CN111595707B - In-situ testing device and method for high-low cycle composite fatigue performance of material - Google Patents
In-situ testing device and method for high-low cycle composite fatigue performance of material Download PDFInfo
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- 238000011065 in-situ storage Methods 0.000 title claims abstract description 65
- 238000012360 testing method Methods 0.000 title claims abstract description 44
- 238000000034 method Methods 0.000 title claims abstract description 29
- 239000002131 composite material Substances 0.000 title claims abstract description 28
- 239000000463 material Substances 0.000 title claims abstract description 15
- 238000012544 monitoring process Methods 0.000 claims abstract description 41
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- 238000003384 imaging method Methods 0.000 claims description 8
- 238000003825 pressing Methods 0.000 claims description 6
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- 238000005452 bending Methods 0.000 claims description 4
- 150000001875 compounds Chemical class 0.000 claims description 4
- 238000003199 nucleic acid amplification method Methods 0.000 claims description 4
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- 238000010998 test method Methods 0.000 claims description 2
- 238000011156 evaluation Methods 0.000 abstract description 5
- 238000012800 visualization Methods 0.000 abstract description 3
- 238000009661 fatigue test Methods 0.000 description 5
- 238000010586 diagram Methods 0.000 description 4
- 230000001681 protective effect Effects 0.000 description 4
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- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/32—Investigating strength properties of solid materials by application of mechanical stress by applying repeated or pulsating forces
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- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
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- G01N3/068—Special adaptations of indicating or recording means with optical indicating or recording means
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- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/32—Investigating strength properties of solid materials by application of mechanical stress by applying repeated or pulsating forces
- G01N3/38—Investigating strength properties of solid materials by application of mechanical stress by applying repeated or pulsating forces generated by electromagnetic means
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/0001—Type of application of the stress
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- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
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- G01N2203/006—Crack, flaws, fracture or rupture
- G01N2203/0062—Crack or flaws
- G01N2203/0064—Initiation of crack
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Abstract
The invention relates to an in-situ testing device and method for high-low cycle composite fatigue performance of a material, and belongs to the field of precise scientific instruments. The instrument support frame in the device is used for realizing stable support and precise positioning of other functional modules; the low-frequency load loading module is driven by servo hydraulic pressure and is used for loading the low-frequency fatigue load of 0.001-50 Hz of the sample; the high-frequency load loading module adopts electromagnetic resonance driving and is used for realizing high-frequency fatigue load loading of 5-5000 Hz of the sample, and the high-frequency load loading module and the high-frequency fatigue load loading module can be used independently or matched with each other to jointly construct high-low cycle composite fatigue load; the in-situ monitoring module is used for realizing high-resolution visual dynamic monitoring of the fatigue crack initiation, propagation and fracture process of the sample. The method has the advantages of wide test frequency band, large load range, high test precision, dynamic visualization and the like, and provides a feasible method for fatigue characteristic test, service safety evaluation and fatigue life prediction of the turbine blade of the aeroengine under the condition of approaching to actual service.
Description
Technical Field
The invention relates to the field of precise scientific instruments, in particular to an in-situ test device and method for high-low cycle composite fatigue performance of a material. The method can construct low-frequency fatigue load, high-frequency fatigue load and high-low cycle composite fatigue load, and combines in-situ imaging equipment to realize high-resolution visual parallel in-situ monitoring of the fatigue crack initiation, propagation and fracture process of the tested sample, thereby providing a feasible method for fatigue characteristic test, service safety evaluation and fatigue life prediction of the turbine blade of the aeroengine under the condition close to the actual service condition.
Background
The aeroengine is the most core component in the aircraft, and the turbine blade is the most important component in the aeroengine, and the structure is complex, the service working condition is bad, so that the service safety evaluation and the reliability prediction become key problems in the aircraft manufacturing industry. Through statistics, in the turbine blade faults, fatigue failure accounts for more than half of the total failure, and the national security and the national economy development are seriously threatened.
The fatigue performance research of the turbine blades of the aircraft engine is always a focus of attention of domestic and foreign scholars, a great number of domestic and foreign scholars develop deeper research on the failure mechanism of the turbine blade materials of the aircraft under the interaction of low cycle fatigue, high cycle fatigue and creep-fatigue, and a plurality of universities and enterprises develop corresponding test equipment. Numerous reports indicate that the fatigue failure of turbine blades is mostly high-cycle load superimposed on the basis of low-cycle load peaks, resulting in high-low cycle composite fatigue failure. Therefore, the development of the high-low cycle composite fatigue research of the turbine blade material is significant for correctly understanding the fatigue failure mechanism and evaluating the service safety. However, limited by the existing instrumentation and testing methods, studies on high and low cycle composite fatigue of turbine blade materials are still in the initiation stage.
The existing high-low cycle compound fatigue test is generally carried out on a conventional fatigue testing machine, the maximum frequency of the conventional fatigue testing machine is generally tens to hundreds of hertz, and the high-frequency vibration load of kilohertz on turbine blades of an aircraft engine cannot be simulated; because the conventional fatigue testing machine cannot realize in-situ observation, macro-micro morphology change and fatigue crack initiation position and extension condition of the surface of the sample in the fatigue testing process are difficult to visually monitor. Therefore, it is important to develop an in-situ testing device for the high-low cycle composite fatigue performance of a material.
Disclosure of Invention
The invention aims to provide an in-situ test device and method for high-low cycle composite fatigue performance of a material, and solves the problems in the prior art. The device provided by the invention consists of an instrument supporting frame, a low-frequency load loading module, a high-frequency load loading module and an in-situ monitoring module, can construct a low-frequency fatigue load, a high-frequency fatigue load and a high-low cycle composite fatigue load, and is combined with in-situ imaging equipment to realize high-resolution visualization parallel in-situ monitoring of the fatigue crack initiation, propagation and fracture process of a tested sample, so that a feasible method is provided for fatigue characteristic test, service safety evaluation and fatigue life prediction of the turbine blade of the aeroengine under the condition close to the actual service condition.
The above object of the present invention is achieved by the following technical solutions:
The in-situ test device for the high-low cycle composite fatigue performance of the material comprises an instrument support frame 1, a low-frequency load loading module 2, a high-frequency load loading module 3 and an in-situ monitoring module 4, wherein the instrument support frame 1 is connected with a foundation through foundation bolts on a support base 104, and a servo oil cylinder 206 of the low-frequency load loading module 2 is rigidly connected with an upper support frame 102 to realize the loading of a low-frequency fatigue load of 0.001-50 Hz to a sample; the high-frequency vibration table 303 of the high-frequency load loading module 3 is rigidly connected with the foundation, so that the high-frequency fatigue load loading of 5-5000 Hz of the sample is realized; the L-shaped connecting plate 402 of the in-situ monitoring module 4 is rigidly connected with the upper supporting frame 102, so that high-resolution visual parallel in-situ monitoring of the specimen fatigue crack initiation, propagation and fracture process is realized.
The low-frequency load loading module 2 is vertically arranged and is rigidly connected with the foundation through screws; the high-frequency load loading module 3 is vertically arranged and is rigidly connected with the instrument support frame 1 through screws; the low-frequency load loading module 2 and the high-frequency load loading module 3 are used independently to respectively realize low-frequency fatigue load loading of 0.001-50 Hz and high-frequency fatigue load loading of 5-5000 Hz of the sample; the low-frequency load loading module 2 and the high-frequency load loading module 3 are matched with each other for use to jointly construct high-low cycle composite fatigue load.
The low-frequency load loading module 2 and the in-situ monitoring module 4 are rigidly connected with an upper support frame 102 of the instrument support frame 1 through screws, the instrument support frame 1 comprises a precise guide mechanism 101, an upper support frame 102, a precise adjusting mechanism 103 and a support base 104, the precise adjusting mechanism 103 is matched with the precise guide mechanism 101 to drive the upper support frame 102 to move precisely, so that the low-frequency load loading module 2 and the in-situ monitoring module 4 are driven to move precisely to adapt to samples with different sizes.
The high-frequency load loading module 3 comprises a high-precision displacement measuring assembly 301, a precise frequency conversion assembly 302 and a high-frequency vibration table 303, wherein the high-precision displacement measuring assembly 301, the precise frequency conversion assembly 302 and the high-frequency vibration table 303 are rigidly connected with a foundation through bolts, and the precise frequency conversion assembly 302 is rigidly connected with the high-frequency vibration table 303 through bolts.
The electric cylinder 30206 of the precise frequency conversion assembly 302 can output precise linear motion, and the cantilever length of the amplitude amplifying arm 30210 is precisely adjusted, so that precise stepless adjustment of the test resonance frequency is realized; the electric cylinder support frame 30207 is rigidly connected with the foundation, the electric cylinder seat 30205 is rigidly connected with the electric cylinder support frame 30207, and the end part of an output shaft 30204 of the electric cylinder 30206 is connected with the left end of the amplitude amplifying arm 30210; the amplitude amplifying arm 30210 is in clearance fit with the groove of the amplifier base 30209, the amplifier base 30209 is rigidly connected with the mounting table of the high-frequency load loading module 3, the locking cylinder support 30208 is rigidly connected with the amplifier base 30209, the hydraulic locking cylinder 30203 is rigidly connected with the locking cylinder support 30208, the output shaft of the hydraulic locking cylinder 30203 is embedded in the upper mounting hole of the amplifier base 30209, the sample 30201 is placed at the clamping position of the amplitude amplifying arm 30210 by the clamping end, the pressing block 30202 is placed on the sample 30201, and the sample is locked by a bolt.
The invention further aims to provide a method for testing the fatigue performance of the high-low cycle composite material in situ, which comprises the following specific steps:
Step one, sample 30201 clamping: placing the clamped end of the sample 30201 at the clamping position of the amplitude amplification arm 30210, covering the pressing block 30202, and locking by a screw to complete clamping of the sample 30201;
step two, test frequency adjustment: adjusting the clamping force of the hydraulic locking cylinder 30203 to bring the amplitude amplifying arm 30210 to an adjustable state; starting an electric cylinder 30206, precisely adjusting the cantilever length of an amplitude amplifying arm 30210 to reach the resonance frequency required by the test by adopting displacement control; adjusting the clamping force of the hydraulic locking cylinder 30203 to firmly clamp the amplitude amplifying arm 30210;
Step three, adjusting the relative position of the upper support 102: starting a precise adjusting mechanism 103, and adjusting the relative position of the upper support frame 102, so that the curved ejector rod of the low-frequency load loading module 2 is ensured to be positioned at the load loading position of the sample 30201, and each in-situ imaging device in the in-situ monitoring module 4 can smoothly observe the sample;
step four, loading a low-frequency load: synchronously starting a low-frequency load loading module 2, an in-situ monitoring module 4 and a laser vibration meter 30103, and loading a sample 30201 with a low-frequency load; the laser vibration meter 30103 feeds back the measured amplitude signal of the end part of the sample 30201 in real time, so that closed-loop control of low-frequency amplitude is realized;
step five, loading high-frequency load: after the low-frequency load is loaded, the high-frequency load loading module 3 is started rapidly, and the high-frequency load is loaded on the sample 30201; the laser vibration meter 30103 feeds back the measured amplitude signal of the end part of the sample 30201 in real time, so that closed-loop control of high-frequency amplitude is realized;
Step six, loading high-low cycle compound load: repeating the fourth and fifth steps according to the load spectrum input in the test process, and loading the high-low cycle composite load on the sample 30201 until the whole load spectrum is completed or the sample 30201 is broken;
step seven, parallel in-situ monitoring: synchronously starting all in-situ imaging equipment in the in-situ monitoring module 4 until the test is finished while performing the step four; the digital speckle strain gauge 401 collects full-field strain information of the sample 30201 in real time, the high-speed camera 404 dynamically observes vibration information of the sample 30201 and captures expansion and fracture of macro cracks on the surface of the sample 30201, and the infrared camera 405 monitors heat dissipation in the test process of the sample 30201 and rapidly positions crack initiation positions of the sample 30201.
The invention has the beneficial effects that:
1. Adopts a modularized design idea. The invention consists of an instrument supporting frame, a low-frequency load loading module, a high-frequency load loading module and an in-situ monitoring module, is highly modularized, and is convenient for maintenance and function expansion.
2. The test frequency range is wide. The low-frequency load loading module and the high-frequency load loading module can respectively realize the low-frequency fatigue load loading of 0.001-50 Hz and the high-frequency fatigue load loading of 5-5000 Hz of the tested sample, and can also be mutually matched for use, so that the fatigue load loading of 0.001-5000 Hz of the tested sample is realized.
3. Can be monitored in situ. The invention is provided with an in-situ monitoring module, comprises a digital speckle strain gauge, a high-speed camera and an infrared camera, and can realize high-resolution visual parallel in-situ monitoring of the fatigue crack initiation, propagation and fracture process of the tested sample.
Drawings
The accompanying drawings, which are included to provide a further understanding of the application and are incorporated in and constitute a part of this specification, illustrate and explain the application and together with the description serve to explain the application.
FIG. 1 is a schematic view of the overall appearance structure of the present invention;
FIG. 2 is a schematic view of the instrument support frame structure of the present invention;
FIG. 3 is a schematic diagram of a low frequency load loading module according to the present invention;
FIG. 4 is a schematic view of a high frequency load loading module structure according to the present invention;
FIG. 5 is a schematic diagram of a high-precision displacement measurement assembly according to the present invention;
FIG. 6 is a schematic diagram of a precision frequency conversion assembly according to the present invention;
FIG. 7 is a schematic diagram of an in-situ monitoring module according to the present invention;
Fig. 8 is a cross-sectional view of a precision frequency conversion assembly of the present invention.
In the figure: 1. an instrument integral frame; 2. a low frequency load loading module; 3. a high frequency load loading module; 4. an in-situ monitoring module; 101. a precision guide mechanism; 102. an upper support frame; 103. a precise adjusting mechanism; 104. a support base; 201. a force sensor; 202. a piston rod; 203. a valve block assembly; 204. a protective sleeve; 205. an accumulator; 206. a servo cylinder; 207. an intermediate connection; 208. bending the ejector rod; 301. a high-precision displacement measurement assembly; 302. a precision frequency conversion assembly; 303. a high frequency vibration table; 30101. a first fixing seat; 30102. a fixing frame; 30103. a laser vibrometer; 30104. a column; 30201. a sample; 30202. briquetting; 30203. a hydraulic locking cylinder; 30204. an output shaft; 30205. an electric cylinder base; 30206. an electric cylinder; 30207. an electric cylinder supporting frame; 30208. a locking cylinder support; 30209. an amplifier base; 30210. an amplitude amplification arm; 401. digital speckle strain gauge; 402. an L-shaped connecting plate; 403. a second fixing seat; 404. a high-speed camera; 405. an infrared camera.
Detailed Description
The details of the present invention and its specific embodiments are further described below with reference to the accompanying drawings.
Referring to fig. 1 to 8, the device and the method for in-situ testing the high-low cycle composite fatigue performance of the material are disclosed, wherein the device comprises an instrument support frame, a low-frequency load loading module, a high-frequency load loading module and an in-situ monitoring module. The instrument support frame is used for realizing stable support and precise positioning of other functional modules; the low-frequency load loading module is driven by servo hydraulic pressure and is used for loading the low-frequency fatigue load of 0.001-50 Hz of the tested sample; the high-frequency load loading module adopts electromagnetic resonance driving and is used for loading the high-frequency fatigue load of 5-5000 Hz of the tested sample, and the high-frequency load loading module can be used independently or matched with each other to jointly construct high-low cycle composite fatigue load; the in-situ monitoring module is mainly used for realizing high-resolution visual dynamic monitoring of the fatigue crack initiation, propagation and fracture process of the tested sample. The method has the advantages of wide test frequency band, large load range, high test precision, dynamic visualization and the like, and provides a feasible method for fatigue characteristic test, service safety evaluation and fatigue life prediction of the turbine blade of the aeroengine under the condition of approaching to actual service.
The invention relates to a material high-low cycle composite fatigue performance in-situ testing device, which comprises an instrument support frame 1, a low-frequency load loading module 2, a high-frequency load loading module 3 and an in-situ monitoring module 4, wherein the instrument support frame 1 comprises a precise guide mechanism 101, an upper support frame 102, a precise adjusting mechanism 103 and a support base 104, and is connected with a foundation through anchor bolts on the support base 104 for realizing stable support and precise positioning of other functional modules. The low-frequency load loading module 2 comprises a force sensor 201, a piston rod 202, a valve block assembly 203, a protective sleeve 204, an energy accumulator 205, a servo oil cylinder 206, a middle connecting piece 207 and a bending ejector rod 208, wherein the servo oil cylinder 206 flange is rigidly connected with the upper support frame 102 through screws and is used for loading the low-frequency fatigue load of 0.001-50 Hz of a sample. The high-frequency load loading module 3 comprises a high-precision displacement measuring assembly 301, a precise frequency conversion assembly 302 and a high-frequency vibration table 303, wherein the lower end of the high-frequency vibration table 303 is rigidly connected with a foundation through a screw, and is used for loading high-frequency fatigue load of 5-5000 Hz to a sample. The in-situ monitoring module 4 comprises a digital speckle strain gauge 401, an L-shaped connecting plate 402, a fixed seat 403, a high-speed camera 404 and an infrared camera 405, wherein the L-shaped connecting plate 402 is rigidly connected with the upper support frame 102 through screws and is used for realizing high-resolution visual parallel in-situ monitoring of the initiation, the expansion and the fracture process of the fatigue crack of the sample.
Referring to fig. 2, the instrument support frame 1 of the present invention comprises a precision guide mechanism 101, an upper support frame 102, a precision adjustment mechanism 103, and a support base 104, wherein: the lower ends of the support base 104 are rigidly connected with the foundation through bolts, the lower ends of the precise guide mechanism 101 and the precise adjustment mechanism 103 are rigidly connected with the upper ends of the support base 104 through bolts, and the lower ends of the upper support frame 102 are rigidly connected with the upper ends of the precise guide mechanism 101 and the precise adjustment mechanism 103 through bolts respectively; eight countersunk holes are formed in the lower end of the upper support frame 102, eight threaded holes are formed in the support base 104, and when the upper support frame 102 moves to a preset position, the lower portion of the upper support frame 102 is connected with the support base 104 through bolts.
Referring to fig. 3, the low frequency load loading module 2 of the present invention is vertically arranged and rigidly connected to the foundation by screws; the high-frequency load loading module 3 is vertically arranged and is rigidly connected with the instrument support frame 1 through screws; the low-frequency load loading module 2 and the high-frequency load loading module 3 are used independently to respectively realize low-frequency fatigue load loading of 0.001-50 Hz and high-frequency fatigue load loading of 5-5000 Hz of the sample; the low-frequency load loading module 2 and the high-frequency load loading module 3 are matched with each other for use to jointly construct high-low cycle composite fatigue load.
The low-frequency load loading module 2 comprises a force sensor 201, a piston rod 202, a valve block assembly 203, a protective sleeve 204, an energy accumulator 205, a servo oil cylinder 206, an intermediate connecting piece 207 and a bending ejector rod 208, wherein: the protective sleeve 204 is rigidly connected with a flange at the rear end of the servo oil cylinder 206 through bolts, external threads on the energy accumulator 205 are rigidly connected with internal threads on the valve block assembly 203, the valve block assembly 203 is rigidly connected with the servo oil cylinder 206 through bolts, the output end of the piston rod 202 is rigidly connected with the upper end of the force sensor 201 through an intermediate connecting piece 207, and a threaded hole at the lower end of the force sensor 201 is matched with external threads at the upper end of the bent ejector rod 208 to realize rigid connection.
The low-frequency load loading module 2 and the in-situ monitoring module 4 are rigidly connected with an upper support frame 102 of the instrument support frame 1 through screws, the instrument support frame 1 comprises a precise guide mechanism 101, an upper support frame 102, a precise adjusting mechanism 103 and a support base 104, the precise adjusting mechanism 103 is matched with the precise guide mechanism 101 to drive the upper support frame 102 to move precisely, so that the low-frequency load loading module 2 and the in-situ monitoring module 4 are driven to move precisely to adapt to samples with different sizes.
Referring to fig. 4, the high-frequency load loading module 3 of the present invention comprises a high-precision displacement measuring assembly 301, a precision frequency conversion assembly 302, and a high-frequency vibration table 303, all of which are rigidly connected to a foundation by bolts, and the precision frequency conversion assembly 302 is rigidly connected to the high-frequency vibration table 303 by bolts.
Referring to fig. 5, the high-precision displacement measurement assembly 301 of the present invention comprises a fixed base 30101, a fixed base 30102, a laser vibrometer 30103 and a stand 30104, wherein: the first fixing base 30101 is rigidly connected with the foundation by bolts, the lower end of the upright post 30104 is in interference fit with the upper end of the fixing base 30101, the fixing frame 30102 is arranged on the upright post 30104, and the laser vibration meter 30103 is rigidly connected with the fixing frame 30102 by bolts.
Referring to fig. 6 and 8, the precision frequency conversion assembly 302 of the present invention includes a sample 30201, a press block 30202, a hydraulic lock cylinder 30203, an output shaft 30204, a cylinder block 30205, a cylinder 30206, a cylinder support 30207, a lock cylinder support 30208, an amplifier base 30209, and an amplitude amplifying arm 30210, wherein: the electric cylinder 30206 can output accurate linear motion, and the cantilever length of the amplitude amplifying arm 30210 is accurately adjusted, so that accurate stepless adjustment of the test resonance frequency is realized; the lower end of the electric cylinder support frame 30207 is rigidly connected with a foundation through a bolt, the electric cylinder seat 30205 is rigidly connected with the electric cylinder support frame 30207 through a bolt, and the end part of an output shaft 30204 of the electric cylinder 30206 is connected with the left end of the amplitude amplifying arm 30210; the amplitude amplifying arm 30210 is in clearance fit with a groove of the amplifier base 30209, the amplifier base 30209 is rigidly connected with a mounting table surface of the high-frequency load loading module 3 through bolts, the locking cylinder support 30208 is rigidly connected with the amplifier base 30209 through bolts, the hydraulic locking cylinder 30203 is rigidly connected with the locking cylinder support 30208 through bolts, an output shaft of the hydraulic locking cylinder 30203 is embedded into an upper mounting hole of the amplifier base 30209, a sample 30201 is placed at a clamping position of the amplitude amplifying arm 30210 by a clamping end, and a pressing block 30202 is placed on the sample 30201 and is locked by bolts.
Referring to fig. 7, the in-situ monitoring module 4 of the present invention comprises a digital speckle strain gauge 401, an "L" shaped connection plate 402, a fixing base 403, a high-speed camera 404, and an infrared camera 405, wherein: the digital speckle strain gauge 401 is rigidly connected with the L-shaped connecting plate 402 through bolts, the high-speed camera 404 and the infrared camera 405 are rigidly connected with the second fixing seat 403 through bolts respectively, and the L-shaped connecting plate 402 and the second fixing seat 403 are rigidly connected with the upper supporting frame 102 through bolts respectively.
Referring to fig. 1 to 8, the in-situ test method for the fatigue performance of the high-low cycle composite material comprises the following specific steps when in-situ test of the fatigue performance of the high-low cycle composite material:
Step one, sample 30201 clamping: placing the clamped end of the sample 30201 at the clamping position of the amplitude amplifying arm 30210, covering the pressing block 30202 and locking by a screw, so as to clamp the sample 30201 (the clamping force is not too small or too large during clamping, otherwise the sample is easy to loosen or generate local plastic deformation);
step two, test frequency adjustment: adjusting the clamping force of the hydraulic locking cylinder 30203 to bring the amplitude amplifying arm 30210 to an adjustable state; starting an electric cylinder 30206, precisely adjusting the cantilever length of an amplitude amplifying arm 30210 to reach the resonance frequency required by the test by adopting displacement control; adjusting the clamping force of the hydraulic locking cylinder 30203 to firmly clamp the amplitude amplifying arm 30210;
Step three, adjusting the relative position of the upper support 102: starting a precise adjusting mechanism 103, and adjusting the relative position of the upper support frame 102, so that the curved ejector rod of the low-frequency load loading module 2 is ensured to be positioned at the load loading position of the sample 30201, and each in-situ imaging device in the in-situ monitoring module 4 can smoothly observe the sample;
step four, loading a low-frequency load: synchronously starting a low-frequency load loading module 2, an in-situ monitoring module 4 and a laser vibration meter 30103, and loading a sample 30201 with a low-frequency load; the laser vibration meter 30103 feeds back the measured amplitude signal of the end part of the sample 30201 in real time, so that closed-loop control of low-frequency amplitude is realized;
step five, loading high-frequency load: after the low-frequency load is loaded, the high-frequency load loading module 3 is started rapidly, and the high-frequency load is loaded on the sample 30201; the laser vibration meter 30103 feeds back the measured amplitude signal of the end part of the sample 30201 in real time, so that closed-loop control of high-frequency amplitude is realized;
Step six, loading high-low cycle compound load: repeating the fourth and fifth steps according to the load spectrum input in the test process, and loading the high-low cycle composite load on the sample 30201 until the whole load spectrum is completed or the sample 30201 is broken;
step seven, parallel in-situ monitoring: synchronously starting all in-situ imaging equipment in the in-situ monitoring module 4 until the test is finished while performing the step four; the digital speckle strain gauge 401 collects full-field strain information of the sample 30201 in real time, the high-speed camera 404 dynamically observes vibration information of the sample 30201 and captures expansion and fracture of macro cracks on the surface of the sample 30201, and the infrared camera 405 monitors heat dissipation in the test process of the sample 30201 and rapidly positions crack initiation positions of the sample 30201.
The above description is only a preferred example of the present invention and is not intended to limit the present invention, but various modifications and variations can be made to the present invention by those skilled in the art. Any modification, equivalent replacement, improvement, etc. of the present invention should be included in the protection scope of the present invention.
Claims (3)
1. The utility model provides a material high low week complex fatigue performance normal position testing arrangement which characterized in that: the device comprises an instrument support frame (1), a low-frequency load loading module (2), a high-frequency load loading module (3) and an in-situ monitoring module (4), wherein the instrument support frame (1) is connected with a foundation through foundation bolts on a support base (104), and a servo oil cylinder (206) of the low-frequency load loading module (2) is rigidly connected with an upper support frame (102) to realize low-frequency fatigue load loading of 0.001-50 Hz on a sample; the high-frequency vibration table (303) of the high-frequency load loading module (3) is rigidly connected with the foundation, so that the high-frequency fatigue load loading of 5-5000 Hz of the sample is realized; the L-shaped connecting plate (402) of the in-situ monitoring module (4) is rigidly connected with the upper supporting frame (102), so that high-resolution visual parallel in-situ monitoring of the specimen fatigue crack initiation, propagation and fracture process is realized;
The low-frequency load loading modules (2) are vertically arranged, the high-frequency load loading modules (3) are vertically arranged, and the low-frequency load loading modules (2) and the high-frequency load loading modules (3) are independently used to respectively realize low-frequency fatigue load loading of 0.001-50 Hz and high-frequency fatigue load loading of 5-5000 Hz of the sample; the low-frequency load loading module (2) and the high-frequency load loading module (3) are matched with each other for use to jointly construct a high-low cycle composite fatigue load;
The high-frequency load loading module (3) comprises a high-precision displacement measuring assembly (301), a precise frequency conversion assembly (302) and a high-frequency vibration table (303), all of which are rigidly connected with a foundation through bolts, and the precise frequency conversion assembly (302) is rigidly connected with the high-frequency vibration table (303) through bolts;
The electric cylinder (30206) of the precise frequency conversion assembly (302) can output precise linear motion, and the cantilever length of the amplitude amplifying arm (30210) is precisely adjusted, so that precise and stepless adjustment of the test resonance frequency is realized; the electric cylinder support frame (30207) is rigidly connected with the foundation, the electric cylinder seat (30205) is rigidly connected with the electric cylinder support frame (30207), and the end part of an output shaft (30204) of the electric cylinder (30206) is connected with the left end of the amplitude amplifying arm (30210); amplitude amplification arm (30210) and the recess clearance fit of amplifier base (30209), amplifier base (30209) and the mounting mesa rigid connection of high frequency load loading module (3), locking jar support (30208) and amplifier base (30209) rigid connection, hydraulic locking jar (30203) and locking jar support (30208) rigid connection, the output shaft embedding of hydraulic locking jar (30203) is in the last mounting hole of amplifier base (30209), sample (30201) is placed at amplitude amplification arm (30210) clamping position by the gripping end, briquetting (30202) are placed on sample (30201) to through bolt locking.
2. The in-situ testing device for high-low cycle composite fatigue performance of a material according to claim 1, wherein the in-situ testing device is characterized in that: the low-frequency load loading module (2) and the in-situ monitoring module (4) are rigidly connected with an upper support frame (102) of the instrument support frame (1) through screws, the instrument support frame (1) comprises a precise guide mechanism (101), the upper support frame (102), a precise adjusting mechanism (103) and a support base (104), the precise adjusting mechanism (103) is matched with the precise guide mechanism (101) to drive the upper support frame (102) to precisely move, so that the low-frequency load loading module (2) and the in-situ monitoring module (4) are driven to precisely move to adapt to samples with different sizes.
3. A material high-low cycle composite fatigue performance in-situ test method is characterized in that: when the fatigue performance in-situ test of the high-low cycle composite material is carried out, the specific steps are as follows:
Step one, sample (30201) clamping: placing the clamped end of the sample (30201) at the clamping position of the amplitude amplifying arm (30210), covering the pressing block (30202) and locking the pressing block by a screw to clamp the sample (30201);
Step two, test frequency adjustment: adjusting the clamping force of the hydraulic locking cylinder (30203) to enable the amplitude amplifying arm (30210) to be in an adjustable state; starting an electric cylinder (30206), and precisely adjusting the cantilever length of an amplitude amplifying arm (30210) to reach the resonance frequency required by the test by adopting displacement control; adjusting the clamping force of a hydraulic locking cylinder (30203) to firmly clamp the amplitude amplifying arm (30210);
Step three, adjusting the relative position of the upper support frame (102): starting a precise adjusting mechanism (103) to adjust the relative position of the upper supporting frame (102), so as to ensure that a bending ejector rod of the low-frequency load loading module (2) is positioned at a load loading position of a sample (30201), and each in-situ imaging device in the in-situ monitoring module (4) can smoothly observe the sample;
Step four, loading a low-frequency load: synchronously starting a low-frequency load loading module (2), an in-situ monitoring module (4) and a laser vibration meter (30103), and loading a sample (30201) with a low-frequency load; the laser vibration meter (30103) feeds back the measured amplitude signal of the end part of the sample (30201) in real time, so that closed-loop control of low-frequency amplitude is realized;
Step five, loading high-frequency load: after the low-frequency load is loaded, the high-frequency load loading module (3) is started rapidly, and the high-frequency load is loaded on the sample (30201); the laser vibration meter (30103) feeds back the measured amplitude signal of the end part of the sample (30201) in real time, so that closed-loop control of high-frequency amplitude is realized;
Step six, loading high-low cycle compound load: repeating the fourth and fifth steps according to the load spectrum input in the test process, and loading the high-low cycle composite load on the sample (30201) until the whole load spectrum is completed or the sample (30201) is broken;
Step seven, parallel in-situ monitoring: synchronously starting all in-situ imaging equipment in the in-situ monitoring module (4) until the test is finished while performing the step four; the digital speckle strain gauge (401) acquires full-field strain information of a sample (30201) in real time, the high-speed camera (404) dynamically observes vibration information of the sample (30201) and captures expansion and fracture of macro-cracks on the surface of the sample (30201), and the infrared camera (405) monitors heat dissipation in the test process of the sample (30201) and rapidly positions crack initiation positions of the sample (30201).
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