CN102944473A - Experimental analysis method of polymer laminating structure ageing failure mechanism - Google Patents

Experimental analysis method of polymer laminating structure ageing failure mechanism Download PDF

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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
critical
aging
ageing
polymkeric substance
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CN102944473B (en
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谢志民
陈思驰
王友善
阎相桥
刘宇艳
万志敏
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Harbin Institute of Technology
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Harbin Institute of Technology
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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

The experiment analytical method of the laminated structure ageing failure of a kind of polymkeric substance mechanism
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
Figure 399602DEST_PATH_IMAGE001
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
Figure 854854DEST_PATH_IMAGE001
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
Figure 635302DEST_PATH_IMAGE001
The laminate structures c's that the integration absolute value forms greater than the cutting of laminate structures b and outside face is critical
Figure 874654DEST_PATH_IMAGE001
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
Figure 500807DEST_PATH_IMAGE001
The laminate structures c's that the integration absolute value forms less than the cutting of laminate structures b and outside face is critical
Figure 887926DEST_PATH_IMAGE001
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:
Figure 664252DEST_PATH_IMAGE002
, B is specimen thickness,
Figure 820427DEST_PATH_IMAGE003
The crack length that is two test specimens is poor,
Figure 617482DEST_PATH_IMAGE004
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
Figure 101607DEST_PATH_IMAGE006
Calculate
Figure 784393DEST_PATH_IMAGE001
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
Figure 848481DEST_PATH_IMAGE008
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
Figure 232188DEST_PATH_IMAGE007
Curve, wherein
Figure 362956DEST_PATH_IMAGE009
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.
Figure 538219DEST_PATH_IMAGE007
Opisometer is calculated the dash area area , get
Figure 836898DEST_PATH_IMAGE010
,
Figure 907622DEST_PATH_IMAGE011
Mean value
Figure 164291DEST_PATH_IMAGE004
, utilize formula:
Figure 4071DEST_PATH_IMAGE002
Obtain
Figure 422414DEST_PATH_IMAGE012
, wherein, BBe specimen thickness,
Figure 714855DEST_PATH_IMAGE003
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
Figure 571953DEST_PATH_IMAGE013
When digestion time is My god,
Figure 589904DEST_PATH_IMAGE015
My god,
Figure 337018DEST_PATH_IMAGE016
My god,
Figure 732228DEST_PATH_IMAGE017
My god,
Figure 281021DEST_PATH_IMAGE018
My god,
Figure 41166DEST_PATH_IMAGE019
My god,
Figure 308199DEST_PATH_IMAGE020
It the time, repeat above-mentioned steps, obtain the fracture critical J-integral value of test specimen I, VI under the different digestion times
Figure 241520DEST_PATH_IMAGE021
,
Figure 113661DEST_PATH_IMAGE022
,
Figure 372604DEST_PATH_IMAGE023
,
Figure 861355DEST_PATH_IMAGE024
, ,
Figure 325014DEST_PATH_IMAGE026
, With
Figure 904473DEST_PATH_IMAGE028
,
Figure 445176DEST_PATH_IMAGE029
,
Figure 26330DEST_PATH_IMAGE030
,
Figure 627076DEST_PATH_IMAGE031
,
Figure 90418DEST_PATH_IMAGE032
,
Figure 372495DEST_PATH_IMAGE033
, , it is depicted as respectively the aging curve of test specimen I, VI With
Figure 530441DEST_PATH_IMAGE036
(horizontal ordinate is days of ageing, and ordinate is
Figure 412946DEST_PATH_IMAGE001
Value).Relatively 2 slope of a curves change, if
Figure 201648DEST_PATH_IMAGE035
Slope variation rate ratio Illustrate that greatly, then the component migration is the aging main cause of laminate structures; If
Figure 988656DEST_PATH_IMAGE035
Slope variation rate ratio
Figure 674852DEST_PATH_IMAGE036
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
Figure 198554DEST_PATH_IMAGE037
,
Figure 123785DEST_PATH_IMAGE038
,
Figure 285776DEST_PATH_IMAGE039
, relatively
Figure 612852DEST_PATH_IMAGE040
With
Figure 897203DEST_PATH_IMAGE041
Size, if
Figure 477439DEST_PATH_IMAGE040
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
Figure 79956DEST_PATH_IMAGE041
, 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
Figure 979779DEST_PATH_IMAGE043
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
Figure 519662DEST_PATH_IMAGE045
Curve.Utilize formula
Figure 145815DEST_PATH_IMAGE046
With
Figure 205038DEST_PATH_IMAGE047
Calculate
Figure 574839DEST_PATH_IMAGE048
With
Figure 167232DEST_PATH_IMAGE049
Value, wherein
Figure 964287DEST_PATH_IMAGE009
Be the pulling force size, Δ is the stress point displacement, and U is strain energy,
Figure 573123DEST_PATH_IMAGE050
Be specimen crack length,
Figure 418719DEST_PATH_IMAGE051
Be specimen width.
Table 2
Figure 429401DEST_PATH_IMAGE052

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
Figure 2012104798280100001DEST_PATH_IMAGE002
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
Figure 2012104798280100001DEST_PATH_IMAGE004
, BBe specimen thickness, The crack length that is two test specimens is poor,
Figure 2012104798280100001DEST_PATH_IMAGE008
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
Figure 2012104798280100001DEST_PATH_IMAGE010
, , wherein
Figure DEST_PATH_IMAGE014
Be the pulling force size, D is the stress point displacement, and U is strain energy,
Figure DEST_PATH_IMAGE016
Be specimen crack length,
Figure DEST_PATH_IMAGE018
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
Figure 887417DEST_PATH_IMAGE002
Integrated value, and critical with fully aging laminate structures b
Figure 804557DEST_PATH_IMAGE002
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
Figure 662923DEST_PATH_IMAGE002
The laminate structures c's that the integration absolute value forms greater than the cutting of laminate structures b and outside face is critical
Figure 58132DEST_PATH_IMAGE002
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
Figure 367071DEST_PATH_IMAGE002
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
Figure 634104DEST_PATH_IMAGE004
, BBe specimen thickness,
Figure 708371DEST_PATH_IMAGE006
The crack length that is two test specimens is poor,
Figure 377249DEST_PATH_IMAGE008
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 ,
Figure 546833DEST_PATH_IMAGE012
, wherein
Figure 159211DEST_PATH_IMAGE014
Be the pulling force size, D is the stress point displacement, and U is strain energy,
Figure 557962DEST_PATH_IMAGE016
Be specimen crack length,
Figure 738539DEST_PATH_IMAGE018
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
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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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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