CN114279844A - Method for testing I/III mixed type interlayer fracture toughness of fiber reinforced composite laminated plate - Google Patents

Method for testing I/III mixed type interlayer fracture toughness of fiber reinforced composite laminated plate Download PDF

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CN114279844A
CN114279844A CN202111632177.XA CN202111632177A CN114279844A CN 114279844 A CN114279844 A CN 114279844A CN 202111632177 A CN202111632177 A CN 202111632177A CN 114279844 A CN114279844 A CN 114279844A
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CN114279844B (en
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赵丽滨
贾若迪
张哲绎
刘丰睿
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Hebei University of Technology
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Abstract

The invention discloses a method for testing I/III mixed type interlayer fracture toughness of a fiber reinforced composite laminated plate, which comprises the following steps: preparing a crack sample of the edge ring of the fiber reinforced composite laminated plate; setting the mixing ratio of the I/III mixed type interlayer fracture toughness test
Figure DDA0003441347710000011
Finding the mixing ratio
Figure DDA0003441347710000012
A relation to the corresponding load ratio q; respectively carrying out loading-unloading tests of the sample in tension and torsion to obtain the tension stiffness KpTorsional rigidity KT(ii) a From q, Kp、KTObtaining the ratio of the pull-twist loading displacement rate
Figure DDA0003441347710000013
Guarantee
Figure DDA0003441347710000014
Developing the set blend ratio in the displacement loading mode without changing
Figure DDA0003441347710000015
Performing an I/III mixed type interlayer fracture toughness test, and recording the tensile load and the torsional load at the moment of failure; and further obtaining an I-type strain energy release rate component and a III-type strain energy release rate component corresponding to the lamination failure moment, and obtaining the I/III mixed type interlayer fracture toughness. The invention can realize the loading test and data processing of I/III mixed type layered fracture in any mixing ratio mode on a pull-twist tester, and is convenient for material performance test and engineering application.

Description

Method for testing I/III mixed type interlayer fracture toughness of fiber reinforced composite laminated plate
Technical Field
The invention relates to the technical field of mechanical property testing and characterization of fiber reinforced composite materials, in particular to a method for testing a layered fracture toughness value of a carbon fiber reinforced composite material laminated plate under any I/III mixed type layered mixing ratio.
Background
The fiber reinforced composite material laminated plate has high specific strength and specific rigidity, can be cut and designed, has good fatigue performance and other excellent mechanical properties, and is widely applied. However, a major drawback of composite laminates in terms of mechanical properties is poor interlaminar performance. As the amount of the composite material laminate used in the structure is gradually increased, the structural form and the loading form become more and more complicated, and the problem of poor interlayer performance has not been ignored. The layered form of the composite material can be divided into three basic forms of an open type (I type), a sliding type (II type) and a tearing type (III type) according to the angle between a crack surface and a load direction. However, in practical structural applications, the delamination of composite laminates tends to be a hybrid of at least two of the three basic forms, and the delamination behavior in hybrid mode and the measurement of interlayer fracture toughness have been of great interest.
In terms of the test method of the interlayer fracture toughness of the hybrid type, two or more single type test methods are generally superimposed into the test method of the hybrid type, and ASTM (american society for testing and materials) combines the type I and type II test methods to establish the test standard of the interlayer fracture toughness of the I/II hybrid type. At the present stage, research on an I/III mixed type layering test method is limited, an accurate and reliable I/III type layer non-splitting toughness test method is not developed, and documents mainly include two methods, one is a test method formed by combining an I type double cantilever beam test and a III type splitting cantilever beam, and the other is a multi-point bending plate test developed by a III type edge crack torsion test to realize I/III mixed type layering. However, both of these methods adopt a conventional linear crack, and the sample distortion is caused by compaction, so that the type II delamination components cannot be eliminated due to the existence of the crack edge effect, and the type I/III hybrid delamination at any mixing ratio cannot be realized.
With the increase of the structural thickness of the structural composite material and the appearance of more structures (such as engine fan blades and helicopter rotors) which need to bear complex loads such as torsion, bending and compression, various III-containing hybrid type delamination occurs, and because the interlaminar fracture toughness value of the I type delamination mode is lower, the I/III hybrid type delamination phenomenon in the actual structure is more and more. Therefore, a test method for establishing the I/III mixed type interlayer fracture toughness of the composite material laminated plate is needed to accurately characterize and evaluate the I/III mixed type interlayer fracture toughness, and simultaneously, the existing test method and test system for the interlayer fracture toughness of the composite material laminated plate can be further perfected.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: the method for testing the I/III mixed type interlayer fracture toughness of the fiber reinforced composite laminated plate is established for the first time based on the edge ring crack sample with a circular closed borderless crack, the load ratio is calculated according to the sample size, the material performance parameters and the mixing ratio, the load ratio is regarded as a formula related to the mixing ratio, the I/III mixed type layered fracture test in any mixing ratio mode can be realized, the universality of the method is improved, the test cost is reduced, and the engineering application is facilitated.
The technical scheme adopted by the invention for solving the technical problems is as follows: a test method for an I/III mixed type interlayer fracture toughness test of a fiber reinforced composite laminate comprises the following steps:
step 1, designing and preparing a fiber reinforced composite material laminated plate edge ring crack sample, wherein the laminating form of the laminated plate sample meets the requirements of symmetry, balance and quasi-isotropy;
step 2, setting the mixing ratio of I/III mixed type interlayer fracture toughness test to be carried out
Figure BDA0003441347690000021
According to a given mixing ratio
Figure BDA0003441347690000022
Calculating a corresponding load ratio q;
step 3, respectively carrying out tensile and torsional loading-unloading tests on the laminated plate edge ring crack sample on a tensile-torsional biaxial testing machine, recording corresponding load-displacement curves, and respectively obtaining the tensile stiffness K under the action of tensile loadpTorsional stiffness K under torsional loadingT；
Step 4, according to the load ratio q and the tensile rigidity KpTorsional rigidity KTCalculating the ratio of the pull-twist load displacement rates
Figure BDA0003441347690000023
Step 5, according to the ratio of the pull-twist loading displacement rate
Figure BDA0003441347690000024
Developing a set blend ratio in a displacement loading mode
Figure BDA0003441347690000025
The tensile load P at the moment of failure is recordedcAnd torsional load Tc；
Step 6, calculating I-type strain energy release rate component G corresponding to the layered damage moment according to a theoretical formulaIAnd type III strain energy release rate component GIII；
Step 7, making the I-type strain energy release rate component GIAnd type III strain energy Release RateGIIIAdding, calculating the total strain energy release rate at the time of layer failure, namely the set mixing ratio
Figure BDA0003441347690000026
Interlaminar fracture toughness G of lower I/III mixed delaminationTCI.e. GTC＝GI+GIII。
The edge ring crack laminate samples meet the requirements of symmetry, balance and quasi-isotropy. For the composite material prepared by the two-dimensional balance fabric prepreg, the layering sequence is as follows:
(0/45/45/0/45/0/0/45/45/0/0/45/0/45/45/0)//crack//(0/45/45/0/45/0/0/45/45/0/0/45/0/45/45/0)。
for the composite material prepared from the unidirectional tape prepreg, the laying sequence is as follows:
(0/90/45/-45/90/-45/45/0/0/-45/45/90/45/-45/90/0)//crack//(0/90/-45/45/90/45/-45/0/0/45/-45/90/-45/45/90/0)。
said step 2 calculating the corresponding load ratio q from the given mixing ratio when the given mixing ratio is given
Figure BDA0003441347690000027
Then, the corresponding concrete load ratio q calculation formula is:
Figure BDA0003441347690000028
wherein P is tensile load, T is torsional load, a is ring crack diameter, b is sample loading zone diameter, E is tensile direction material tensile modulus, G is material 1-3 direction shear modulus,
Figure BDA0003441347690000029
and
Figure BDA00034413476900000210
given by:
Figure BDA00034413476900000211
Figure BDA00034413476900000212
step 3, calculating corresponding rigidity by the load displacement curve and tensile rigidity under tensile load
Figure BDA0003441347690000031
Torsional stiffness under torsional loading
Figure BDA0003441347690000032
Where Δ P is a change in tensile load, Δ T is a change in torque load, Δ u is a change in tensile displacement, and Δ α is a change in torsion angle.
In the step 4, the load ratio q calculated in the step 2 and the tensile rigidity K determined in the step 3pTorsional rigidity KTThe pull-twist load displacement rate ratio is calculated and is given by:
Figure BDA0003441347690000033
wherein vPFor tensile displacement load rate, vTIs the rate of torsional displacement loading.
In the step 6, the I-type layered strain energy release rate component GIIs composed of
Figure BDA0003441347690000034
And (3) calculating:
wherein ,
Figure BDA0003441347690000035
Figure BDA0003441347690000036
type III layered strain energy release rate component GIIIBy
Figure BDA0003441347690000037
And (3) calculating:
wherein ,
Figure BDA0003441347690000038
Figure BDA0003441347690000039
compared with the prior art, the invention has the advantages that:
1. the invention firstly provides an I/III mixed type layered fracture toughness testing method suitable for fiber reinforced composite laminated plates, which can realize the testing of I/III mixed type interlayer fracture toughness in any mixing ratio and can also realize the layered testing of pure I type and pure III type.
2. The invention provides a method for testing I/III mixed type layered fracture toughness of a fiber reinforced composite material laminate, which can be used for testing I/III mixed type layered fracture toughness of the fiber reinforced composite material laminate under different material systems such as unidirectional tape materials, woven materials and the like, and has wide application range. The I-type and III-type loads are introduced by applying tension and torsion of the tension-torsion biaxial testing machine at the same time, so that I/III mixed type layering is realized, the parameter of a clamp is irrelevant, and the load ratio q concept relevant to the mixing ratio is introduced, so that the testing method can be suitable for the situation of any mixing ratio.
3. Compared with other existing methods, the test result of the invention has the advantages that the adopted edge ring crack sample has circular closed cracks, the sample layering form simultaneously meets the requirements of symmetry, balance and quasi-isotropy, the problem of the edge effect of the cracks in other test methods is avoided, the I/III mixed type layered test is realized, the II type layered component is not introduced, the defect that the II type layered component cannot be eliminated by other methods is overcome, the test is convenient, and the accuracy is reliable.
Drawings
FIG. 1 is a flow chart of an implementation of the present invention;
FIG. 2 is a schematic view of a test piece configuration of the present invention;
FIG. 3 is a schematic view of the loading of the present invention in operation.
The symbols in the drawings illustrate that: 1. the test piece comprises a 0-degree direction laying layer, 2-degree and 45-degree direction laying layers, 3 a polytetrafluoroethylene film, 4 a test piece annular adhesive area, 5 a testing machine upper chuck, 6 an upper rigid loading plate, 7 an edge ring crack test piece, 8 a lower rigid loading plate, 9 a testing machine lower chuck.
Detailed Description
The invention is described in further detail below with reference to the figures and specific examples.
The invention relates to a method for testing I/III mixed type interlayer fracture toughness of a fiber reinforced composite laminated plate, the implementation flow is shown in figure 1, and the method comprises the following concrete implementation steps:
example (b):
step 1: designing and preparing a crack sample of the edge ring of the fiber reinforced composite material laminated plate; the prepreg is manufactured by weaving T300 carbon fiber/epoxy resin 3k plain weave balance. The schematic configuration diagram of the test piece is shown in FIG. 2, wherein 1 in FIG. 2 represents a 0-degree direction layer, 2 represents a 45-degree direction layer, and 3 represents a polytetrafluoroethylene film, the configuration mode of the test piece is (0/45/45/0/45/0/0/45/45/0/0/45/0/45/45/0)// crack// (0/45/45/0/45/0/0/45/45/0/0/45/0/45/45/0), and the layering mode of the upper sub-layer plate and the lower sub-layer plate meets the requirement A16＝A26＝Bij＝D16＝D260, wherein Aij，Bij，DijThe components of the rigidity matrixes A, B and D of the laminated plate respectively meet the requirements of symmetry, balance and quasi-isotropy; cutting the prepreg into a 120 multiplied by 120mm square shape in the 0-degree direction and the 45-degree direction for laying; and inserting the polytetrafluoroethylene film 3 with the central gap and the thickness of less than 25 mu m into the middle plane of the prepreg plate to form a prefabricated crack. And after the solidification is finished, scanning and marking the center of the circle by ultrasonic C and checking the possible defects of the solidified plate. And cutting and polishing the edge of the test piece by using a high-speed diamond cutter.
Step 2: connecting the edge ring crack sample 7 with an upper rigid loading plate (6) and a lower rigid loading plate (8) in a gluing mode, wherein a sample gluing area 4 is shown in figure 2; after the cementing agent is solidified, the assembly of the rigid loading plate and the test piece is placed on a testing machine and is connected with upper and lower chucks (5 and 9) of the testing machine through fastening bolts, and the loading is schematically shown in figure 3. When a mixing ratio is given
Figure BDA0003441347690000041
Then, the corresponding concrete load ratio q calculation formula is:
Figure BDA0003441347690000042
wherein P is tensile load, T is torsional load, a is ring crack diameter, b is sample loading area diameter, E is tensile modulus of the material in the tensile direction, G13Is the shear modulus of the material in the 1-3 directions,
Figure BDA0003441347690000043
and
Figure BDA0003441347690000044
given by:
Figure BDA0003441347690000045
Figure BDA0003441347690000046
the expression of the mixing ratio is
Figure BDA0003441347690000051
GI and GIIIThe strain energy release rates of the I type strain energy release rate and the III type strain energy release rate are respectively, and when the strain energy release rates are set, specific values of the mixing ratio can be set at will, and the value range is 0-1. The load ratio can be expressed as a formula related to the dimensional parameters of the sample, the material performance parameters and the mixing ratio, and is broadly understood to be tensile load and torqueThe ratio of the loads is the load ratio, E and G13The material property parameters for the test pieces are known values.
And step 3: and respectively performing a tensile stiffness test and a torsional stiffness test under a small load on the same sample by adopting a loading-unloading mode, and correspondingly recording the displacement change of the sample under the tensile load and the displacement change of the sample under the torsional load to obtain a corresponding load-displacement curve. Calculating corresponding rigidity by using the linear section of the load-displacement curve, and calculating the tensile rigidity under the action of tensile load
Figure BDA0003441347690000052
The torsional rigidity under the action of torsional load is obtained by
Figure BDA0003441347690000053
Obtaining; where Δ P is a change in tensile load, Δ T is a change in torque load, Δ u is a change in tensile displacement, and Δ α is a change in torsion angle.
And 4, step 4: calculating the tension-torsion loading displacement rate ratio according to the following formula by using the load ratio q in the step 2 and the torsional rigidity and the tensile rigidity calculated on the basis of the load-displacement curve
Figure BDA0003441347690000054
Figure BDA0003441347690000055
wherein vPFor tensile loading rate, units mm/min, vTThe rate of torsional loading was, ° per min.
And 5: the pulling-twisting loading displacement rate ratio calculated in the step 4
Figure BDA0003441347690000056
Simultaneously applying torque and tension to a sample, inputting two loading displacement rate parameters of tension-torsion into a testing machine by adopting a displacement control mode to ensure that the requirement of the loading displacement rate ratio of tension-torsion is met, continuously loading the sample, and arranging a sensor of the testing machine at one positionAnd continuously recording the displacement and the load of the loading point in a fixed time interval. Until delamination failure was reached and 30% drop from the maximum load value. Recording the Torque load T at delamination failureCAnd a tensile load PCAnd are denoted as maximum torque load and maximum tensile load.
Step 6: calculating I-type strain energy release rate component G corresponding to layered damage moment according to a theoretical formulaIAnd type III strain energy release rate component GIII(ii) a Calculation of G from the following equationI、GIII and GTC：
Type I fracture toughness component GIAccording to the maximum tensile load PCAnd the dimensional parameters of the sample to obtain a type I stress intensity factor KIIs further based on
Figure BDA0003441347690000057
Obtaining GI：
Figure BDA0003441347690000058
Figure BDA0003441347690000059
Type III fracture toughness component GIIIAccording to the maximum torsion load TCAnd the dimensional parameters of the sample to obtain a III type stress intensity factor KIIIIs further based on
Figure BDA00034413476900000510
Obtaining GIII，
wherein ,
Figure BDA00034413476900000511
Figure BDA0003441347690000061
step 7, making the I-type strain energy release rate component GIAnd type III strain energy Release Rate GIIIAdding, calculating the total strain energy release rate at the time of layer failure, and calculating the total strain energy release rate according to the formula GTC＝GI+GIIICalculation is carried out, i.e. the set mixing ratio
Figure BDA0003441347690000062
Interlaminar fracture toughness G of lower I/III mixed delaminationTC。
The invention has not been described in detail and is part of the common general knowledge of a person skilled in the art.
Although illustrative embodiments of the present invention have been described above to facilitate the understanding of the present invention by those skilled in the art, it should be understood that the present invention is not limited to the scope of the embodiments, and various changes may be made apparent to those skilled in the art as long as they are within the spirit and scope of the present invention as defined and defined by the appended claims, and all matters of the invention which utilize the inventive concepts are protected.

Claims (6)

1. A method for testing I/III mixed type interlayer fracture toughness of a fiber reinforced composite laminated plate is characterized by comprising the following steps:
step 1, preparing a fiber reinforced composite material laminated plate edge ring crack sample, wherein the layering form of the laminated plate edge ring crack sample simultaneously meets the requirements of symmetry, balance and quasi-isotropy;
step 2, setting a mixing ratio phi of an I/III mixed type interlayer fracture toughness test to be developed, and deducing an expression of a load ratio q according to the mixing ratio phi;
step 3, respectively carrying out tensile and torsional loading-unloading tests on the laminated plate edge ring crack sample on a tensile-torsional biaxial testing machine, recording corresponding load-displacement curves, and respectively obtaining the tensile stiffness K under the action of tensile loadpTorsional rigidity under torsional load KT；
Step 4, according to the load ratio q and the tensile rigidity KpTorsion, torsion ofRigidity KTObtaining the ratio of the pull-twist loading displacement rate
Figure FDA0003441347680000011
wherein vPFor tensile displacement load rate, vTIs the torsional displacement load rate;
step 5, according to the ratio of the pull-twist loading displacement rate
Figure FDA0003441347680000012
Carrying out an I/III mixed type interlayer fracture toughness test under a set mixing ratio phi in a displacement loading mode, and recording a tensile load P at the moment of failurecAnd torsional load Tc；
Step 6, calculating I-type strain energy release rate component G corresponding to the layered damage moment according to a theoretical formulaIAnd type III strain energy release rate component GIII；
Step 7, making the I-type strain energy release rate component GIAnd type III strain energy release rate component GIIIAdding, calculating the total strain energy release rate at the moment of delamination failure, namely the interlayer fracture toughness G of the I/III mixed delamination under the set mixing ratio phiTCI.e. GTC＝GI+GIII。
2. The method for testing I/III hybrid interlayer fracture toughness of a fiber reinforced composite laminate according to claim 1, wherein: the crack sample of the edge ring of the laminated plate is a composite material prepared by two-dimensional balance fabric prepreg, and the layering sequence is as follows:
(0/45/45/0/45/0/0/45/45/0/0/45/0/45/45/0)//crack//(0/45/45/0/45/0/0/45/45/0/0/45/0/45/45/0)；
the laminated plate edge ring crack sample is a composite material prepared from unidirectional tape prepreg, and the layering sequence is as follows:
(0/90/45/-45/90/-45/45/0/0/-45/45/90/45/-45/90/0)//crack//(0/90/-45/45/90/45/-45/0/0/45/-45/90/-45/45/90/0)。
3. the method for testing I/III hybrid interlayer fracture toughness of a fiber reinforced composite laminate according to claim 1, wherein: the load ratio q in the step 2 is calculated by the following formula:
Figure FDA0003441347680000013
wherein a is the diameter of the ring crack, b is the diameter of the loading area of the sample, E is the tensile modulus of the material in the tensile direction, G13Is the shear modulus of the material in the 1-3 directions,
Figure FDA0003441347680000014
and
Figure FDA0003441347680000015
given by:
Figure FDA0003441347680000021
Figure FDA0003441347680000022
4. the method for testing I/III hybrid interlayer fracture toughness of a fiber reinforced composite laminate according to claim 1, wherein: in the step 3, the tensile stiffness under tensile load
Figure FDA0003441347680000023
Torsional stiffness under torsional loading
Figure FDA0003441347680000024
Where Δ P is a change in tensile load, Δ T is a change in torque load, Δ u is a change in tensile displacement, and Δ α is a change in torsion angle.
5. The method for testing I/III hybrid interlayer fracture toughness of a fiber reinforced composite laminate according to claim 1, wherein: in step 4, the ratio of the pull-twist loading displacement rate is given by:
Figure FDA0003441347680000025
wherein vPFor tensile displacement load rate, vTIs the rate of torsional displacement loading.
6. The method for testing I/III hybrid interlayer fracture toughness of a fiber reinforced composite laminate according to claim 1, wherein: in the step 6, the I-type layered strain energy release rate component GIIs composed of
Figure FDA0003441347680000026
And (3) calculating: wherein,
Figure FDA0003441347680000027
Figure FDA0003441347680000028
type III layered strain energy release rate component GIIIBy
Figure FDA0003441347680000029
And (3) calculating:
wherein ,
Figure FDA00034413476800000210
Figure FDA00034413476800000211
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