CN111595707A - Material high-low cycle composite fatigue performance in-situ test device and method - Google Patents
Material high-low cycle composite fatigue performance in-situ test device and method Download PDFInfo
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Abstract
The invention relates to a device and a method for testing the high-low cycle composite fatigue performance of a material in situ, belonging to the field of precise scientific instruments. An instrument supporting frame in the device is used for realizing stable supporting and precise positioning of other functional modules; the low-frequency load loading module is driven by servo hydraulic pressure and is used for loading a low-frequency fatigue load of the sample at 0.001-50 Hz; the high-frequency load loading module is driven by electromagnetic resonance and is used for loading a high-frequency fatigue load of a sample at 5-5000 Hz, and the high-frequency load loading module and the high-frequency fatigue load can be used independently or matched with each other to jointly construct a high-low cycle composite fatigue load; the in-situ monitoring module is used for realizing high-resolution visual dynamic monitoring on the fatigue crack initiation, propagation and fracture processes 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 aero-engine under the working condition close to the actual service.
Description
Technical Field
The invention relates to the field of precise scientific instruments, in particular to a device and a method for testing the high-low cycle composite fatigue performance of a material in situ. The method can construct low-frequency fatigue load, high-frequency fatigue load and high-low cycle composite fatigue load, realizes high-resolution visual parallel in-situ monitoring on the fatigue crack initiation, expansion and fracture process of the tested sample by combining in-situ imaging equipment, and provides a feasible method for fatigue characteristic test, service safety evaluation and fatigue life prediction of the turbine blade of the aero-engine under the working condition close to actual service.
Background
The aircraft engine is the most central part of the aircraft, and the turbine blade is the most important component of the aircraft engine, and the structure is complex, the service condition is bad, so the service safety evaluation and reliability prediction become the key problems in the aircraft manufacturing industry. Statistics shows that fatigue failure accounts for more than half of the total failure of the turbine blade in the turbine blade failure, and the development of national safety and national economy is seriously threatened.
The fatigue performance research of the turbine blade of the aircraft engine is always a focus of concern of domestic and foreign scholars, a large number of domestic and foreign scholars carry out deeper research on the failure mechanism of the turbine blade material of the aircraft under the interaction of low-cycle fatigue, high-cycle fatigue and creep-fatigue, and a plurality of colleges and universities and enterprises also research and develop corresponding test equipment. A great number of reports indicate that the fatigue failure of the turbine blade is mostly high-low cycle composite fatigue failure caused by the superposition of high-low cycle load on the basis of low-cycle load peak. Therefore, development of high-low cycle compound fatigue research on turbine blade materials has great significance for correctly understanding fatigue failure mechanisms and carrying out service safety evaluation. However, limited by the existing instruments and testing methods, the research on the high-low cycle composite fatigue of turbine blade materials is still in the beginning stage.
The conventional high and low cycle composite fatigue test is generally carried out on a conventional fatigue testing machine, the maximum frequency of the conventional fatigue testing machine is generally dozens to hundreds of hertz, and the high-frequency vibration load of kilohertz on a turbine blade of an aircraft engine cannot be simulated; because the conventional fatigue testing machine can not realize in-situ observation, the macro-micro morphology change of the surface of the sample and the fatigue crack initiation part and the expansion condition in the fatigue testing process are difficult to be visually monitored. Therefore, the development of an in-situ testing device for the high-low cycle composite fatigue performance of the material is very important.
Disclosure of Invention
The invention aims to provide a device and a method for testing the high-low cycle composite fatigue performance of a material in situ, which solve the problems in the prior art. The device comprises an instrument supporting frame, a low-frequency load loading module, a high-frequency load loading module and an in-situ monitoring module, can construct low-frequency fatigue loads, high-frequency fatigue loads and high-low cycle composite fatigue loads, realizes high-resolution visual parallel in-situ monitoring on the fatigue crack initiation, expansion and fracture process of a tested sample by combining in-situ imaging equipment, and provides a feasible method for fatigue characteristic testing, service safety evaluation and fatigue life prediction of the turbine blade of the aero-engine under the working condition close to the actual service.
The above object of the present invention is achieved by the following technical solutions:
the material high-low cycle composite fatigue performance in-situ testing device comprises an instrument supporting 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 supporting frame 1 is connected with a foundation through foundation bolts on a supporting base 104, a servo oil cylinder 206 of the low-frequency load loading module 2 is rigidly connected with an upper supporting frame 102, and the low-frequency fatigue load of a test sample at 0.001-50 Hz is loaded; the high-frequency vibration table 303 of the high-frequency load loading module 3 is rigidly connected with the foundation to realize the loading of the high-frequency fatigue load of the sample at 5-5000 Hz; the L-shaped connecting plate 402 of the in-situ monitoring module 4 is rigidly connected with the upper support frame 102, so that high-resolution visual parallel in-situ monitoring of the fatigue crack initiation, expansion and fracture processes of the sample is realized.
The low-frequency load loading module 2 is vertically arranged and is rigidly connected with a foundation through a screw; the high-frequency load loading module 3 is vertically arranged and is rigidly connected with the instrument supporting frame 1 through a screw; the low-frequency load loading module 2 and the high-frequency load loading module 3 are independently used, and 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 sample; the low-frequency load loading module 2 and the high-frequency load loading module 3 are matched with each other for use, and high-low cycle composite fatigue loads are constructed together.
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 measurement assembly 301, a precision frequency conversion assembly 302 and a high-frequency vibration table 303, wherein the high-precision displacement measurement assembly 301, the precision frequency conversion assembly 302 and the high-frequency vibration table 303 are all rigidly connected with a foundation through bolts, and the precision frequency conversion assembly 302 is rigidly connected with the high-frequency vibration table 303 through bolts.
The electric cylinder 30206 of the precision frequency conversion assembly 302 can output precise linear motion, and the cantilever length of the amplitude amplification arm 30210 is precisely adjusted, so that precise and stepless adjustment of the test resonance frequency is realized; the electric cylinder support 30207 is rigidly connected with the foundation, the electric cylinder base 30205 is rigidly connected with the electric cylinder support 30207, and the end of the 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 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, an output shaft of the hydraulic locking cylinder 30203 is embedded in an upper mounting hole of the amplifier base 30209, the clamped end of the test piece 30201 is placed at the clamping position of the amplitude amplifying arm 30210, and the pressure block 30202 is placed on the test piece 30201 and locked by bolts.
The invention also aims to provide a material high-low cycle composite fatigue performance in-situ test method, which comprises the following specific steps when performing a high-low cycle composite fatigue performance in-situ test:
step one, clamping a sample 30201: placing the clamped end of the sample 30201 on 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, adjusting the test frequency: the clamping force of the hydraulic locking cylinder 30203 is adjusted, so that the amplitude amplifying arm 30210 is in an adjustable state; starting the electric cylinder 30206, precisely adjusting the cantilever length of the amplitude amplifying arm 30210 to the resonance frequency required by the test by displacement control; the clamping force of the hydraulic locking cylinder 30203 is adjusted to firmly clamp the amplitude amplifying arm 30210;
step three, adjusting the relative position of the upper support frame 102: starting the precision adjusting mechanism 103, and adjusting the relative position of the upper support frame 102, so as to ensure that the bending mandril of the low-frequency load loading module 2 is 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, low-frequency load loading: synchronously starting the low-frequency load loading module 2, the in-situ monitoring module 4 and the laser vibration meter 30103 to load the low-frequency load 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 to realize closed-loop control of low-frequency amplitude;
step five, high-frequency load loading: after the low-frequency load loading is finished, the high-frequency load loading module 3 is quickly started to load the high-frequency load 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 to realize closed-loop control of high-frequency amplitude;
step six, loading high and low cycle composite loads: according to the load spectrum input in the test process, the fourth step and the fifth step are repeated, and high-low cycle composite load loading is carried out on the sample 30201 until the whole load spectrum is completed or the sample 30201 is fractured;
step seven, parallel in-situ monitoring: synchronously starting all in-situ imaging equipment in the in-situ monitoring module 4 while the step four is carried out until the test is finished; 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 the expansion and fracture of a macrocrack on the surface of the sample 30201, and the infrared camera 405 monitors heat dissipation in the test process of the sample 30201 and quickly locates the crack initiation position of the sample 30201.
The invention has the beneficial effects that:
1. adopts a modular 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 load a low-frequency fatigue load of 0.001-50 Hz and a high-frequency fatigue load of 5-5000 Hz of a tested sample, and can be used in a matched manner to load a fatigue load of 0.001-5000 Hz of the tested sample.
3. Monitoring may be performed in situ. The in-situ monitoring module is configured, comprises a digital speckle strain measuring instrument, a high-speed camera and an infrared camera, and can realize high-resolution visual parallel in-situ monitoring on fatigue crack initiation, expansion and fracture processes of a tested sample.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this application, illustrate embodiment(s) of the invention and together with the description serve to explain the invention without limiting the invention.
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 structural diagram of a low frequency load loading module according to the present invention;
FIG. 4 is a schematic structural diagram of a high-frequency load loading module according to the present invention;
FIG. 5 is a schematic view of the high precision displacement measuring assembly of the present invention;
FIG. 6 is a schematic structural 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;
figure 8 is a cross-sectional view of a precision variable frequency 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 precision adjustment 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 connecting member; 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 fixed seat; 30102. a fixed mount; 30103. a laser vibrometer; 30104. a column; 30201. a sample; 30202. briquetting; 30203. a hydraulic locking cylinder; 30204. an output shaft; 30205. a cylinder base; 30206. an electric cylinder; 30207. an electric cylinder support frame; 30208. locking a cylinder support; 30209. an amplifier base; 30210. an amplitude amplifying arm; 401. a digital speckle strain gauge; 402. an L-shaped connecting plate; 403. a second fixed seat; 404. a high-speed camera; 405. an infrared camera.
Detailed Description
The details of the present invention and its embodiments are further described below with reference to the accompanying drawings.
Referring to fig. 1 to 8, the device and the method for testing the high-low cycle composite fatigue performance of the material in situ comprise an instrument supporting frame, a low-frequency load loading module, a high-frequency load loading module and an in-situ monitoring module. The instrument supporting frame is used for realizing stable supporting and precise positioning of other functional modules; the low-frequency load loading module is driven by servo hydraulic pressure and is used for loading a low-frequency fatigue load of a tested sample at 0.001-50 Hz; the high-frequency load loading module is driven by electromagnetic resonance and is used for loading a high-frequency fatigue load of a tested sample at 5-5000 Hz, and the high-frequency load loading module and the high-frequency fatigue load can be used independently or matched with each other to jointly construct a high-low cycle composite fatigue load; the in-situ monitoring module is mainly used for realizing high-resolution visual dynamic monitoring on 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 aero-engine under the working condition close to the actual service.
The material high-low cycle composite fatigue performance in-situ testing device comprises an instrument supporting 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 supporting frame 1 comprises a precise guide mechanism 101, an upper supporting frame 102, a precise adjusting mechanism 103 and a supporting base 104, and the precise guiding mechanism is connected with a foundation through foundation bolts on the supporting base 104 and used for realizing stable supporting 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, an intermediate connecting piece 207 and a bent ejector rod 208, wherein a flange of the servo oil cylinder 206 is rigidly connected with the upper support frame 102 through a screw, and is used for loading the low-frequency fatigue load of the sample at 0.001-50 Hz. The high-frequency load loading module 3 comprises a high-precision displacement measurement assembly 301, a precision 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 a high-frequency fatigue load of a sample of 5-5000 Hz. The in-situ monitoring module 4 comprises a digital speckle strain gauge 401, an "L" -shaped connecting plate 402, a fixing 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 fatigue crack initiation, propagation and fracture processes 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 end of the supporting base 104 is rigidly connected with the foundation through bolts, the lower ends of the precision guide mechanism 101 and the precision adjusting mechanism 103 are rigidly connected with the upper end of the supporting base 104 through bolts, and the lower end of the upper supporting frame 102 is rigidly connected with the upper ends of the precision guide mechanism 101 and the precision adjusting mechanism 103 through bolts; eight countersunk holes are processed at the lower end of the upper support frame 102, eight threaded holes are processed on the support base 104, and when the upper support frame 102 moves to a preset position, the lower part 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 supporting frame 1 through a screw; the low-frequency load loading module 2 and the high-frequency load loading module 3 are independently used, and 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 sample; the low-frequency load loading module 2 and the high-frequency load loading module 3 are matched with each other for use, and high-low cycle composite fatigue loads are constructed together.
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 mandril 208, wherein: the protective sleeve 204 is rigidly connected with a flange at the rear end of the servo oil cylinder 206 through a bolt, an external thread on the energy accumulator 205 is rigidly connected with an internal thread on the valve block assembly 203, the valve block assembly 203 is rigidly connected with the servo oil cylinder 206 through a bolt, 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 an external thread at the upper end of the bent push 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 includes 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 the 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 measuring assembly 301 of the present invention includes a fixing base 30101, a fixing frame 30102, a laser vibration meter 30103, and a column 30104, wherein: the first fixing seat 30101 is rigidly connected with a foundation through bolts, the lower end of the upright post 30104 is in interference fit with the upper end of the fixing seat 30101, the fixing frame 30102 is installed on the upright post 30104, and the laser vibration meter 30103 is rigidly connected with the fixing frame 30102 through bolts.
Referring to fig. 6 and 8, the precision frequency conversion assembly 302 of the present invention comprises a test piece 30201, a pressure block 30202, a hydraulic locking cylinder 30203, an output shaft 30204, an electric cylinder block 30205, an electric cylinder 30206, an electric cylinder support 30207, a locking cylinder support 30208, an amplifier base 30209, and an amplitude amplifying arm 30210, wherein: the electric cylinder 30206 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 lower end of the electric cylinder support 30207 is rigidly connected with a foundation through a bolt, the electric cylinder base 30205 is rigidly connected with the electric cylinder support 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 an 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 of the high-frequency load loading module 3 through a bolt, the locking cylinder support 30208 is rigidly connected with the amplifier base 30209 through a bolt, the hydraulic locking cylinder 30203 is rigidly connected with the locking cylinder support 30208 through a bolt, an output shaft of the hydraulic locking cylinder 30203 is embedded in an upper mounting hole of the amplifier base 30209, the clamped end of the test piece 30201 is placed at the clamping position of the amplitude amplifying arm 30210, and the pressure block 30202 is placed on the test piece 30201 and is locked through a bolt.
Referring to fig. 7, the in-situ monitoring module 4 of the present invention includes 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, and the L-shaped connecting plate 402 and the second fixing seat 403 are rigidly connected with the upper support frame 102 through screws.
Referring to fig. 1 to 8, the method for testing the fatigue performance of the high-low cycle composite material in situ provided by the invention comprises the following specific steps when performing the fatigue performance test of the high-low cycle composite material in situ:
step one, clamping a sample 30201: 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 complete clamping of 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, adjusting the test frequency: the clamping force of the hydraulic locking cylinder 30203 is adjusted, so that the amplitude amplifying arm 30210 is in an adjustable state; starting the electric cylinder 30206, precisely adjusting the cantilever length of the amplitude amplifying arm 30210 to the resonance frequency required by the test by displacement control; the clamping force of the hydraulic locking cylinder 30203 is adjusted to firmly clamp the amplitude amplifying arm 30210;
step three, adjusting the relative position of the upper support frame 102: starting the precision adjusting mechanism 103, and adjusting the relative position of the upper support frame 102, so as to ensure that the bending mandril of the low-frequency load loading module 2 is 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, low-frequency load loading: synchronously starting the low-frequency load loading module 2, the in-situ monitoring module 4 and the laser vibration meter 30103 to load the low-frequency load 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 to realize closed-loop control of low-frequency amplitude;
step five, high-frequency load loading: after the low-frequency load loading is finished, the high-frequency load loading module 3 is quickly started to load the high-frequency load 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 to realize closed-loop control of high-frequency amplitude;
step six, loading high and low cycle composite loads: according to the load spectrum input in the test process, the fourth step and the fifth step are repeated, and high-low cycle composite load loading is carried out on the sample 30201 until the whole load spectrum is completed or the sample 30201 is fractured;
step seven, parallel in-situ monitoring: synchronously starting all in-situ imaging equipment in the in-situ monitoring module 4 while the step four is carried out until the test is finished; 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 the expansion and fracture of a macrocrack on the surface of the sample 30201, and the infrared camera 405 monitors heat dissipation in the test process of the sample 30201 and quickly locates the crack initiation position 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, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, improvement and the like of the present invention shall be included in the protection scope of the present invention.
Claims (6)
1. The utility model provides a compound fatigue performance normal position testing arrangement of material height week which characterized in that: the device comprises an instrument supporting 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 supporting frame (1) is connected with a foundation through foundation bolts on a supporting base (104), a servo oil cylinder (206) of the low-frequency load loading module (2) is rigidly connected with an upper supporting frame (102), and the low-frequency fatigue load loading of a test sample at 0.001-50 Hz is realized; a high-frequency vibration table (303) of the high-frequency load loading module (3) is rigidly connected with a foundation, so that the high-frequency fatigue load of the sample of 5-5000 Hz is loaded; the L-shaped connecting plate (402) of the in-situ monitoring module (4) is rigidly connected with the upper support frame (102), so that high-resolution visual parallel in-situ monitoring on the fatigue crack initiation, expansion and fracture processes of the sample is realized.
2. The material high-low cycle composite fatigue performance in-situ test device according to claim 1, characterized in that: the low-frequency load loading module (2) is vertically arranged and is rigidly connected with the foundation through a screw; the high-frequency load loading module (3) is vertically arranged and is rigidly connected with the instrument supporting frame (1) through a screw; the low-frequency load loading module (2) and the high-frequency load loading module (3) are used independently, and are used for respectively loading a low-frequency fatigue load of 0.001-50 Hz and a high-frequency fatigue load of 5-5000 Hz on the sample; the low-frequency load loading module (2) and the high-frequency load loading module (3) are matched with each other for use, and high-low cycle composite fatigue loads are constructed together.
3. The material high-low cycle composite fatigue performance in-situ test device according to claim 1, characterized in that: low frequency load loading module (2) and normal position monitoring module (4) all through upper support frame (102) rigid connection of screw with instrument braced frame (1), instrument braced frame (1) contains accurate guiding mechanism (101), upper support frame (102), accurate adjustment mechanism (103), supporting pedestal (104), accurate adjustment mechanism (103) and accurate guiding mechanism (101) mutually support, drive upper support frame (102) accurate removal to drive low frequency load loading module (2) and normal position monitoring module (4) accurate removal, with the sample of adaptation not unidimensional.
4. The material high-low cycle composite fatigue performance in-situ test device according to claim 1, characterized in that: the high-frequency load loading module (3) comprises a high-precision displacement measurement assembly (301), a precision frequency conversion assembly (302) and a high-frequency vibration table (303), the high-precision displacement measurement assembly, the precision frequency conversion assembly (302) and the high-frequency vibration table (303) are all in rigid connection through bolts and a foundation, and the precision frequency conversion assembly (302) is in rigid connection with the high-frequency vibration table (303) through bolts.
5. The material high-low cycle composite fatigue performance in-situ test device according to claim 4, characterized in that: the electric cylinder (30206) of the precision frequency conversion assembly (302) can output precise linear motion, and the cantilever length of the amplitude amplification arm (30210) is precisely adjusted, so that the 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 base (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 amplification arm (30210); the amplitude amplification arm (30210) is in clearance fit with a groove of an amplifier base (30209), the amplifier base (30209) is rigidly connected with a mounting table top of a high-frequency load loading module (3), a locking cylinder support (30208) is rigidly connected with an amplifier base (30209), a hydraulic locking cylinder (30203) is rigidly connected with the locking cylinder support (30208), 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 amplification arm (30210) by a clamping end, and a pressing block (30202) is placed on the sample (30201) and is locked by a bolt.
6. An in-situ test method for the high-low cycle composite fatigue performance of a material is characterized by comprising the following steps: when the fatigue performance in-situ test of the high-low cycle composite material is carried out, the method comprises the following specific steps:
step one, clamping a sample (30201): placing the clamped end of the sample (30201) at the clamping position of the amplitude amplification arm (30210), covering a pressing block (30202) and locking by a screw to finish clamping the sample (30201);
step two, adjusting the test frequency: the clamping force of a hydraulic locking cylinder (30203) is adjusted, so that the amplitude amplification arm (30210) is in an adjustable state; starting an electric cylinder (30206), and precisely adjusting the cantilever length of an amplitude amplification arm (30210) to reach the resonance frequency required by the test by adopting displacement control; the clamping force of a hydraulic locking cylinder (30203) is adjusted, and the amplitude amplification arm (30210) is firmly clamped;
thirdly, adjusting the relative position of the upper support frame (102): starting a precision adjusting mechanism (103), adjusting the relative position of an upper support frame (102), so as to ensure that a bending mandril of a low-frequency load loading module (2) is positioned at a load loading position of a sample (30201), and each in-situ imaging device in an in-situ monitoring module (4) can smoothly observe the sample;
step four, low-frequency load loading: synchronously starting the low-frequency load loading module (2), the in-situ monitoring module (4) and the laser vibration meter (30103) to load the low-frequency load 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 to realize closed-loop control of low-frequency amplitude;
step five, high-frequency load loading: after the low-frequency load is loaded, the high-frequency load loading module (3) is started quickly, 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 to realize closed-loop control of high-frequency amplitude;
step six, loading high and low cycle composite loads: according to the load spectrum input in the test process, repeating the fourth and fifth steps, 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) while the step four is carried out until the test is finished; the digital speckle strain gauge (401) collects the full-field strain information of the sample (30201) in real time, the high-speed camera (404) dynamically observes the vibration information of the sample (30201) and captures the expansion and fracture of the macrocracks on the surface of the sample (30201), and the infrared camera (405) monitors the heat dissipation of the sample (30201) in the test process and rapidly positions the crack initiation position of the sample (30201).
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