CN102944473A - Experimental analysis method of polymer laminating structure ageing failure mechanism - Google Patents
Experimental analysis method of polymer laminating structure ageing failure mechanism Download PDFInfo
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- CN102944473A CN102944473A CN2012104798280A CN201210479828A CN102944473A CN 102944473 A CN102944473 A CN 102944473A CN 2012104798280 A CN2012104798280 A CN 2012104798280A CN 201210479828 A CN201210479828 A CN 201210479828A CN 102944473 A CN102944473 A CN 102944473A
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- laminate structures
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Abstract
The invention relates to an experimental analysis method of a laminating structure ageing failure mechanism and particularly relates to an experimental analysis method of a polymer laminating structure ageing failure mechanism. By means of the experiment method, ageing of a laminating structure is only influenced by single factors, ageing curves are drawn by determining critical integral values of different ageing time, and the main mechanism of interfacial ageing is judged by comparing the two curves; and simultaneously, different parts of the laminating structure are cut to form a new laminating structure, a critical integral value of the new laminating structure is determined, and the critical integral values of completely ageing laminating structures are compared with the critical integral value of the new laminating structure so as to judge the inhomogeneous ageing trend of component materials in the laminating structure. The experimental analysis method can be applicable to ageing estimation of various laminating structures and has broad application prospects in fields of aerospace and aviation.
Description
Technical field
The present invention relates to a kind of experiment analytical method of ageing failure mechanism of laminate structures, relate in particular to a kind of experimental technique that utilizes critical integrated value to analyze the performance degradation failure mechanism that molecular migration in the laminate structures or polymer body material aging cause.
Background technology
The laminate structures that is comprised of two or more polymeric materials is widely used in the fields such as space flight, machinery, in the storage and environment for use of reality, because the impact of the many factors such as temperature, humidity, oxygen rate of diffusion and component migration, laminate structures occur non-homogeneous aging.In actual applications, the ageing failure of laminate structures often shows as the bonding interface unsticking, and the performance degradation that the little molecular migration that adds in the mechanism of structural failure and the polymkeric substance and polymer body material aging cause is relevant, how to judge that the failure mechanism that is dominant is significant to improve the structure ageing-resistant performance to improving design of material.At present, for judging aging main cause, and non-homogeneous aging trend generally all is to adopt chemistry, the method of materialogy, operation is loaded down with trivial details, and is with high costs, and the often coupling of performance degradation that the laminate structures small molecular moves and the polymer body material aging causes, should not distinguish, therefore seek the problem that a kind of simple experiment test method is the required solution of research laminate structures ageing failure mechanism.
Summary of the invention
For the problem that prior art exists, the invention provides the experiment analytical method of the laminated structure ageing failure of a kind of simple polymkeric substance mechanism.
The objective of the invention is to be achieved through the following technical solutions:
Laminate structures a of the present invention is comprised of two or more polymeric materials, the test specimen that adopts above-mentioned homogenous material to form is bonded to laminate structures b again after cutting at the interface, by measuring the critical of different digestion times
Integrated value, draw out aging curve, by the comparison to laminate structures a and two aging curves of laminate structures b, determine the dominant mechanism of interfacial age, its determination methods is: if the slope variation rate of laminate structures a is larger than laminate structures b, illustrate that then the component migration is the aging main cause of laminate structures; If the slope variation rate of laminate structures a is less than laminate structures b, the diffusion that oxygen then is described is the aging main cause of laminate structures; Simultaneously, laminate structures a different piece is cut composition laminate structures c, measure critical that it wears out fully
Integrated value, and critical with fully aging laminate structures b
Integrated value compares, and judges the non-homogeneous aging trend of component materials in the laminate structures, and its determination methods is: if the laminate structures c's that laminate structures b and close interface cut form is critical
The laminate structures c's that the integration absolute value forms greater than the cutting of laminate structures b and outside face is critical
The absolute difference of integration illustrates that then the oxygen rate of propagation of outside face in this laminate structures is faster than the oxygen rate of propagation at interface, if the laminate structures c's that laminate structures b and close interface cut form is critical
The laminate structures c's that the integration absolute value forms less than the cutting of laminate structures b and outside face is critical
The absolute difference of integration illustrates that then the oxygen rate of propagation of outside face in this laminate structures is slower than the oxygen rate of propagation at interface.
For the laminate structures under the elastic deformation:
, B is specimen thickness,
The crack length that is two test specimens is poor,
Be the dash area area, A, 2 of B are the knick point that rises of crackle, and O is initial point.
For the laminate structures under the elastic-plastic deformation: utilize formula
With
Calculate
Value.
The present invention can judge non-homogeneous aging tendency in the laminate structures, also can determine the principal element of laminate structures interfacial age simultaneously.Compared with prior art have following advantage:
1, the present invention does not adopt traditional chemistry, materialogy means of testing, and has compared oxygen diffusion and component migration for the aging impact of laminate structures with the mechanics methods analyst, can judge in the different component materials situations which is to cause the main cause that wears out;
2, can compare laminate structures outside surface and interface oxygen rate of diffusion;
3, applicable to the Aging Assessment problem of various laminate structures, in space flight, aviation field has broad application prospects.
Description of drawings
Fig. 1 is the structural representation of test specimen I;
Fig. 2 is the structural representation of test specimen II;
Fig. 3 is the structural representation of test specimen III;
Fig. 4 is the structural representation of test specimen IV;
Fig. 5 is test specimen V structural representation;
Fig. 6 be the test specimen VI structural representation;
Fig. 7 is
Curve map;
Fig. 8 is cutting and the sticking structure schematic diagram of test specimen VII, VIII;
Fig. 9 is the structural representation of test specimen IX.
Embodiment
Elaborate technical scheme of the present invention below in conjunction with accompanying drawing, but do not limit protection scope of the present invention.
Embodiment one: the laminate structures of present embodiment is comprised of materials A and material B, leave at the interface initial crack, shown in Fig. 1-5, wherein the test specimen I is sealed at both ends, prevent that air from entering, the test specimen II, III, IV, the laminate structures that is formed by homogenous material that V adopts, prevent from occurring between the interface component migration, I wherein, II, III is of a size of 60mm*40mm*20mm, the test specimen IV, V is of a size of 60mm*40mm*10mm, by the crack length difference test specimen is divided into 3 groups, number of test-pieces sees Table 1, the test specimen I, II, III is positioned in 50 ℃ the environment aging, the test specimen IV, V is positioned in 70 ℃ of environment aging, carries out following experiment:
Digestion time is
It the time, from 1. 2. 3. respectively taking out one of test specimen I, II, III the group, along again being bonded to test specimen VI (such as Fig. 6) after the cutting at the interface, grouping is pulled to fracture critical point with test specimen with test specimen I, VI to each group under the fixing condition of rate of extension with test specimen II, III, and test specimen I, VI respectively organized in record
Curve, wherein
Be the pulling force size, Δ is the stress point displacement.For the test specimen I, get 1. group, 2. group
Curve (such as Fig. 7), wherein A, 2 of B are the knick point that rises of crackle, calculate the dash area area
, get equally group 2., group 3.
Opisometer is calculated the dash area area
, get
,
Mean value
, utilize formula:
Obtain
, wherein,
BBe specimen thickness,
The crack length that is two test specimens is poor; For the test specimen VI, adopt to use the same method with the test specimen I and obtain
When digestion time is
My god,
My god,
My god,
My god,
My god,
My god,
It the time, repeat above-mentioned steps, obtain the fracture critical J-integral value of test specimen I, VI under the different digestion times
,
,
,
,
,
,
With
,
,
,
,
,
,
, it is depicted as respectively the aging curve of test specimen I, VI
With
(horizontal ordinate is days of ageing, and ordinate is
Value).Relatively 2 slope of a curves change, if
Slope variation rate ratio
Illustrate that greatly, then the component migration is the aging main cause of laminate structures; If
Slope variation rate ratio
Little, the diffusion that oxygen then is described is the aging main cause of laminate structures.
When digestion time is D
7It the time, from 1. 2. 3. the group respectively take out test specimen II, III, IV, V by cutting as shown in Figure 8 and bond, every group of test specimen VII, VIII, IX that obtains separately.Carry out equally the fixing stretching experiment of rate of extension, record
Curve, and utilize the same method to calculate the critical J-integral value of test specimen VII this moment, VIII, IX
,
,
, relatively
With
Size, if
Greater than
, illustrate that then the oxygen rate of propagation of outside face in this laminate structures is faster than the oxygen rate of propagation at interface, if
Less than
, illustrate that then the oxygen rate of propagation of outside face in this laminate structures is slower than the oxygen rate of propagation at interface.
Present embodiment is applicable to the laminate structures under the elastic deformation.
Table 1
Embodiment two: what present embodiment and embodiment one were different is that for the elastoplasticity modification, required number of test-pieces only uses crack length to be the test specimen of 20mm such as table 2(), digestion time is
It the time, test specimen II, III along again being bonded to test specimen VI (such as Fig. 6) after the cutting at the interface, be pulled to fracture critical point with test specimen with test specimen I, VI under the fixing condition of rate of extension, test specimen I, VI respectively organized in record
Curve.Utilize formula
With
Calculate
With
Value, wherein
Be the pulling force size, Δ is the stress point displacement, and U is strain energy,
Be specimen crack length,
Be specimen width.
Table 2
Claims (8)
1. the experiment analytical method of the laminated structure ageing failure of a polymkeric substance mechanism is characterized in that described method is:
Laminate structures a is comprised of two or more polymeric materials, the test specimen that adopts above-mentioned homogenous material to form is bonded to laminate structures b again after cutting at the interface, by measuring the critical of different digestion times
Integrated value is drawn out aging curve, by the comparison to laminate structures a and two aging curves of laminate structures b, determines the dominant mechanism of interfacial age.
2. the experiment analytical method of the laminated structure ageing failure of polymkeric substance according to claim 1 mechanism, the determination methods that it is characterized in that described interfacial age cardinal principle is: if the slope variation rate of laminate structures a is larger than laminate structures b, illustrate that then the component migration is the aging main cause of laminate structures; If the slope variation rate of laminate structures a is less than laminate structures b, the diffusion that oxygen then is described is the aging main cause of laminate structures.
3. the experiment analytical method of the laminated structure ageing failure of polymkeric substance according to claim 1 mechanism is characterized in that for the laminate structures under the elastic deformation, and is described
,
BBe specimen thickness,
The crack length that is two test specimens is poor,
Be the dash area area, A, 2 of B are the knick point that rises of crackle, and O is initial point.
4. the experiment analytical method of the laminated structure ageing failure of polymkeric substance according to claim 1 mechanism is characterized in that for the laminate structures under the elastic-plastic deformation, and is described
,
, wherein
Be the pulling force size, D is the stress point displacement, and U is strain energy,
Be specimen crack length,
Be specimen width.
5. the experiment analytical method of the laminated structure ageing failure of a polymkeric substance mechanism is characterized in that described method is:
Laminate structures a is comprised of two or more polymeric materials, and the test specimen that adopts above-mentioned homogenous material to form is being bonded to laminate structures b after the cutting at the interface again, laminate structures a different piece is cut form laminate structures c, measures critical that it wears out fully
Integrated value, and critical with fully aging laminate structures b
Integrated value compares, and judges the non-homogeneous aging trend of component materials in the laminate structures.
6. the experiment analytical method of the laminated structure ageing failure of polymkeric substance according to claim 5 mechanism is characterized in that the determination methods of the non-homogeneous aging tendency of component materials in the described laminate structures is: if the laminate structures c's that laminate structures b and close interface cut form is critical
The laminate structures c's that the integration absolute value forms greater than the cutting of laminate structures b and outside face is critical
The absolute difference of integration illustrates that then the oxygen rate of propagation of outside face in this laminate structures is faster than the oxygen rate of propagation at interface, if the laminate structures c's that laminate structures b and close interface cut form is critical
The laminate structures c's that the integration absolute value forms less than the cutting of laminate structures b and outside face is critical
The absolute difference of integration illustrates that then the oxygen rate of propagation of outside face in this laminate structures is slower than the oxygen rate of propagation at interface.
7. the experiment analytical method of the laminated structure ageing failure of polymkeric substance according to claim 5 mechanism is characterized in that for the laminate structures under the elastic deformation, and is described
,
BBe specimen thickness,
The crack length that is two test specimens is poor,
Be the dash area area, A, 2 of B are the knick point that rises of crackle, and O is initial point.
8. the experiment analytical method of the laminated structure ageing failure of polymkeric substance according to claim 5 mechanism is characterized in that for the laminate structures under the elastic-plastic deformation, and is described
,
, wherein
Be the pulling force size, D is the stress point displacement, and U is strain energy,
Be specimen crack length,
Be specimen width.
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CN104634950A (en) * | 2014-06-30 | 2015-05-20 | 哈尔滨工业大学 | Method for analyzing silicone rubber aging mechanism by utilizing variable activation energy |
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JP4229740B2 (en) * | 2003-03-28 | 2009-02-25 | 株式会社栗本鐵工所 | Numerical analysis method of adhesion of organic coating to metal surface |
CN101487832A (en) * | 2009-02-10 | 2009-07-22 | 哈尔滨工业大学 | Method for characterizing epoxy resin composite material interface mechanism |
US8202932B2 (en) * | 2004-12-03 | 2012-06-19 | Loctite (R&D) Limited | Adhesive bonding systems having adherence to low energy surfaces |
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JP4229740B2 (en) * | 2003-03-28 | 2009-02-25 | 株式会社栗本鐵工所 | Numerical analysis method of adhesion of organic coating to metal surface |
US8202932B2 (en) * | 2004-12-03 | 2012-06-19 | Loctite (R&D) Limited | Adhesive bonding systems having adherence to low energy surfaces |
CN101487832A (en) * | 2009-02-10 | 2009-07-22 | 哈尔滨工业大学 | Method for characterizing epoxy resin composite material interface mechanism |
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Cited By (2)
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CN104634950A (en) * | 2014-06-30 | 2015-05-20 | 哈尔滨工业大学 | Method for analyzing silicone rubber aging mechanism by utilizing variable activation energy |
CN104634950B (en) * | 2014-06-30 | 2016-04-13 | 哈尔滨工业大学 | A kind of utilization becomes the method that energy of activation analyzes silicon rubber agine mechaism |
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