CN102944473B - 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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- CN102944473B CN102944473B CN201210479828.0A CN201210479828A CN102944473B CN 102944473 B CN102944473 B CN 102944473B CN 201210479828 A CN201210479828 A CN 201210479828A CN 102944473 B CN102944473 B CN 102944473B
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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 J<IC> 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 J<IC> integral value of the new laminating structure is determined, and the critical J<IC> integral values of completely ageing laminating structures are compared with the critical J<IC> 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 laminate structures or polymer body material aging cause.
Background technology
The laminate structures being comprised of two or more polymeric materials is widely used in the fields such as space flight, machinery, in actual storage and environment for use, due to the impact of the many factors such as temperature, humidity, oxygen rate of diffusion and component migration, laminate structures occurs non-homogeneous aging.In actual applications, the ageing failure of laminate structures often shows as bonding interface unsticking, and the mechanism of structural failure is relevant to the performance degradation that the little molecular migration adding in polymkeric substance and polymer body material aging cause, how to judge that the failure mechanism being dominant is significant to improve structure ageing-resistant performance to improving design of material.At present, for the aging main cause of judgement, and non-homogeneous aging trend is all generally to adopt chemistry, the method of materialogy, operation is loaded down with trivial details, with high costs, and the often coupling of performance degradation that laminate structures small molecular moves and polymer body material aging causes, should not distinguish, therefore find 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 of prior art existence, the invention provides the experiment analytical method of the laminated structure ageing failure of a kind of simple polymkeric substance mechanism.
The object 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 again bonded to laminate structures b after the cutting of 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 component migration is the main cause that laminate structures is aging; If the slope variation rate of laminate structures a is less than laminate structures b, the diffusion that oxygen is described is the main cause that laminate structures is aging; Meanwhile, laminate structures a different piece is cut and formed laminate structures c, measure that it is completely aging critical
integrated value, and critical with completely aging laminate structures b
integrated value contrasts, the non-homogeneous aging trend of component materials in judgement laminate structures, and its determination methods is: if the laminate structures c's that laminate structures b and close interface cut form is critical
integration absolute value is greater than the critical of laminate structures c that the cutting of laminate structures b and outside face forms
the absolute difference of integration, illustrates that 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
integration absolute value is less than the critical of laminate structures c that the cutting of laminate structures b and outside face forms
the absolute difference of integration, illustrates that 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 elastic deformation:
, B is specimen thickness,
the crack length that is two test specimens is poor,
for dash area area, the knick point that A, 2 of B are crackle, O is initial point.
For the laminate structures under elastic-plastic deformation: utilize formula
with
calculate
value.
The present invention can judge non-homogeneous aging tendency in laminate structures, also can determine the principal element of laminate structures interfacial age simultaneously.Compared with prior art there is following advantage:
1, the present invention does not adopt traditional chemistry, materialogy means of testing, and compared oxygen diffusion with mechanics methods analyst, moves for the aging impact of laminate structures with component, can judge in different component materials situations which is to cause aging main cause;
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.
Accompanying drawing explanation
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 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
Below in conjunction with accompanying drawing, elaborate technical scheme of the present invention, 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, initial crack is left in interface, as Figure 1-5, wherein test specimen I is sealed at both ends, prevent that air from entering, test specimen II, III, IV, the laminate structures being formed by homogenous material that V adopts, prevent from occurring that component moves between interface, I wherein, II, III is of a size of 60mm*40mm*20mm, test specimen IV, V is of a size of 60mm*40mm*10mm, by crack length difference, test specimen is divided into 3 groups, number of test-pieces is in Table 1, test specimen I, II, III is positioned in the environment of 50 ℃ aging, test specimen IV, V is positioned in 70 ℃ of environment aging, test as follows:
Digestion time is
it time, from 1. 2. 3. respectively taking out one of test specimen I, II, III group, each group is again bonded to test specimen VI (as Fig. 6) by test specimen II, III after the cutting of interface, grouping is pulled to fracture critical point by test specimen by test specimen I, VI under the fixing condition of rate of extension, and test specimen I, VI respectively organized in record
curve, wherein
for pulling force size, Δ is stress point displacement.For test specimen I, get 1. group, 2. group
curve (as Fig. 7), the knick point that wherein A, 2 of B are crackle, calculates dash area area
, get equally group 2., group 3.
opisometer is calculated dash area area
, get
,
mean value
, utilize formula:
obtain
, wherein,
bfor specimen thickness,
the crack length that is two test specimens is poor; For test specimen VI, adopt to use the same method with test specimen I and obtain
.
When digestion time is
my god,
my god,
my god,
my god,
my god,
my god,
it time, repeat above-mentioned steps, obtain the fracture critical J-integral value of test specimen I, VI under different digestion times
,
,
,
,
,
,
with
,
,
,
,
,
,
, it is depicted as respectively to 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
greatly, illustrate that component migration is the main cause that laminate structures is aging; If
slope variation rate ratio
little, the diffusion that oxygen is described is the main cause that laminate structures is aging.
When digestion time is D
7it time, from 1. 2. 3. respectively taking out test specimen II, III, IV, V group by cutting as shown in Figure 8 and bonding, every group of test specimen VII, VIII, IX obtaining separately.Carry out equally the fixing stretching experiment of rate of extension, record
curve, and utilize the same method to calculate the now critical J-integral value of test specimen VII, VIII, IX
,
,
, relatively
with
size, if
be greater than
, illustrate that the oxygen rate of propagation of outside face in this laminate structures is faster than the oxygen rate of propagation at interface, if
be less than
, illustrate that 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 elastic deformation.
Table 1
Embodiment two: present embodiment is different from embodiment one, for elastoplasticity modification, required number of test-pieces is only used as shown 2(the test specimen that crack length is 20mm), digestion time is
it time, test specimen II, III are again bonded to test specimen VI (as Fig. 6) after the cutting of interface, test specimen I, VI be pulled to fracture critical point by test specimen under the fixing condition of rate of extension, test specimen I, VI respectively organized in record
curve.Utilize formula
with
calculate
with
value, wherein
for pulling force size, Δ is stress point displacement, and U is strain energy,
for specimen crack length,
for specimen width.
Table 2
Claims (4)
1. an experiment analytical method for the laminated structure ageing failure of polymkeric substance mechanism, is characterized in that described method is:
Laminate structures a is comprised of two or more polymeric materials, by adopting the test specimen being comprised of single polymers material in above-mentioned two or more polymeric materials to be again bonded to laminate structures b after the cutting of interface, by measuring the critical J of different digestion times
iCintegrated value, draws 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, wherein:
For the laminate structures under elastic deformation, described J
iC=S
oABO/ B △ a, B is specimen thickness, △ a is that the crack length of two test specimens is poor, S
oABOfor dash area area, the knick point that A, 2 of B are crackle, O is initial point;
For the laminate structures under elastic-plastic deformation, described in
wherein P is pulling force size, and △ is stress point displacement, and U is strain energy, and a is specimen crack length, and W is specimen width.
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 the dominant mechanism of described interfacial age is: if the slope variation rate of laminate structures a is larger than laminate structures b, illustrate that component migration is the main cause that laminate structures is aging; If the slope variation rate of laminate structures a is less than laminate structures b, the diffusion that oxygen is described is the main cause that laminate structures is aging.
3. an experiment analytical method for the laminated structure ageing failure of polymkeric substance mechanism, is characterized in that described method is:
Laminate structures a is comprised of two or more polymeric materials, to adopt the test specimen being formed by single polymers material in above-mentioned two or more polymeric materials to be again bonded to laminate structures b after the cutting of interface, laminate structures a different piece is cut and formed laminate structures c, measure its aging critical J completely
iCintegrated value, and with the critical J of completely aging laminate structures b
iCintegrated value contrasts, the non-homogeneous aging trend of component materials in judgement laminate structures, wherein:
For the laminate structures under elastic deformation, described J
iC=S
oABO/ B △ a, B is specimen thickness, △ a is that the crack length of two test specimens is poor, S
oABOfor dash area area, the knick point that A, 2 of B are crackle, O is initial point;
For the laminate structures under elastic-plastic deformation, described in
wherein P is pulling force size, and △ is stress point displacement, and U is strain energy, and a is specimen crack length, and W is specimen width.
4. the experiment analytical method of the laminated structure ageing failure of polymkeric substance according to claim 3 mechanism, is characterized in that the determination methods of the non-homogeneous aging tendency of component materials in described laminate structures is: if the critical J of the laminate structures c that laminate structures b and close interface cut form
iCintegration absolute value is greater than the critical J of the laminate structures c of laminate structures b and outside face cutting composition
iCthe absolute difference of integration, illustrates that the oxygen rate of propagation of outside face in this laminate structures is faster than the oxygen rate of propagation at interface, if the critical J of the laminate structures c that laminate structures b and close interface cut form
iCintegration absolute value is less than the critical J of the laminate structures c of laminate structures b and outside face cutting composition
iCthe absolute difference of integration, illustrates that the oxygen rate of propagation of outside face in this laminate structures is slower than the oxygen rate of propagation at interface.
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| Publication number | Priority date | Publication date | Assignee | Title |
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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 |
Non-Patent Citations (1)
| Title |
|---|
| 张颖军.《聚合物基复合材料老化剩余强度等效预测方法研究》.《材料导报B：研究篇》.2012,第26卷(第4期), * |
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