CN109902444A - A method of prediction wing crack propagation path - Google Patents
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Abstract
The invention discloses a kind of methods for predicting wing crack propagation path, belong to rock mass mechanics analysis field, and the present invention passes through theoretical calculation first, and combines the correction of test result, obtains tip crackle crack initiation angle of the crack open of different crack dips under compression shear state；Next it based on the relationship at crack dip and crackle crack initiation angle, determines wing crack propagation path of the initial crack in micro- section, then connects the endpoint of two wing crackles, constitute a new crack, as equivalent crack；With equivalent crack for initial crack, continue to determine next micro- section of extension, and so on, obtain the Extended workflow-net of wing crackle.Prediction result and test result of the invention is coincide preferably, and compared with traditional Mechanics Calculation determines the Extended workflow-net of crackle, method provided by the invention can easily obtain wing crack propagation path, and method is simple, it can be readily appreciated that convenient for operation.
Description
Technical field
The invention belongs to rock mass mechanics analysis fields, are related to a kind of method for predicting wing crack propagation path, and in particular to
The prediction technique of the wing centre section of sample containing crack open crack propagation path under the conditions of compression shear.
Background technique
Rock in nature forms desultory discontinuity surface in geological activity, and the presence of discontinuity surface causes
Mechanical property has stronger anisotropic character, reduces the stability of rock mass, brings many to rock mass engineering project construction
Uncertainty, therefore to the thing that the research containing crack rock is just primarily solved at engineering construction is carried out.
Wherein, basis of the rupture failure process of the sample containing Single Fracture as fracture mechanics research, importance are even more not
It says and explains.Sample containing Single Fracture in compression process, wing crackle be it is observed that first running crack, when there is no confining pressure
When, wing crackle extends rapidly perforation sample, and when there is confining pressure, wing crackle is then stable to be extended to certain length and stop.It compares
In the position that secondary crackle (Mixed Mode Crack etc. is cut in anti-wing crackle, shear fissure and drawing), wing crackle occur and the track of extension
It is all relatively very fixed.And it has been investigated that the length of wing crackle and the peak strength of the sample containing crack have very strong correlation,
Secondary crackle is frequently experienced in the peak late intensity decline stage.Therefore, particularly important is become to the research of wing crackle.
Currently, have scholar by the complicated calculations of fracture mechanics obtained wing crackle crack initiation condition and crack initiation angle [1,
2], there are also scholar by by wing crackle be reduced to straight line calculate, using complex function iteration obtain wing crackle Extended workflow-net [3,
4].Since wing crackle is actually curve extension, be reduced to line processing per se with certain approximation, cause error compared with
Greatly, and its Mechanical Calculation and Analysis process is complicated, in application analysis and inconvenient.
Summary of the invention
In view of the deficiencies of the prior art, that the purpose of the present invention is to provide a kind of calculating process is simple, error is lesser pre-
The method for surveying wing crack propagation path, this method can be good at simulating the Extended workflow-net of wing crackle, have accuracy height, application
Convenient advantage.
In order to achieve the above object, the present invention the following technical schemes are provided:
The method of this prediction wing crack propagation path provided by the invention, comprising the following steps:
S1. the prefabricated sample containing crack open, crack dip α；
S2. under compression shear state, stress analysis is carried out to crack open tip, obtains the stress field at crack tip, in turn
Obtain the crackle crack initiation angle θ at crack open tip；
S3. by theoretical calculation, when obtaining considering crack tip curvature, the pass between crack dip α and crackle crack initiation angle θ
System is modified the crackle crack initiation angle θ in low-angle, obtains revised crack in conjunction with test and analog result
Relationship between inclination angle and crackle crack initiation angle；
S4. when selection crack tip curvature is larger, the relationship between revised crack dip and crackle crack initiation angle is base
Plinth determines wing crack propagation path of the initial crack in micro- section；
S5. according to the crack propagation path in step S4, wing crackle endpoint is connected using straight line, line is intended regarding as new
Prefabricated crack, referred to as equivalent crack；
S6. judge whether the crack dip in equivalent crack reaches 90 °, if it is not, then equivalent crack is regarded as initial crack,
It repeats step S2~S5 and obtains the Extended workflow-net of wing crackle if it is, iteration terminates.
In a specific embodiment, in step S1, crack dip α is fissure-plane and horizontal plane angle.
In a specific embodiment, in step S1, crack open has certain opening width, splits at crack tip
Fissure-plane will not be closed before line crack initiation destroys.
In a specific embodiment, in step S2, the expression formula of crackle crack initiation angle θ are as follows:
In formula (1), KII、KIRespectively the II type at crack tip, I type stress intensity factor, according to J.Tirosh's as a result,
Under the conditions of considering different tip curvatures, KII、KIExpression formula are as follows:
In formula (2), σ is the stress at uniaxial compression sample both ends, and a is half length of prefabricated Single Fracture, and α is inclining for prefabricated crack
Angle, is prefabricated Single Fracture and horizontal direction angle, and ρ is crack tip curvature.
In a specific embodiment, it in step S4, chooses crack tip curvature and is greater than 10, revised crack is inclined
Based on relationship between angle and crackle crack initiation angle.
In a specific embodiment, in step S4, the wing crackle selection in micro- section is small as far as possible, is up to initial pre-
The 1/20 of crack length processed.
Compared with prior art, advantageous effects of the invention are as follows:
The present invention provides a kind of methods for predicting wing crack propagation path, and the method overcome previous mechanical analyses to determine
Complicated calculations process when crack propagation path has preferable practicability again in practice, can accurate prediction compression shear condition
The Extended workflow-net of lower crack open tip wing crackle, method is simple, it can be readily appreciated that convenient for operation.
Detailed description of the invention
Fig. 1 is a kind of step flow chart for the method for predicting wing crack propagation path of the present invention.
Fig. 2 is crack dip and crackle crack initiation angular curve under the conditions of different tip curvatures.
Fig. 3 is the crack propagation figure of sample containing crack that crack dip is 15 ° under Uniaxial Compression.
Fig. 4 is crack propagation path depiction in Fig. 3.
Fig. 5 is revised crack dip and tip crackle crack initiation angular curve.
Fig. 6 is equivalent crack schematic diagram.
Fig. 7 is the method provided by the present invention crack propagation path when crack tip curvature is 12.5.
Fig. 8 is the Extended workflow-net comparison diagram of crack propagation path and prior art test result in Fig. 7；
Wherein, (a) prefabricated crack inclination angle is 0 ° of crack propagation path；(b) prefabricated crack inclination angle is 15 ° of crack propagation rails
Mark；(c) prefabricated crack inclination angle is 30 ° of crack propagation paths；(d) prefabricated crack inclination angle is 45 ° of crack propagation paths；(e) prefabricated
Crack dip is 60 ° of crack propagation paths；(f) prefabricated crack inclination angle is 75 ° of crack propagation paths.
Specific embodiment
The present invention program is further elaborated with attached drawing combined with specific embodiments below.
As shown in Figure 1, the present invention provides a kind of method for predicting wing crack propagation path, comprising the following steps:
Step 1: the prefabricated sample containing crack open, control crack dip is α；
Step 2: stress analysis is carried out to crack open tip, obtains the stress field at crack tip under the conditions of compression shear,
And then obtain the crackle crack initiation angle θ at crack open tip, expression formula are as follows:
In formula (1), KII、KIRespectively the II type at crack tip, I type stress intensity factor, according to the result of J.Tirosh
[2], under the conditions of considering different tip curvatures, KII、KIExpression formula are as follows:
In formula (2), σ is the stress at uniaxial compression sample both ends, and a is half length of prefabricated Single Fracture, and α is inclining for prefabricated crack
Angle, is prefabricated Single Fracture and horizontal direction angle, and ρ is crack tip curvature.
Step 3: by theoretical calculation, when obtaining considering crack tip curvature, between crack dip α and crackle crack initiation angle θ
Relationship, in conjunction with test and analog result, the crackle crack initiation angle θ in low-angle is modified, is obtained revised
Relationship between crack dip and crackle crack initiation angle；
According to the expression formula in step S2, determines the relationship between crackle crack initiation angle θ and crack dip α, obtain different points
Crack dip and crackle crack initiation angular curve (as shown in Figure 2) under the conditions of the curvature of end, by Fig. 2 and comparison of test results, it can be seen that
Notional result and test result are almost the same in wide-angle (30 ° of >) range, and at low-angle (30 ° of <), notional result
180 ° (crack initiation angle is 180 ° and then represents crack open face itself, it becomes virtually impossible to occur) are constantly tended to, and actual are split
Line crack initiation angle maximum only has 125 ° or so.
This is because the tip stress fields calculated when (1) formula of derivation are only limited near the tip of crack, can not be included in far from point
The destruction at end.And for crack open, internal cavity make crack inner surface central region generate it is stronger by
Drawing effect, so as to cause might not be from the crack initiation of crack tip in low-angle crack dip, such as when α=0 °, crackle has
When the crack initiation in the middle part of the crack；And when α=15 °, in the fracture surface away from crack tip certain distance, this point is in past multidigit
It can see in the achievement of scholar.Crack dip and crackle crack initiation angular curve when therefore needing to low-angle make a periodical repair
Just.
Then found during being simulated using ANSYS, when crack dip is low-angle, around prefabricated crack,
The position of maximum principal stress is not at crack tip, maximum but in the upper surface in crack, and with the increase of crack dip
The position of principal stress is gradually by leveling off in the middle part of fissure-plane near the tip of crack.When crack dip is 30 °, maximum principal stress
Position reaches tip and results in crack from the crack initiation at a certain distance from tip just because of this point.Since crack is sky
Chamber, inner surface do not have edge-restraint condition, and biggest principal stress direction is also parallel with fissure-plane direction, therefore answer according to maximum master
The crack crack initiation direction that power determines should be perpendicular to fissure-plane, as 90 °.In makeover process, if assume low-angle, the initial wing
Crackle is from crack initiation near the tip of crack, then crackle crack initiation angle will not be shown in Fig. 2 as a result, will not be 90 °.
Simultaneously carried out in ANSYS one simulation, it is assumed that in the crack sample of small inclination, precrack tip with
90 ° of crack initiation angle crack initiation has generated the small wing crackle of a vertical fissure-plane at crack tip, micro- wing is split at this time for observation
Line tip biggest principal stress direction (with horizontal direction angle) as a result counts such as table 1, and analog result is shown to be split even if initially
Line, with the direction crack initiation perpendicular to fissure-plane, after expanding into rock mass inside, under the action of tip stress fields, also can at tip
Continue the deviation of generation wide-angle, and the maximum compared at tip maximum principal stress at this time and original fissure-plane medium position is main
Stress value finds that the principal stress value on fissure-plane is significantly smaller, illustrates that next step crackle is continued to along micro- wing crack tip
Extension.
The micro- wing crack tip biggest principal stress direction of table 1 statistics
Fig. 3 is the crack propagation figure of sample containing crack that crack dip is 15 ° under Uniaxial Compression, tests process are as follows: will
The sample of crack open containing single, which is placed on uniaxial compression test machine, to be loaded, and smears grease, placement rubber slab at sample both ends,
To completely eliminate end friction effect.It can see sample at tip first approximately along fissure-plane vertical direction by details enlarged drawing
One section of distance element of very little is extended, then deviation angle increases, then the just gradually direction deviation extension of maximum principal stress in the axial direction.
The trace of prefabricated crack and running crack in the sample is described, as shown in fig. 4, it can be seen that passing through survey
After having small crack initiation approximately perpendicular to fissure-plane, crackle continues to extend the angle of deviation to be about to tie in 146 °, with table 1 amount
Fruit is almost the same, and dotted portion, which represents, in Fig. 4 will play the crackle crack initiation side of a hypothesis after knick point is connected with subsequent crackle
To with track (referred to as " assuming that crackle ").The construction crack initiation crackle and horizontal direction angle assumed by measurement upper and lower ends are distinguished
For 132 ° and 122 °, so the average value at crackle crack initiation angle is (132 °+122 °)/2-15 °=112 °；It is similar to 0 ° and
30 ° of samples are tested, and determine corresponding crackle crack initiation angle correction value.
Fig. 5 is revised crack dip and tip crackle crack initiation angular curve, it is contemplated that in wing crack propagation process, crackle
Tip curvature is higher, determine herein the relationship between crack dip and crackle crack initiation angle be in Fig. 5 when curvature=12.5
Crackle crack initiation angle result.
Step 4: according to the relationship of the crack dip and crackle crack initiation angle that are determined in Fig. 5, selection crack tip curvature=
When 12.5, based on revised crack dip and crackle crack initiation angular curve, the rail of the small one section of wing crackle in crack tip is determined
Mark, small one section of value is 1/20 length of prefabricated crack length here；
Step 5: wing crackle endpoint is connected using straight line, line is intended seeing as according to the crack propagation situation in S4
New prefabricated crack, referred to as equivalent crack, as shown in Figure 6；
Step 6: judging whether the crack dip in equivalent crack reaches 90 °, if it is not, then equivalent crack is regarded as initially
Crack repeats S2~S5, if it is, terminating iteration, obtains the Extended workflow-net of wing crackle.
Fig. 7 is the method provided by the present invention crack propagation path when crack tip curvature is 12.5, wherein figure (a) is difference
Crack dip spreading result, figure (b) is the schematic diagram that different Extended workflow-net curves are placed into same point.
In order to verify the reasonability of equivalent crack model, prediction technique of the present invention and Zhao Cheng [5], Heekwang Lee are summarized
[6], the multidigits scholar such as LNY Wong [7] is in uniaxial compression, and the test result of crack open load then will be of the invention
Obtained expansion curve and test result curve comparison.Since the sample material that different researchers use is different, and place result
Schematic diagram is final destruction figure, and individual sample fragmentation is serious, therefore gives up spot sample.Extended workflow-net is complete, the clearly wing
Crackle is described using CAD, and zooms under same ratio, then by taking point location, obtains corresponding expansion curve rail
Mark coordinate curve.In the case of each crack dip, different researchers test result summarizes, as shown in Figure 8.
From figure 8, it is seen that equivalent crack model and multidigit scholar test result are coincide well.In order to preferably quantify to kiss
More people are tested tracing point and " equivalent crack model " the data obtained Comparative result, utilize coefficient of determination-recurrence square by conjunction degree
With the ratio with total sum of squares of deviations, numerical value is equal to square of related coefficient.To measure the identical journey of model and real data
Degree.
Herein, by the track discretization in more people's results, volume of data point is obtained, and equivalent crack model is obtained
Curve regards the prediction model (being the equal of the regression beeline equation in regression analysis) of these data points as, to utilize following formula
Obtain the coefficient of determination of response curve.
Wherein residual sum of squares (RSS) of the SSE between discrete data point and model, SST are the total sum of squares of discrete data point,
Respectively such as following formula:
Obtain the coefficient of determination such as table 2 of different curves:
Table 2: the coefficient of determination table of different curves
In conjunction with Fig. 8 and table 2, it can be seen that most of data coincidence is all very high.When prefabricated crack inclination angle is 75 °, two
The coefficient of determination of a data is all negative value, this is because the angle of crackle crack initiation at this time itself is smaller, upon crack initiation, almost just along most
Big principal direction of stress extension.Therefore it causes the total sum of squares of data point itself smaller, causes final coefficient of determination to be inclined to be
Negative value, practical to can see by Fig. 8 (f), several curve degree of agreement are preferable.
Bibliography
[1]Tirosh J.Incipient fracture angle,fracture loci and critical
stress for mixed mode loading[J].Engineering Fracture Mechanics,1977,9(3):
607-616.
[2]Tirosh J,Catz E.Mixed-mode fracture angle and fracture locus of
materials subjected to compressive loading[J].Engineering Fracture Mechanics,
1981,14:27-38.
[3]Horii H,Nemat-Nasser S.Compression-induced microcrack growth in
brittle solids:Axial splitting and shear failure[J].Journal of Geophysical
Research,1985,90(B4):3105.
[4]Nemat-Nasser S,Horii H.Compression-induced nonplanar crack
extension with application to splitting,exfoliation,and rockburst[J].Journal
of Geophysical Research Solid Earth,1982,87(B8):6805-6821.
[5] Zhao Cheng, Liu Fengming, Tian Jiashen wait to advise based on the rock list crack propagation and damage development of uniaxial compression test
Rule research [J] Chinese Journal of Rock Mechanics and Engineering, 2016 (S2): 3626-3632.
[6]Lee H,Jeon S.An experimental and numerical study of fracture
coalescence in pre-cracked specimens under uniaxial compression[J]
.International Journal of Solids and Structures,2011,48(6):979-999.
[7]Wong L N Y,Einstein H H.Fracturing Behavior of Prismatic Specimens
Containing Single Flaws:the 41st U.S.Rock Mechanics Symposium-ARMA's Golden
Rocks 2006-50 Years of Rock Mechanics,Cambridge,MA,USA,2006[C].
Claims (6)
1. a kind of method for predicting wing crack propagation path, which comprises the following steps:
S1. the prefabricated sample containing crack open, crack dip α；
S2. under compression shear state, stress analysis is carried out to crack open tip, obtains the stress field at crack tip, and then obtain
The crackle crack initiation angle θ at crack open tip；
S3. by theoretical calculation, when obtaining considering crack tip curvature, the relationship between crack dip α and crackle crack initiation angle θ,
In conjunction with test and analog result, the crackle crack initiation angle θ in low-angle is modified, revised crack dip is obtained
With the relationship between crackle crack initiation angle；
S4. when selection crack tip curvature is larger, based on the relationship between revised crack dip and crackle crack initiation angle, really
Fixed wing crack propagation path of the initial crack in micro- section；
S5. according to the crack propagation path in step S4, wing crackle endpoint is connected using straight line, by line it is quasi- regard as it is new pre-
Crack processed, referred to as equivalent crack；
S6. judge whether the crack dip in equivalent crack reaches 90 °, if it is not, then equivalent crack is regarded as initial crack, repeat
Step S2~S5 obtains the Extended workflow-net of wing crackle if it is, iteration terminates.
2. the method for prediction wing crack propagation path according to claim 1, which is characterized in that in step S1, crack is inclined
Angle α is fissure-plane and horizontal plane angle.
3. the method for prediction wing crack propagation path according to claim 1, which is characterized in that in step S1, opening is split
Gap has certain opening width, and fissure-plane will not be closed before at crack tip, crackle crack initiation is destroyed.
4. the method for prediction wing crack propagation path according to claim 1, which is characterized in that in step S2, crackle is risen
Split the expression formula of angle θ are as follows:
In formula (1), KII、KIRespectively the II type at crack tip, I type stress intensity factor, according to J.Tirosh's as a result, examining
Under the conditions of considering different tip curvatures, KII、KIExpression formula are as follows:
In formula (2), σ is the stress at uniaxial compression sample both ends, and a is half length of prefabricated Single Fracture, and α is the inclination angle of prefabricated crack,
For prefabricated Single Fracture and horizontal direction angle, ρ is crack tip curvature.
5. the method for prediction wing crack propagation path according to claim 1, which is characterized in that in step S4, selection is split
Gap tip curvature is greater than 10, based on the relationship between revised crack dip and crackle crack initiation angle.
6. the method for prediction wing crack propagation path according to claim 1, which is characterized in that in step S4, in micro- section
Wing crackle choose it is small as far as possible, be up to the 1/20 of initial prefabrication crack length.
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110274835A (en) * | 2019-07-12 | 2019-09-24 | 中南大学 | A method of improving Burgers rock shearing creep model |
| CN114689448A (en) * | 2020-12-30 | 2022-07-01 | 中国石油大学(华东) | Damage fracture analysis method for opening fracture, compacting, closing and timely and effectively expanding |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20140136173A1 (en) * | 2007-01-29 | 2014-05-15 | Schlumberger Technology Corporation | Methods of hydraulically fracturing a subterranean formation |
| CN105138738A (en) * | 2015-07-31 | 2015-12-09 | 中南大学 | Calculation method of three-dimensional permeability tensor |
| CN108509711A (en) * | 2018-03-29 | 2018-09-07 | 中国地质大学（北京） | The construction method of intermittent fracture Rock Damage constitutive model under plane compression-shear stress |
| CN109117534A (en) * | 2018-07-31 | 2019-01-01 | 中国华能集团有限公司 | A kind of fracture and crack prediction method based on geological map |
-
2019
- 2019-03-29 CN CN201910250732.9A patent/CN109902444B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20140136173A1 (en) * | 2007-01-29 | 2014-05-15 | Schlumberger Technology Corporation | Methods of hydraulically fracturing a subterranean formation |
| CN105138738A (en) * | 2015-07-31 | 2015-12-09 | 中南大学 | Calculation method of three-dimensional permeability tensor |
| CN108509711A (en) * | 2018-03-29 | 2018-09-07 | 中国地质大学（北京） | The construction method of intermittent fracture Rock Damage constitutive model under plane compression-shear stress |
| CN109117534A (en) * | 2018-07-31 | 2019-01-01 | 中国华能集团有限公司 | A kind of fracture and crack prediction method based on geological map |
Non-Patent Citations (2)
| Title |
|---|
| 杨庆 等: "翼型裂纹扩展特性的试验和数值分析", 《水利学报》 * |
| 杨横涛 等: "岩样单裂隙几何参数对其破坏模式与强度的影响", 《长江科学院院报》 * |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110274835A (en) * | 2019-07-12 | 2019-09-24 | 中南大学 | A method of improving Burgers rock shearing creep model |
| CN110274835B (en) * | 2019-07-12 | 2021-04-30 | 中南大学 | Method for improving Burgers rock shear creep model |
| CN114689448A (en) * | 2020-12-30 | 2022-07-01 | 中国石油大学(华东) | Damage fracture analysis method for opening fracture, compacting, closing and timely and effectively expanding |
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