CN111965018A - Ceramic-based fiber bundle composite material transverse stretching matrix crack experimental device and method - Google Patents
Ceramic-based fiber bundle composite material transverse stretching matrix crack experimental device and method Download PDFInfo
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- CN111965018A CN111965018A CN202010692881.3A CN202010692881A CN111965018A CN 111965018 A CN111965018 A CN 111965018A CN 202010692881 A CN202010692881 A CN 202010692881A CN 111965018 A CN111965018 A CN 111965018A
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- G—PHYSICS
- G01—MEASURING; TESTING
- 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
- G01N3/08—Investigating strength properties of solid materials by application of mechanical stress by applying steady tensile or compressive forces
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
- G01B11/00—Measuring arrangements characterised by the use of optical techniques
- G01B11/02—Measuring arrangements characterised by the use of optical techniques for measuring length, width or thickness
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- G—PHYSICS
- G01—MEASURING; TESTING
- 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
- G01N3/02—Details
Abstract
The invention relates to a ceramic matrix fiber bundle composite transverse stretching matrix crack experimental device and a method, wherein the device comprises the following components: the device comprises a ceramic-based fiber bundle composite material, two reinforcing sheets, an in-situ loading platform, an optical microscope, a computer and a load indicator, wherein the two reinforcing sheets are used for clamping the ceramic-based fiber bundle composite material, the in-situ loading platform comprises a rocker, a gear box, a screw rod, a left chuck, a right chuck, a base and a force sensor, the force sensor is fixedly connected with a left mounting plate, the rocker can drive the left chuck to horizontally move through rotation, a lens of the optical microscope directly faces to the middle part of the ceramic-based fiber bundle composite material from the upper part, the optical microscope is connected with the computer, and the computer is used for measuring, recording and displaying data of cracks of a transversely stretched matrix of the ceramic-based fiber bundle. The method has the advantage of realizing the in-situ analysis of the crack propagation rule of the ceramic matrix fiber bundle composite transverse stretching matrix.
Description
Technical Field
The invention belongs to the field of composite material mechanical behavior tests, and particularly relates to a device and a method for a ceramic matrix fiber bundle composite transverse stretching matrix crack test.
Background
The woven ceramic matrix composite material has low density and still has ideal mechanical properties in a high-temperature environment, and is a preferred material for a high-performance aircraft engine hot-end component. The ceramic matrix fiber bundle composite is a basic bearing unit of the woven ceramic matrix composite and is an ideal medium for researching the damage evolution mechanism of the woven ceramic matrix composite. The load born by the ceramic matrix composite material in the service process is complex, and besides the axial tensile load, the transverse tensile load also exists. The basic unit, ceramic matrix fiber bundle composite, will also be subjected to various types of loads. The anisotropy of the mechanical property of the ceramic matrix fiber bundle composite material is remarkable, the damage evolution process and the axial difference shown under the action of transverse load are large, and the damage evolution analysis under the transverse tensile load needs to be independently carried out.
Research shows that the matrix is cracked firstly during the transverse stretching damage process of the ceramic matrix fiber bundle composite. With the increase of load, the transverse tensile matrix crack continuously expands, and meanwhile, damages such as interface debonding, interface fracture, fiber fracture and the like are initiated and developed. When the matrix is completely cracked, the bearing capacity of the ceramic matrix fiber bundle composite reaches a limit value. Therefore, the initiation and the propagation process of the matrix crack penetrate through the whole transverse stretching damage process of the ceramic matrix fiber bundle composite material, and the method has important significance for the research on the transverse stretching damage evolution of the ceramic matrix fiber bundle composite material.
The crack spacing of the ceramic matrix fiber bundle composite substrate is usually small, so that the accurate observation of the crack propagation process needs to use higher observation resolution. In addition, because of the low transverse tensile strength of the ceramic matrix fiber bundle composite, an oversized sample cannot be used for the purpose of allowing the test to be reliably performed. The two factors result in a very large number of observation regions of the sample, and if a set of feasible observation process is not available, a reasonable observation result cannot be obtained. Meanwhile, the distribution and development process of transverse matrix cracks are different from that of axial matrix cracks, so the method for representing the density of axial tensile matrix cracks is not suitable for transverse tensile matrix cracks.
Therefore, there is a need to provide a sample, a device and a method capable of performing transverse in-situ loading and observation on a ceramic matrix fiber bundle composite material, so as to realize in-situ analysis of the crack propagation law of the transverse tensile matrix of the ceramic matrix fiber bundle composite material.
Disclosure of Invention
Aiming at the defects in the prior art, the invention provides a device and a method for a transverse tensile test of a ceramic-based fiber bundle composite material, so as to realize the in-situ analysis of the crack propagation rule of the transverse tensile matrix of the ceramic-based fiber bundle composite material.
In order to achieve the technical purpose, the technical scheme adopted by the invention is as follows:
ceramic matrix fiber bundle composite transverse stretching matrix crack experimental apparatus, wherein: the device comprises a ceramic-based fiber bundle composite material, two reinforcing sheets, an in-situ loading platform, an optical microscope, a computer and a load indicator, wherein the reinforcing sheets are of stepped flat plate structures, and the lower end parts of the stepped flat plate structures are shorter than the high end parts; the ceramic-based fiber bundle composite material is of a sheet-shaped structure, and the lower surfaces of two ends of the ceramic-based fiber bundle composite material are adhered to the lower end parts of corresponding reinforcing sheets through thin epoxy resin glue; the upper surfaces of two ends of the ceramic-based fiber bundle composite material are reinforced by coating a layer of thick epoxy resin glue again, and the outer surface of the thick epoxy resin glue is coated into an inclined surface; the middle part of the ceramic-based fiber bundle composite material is exposed, the in-situ loading platform comprises a rocker, a gear box, a screw rod, a left chuck, a right chuck, a base and a force sensor, two ends of the base are bent upwards to form a left mounting plate and a right mounting plate, the gear box is fixed on the right mounting plate, the left chuck fixedly clamps one reinforcing sheet, the right chuck fixedly clamps the other reinforcing sheet, the left chuck is connected with the force sensor, the force sensor is fixedly connected with the left mounting plate, the force sensor is connected with a load indicator and can transmit the sensed tension value to the load indicator, the right chuck is connected with the gear box through the screw rod, the rocker is connected with the gear box, the rocker drives the gear box to follow up through rotation, the gear box drives the screw rod to transversely move left and right, the distance between the left chuck and the right chuck is further changed, the optical microscope is provided, the object stage can move up and down, the lens of the optical microscope is right opposite to the middle part of the ceramic-based fiber bundle composite material from the upper part, the optical microscope is connected with the computer, and the computer is used for measuring, recording and displaying the data of the ceramic-based fiber bundle composite material transverse stretching matrix crack.
In order to optimize the structural form, the specific measures adopted further comprise:
the middle position of the reinforcing piece is provided with a fixing through hole, the left chuck and the right chuck are provided with butt joint holes corresponding to the fixing through hole, and the chuck pin penetrates through the butt joint holes and the fixing through hole simultaneously to fix the reinforcing piece with the corresponding left chuck and the right chuck together.
A left mounting threaded hole is formed in the left mounting plate, and the force sensor is fixedly connected with the left mounting threaded hole and the left chuck through threaded heads.
A screw rod through hole and a plurality of mounting plate fixing holes are formed in the right mounting plate, the gear box is located on the right side of the right mounting plate, a gear box fixing bolt penetrates through the mounting plate fixing holes to fix the gear box on the right mounting plate, the screw rod penetrates through the screw rod through hole, one end of the screw rod is connected with the gear box, and the other end of the screw rod is connected with a screw rod connecting hole of the right chuck.
The ceramic matrix fiber bundle composite transverse stretching matrix crack experimental method comprises the following steps:
step 1: coating a layer of thin epoxy resin glue on the surface of the lower end part of each reinforcing sheet, and then adhering the ceramic-based fiber bundle composite material to the lower end parts of the two reinforcing sheets;
step 2: coating a layer of thick epoxy resin adhesive on the upper surface of the ceramic-based fiber bundle composite material, and then coating an inclined plane on the surface of the thick epoxy resin adhesive by using a scraper;
and step 3: starting an optical microscope and a computer;
and 4, step 4: calibrating a scale of the optical microscope by using a micrometer;
and 5: after the epoxy resin adhesive in the sample prepared in the step 2 is cured, placing the epoxy resin adhesive between a left chuck and a right chuck of the in-situ loading platform, and then fixing the reinforcing sheet with the left chuck and the right chuck respectively;
step 6: starting the load indicator, and rotating a rocker of the original position loading platform to enable the reading F =0N of the load indicator;
and 7: the knob of the optical microscope is rotated to adjust the position of the objective table, so that the part of the ceramic-based fiber bundle composite material exposed outside is used as a sample and positioned in the observation field of the optical microscope;
and 8: adjusting the magnification and the focal length of the optical microscope to obtain a proper observation visual field;
and step 9: rotating a rocker of the in-situ loading platform to load the sample, and stopping loading when the reading F = F + delta F of the load indicator;
step 10: judging whether the sample fails, if so, executing a step 18, and if not, continuing to execute the step 11;
step 11: moving the objective table through a knob of the optical microscope, positioning an observation visual field to the upper left corner of the sample, marking the scanning times n =0 of the crack column at the moment, and marking the total length L =0mm of the crack;
step 12: measuring the length delta L of the transverse tensile matrix crack in a visual field, and calculating the total length L = L + delta L of the crack under the load F;
step 13: moving the object stage downwards by a knob of an optical microscope for 1 observation visual field, measuring the length delta L of the transverse tensile matrix crack in the visual field, and calculating the total length L = L + delta L of the crack under the load F;
step 14: judging whether the observation visual field reaches the lower boundary of the sample, if not, returning to the step 13 until the observation visual field reaches the lower boundary of the sample, and if so, executing the step 15;
step 15: moving the objective table through a knob of the optical microscope to return the observation visual field to the upper left corner of the sample and marking the scanning times of the crack columns at the moment, wherein n = n + 1;
step 16: moving the object stage to the right by a knob of the optical microscope for 1 observation visual field range;
and step 17: judging whether the sample reaches the right boundary of the sample, and if the observation visual field does not reach the right boundary, returning to execute the step 12; if the observation visual field reaches the right boundary of the sample, returning to the step 9 of applying larger load to the sample;
step 18: and (4) completing an in-situ observation test of the transverse matrix crack, and inputting the in-situ loading load F and the crack length L measured under the load into a computer.
Step 19: and (3) expressing the crack density of the transverse tensile matrix by the ratio of the crack length L of the matrix to the total length M of the sample under the load F, and drawing a change diagram of the transverse tensile stress and the crack density of the matrix to obtain the crack propagation rule of the transverse tensile matrix of the ceramic matrix fiber bundle composite material.
The invention has the beneficial effects that:
1. the method realizes the in-situ test analysis of the crack density of the transverse tensile matrix of the fiber bundle grade ceramic matrix composite, and can obtain the change relation of the crack density of the transverse tensile matrix along with the transverse tensile stress.
2. The method defines the crack density of the transverse stretching matrix, gives a clear measurement standard for the crack propagation process of the transverse stretching matrix and avoids generating ambiguity.
3. The method has the advantages of strong programming, no omission and repeated statistics of observation areas and high reliability of results. Meanwhile, the programmed mode reduces the implementation difficulty of testers and ensures the stability of test results.
Drawings
FIG. 1 is a schematic view of an observation specimen for transverse tensile matrix cracking according to the present invention;
FIG. 2 is a schematic view of a reinforcing sheet of the present invention;
FIG. 3 is a schematic illustration of a platelet-shaped ceramic matrix fiber bundle composite material used in the present invention;
FIG. 4 is a schematic view of a transverse tensile matrix crack observation system of the present invention;
FIG. 5 is a schematic view of the in situ load station of the present invention;
FIG. 6 is a schematic view of a base of the present invention;
FIG. 7 is a schematic view of the chuck of the present invention;
FIG. 8 is a flow chart of the transverse matrix crack test observation of the present invention;
FIG. 9 is a graph showing the results of the test according to the present invention.
Wherein the reference numerals are: 1-ceramic-based fiber bundle composite material, 2-reinforcing sheet, 201-fixing through hole, 202-low end part, 203-high end part, 3-thin epoxy resin glue, 4-thick epoxy resin glue, 5-in-situ loading platform, 501-rocker, 502-gear box, 503-lead screw, 504-left chuck, 505-right chuck, 505 a-lead screw connecting hole, 506-base, 506 a-left mounting threaded hole, 506 b-lead screw through hole, 506 c-mounting plate fixing hole, 506 d-left mounting plate, 506 e-right mounting plate, 507-force sensor, 507 a-sensor fixing threaded head, 508-chuck pin, 509-gear box fixing bolt, 6-optical microscope, 601-objective table, 602-knob, 7-computer, 8-load indicator.
Detailed Description
Embodiments of the present invention are described in further detail below with reference to the accompanying drawings.
In this embodiment, as shown in FIG. 1, the sample for the ceramic matrix fiber bundle composite transverse tensile matrix crack appearance of the present invention comprises a ceramic matrix fiber bundle composite 1 and a reinforcement sheet 2. As shown in fig. 2, the reinforcing sheet 2 is a stepped flat plate with fixing through holes 201; the lower portion 202 of the stepped structure is shorter than the upper portion 203; the fixing through-hole 201 is located in the middle of the reinforcing sheet 2; as shown in FIG. 3, the ceramic matrix fiber bundle composite 1 is in the form of a thin sheet; the lower surface of the ceramic-based fiber bundle composite material 1 is stuck to the lower end part 202 of the reinforcing sheet 2 through a layer of thin epoxy resin glue 3; the upper surface of the ceramic-based fiber bundle composite material 1 is reinforced by coating a layer of thick epoxy resin glue 4 again, and the outer surface of the thick epoxy resin glue 4 is coated into an inclined plane to avoid influencing observation light.
As shown in FIG. 4, a test system for crack observation of a transverse tensile matrix of a ceramic matrix fiber bundle composite is provided, which comprises: a home position loading station 5 (fig. 5), an optical microscope 6, a computer 7, and a load indicator 8; the in-situ loading platform 5 comprises a rocker 501, a gear box 502, a screw 503, a left chuck 504, a right chuck 505, a base 506, a force sensor 507, a chuck pin 508 and a gear box fixing bolt 509; the base 506 is a C-shaped structure (fig. 6), one end of the base is provided with a left mounting threaded hole 506a, and the other end of the base is provided with a screw rod through hole 506b at a position opposite to the left mounting threaded hole 506 a; four mounting plate fixing holes 506c are formed around the screw rod through hole 506 b; the base 506 is connected with the gear box 502 through a gear box fixing bolt 509, and the gear box fixing bolt 509 passes through a mounting plate fixing hole 506c on the base; as shown in fig. 7, the left loading head 504 and the right loading head 505 are C-shaped structures with identical structures and through holes at the centers, and the ends of the left loading head 504 and the right loading head 505 are provided with threaded holes; a screw rod connecting hole 505a of the right loading head 505 is connected with a screw rod 503 and then passes through a screw rod through hole 506b on the base 506 to be connected with the gear box 502; the force sensor 507 is respectively connected with the threaded hole of the left clamping head 504 and the left mounting threaded hole 506a of the base 506 through a sensor fixing threaded head 507a on the force sensor 507; two chuck pins 508 respectively penetrate through the left loading head 504, the right loading head 505 and the fixing through hole 201 of the reinforcing sheet 2 for fixing and loading a sample; the rocker 501 is connected with the gear box 502, and the gear box 502 can be driven to work through the rotation of the rocker 501, so that the right loading head 505 is driven to move horizontally; the in-situ loading platform is arranged on an object stage 601 of the optical microscope 6; the optical microscope 6 is provided with a knob 602 which can control the in-plane movement of the object stage 601; the computer 7 is connected with the optical microscope 6 and is used for displaying and measuring the transverse stretching matrix cracks; the load indicator 8 is connected to a force sensor 507.
An in-situ test method for matrix crack propagation rules by adopting the test sample and the device comprises the following steps:
step 1: coating a layer of thin epoxy resin glue 3 on the surface of the lower end part 202 of the reinforcing plate 2, and then adhering the ceramic matrix fiber bundle composite material 1 to the lower end parts 202 of the two reinforcing plates 2;
step 2: coating a layer of thick epoxy resin glue 4 on the upper surface of the ceramic-based fiber bundle composite material 1, and then coating an inclined plane on the surface of the thick epoxy resin glue 4 by using a scraper;
and step 3: starting the optical microscope 6 and the computer 7;
and 4, step 4: calibrating the scale of the optical microscope 6 using a micrometer;
and 5: after the epoxy resin adhesive in the sample prepared in the step 2 is cured, placing the cured epoxy resin adhesive between a left clamp 504 and a right clamp 505 of the in-situ loading table 5, and then placing a chuck pin 508 to fix the sample and the clamp;
step 6: starting the load indicator 8, rotating the rocker 501 of the home position loading platform 5 to make the reading F =0N of the load indicator 8;
and 7: the position of the in-situ loading platform 5 on the object stage 601 is adjusted through the knob 602, so that the sample is positioned in the observation field of the optical microscope 6;
and 8: adjusting the magnification and the focal length of the optical microscope 6 to obtain a proper observation visual field;
and step 9: rotating a rocker 501 of the in-situ loading table 5 to load the sample, and stopping loading when the reading F = F + Δ F of the load indicator 8;
step 10: and judging whether the sample fails or not. If the sample fails, executing step 18, and if the sample does not fail, continuing to execute step 11;
step 11: the stage 601 is moved by the knob 602 of the optical microscope 6 to position the observation field to the upper left corner of the specimen. Marking the scanning times n =0 of the crack columns at the moment, and marking the total length L =0mm of the cracks;
step 12: measuring the length delta L of the transverse tensile matrix crack in a visual field, and calculating the total length L = L + delta L of the crack under the load F;
step 13: moving the stage 601 downward by a knob 602 of the optical microscope 6 for 1 observation field, measuring the length Δ L of the transverse tensile matrix crack in the field, and calculating the total length L = L + Δ L of the crack under the load F;
step 14: it is determined whether the observation field of view reaches the lower boundary of the sample. If the lower boundary of the specimen is not reached, the process returns to step 13 until the observation field reaches the lower boundary of the specimen. If the observation field of view has reached the lower boundary then step 15 is performed;
step 15: moving the stage 601 by the knob 602 of the optical microscope 6 returns the observation field to the upper left corner of the specimen and marks the number of crack row scans n = n +1 at that time;
step 16: the stage 601 is moved rightward by the knob 602 of the optical microscope 6 by 1 observation visual field range;
and step 17: and judging whether the sample reaches the right boundary of the sample. If the observation field of view does not reach the right boundary, the process returns to step 12. If the observation visual field reaches the right boundary of the sample, returning to the step 9 of applying larger load to the sample;
step 18: and (4) completing an in-situ observation test of the transverse matrix crack, and inputting the in-situ loading load F and the crack length L measured under the load into a computer.
Step 19: and (3) expressing the crack density of the transverse tensile matrix by the ratio of the crack length L of the matrix to the total length M of the sample under the load F, and drawing a change diagram of the transverse tensile stress and the crack density of the matrix to obtain the crack propagation rule of the transverse tensile matrix of the ceramic matrix fiber bundle composite material.
The above is only a preferred embodiment of the present invention, and the protection scope of the present invention is not limited to the above-mentioned embodiments, and all technical solutions belonging to the idea of the present invention belong to the protection scope of the present invention. It should be noted that modifications and adaptations to those skilled in the art may occur to one skilled in the art without departing from the scope and spirit of the present invention.
Claims (5)
1. Ceramic matrix fiber bundle composite transverse stretching matrix crack experimental apparatus, characterized by: the device comprises a ceramic-based fiber bundle composite material (1), two reinforcing sheets (2), an in-situ loading platform (5), an optical microscope (6), a computer (7) and a load indicator (8), wherein the reinforcing sheets (2) are of a stepped flat plate structure, and the lower end part (202) of the stepped flat plate structure is shorter than the higher end part (203); the ceramic-based fiber bundle composite material (1) is of a sheet-shaped structure, and the lower surfaces of two ends of the ceramic-based fiber bundle composite material (1) are adhered to the lower end parts (202) of the corresponding reinforcing sheets (2) through thin epoxy resin glue (3); the upper surfaces of two ends of the ceramic-based fiber bundle composite material (1) are reinforced by coating a layer of thick epoxy resin glue (4) again, and the outer surface of the thick epoxy resin glue (4) is coated into an inclined plane; the middle part of the ceramic-based fiber bundle composite material (1) is exposed, the in-situ loading platform (5) comprises a rocker (501), a gear box (502), a screw rod (503), a left chuck (504), a right chuck (505), a base (506) and a force sensor (507), two ends of the base (506) are bent upwards to form a left mounting plate (506d) and a right mounting plate (506e), the gear box (502) is fixed on the right mounting plate (506e), the left chuck (504) is fixedly clamped with one reinforcing sheet (2), the right chuck (505) is fixedly clamped with another reinforcing sheet (2), the left chuck (504) is connected with the force sensor (507), the force sensor (507) is fixedly connected with the left mounting plate (506d), the force sensor (507) is connected with a load indicator (8), and can transmit the sensed tension value to the load indicator (8), the right chuck (505) is connected with the gear box (502) through a screw rod (503), the rocker (501) is connected with the gear box (502), the rocker (501) can drive the gear box (502) to follow up through rotation, the gear box (502) drives the screw rod (503) to move transversely, further changing the distance between the left chuck (504) and the right chuck (505), the optical microscope (6) is provided with an object stage (601), a base (506) can be placed on the object stage (601), the object stage (601) can move up and down back and forth and left and right, the lens of the optical microscope (6) is directly opposite to the middle part of the ceramic-based fiber bundle composite material (1) from the upper part, the optical microscope (6) is connected with the computer (7), and the computer (7) is used for measuring, recording and displaying the data of the transverse tensile matrix crack of the ceramic matrix fiber bundle composite material (1).
2. The ceramic matrix fiber bundle composite transverse tensile matrix crack test device of claim 1, wherein: the middle position of reinforcing piece (2) be provided with fixed through hole (201), left chuck (504) and right chuck (505) on be provided with the butt joint hole that corresponds with fixed through hole (201), chuck pin (508) pass butt joint hole and fixed through hole (201) simultaneously, will strengthen piece (2) and corresponding left chuck (504) and right chuck (505) fixed together.
3. The ceramic matrix fiber bundle composite transverse tensile matrix crack test device of claim 2, wherein: and a left mounting threaded hole (506a) is formed in the left mounting plate (506d), and the force sensor (507) is fixedly connected with the left mounting threaded hole (506a) and the left chuck (504) through a threaded head (507 a).
4. The ceramic matrix fiber bundle composite transverse tensile matrix crack test device of claim 3, wherein: the right mounting plate (506e) is provided with a screw rod through hole (506b) and a plurality of mounting plate fixing holes (506c), the gear box (502) is located on the right side of the right mounting plate (506e), a gear box fixing bolt (509) penetrates through the mounting plate fixing holes (506c) to fix the gear box (502) on the right mounting plate (506e), a screw rod (503) penetrates through the screw rod through hole (506b), one end of the screw rod is connected with the gear box (502), and the other end of the screw rod is connected with a screw rod connecting hole (505a) of the right chuck (505).
5. The experimental method of the ceramic matrix fiber bundle composite transverse tension matrix crack experimental device according to claim 4, characterized in that: the method comprises the following steps:
step 1: coating a layer of thin epoxy resin glue (3) on the surface of the lower end part of each reinforcing sheet (2), and then adhering the ceramic-based fiber bundle composite material (1) to the lower end parts (202) of the two reinforcing sheets (2);
step 2: coating a layer of thick epoxy resin adhesive (4) on the upper surface of the ceramic-based fiber bundle composite material (1), and then coating an inclined plane on the surface of the thick epoxy resin adhesive (4) by using a scraper;
and step 3: starting the optical microscope (6) and the computer (7);
and 4, step 4: -calibrating the scale of the optical microscope (6) using a micrometer;
and 5: after the epoxy resin glue in the sample prepared in the step 2 is cured, placing the sample between a left chuck (504) and a right chuck (505) of an in-situ loading platform (5), and then fixing the reinforcing sheet (2) with the left chuck (504) and the right chuck (505) respectively;
step 6: starting the load indicator (8), and rotating a rocker (501) of the home position loading platform (5) to enable the load indicator (8) to indicate F = 0N;
and 7: the position of an objective table (601) is adjusted by rotating a knob (602) of an optical microscope (6), so that the part of the ceramic-based fiber bundle composite material (1) exposed outside is positioned in the observation field of the optical microscope as a sample;
and 8: adjusting the magnification and the focal length of the optical microscope (6) to obtain a proper observation visual field;
and step 9: rotating a rocker (501) of the in-situ loading platform (5) to load the sample, and stopping loading when the reading F = F + delta F of the load indicator;
step 10: judging whether the sample fails, if so, executing a step 18, and if not, continuing to execute the step 11;
step 11: moving the objective table (601) through a knob (602) of the optical microscope (6), positioning an observation visual field to the upper left corner of the sample, marking the scanning times n =0 of the crack column at the moment, and marking the total length L =0mm of the crack;
step 12: measuring the length delta L of the transverse tensile matrix crack in a visual field, and calculating the total length L = L + delta L of the crack under the load F;
step 13: moving the object stage (601) downwards by a knob (602) of the optical microscope (6) for 1 observation visual field, then measuring the length delta L of the transverse tensile matrix crack in the visual field, and calculating the total length L = L + delta L of the crack under the load F;
step 14: judging whether the observation visual field reaches the lower boundary of the sample, if not, returning to the step 13 until the observation visual field reaches the lower boundary of the sample, and if so, executing the step 15;
step 15: moving the stage (601) by a knob (602) of the optical microscope (6) to return the observation field to the upper left corner of the sample and mark the number of crack column scans n = n +1 at that time;
step 16: moving the object stage (601) by a knob (602) of the optical microscope (6) to move 1 observation visual field range to the right;
and step 17: judging whether the sample reaches the right boundary of the sample, and if the observation visual field does not reach the right boundary, returning to execute the step 12; if the observation visual field reaches the right boundary of the sample, returning to the step 9 of applying larger load to the sample;
step 18: completing an in-situ observation test of the transverse matrix crack, and inputting an in-situ loading load F and the crack length L measured under the load into a computer;
step 19: and (3) expressing the crack density of the transverse tensile matrix by the ratio of the crack length L of the matrix to the total length M of the sample under the load F, and drawing a change diagram of the transverse tensile stress and the crack density of the matrix to obtain the crack propagation rule of the transverse tensile matrix of the ceramic matrix fiber bundle composite material.
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| CN112198048A (en) * | 2020-12-07 | 2021-01-08 | 南京仪汇仪器设备有限公司 | Textile fiber strength detection equipment |
| CN113125255A (en) * | 2021-03-22 | 2021-07-16 | 株洲时代新材料科技股份有限公司 | Device and method for testing tensile fatigue of embedded part of blade root of wind power blade |
| WO2022109830A1 (en) * | 2020-11-25 | 2022-06-02 | 苏州昇特智能科技有限公司 | Clamp device for measuring interfacial properties of composite material |
| CN113624600B (en) * | 2021-07-21 | 2024-04-26 | 西安工程大学 | Three-dimensional solid device of functional microfilament |
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