、0.25*Tg/T1f、
0.05*Tg/T1f；
S332: it after sample installation, follows the steps below:
A) analog temperature control is arranged in 4 ± 2 DEG C, cabin at 4~32 DEG C in analog temperature to testing equipment out of my cabin, carries out load cycle
0.45*Tg/T1fIt is secondary；Electric heating function is opened by practical maximum service rating Pw when each load cycle starts, completes load
P3 protect carry when Tp3 close electricity heating function, in a cyclic process by electric heating to windscreen Transparent Parts realize heating and it is extensive
Again to environment temperature；Simultaneously when the electric heating time reaching Tp3-Tc, a length of Tc when starting to implement windscreen Transparent Parts outer surface
Super-cooling waterdrop impact, super-cooling waterdrop parameter be 0~-10 DEG C of temperature, 5~20um of drop diameter, 0.2~10g/ of Liquid water content
m3；
B) analog temperature drops to -4 ± 2 DEG C to testing equipment out of my cabin, and temperature fall off rate is greater than 10 DEG C/min, analog temperature in cabin
Control carries out load cycle, 0.25*Tg/T at 4~32 DEG C1fIt is secondary；When each load cycle starts by practical maximum functional function
Rate Pw opens electric heating function, completes Tp3 when the guarantor of load p 3 carries and closes electricity heating function, is added in a cyclic process by electricity
Heat is realized heating to windscreen Transparent Parts and is restored to environment temperature；Simultaneously when the electric heating time reaching Tp3-Tc, start to wind
The super-cooling waterdrop for keeping off a length of Tc when Transparent Parts outer surface is implemented impacts, and 0~-10 DEG C of super-cooling waterdrop parameters of temperature, drop diameter 5~
20um, 0.2~10g/m3 of Liquid water content；
C) analog temperature drops to -32 ± 2 DEG C to testing equipment out of my cabin, and temperature fall off rate is greater than 10 DEG C/min, simulates temperature in cabin
Degree control carries out load cycle 0.25*Tg/T at 4~32 DEG C1fIt is secondary；
D) analog temperature drops to -55 ± 2 DEG C to testing equipment out of my cabin, and temperature fall off rate is greater than 10 DEG C/min, simulates temperature in cabin
Degree control carries out load cycle 0.05*Tg/T at 4~32 DEG C1fIt is secondary；
E) every completion Tg/T1fThe circulation of secondary step a, step b, step c, step d take out sample and carry out quality testing, such as occurs
Failure mode stops test, records test period；Continue to repeat step a, step b, step c, step as without failure
Rapid d until sample failure or reaches specified test period；
F) step a, step b, step c, step d, step e are pressed, sample efficiency test time T is obtained2。
9. special according to the helicopter of claim 7 or 8 electric heating windscreen Transparent Parts durability test and lifetime estimation method
Sign is that the predetermined time interval Tg is 100h.
10. helicopter according to claim 1 electric heating windscreen Transparent Parts durability test and lifetime estimation method, feature
It is, in step S400, inorganic non-metallic material coefficient of dispersion n value is 4~6.
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