CN109557286B - Durability test and service life evaluation method for electric heating windshield transparent part for helicopter - Google Patents
Durability test and service life evaluation method for electric heating windshield transparent part for helicopter Download PDFInfo
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- 238000012360 testing method Methods 0.000 title claims abstract description 166
- 238000005485 electric heating Methods 0.000 title claims abstract description 49
- 238000011156 evaluation Methods 0.000 title claims abstract description 16
- 238000000034 method Methods 0.000 claims abstract description 42
- 230000000694 effects Effects 0.000 claims abstract description 12
- 238000001816 cooling Methods 0.000 claims abstract description 9
- 230000032683 aging Effects 0.000 claims abstract description 7
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 34
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- 238000004088 simulation Methods 0.000 claims description 15
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- 238000001514 detection method Methods 0.000 claims description 7
- 239000006185 dispersion Substances 0.000 claims description 6
- 230000014759 maintenance of location Effects 0.000 claims description 6
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- 238000009434 installation Methods 0.000 description 5
- LFQSCWFLJHTTHZ-UHFFFAOYSA-N Ethanol Chemical compound CCO LFQSCWFLJHTTHZ-UHFFFAOYSA-N 0.000 description 4
- 239000000498 cooling water Substances 0.000 description 4
- 239000011521 glass Substances 0.000 description 4
- 230000003993 interaction Effects 0.000 description 4
- 238000004781 supercooling Methods 0.000 description 4
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- 238000011161 development Methods 0.000 description 3
- 230000018109 developmental process Effects 0.000 description 3
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- 229920006264 polyurethane film Polymers 0.000 description 3
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Abstract
The application provides a durability test and service life evaluation method for an electric heating windshield transparent part for a helicopter, which comprises the following steps: s100: taking a full-size windshield transparent piece as a sample, carrying out a damp-heat aging test on the sample, carrying out a photochemical effect test on the test after cooling at room temperature, and cooling at room temperature; s200: mounting the processed sample on test equipment according to the actual mounting state of the sample on a helicopter; s300: the method comprises the following steps of (1) testing a sample, wherein the testing of the sample comprises the steps of determining the load of the sample, testing the hot climate type environment of the sample and testing the cold climate type environment of the sample; s400: determining windshield valid test time T in a single use environment1Or T2And selecting the time T1And T2Minimum value of (1) is the windshield effective test time T under two environmentste(ii) a And obtaining the effective flight life time of the windshield according to the effective test time of the windshield. The application simulates the actual working state more truly, so that the examination result is more reliable.
Description
Technical Field
The application belongs to the technical field of helicopter durability tests, and particularly relates to a durability test and service life evaluation method for an electric heating windshield transparent part for a helicopter.
Background
With the strong demand of full territory and all-weather use of helicopters, the application of the electric heating windshield transparent piece with the functions of ice prevention and demisting in the helicopters is increased sharply. The electric heating windshield transparent part is usually of a sandwich composite structure, compared with a traditional single-layer windshield transparent part, the electric heating windshield transparent part is more in material variety and more complex in structure, so that factors influencing the durability of windshield products are greatly increased, comprehensive assessment work in the development process of the electric heating windshield transparent part is difficult to implement, and the test assessment life cannot be obtained.
In the assessment process of the existing windshield products, the windshield is generally subjected to single test environment assessment according to design requirements, such as high and low temperature, vibration and the like, and the test process cannot reflect the interaction of multiple factors; meanwhile, the influence of the reduction of the product performance on the use process of the product caused by the environmental factors with long-term effect cannot be examined; in addition, the common severe environment assessment in the practical use process of the windshield is lacked, for example, the low-temperature impact effect on the windshield is caused by the fact that the helicopter enters a cloud layer containing supercooled water drops when the electric heating function is started. Because the existing method for testing the durability of the multi-comprehensive environment of the electric heating windshield glass of the helicopter is in a blank stage, the service life of the windshield product cannot be evaluated by a test method, so that the failure of the windshield product cannot be determined when the windshield product fails in the service process, and the use safety has great hidden danger. .
Disclosure of Invention
The application aims to provide a durability test and service life evaluation method for an electric heating windshield transparent part for a helicopter, so as to solve any one of the problems.
The technical scheme of the application is as follows: a durability test and service life evaluation method for an electric heating windshield transparent part for a helicopter comprises the following steps:
s100: taking a full-size windshield transparent piece as a sample, carrying out a damp-heat aging test on the sample, carrying out a photochemical effect test on the test after cooling at room temperature, and cooling at room temperature;
s200: mounting the processed sample on test equipment according to the actual mounting state of the sample on a helicopter;
s300: the method comprises the following steps of (1) testing a sample, wherein the testing of the sample comprises the steps of determining the load of the sample, testing the hot climate type environment of the sample and testing the cold climate type environment of the sample;
s400: determining windshield valid test time T in a single use environmentte，TteIs T1Or T2Selecting a time T1And T2Minimum value of (1) is the windshield effective test time T under two environmentste；
The effective flight life time of the windshield is
n is the fatigue dispersion coefficient of the inorganic non-metallic material.
In the present application, in step S100, the method for testing the sample for humid heat aging includes: the sample is placed in an environment with the air temperature of 43 +/-2 ℃ and the humidity RH of more than or equal to 95 percent for 240 hours.
In the present application, in step S100, the method for testing the photochemical effect of the sample includes: the sample is placed in an environment with air temperature of 49 +/-2 ℃ and irradiance of 1120W/m2 for 240 h.
In the present application, the sample load determination in step S300 includes: s311: a single load cycle P1 → P2 → P3 → P1 is used to simulate the variation of the air pressure load of a transparent windshield during takeoff and landing, and a time of flight T1fThe sample is based on the maximum flying speed V of the helicoptermaxCruise speed VcDetermining; s312: the load P1 and the load P3 in the three-stage load are kept for a first preset time, the load P2 is kept for a second preset time, the load change rate is preset, and the load change time is a complete load cycle time TtpIt is not less than 0.5 min.
In the present application, in step 311, the load P1 ═ Vmax 2X eta/1600, load P2 ═ Vc 2X η/1600, load P3 ═ 0.8Vc)2And x eta/1600, wherein eta is the height variation coefficient of wind pressure, and the load direction is from the outer side to the inner side of the windshield and is vertical to the surface of the windshield.
In this application, in step 312, the first predetermined time is 2s to 10s, the second predetermined time is 2s to 80s, the predetermined load change rate is 10Pa/s to 400Pa/s, and the complete load cycle time Ttp is 0.5min to 15 min.
In the present application, in step S300, the hot climate type environment test of the sample includes:
s321: the hot climate environment type test is carried out by adopting a temperature-load orthogonal combination so as toThe predetermined time interval Tg is a test inspection cycle requirement for inspecting the windshield transparency at intervals, i.e. the total number of cycles Tg/T within the predetermined time interval Tg1fSecondly; the temperature gradient in the hot climate type is defined as 38 ℃ accounting for 95% of the implementation period and 52 ℃ accounting for 5% of the implementation period, namely the circulation times are respectively 0.95 × Tg/T1f、0.05*Tg/T1；
S322: after the sample is mounted, the following steps are carried out:
a) the simulation temperature outside the test equipment is controlled to be 38 +/-2 ℃, the simulation temperature inside the test equipment is controlled to be 4-32 ℃, and the load cycle (P1 → P2 → P3 → P1) is carried out by 0.95 Tg/T1fSecondly;
b) the simulated temperature outside the test equipment cabin rises to 52 +/-2 ℃, the temperature rising rate is more than 10 ℃/min, the simulated temperature in the cabin is controlled to be 4-32 ℃, and load circulation is carried out, wherein the load circulation frequency is 0.05 × Tg/T1f；
c) Tg/T per completion1fC, circulating from the step a to the step b, taking out the sample for quality detection, stopping the test if a failure mode occurs, and recording the test time; if no fault occurs, continuing to repeat the steps a to b until the sample fails or the specified test time is reached;
d) obtaining the effective test time T of the sample according to the step a, the step b and the step c1。
In the present application, the cold climate type environment test of the sample in step S300 includes
S331: the cold climate environment type test is also carried out by adopting a temperature-load orthogonal combination, namely, a complete load cycle is carried out under a certain temperature environment condition, namely, a flight rise and fall is simulated, and meanwhile, a preset time interval Tg is defined as the requirement of the test inspection period for inspecting the windshield transparent part, namely, the total cycle time Tg/T in the preset time interval Tg1fSecondly; the cold climate type temperature gradient is defined as 4 deg.C in 45% of the implementation period, 4 deg.C in 25% of the implementation period, 32 deg.C in 25% of the implementation period, 55 deg.C in 5% of the implementation period, i.e. the cycle number is 0.45 Tg/T1f、0.25*Tg/T1f、0.25*Tg/T1f、0.05*Tg/T1f；
S332: after the sample is mounted, the following steps are carried out:
a) the simulation temperature outside the test equipment cabin is set to be 4 +/-2 ℃, the simulation temperature in the cabin is controlled to be 4-32 ℃, and the load circulation is carried out at 0.45 × Tg/T1fSecondly; starting the electric heating function according to the actual maximum working power Pw at the beginning of each load cycle, finishing the electric heating function of Tp3 when the load P3 is preserved, and realizing heating and recovering to the ambient temperature of the windshield transparent part by electric heating in a cycle process; meanwhile, when the electric heating time reaches Tp3-Tc, beginning to impact supercooled water drops with the duration of Tc on the outer surface of the windshield transparent part, wherein the supercooled water drops have the parameters of the temperature of 0-minus 10 ℃, the diameter of the water drops of 5-20 um and the liquid water content of 0.2-10 g/m 3;
b) the simulated temperature outside the test equipment cabin is reduced to minus 4 +/-2 ℃, the temperature reduction rate is more than 10 ℃/min, the simulated temperature in the cabin is controlled to be 4-32 ℃, and load circulation is carried out, wherein 0.25 × Tg/T1fSecondly; starting the electric heating function according to the actual maximum working power Pw at the beginning of each load cycle, finishing the electric heating function of Tp3 when the load P3 is preserved, and realizing heating and recovering to the ambient temperature of the windshield transparent part by electric heating in a cycle process; meanwhile, when the electric heating time reaches Tp3-Tc, beginning to impact the supercooled water drops with the duration of Tc on the outer surface of the windshield transparent part, wherein the parameter temperature of the supercooled water drops is 0-minus 10 ℃, the diameter of the water drops is 5-20 um, and the liquid water content is 0.2-10 g/m 3;
c) the simulated temperature outside the test equipment cabin is reduced to minus 32 +/-2 ℃, the temperature reduction rate is more than 10 ℃/min, the simulated temperature in the cabin is controlled to be 4-32 ℃, and the load circulation is carried out for 0.25 × Tg/T1fSecondly;
d) the simulated temperature outside the test equipment cabin is reduced to minus 55 +/-2 ℃, the temperature reduction rate is more than 10 ℃/min, the simulated temperature in the cabin is controlled to be 4-32 ℃, and the load circulation is carried out for 0.05 × Tg/T1fSecondly;
e) Tg/T per completion1fStep a, step b, step c and step d are repeated, the sample is taken out for quality detection, if a failure mode occurs, the test is stopped, and the test time is recorded; if no fault occurs, continuing to repeat the steps a, b, c and d until the sample fails or the specified test time is reached;
f) obtaining the effective test time T of the sample according to the steps a, b, c, d and e2。
In the present application, the predetermined time interval Tg is 100 h.
In the present application, in step S400, the dispersion coefficient n of the inorganic non-metallic material is 4-6.
The test and service life evaluation method can detect potential defects existing in the design and process to the maximum extent in the development stage of the electric heating windshield transparent part, ensures that the electric heating windshield transparent part can execute correction measures in a cost-effective manner, guarantees the first flight safety of the helicopter, and can be used for guiding the outfield use of the windshield transparent part to improve the use safety of the product during service.
Drawings
In order to more clearly illustrate the technical solutions provided by the present application, the following briefly introduces the accompanying drawings. It is to be expressly understood that the drawings described below are only illustrative of some embodiments of the invention.
FIG. 1 is a flow chart of the steps of a windshield durability test and life assessment method of the present application;
FIG. 2 is a reference diagram of an experimental setup of an embodiment employed in the methods of the present application;
FIG. 3 is a method summary test spectrum block of the present application.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application.
In the description of the present application, the terms "central," "longitudinal," "lateral," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like refer to orientations or positional relationships illustrated in the drawings, which are used for convenience in describing the present application and to simplify the description, but do not indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and are therefore not to be considered limiting of the scope of the present application.
The application discloses a durability test and service life evaluation method for an electric heating windshield transparent part for a helicopter, which mainly comprises the following steps: sample (full-size windshield) pretreatment (damp heat-ultraviolet), test piece installation, test implementation and life evaluation judgment. The number of samples is determined according to the natural environment climate of the helicopter service area: the service environment types are divided into hot climate types and cold climate types, if the service environment types are used in a single environment climate type, 1 test corresponding to the environment climate types is carried out; if the test is used in two environments, the service life result is low after 1 test in each environment.
The durability test and service life evaluation method for the electric heating windshield transparent part for the helicopter is shown in the figures 1 to 3, and specifically comprises the following steps:
s100, sample pretreatment
S101, selecting a full-size windshield as a sample, placing the sample in an environment with the air temperature of 43 +/-2 ℃ and the humidity RH of more than or equal to 95% for 240 hours, cooling to room temperature after the damp-heat aging is finished, and taking out the sample;
s102, placing the sample after the damp and hot treatment at the air temperature of 49 +/-2 ℃ and the irradiance of 1120W/m2The interaction between the moist heat and the photochemical effect factor on the test piece is realized in 240 hours, and the test piece is cooled to room temperature and taken out after the photochemical effect is finished;
s200, mounting a sample
Referring to fig. 2, the preprocessed sample is installed on a test testing device (the skeleton outline dimension of the simulation cabin is consistent with the actual state of the background helicopter) according to the actual installation state on the helicopter, and the connection standard component, the material, the installation method and the like related to installation are consistent with the actual state;
s300, carrying out tests, wherein the test sample test comprises the steps of determining the load of the test sample, testing the hot climate type environment of the test sample and testing the cold climate type environment of the test sample
S310, determining sample load parameters
S311, single load cycle of the test (P1 → P2 →P3 → P1) for simulating a flight take-off and landing (a flight take-off and landing time is defined as T1fUnit h) air pressure load change of the windscreen transparency, in particular according to the maximum flying speed V of the background helicopter to which the windscreen transparency is appliedmaxCruise speed VcAnd (4) determining. Specifically, three load gradients P1, P2, P3 are defined for a single load cycle: p1 is Vmax 2X eta/1600 and P2 is Vc 2X eta/1600 and P3 is (0.8V)c)2X eta/1600, eta is the wind pressure height change coefficient, the load direction points to the inner side from the outer side of the windshield and is vertical to the surface of the windshield;
s312, the P1 and P3 load retention time in the three-level load is better than 2S-10S, the P2 load retention time is better than 2S-80S, the load change rate is better than 10 Pa/S-400 Pa/S, and a complete load cycle time TtpIs better than 0.5min to 15 min;
s320, testing the type of the hot climate environment
S321, carrying out a hot climate environment type test by adopting a temperature-load orthogonal combination, namely carrying out a complete load cycle under a certain temperature environment condition is equivalent to simulating a flight rise and fall, and simultaneously defining 100h as a test inspection period requirement for inspecting a windshield transparent part, namely defining the total cycle time within 100h as 100/T1fNext, the process is carried out. The temperature steps in the hot climate type are defined as 38 ℃ (95% implementation period) and 52 ℃ (5% implementation period), i.e. the cycle times are respectively 95/T1f、5/T1f。
To improve the feasibility of the test, a full inspection of the windshield quality is performed by simulating a flight time of 100h, see step S322.
S322, after the sample is mounted, the following steps are carried out:
a) the simulated temperature outside the test equipment is controlled to be 38 +/-2 ℃, the simulated temperature inside the test equipment is controlled to be 4-32 ℃, and load cycle (P1 → P2 → P3 → P1)95/T is carried out1fSecondly;
b) the simulated temperature outside the test equipment cabin rises to 52 +/-2 ℃, the temperature rising rate is more than 10 ℃/min, the simulated temperature inside the test equipment cabin is controlled to be 4-32 ℃, and load circulation (P1 → P2 → P3 → P1) is carried out, wherein the load circulation frequency is 5/T1f；
c) 100/T per completion1fAnd (c) repeating the steps from a to b (the speed of reducing the simulation temperature outside the cabin from 52 +/-2 ℃ to 38 ℃ in the circulating process is more than 10 ℃/min), and taking out a sample for quality detection. If a failure mode (electric heating function failure, cracks and delamination of inner and outer layer glass, bubbles of middle layer polyurethane film and the like) occurs, the test is stopped, and the test time is recorded; if no fault occurs, continuing to repeat the steps a to b until the sample fails or the specified test time is reached;
d) obtaining the effective test time T of the sample according to the steps a), b) and c)1。
S330 Cold climate type test
S331, the cold climate environment type test is also carried out by adopting a temperature-load orthogonal combination, namely, a complete load cycle is carried out under a certain temperature environment condition, namely, a flight rise and fall is simulated, and simultaneously 100h is defined as the test inspection period requirement for inspecting the windshield transparent part, namely, the total cycle time within 100h is 100/T1fNext, the process is carried out. The temperature steps in the cold climate type are defined as 4 ℃ (implementation period accounts for 45%), -4 ℃ (implementation period accounts for 25%), -32 ℃ (implementation period accounts for 25%), -55 ℃ (implementation period accounts for 5%), i.e. the number of cycles is 45/T respectively1f、25/T1f、25/T1f、5/T1f。
S332, after the sample is mounted, the following steps are carried out:
a) the simulation temperature outside the test equipment is set to be 4 +/-2 ℃, the simulation temperature inside the test equipment is controlled to be 4-32 ℃, and the load cycle (P1 → P2 → P3 → P1) is carried out at 45/T1fNext, the process is carried out. And starting the electric heating function according to the actual maximum working power Pw at the beginning of each load cycle, closing the electric heating function Tp3 when the load P3 is kept, and heating and recovering the windshield transparent part to the ambient temperature through electric heating in a cycle process. Meanwhile, when the electric heating time reaches Tp3-Tc (Tc is superior to 1S-30S), the outer surface of the windshield transparent part is impacted by supercooled water drops with the duration of Tc, and the parameters of the supercooled water drops (which can contain solvents such as alcohol and the like which do not damage the performance of the windshield transparent part) are superior to the temperature of 0-minus 10 ℃, the diameter of the water drops is 5-20 um, and the liquid water content is 0.2-10 g/m 3;
b) the simulated temperature outside the test equipment is reduced to minus 4 +/-2 ℃, the temperature reduction rate is more than 10 ℃/min, the simulated temperature inside the test equipment is controlled to be 4-32 ℃, and load circulation (P1 → P2 → P3 → P1) is carried out, wherein the ratio of the simulated temperature to the simulated temperature is 25/T1fNext, the process is carried out. At the beginning of each load cycle at the actual maximum operating power PwT is achieved when the electric heating function is started to finish the load P3 load protectionp3The electrical heating function is turned off, and the windshield transparent member is heated and restored to the ambient temperature by electrical heating in one cycle process. At the same time, T is reached in the electric heating timep3When the temperature is-Tc (Tc is better than 1S-30S), the super-cooled water drop impact with the duration Tc is started to be carried out on the outer surface of the windshield transparent part, the parameters of the super-cooled water drop (which can contain solvents such as alcohol and the like which do not damage the performance of the windshield transparent part) are better than that of the temperature of 0-10 ℃, the diameter of the water drop of 5-20 um and the liquid water content of 0.2-10 g/m3；
c) The simulated temperature outside the test equipment is reduced to minus 32 +/-2 ℃, the temperature reduction rate is more than 10 ℃/min, the simulated temperature inside the test equipment is controlled to be 4-32 ℃, and the load cycle (P1 → P2 → P3 → P1) is carried out at 25/T1fSecondly;
d) the simulated temperature outside the test equipment is reduced to minus 55 +/-2 ℃, the temperature reduction rate is more than 10 ℃/min, the simulated temperature inside the test equipment is controlled to be 4-32 ℃, and the load cycle (P1 → P2 → P3 → P1) is carried out for 5/T1fSecondly;
e) 100/T per completion1fStep a, step b, step c and step d are repeated (the speed of raising the simulation temperature outside the cabin from minus 55 +/-2 ℃ to 4 +/-2 ℃ in the circulation process is more than 10 ℃/min), the sample is taken out for quality detection, if a failure mode (electric heating function failure, cracks and delamination of inner and outer layer glass, bubbles of middle layer polyurethane film and the like) occurs, the test is stopped, and the test time is recorded; if no fault occurs, continuing to repeat the steps a, b, c and d until the sample fails or the specified test time is reached;
f) obtaining the effective test time T of the sample according to the steps a, b, c, d and e2。
S400, life evaluation judgment comprises the following steps:
s410, obtaining a single environment class in the stepEffective test time T of windshield for typeteIs T1(or T)2) Selecting effective test time T of windshield for two environment typesteIs T1、T2Lower values of;
s420, calculating the effective flight life time of the windshield transparent part
The unit is h, wherein n is the fatigue dispersion coefficient of the inorganic non-metallic material, and the recommended value is 4-6.
For a further understanding and appreciation of the contents and steps of the present application, a helicopter of some type will be described in detail by way of example.
The durability test method for the electric heating windshield transparent part for the helicopter comprises the following steps:
s100, sample pretreatment:
1) selecting a full-size windshield as a sample, placing the sample in an environment with the temperature of 43 +/-2 ℃ and the humidity RH of more than or equal to 95% for 240 hours, cooling to room temperature after the damp-heat aging is finished, and taking out the sample;
2) the samples after the damp-heat treatment are placed at the temperature of 49 +/-2 ℃ and the irradiance of 1120W/m2After the photochemical effect is finished, cooling to room temperature and taking out the product after the photochemical effect is finished in 240 hours;
s200, sample installation, comprising:
mounting the preprocessed sample on test testing equipment (the outline dimension of a skeleton of a simulation cabin is consistent with the actual state of a background helicopter) according to the actual mounting state on the helicopter, and keeping the connection standard part, the material, the mounting method and the like related to mounting consistent with the actual state;
s300, carrying out an experiment, comprising:
s310, determining load parameters
S311, maximum flight speed V of some helicoptersmaxIs 260km/h and a cruising speed VcThe wind pressure height change coefficient eta is 1.23 according to the height of 20m above the ground and the roughness of the B-type ground, and three-level load gradients P1, P2 and P3 are respectively as follows: 4010Pa (P1), 3590Pa (P2), 2297Pa (P3);
s312, the load in the test is 1 load cycle from P1 → P2 → P3 → P1, wherein the load holding time of P1 and P3 is 3S, the load holding time of P2 is 6S, the load change rate is 50Pa/S, and the complete load cycle time Tp is 1.342 min.
S320, supposing that the helicopter is in service in a cold climate type area, after the test sample is installed, carrying out the following steps in a cold climate type environment test:
s321, assuming that the flight time of one helicopter is defined as 10min (1/6h), the total cycle is 100/T within the 100h inspection period 1f400 times, and the circulation times of 4 ℃, 32 ℃ and 55 ℃ of each temperature step are 270, 150 and 30 respectively.
S322, after the sample is mounted, the following steps are carried out:
a) the simulated temperature outside the test equipment is controlled to be 4 +/-2 ℃, the simulated temperature inside the test equipment is controlled to be 4-32 ℃, and the load cycle (P1 → P2 → P3 → P1) is carried out for 270 times. According to step 3.1.2, from 0 to 46.3S (T) per load cyclep3) During which the power P is switched on at the actual maximum operating powerwThe electric heating function is performed, and at 40.3S, the super-cooling water drop impact of 6S is performed, and the super-cooling water drop is selected from alcohol water solution (temperature-4 deg.C, water drop diameter of 10um, liquid water content of 1g/m3)。
b) The simulated temperature outside the test equipment is controlled to be reduced to minus 4 +/-2 ℃, the temperature reduction rate is more than 10 ℃/min, the simulated temperature inside the test equipment is controlled to be 4-32 ℃, and load circulation (P1 → P2 → P3 → P1) is carried out for 150 times. 0-46.3S (T) in each load cyclep3) During which the power P is switched on at the actual maximum operating powerwThe electric heating function is performed, and at 40.3S, the super-cooling water drop impact of 6S is performed, and the super-cooling water drop is selected from alcohol-containing water solution (temperature-4 deg.C, water drop diameter of 10um, liquid water content of 1g/m3)。
c) The simulated temperature outside the test equipment is controlled to be reduced to minus 32 +/-2 ℃, the temperature reduction rate is more than 10 ℃/min, the simulated temperature inside the test equipment is controlled to be 4-32 ℃, and the load cycle (P1 → P2 → P3 → P1) is carried out for 150 times.
d) The simulated temperature outside the test equipment is controlled to be reduced to minus 55 +/-2 ℃, the temperature reduction rate is greater than 10 ℃/min, the simulated temperature inside the test equipment is controlled to be 4-32 ℃, and the load cycle (P1 → P2 → P3 → P1) is carried out for 30 times;
e) after the step a, the step b, the step c and the step d are completed for 600 times (the speed of raising the simulation temperature outside the cabin from minus 55 plus or minus 2 ℃ to 4 plus or minus 2 ℃ in the circulating process is more than 10 ℃/min), taking out a sample for quality detection, stopping the test if a failure mode (electric heating function failure, cracks and delamination of inner and outer layer glass, bubbles of a middle layer polyurethane film and the like) occurs, and recording the test time; if no fault occurs, continuing to repeat the steps a, b, c and d until the sample fails or the specified test time is reached;
f) totally completing 10 times of complete cycles according to the steps a, b, c, d and e to obtain the effective test time T of the sample2Is 1500 h.
S400, judging the service life, including:
taking the fatigue dispersion coefficient n of the inorganic non-metallic material as 4 and the effective flight life time T of the windshield transparent partL＝1500×10/1.342/4＝2794h。
The durability test and service life evaluation method for the electric heating windshield transparent part for the helicopter has the following advantages:
1) a brand-new durability test method and a brand-new durability test flow for the electric heating windshield transparent part are provided, the blank of the prior art is filled, and the effect which cannot be achieved by the prior method can be realized: potential defects existing in the design and process are detected to the maximum extent in the development stage, and the service life of the windshield transparent part is obtained;
2) the interaction caused by a plurality of environment assessment factors is considered, the interaction assessment factors comprise damp heat, photochemical effect, load, temperature and temperature impact, and the method is different from the existing traditional test method which adopts a single-factor or double-factor assessment factor incomplete assessment method;
3) a temperature impact test method based on a real working condition is designed, and a test method and parameters for realizing temperature impact by implementing low-temperature supercooled water drops through windshield electric heating are established;
4) the method adopts the aerodynamic load and temperature impact factors based on the flight process of the helicopter, is different from the prior traditional test which mainly adopts the assessment factors based on the storage environment, more truly simulates the actual working state, and has more reliable assessment results;
5) the temperature-load orthogonal combination test implementation method based on the preset time interval as the inspection period is adopted, so that the test period is more compact, and lower test cost and higher feasibility are obtained.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (5)
1. A durability test and service life evaluation method for an electric heating windshield transparent part for a helicopter is characterized by comprising the following steps:
s100: taking a full-size windshield transparent part as a sample, carrying out a damp-heat aging test on the sample, carrying out a photochemical effect test on the sample after cooling at room temperature, and cooling at room temperature, wherein the damp-heat aging test method of the sample comprises the following steps: placing the sample in an environment with air temperature of 43 +/-2 ℃ and humidity RH being more than or equal to 95% for 240 h; the photochemical effect test method of the sample comprises the following steps: placing the sample in an environment with air temperature of 49 +/-2 ℃ and irradiance of 1120W/m2 for 240 h;
s200: mounting the processed sample on test equipment according to the actual mounting state of the sample on a helicopter;
s300: the sample test, the sample test includes that sample load confirms, the hot climate type environmental test of sample and the cold climate type environmental test of sample, wherein:
the process of determining the specimen load comprises:
s311: a single load cycle P1 → P2 → P3 → P1 is used to simulate the variation of the air pressure load of a transparent windshield during takeoff and landing, and a time of flight T1fThe sample load being dependent on the maximum flying speed V of the helicoptermaxCruise speed VcDetermining;
s312: the load P1 and the load P3 in the three-stage load are kept for a first preset time, the load P2 is kept for a second preset time, the load change rate is preset, and the load cycle time T is one complete load cycle timetpIs not less than 0.5 min;
the hot climate type environmental test process of the test sample comprises the following steps:
s321: the hot climate environment type test is carried out by adopting a temperature-load orthogonal combination, and a preset time interval Tg is taken as the test inspection period requirement for inspecting the windshield transparent part at intervals, namely the total cycle time Tg/T in the preset time interval Tg1fSecondly; the temperature gradient in the hot climate type is defined as 38 ℃ accounting for 95% of the implementation period and 52 ℃ accounting for 5% of the implementation period, namely the circulation times are respectively 0.95 × Tg/T1f、0.05*Tg/T1；
S322: after the sample is mounted, the following steps are carried out:
a) the simulation temperature outside the test equipment is controlled to be 38 +/-2 ℃, the simulation temperature inside the test equipment is controlled to be 4-32 ℃, and the load cycle (P1 → P2 → P3 → P1) is carried out by 0.95 Tg/T1fSecondly;
b) the simulated temperature outside the test equipment cabin rises to 52 +/-2 ℃, the temperature rising rate is more than 10 ℃/min, the simulated temperature in the cabin is controlled to be 4-32 ℃, and load circulation is carried out, wherein the load circulation frequency is 0.05 × Tg/T1f；
c) Tg/T per completion1fC, circulating from the step a to the step b, taking out the sample for quality detection, stopping the test if a failure mode occurs, and recording the test time; if no fault occurs, continuing to repeat the steps a to b until the sample fails or the specified test time is reached;
d) obtaining the effective test time T of the sample according to the step a, the step b and the step c1；
The cold climate type environmental test procedure of the test specimen includes:
s331: the cold climate environment type test is also carried out by adopting a temperature-load orthogonal combination, namely, a complete load cycle is carried out under a certain temperature environment condition, which is equivalent to simulating a flight rise and fall, and meanwhile, a preset time interval Tg is defined as the test inspection period requirement for inspecting the windshield transparent part, namelyTotal number of cycles Tg/T within a predetermined time interval Tg1fSecondly; the cold climate type temperature gradient is defined as 4 deg.C in 45% of the implementation period, 4 deg.C in 25% of the implementation period, 32 deg.C in 25% of the implementation period, 55 deg.C in 5% of the implementation period, i.e. the cycle number is 0.45 Tg/T1f、0.25*Tg/T1f、0.25*Tg/T1f、0.05*Tg/T1f；
S332: after the sample is mounted, the following steps are carried out:
a) the simulation temperature outside the test equipment cabin is set to be 4 +/-2 ℃, the simulation temperature in the cabin is controlled to be 4-32 ℃, and the load circulation is carried out at 0.45 × Tg/T1fSecondly; starting the electric heating function according to the actual maximum working power Pw at the beginning of each load cycle, closing the electric heating function when the load retention time Tp3 of the load P3 is completed, and realizing temperature rise and recovery to the ambient temperature of the windshield transparent part through electric heating in a cycle process; meanwhile, when the electric heating time reaches the difference value between the load retention time Tp3 and the impact time length Tc of the supercooled water drops, the supercooled water drops with the time length Tc are impacted on the outer surface of the windshield transparent piece, and the supercooled water drops have the parameters of the temperature of 0-minus 10 ℃, the water drop diameter of 5-20 mu m and the liquid water content of 0.2-10 g/m 3;
b) the simulated temperature outside the test equipment cabin is reduced to minus 4 +/-2 ℃, the temperature reduction rate is more than 10 ℃/min, the simulated temperature in the cabin is controlled to be 4-32 ℃, and load circulation is carried out, wherein 0.25 × Tg/T1fSecondly; starting the electric heating function according to the actual maximum working power Pw at the beginning of each load cycle, closing the electric heating function when the load retention time Tp3 of the load P3 is completed, and realizing temperature rise and recovery to the ambient temperature of the windshield transparent part through electric heating in a cycle process; meanwhile, when the electric heating time reaches the difference value between the load retention time Tp3 and the impact time length Tc of the supercooled water drops, the supercooled water drops with the time length Tc are impacted on the outer surface of the windshield transparent part, the parameter temperature of the supercooled water drops is 0-minus 10 ℃, the diameter of the water drops is 5-20 mu m, and the liquid water content is 0.2-10 g/m 3;
c) the simulated temperature outside the test equipment cabin is reduced to minus 32 +/-2 ℃, the temperature reduction rate is more than 10 ℃/min, the simulated temperature in the cabin is controlled to be 4-32 ℃, and the load circulation is carried out for 0.25 × Tg/T1fSecondly;
d) test apparatusThe simulated temperature outside the cabin is reduced to minus 55 +/-2 ℃, the temperature reduction rate is more than 10 ℃/min, the simulated temperature in the cabin is controlled to be 4-32 ℃, and the load cycle is carried out at 0.05 × Tg/T1fSecondly;
e) Tg/T per completion1fStep a, step b, step c and step d are repeated, the sample is taken out for quality detection, if a failure mode occurs, the test is stopped, and the test time is recorded; if no fault occurs, continuing to repeat the steps a, b, c and d until the sample fails or the specified test time is reached;
f) obtaining the effective test time T of the sample according to the steps a, b, c, d and e2；
S400: determining windshield valid test time T in a single use environmentte，TteIs T1Or T2Selecting a time T1And T2Minimum value of (1) is the windshield effective test time T under two environmentste；
The effective flight life time of the windshield is
n is the fatigue dispersion coefficient of the inorganic non-metallic material.
2. The method for testing durability and evaluating life span of a transparent member of an electrically heated windshield for a helicopter of claim 1, wherein in step S311, the load P1 ═ Vmax 2X eta/1600, load P2 ═ Vc 2X η/1600, load P3 ═ 0.8Vc)2And x eta/1600, wherein eta is the height variation coefficient of wind pressure, and the load direction is from the outer side to the inner side of the windshield and is vertical to the surface of the windshield.
3. The method for durability test and life evaluation of a transparency for a helicopter in accordance with claim 2, wherein in step S312, the first predetermined time is 2S to 10S, the second predetermined time is 2S to 80S, the predetermined load change rate is 10Pa/S to 400Pa/S, and the complete load cycle time is tpTIs 0.5min to 15 min.
4. The method for durability testing and life evaluation of an electrically heated windshield transparency for a helicopter as claimed in claim 1 wherein said predetermined time interval Tg is 100 hours.
5. The durability test and service life evaluation method for the helicopter electric heating windshield transparent part according to claim 1, characterized in that in step S400, the dispersion coefficient n of the inorganic non-metallic material is 4-6.
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