Comparative Analysis of Crack Resistance of Fiber Metal Laminates with HS2 Glass/T700 Carbon Layers for Various Stress Ratios
Because of good crack growth resistance owe to the fibers between the aluminum layers, fiber metal laminates (FML) offer significant improvements compared to currently applied materials for aircraft structures. The crack resistance of different reinforced fibers, glass fiber, and carbon fiber, under...
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| Cite this: | Comparative Analysis of Crack Resistance of Fiber Metal Laminates with HS2 Glass/T700 Carbon Layers for Various Stress Ratios / X. Song, Z.Y. Li, Y. Shen, Y.L. Chen, J.Z. Zhang // Проблемы прочности. — 2016. — № 1. — С. 138-144. — Бібліогр.: 9 назв. — англ. |
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Song, X. Li, Z.Y Shen, Y. Chen, Y.L. Zhang, J.Z. 2020-12-03T20:58:31Z 2020-12-03T20:58:31Z 2016 Comparative Analysis of Crack Resistance of Fiber Metal Laminates with HS2 Glass/T700 Carbon Layers for Various Stress Ratios / X. Song, Z.Y. Li, Y. Shen, Y.L. Chen, J.Z. Zhang // Проблемы прочности. — 2016. — № 1. — С. 138-144. — Бібліогр.: 9 назв. — англ. 0556-171X https://nasplib.isofts.kiev.ua/handle/123456789/173427 539.4 Because of good crack growth resistance owe to the fibers between the aluminum layers, fiber metal laminates (FML) offer significant improvements compared to currently applied materials for aircraft structures. The crack resistance of different reinforced fibers, glass fiber, and carbon fiber, under stress ratio R = -1, 0.1, and 0.5, respectively, are analyzed through test data. The results showed significant scatter in the positive stress ratio and obvious difference between two outer aluminum layers. So, the failure criterions of metal materials specified in the test standard are unsuitable for the FMLs fatigue test, and it is a problem to determine the failure criterion according to the engineering applications. This study is an experimental investigations with respect to the FMLs crack resistance and a qualitative conclusions have been drawn from the data analysis. The work was supported by the National Nature Science Foundation of China under the Contract No. 51271067. en Інститут проблем міцності ім. Г.С. Писаренко НАН України Проблемы прочности Научно-технический раздел Comparative Analysis of Crack Resistance of Fiber Metal Laminates with HS2 Glass/T700 Carbon Layers for Various Stress Ratios Сравнительный анализ трещиностойкости металловолоконных многослойных материалов со слоями стекла HS2 и углерода Т700 при различных коэффициентах асимметрии цикла Article published earlier |
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Comparative Analysis of Crack Resistance of Fiber Metal Laminates with HS2 Glass/T700 Carbon Layers for Various Stress Ratios |
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Comparative Analysis of Crack Resistance of Fiber Metal Laminates with HS2 Glass/T700 Carbon Layers for Various Stress Ratios Song, X. Li, Z.Y Shen, Y. Chen, Y.L. Zhang, J.Z. Научно-технический раздел |
| title_short |
Comparative Analysis of Crack Resistance of Fiber Metal Laminates with HS2 Glass/T700 Carbon Layers for Various Stress Ratios |
| title_full |
Comparative Analysis of Crack Resistance of Fiber Metal Laminates with HS2 Glass/T700 Carbon Layers for Various Stress Ratios |
| title_fullStr |
Comparative Analysis of Crack Resistance of Fiber Metal Laminates with HS2 Glass/T700 Carbon Layers for Various Stress Ratios |
| title_full_unstemmed |
Comparative Analysis of Crack Resistance of Fiber Metal Laminates with HS2 Glass/T700 Carbon Layers for Various Stress Ratios |
| title_sort |
comparative analysis of crack resistance of fiber metal laminates with hs2 glass/t700 carbon layers for various stress ratios |
| author |
Song, X. Li, Z.Y Shen, Y. Chen, Y.L. Zhang, J.Z. |
| author_facet |
Song, X. Li, Z.Y Shen, Y. Chen, Y.L. Zhang, J.Z. |
| topic |
Научно-технический раздел |
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Научно-технический раздел |
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2016 |
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English |
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Проблемы прочности |
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Інститут проблем міцності ім. Г.С. Писаренко НАН України |
| format |
Article |
| title_alt |
Сравнительный анализ трещиностойкости металловолоконных многослойных материалов со слоями стекла HS2 и углерода Т700 при различных коэффициентах асимметрии цикла |
| description |
Because of good crack growth resistance owe to the fibers between the aluminum layers, fiber metal laminates (FML) offer significant improvements compared to currently applied materials for aircraft structures. The crack resistance of different reinforced fibers, glass fiber, and carbon fiber, under stress ratio R = -1, 0.1, and 0.5, respectively, are analyzed through test data. The results showed significant scatter in the positive stress ratio and obvious difference between two outer aluminum layers. So, the failure criterions of metal materials specified in the test standard are unsuitable for the FMLs fatigue test, and it is a problem to determine the failure criterion according to the engineering applications. This study is an experimental investigations with respect to the FMLs crack resistance and a qualitative conclusions have been drawn from the data analysis.
|
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0556-171X |
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https://nasplib.isofts.kiev.ua/handle/123456789/173427 |
| citation_txt |
Comparative Analysis of Crack Resistance of Fiber Metal Laminates with HS2 Glass/T700 Carbon Layers for Various Stress Ratios / X. Song, Z.Y. Li, Y. Shen, Y.L. Chen, J.Z. Zhang // Проблемы прочности. — 2016. — № 1. — С. 138-144. — Бібліогр.: 9 назв. — англ. |
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UDC 539.4
Comparative Analysis of Crack Resistance of Fiber Metal Laminates with
HS2 Glass/T700 Carbon Layers for Various Stress Ratios
X. Song,
a,1
Z. Y. Li,
a
Y. Shen,
a
Y. L. Chen,
a
and J. Z. Zhang
a,b
a School of Mechanical and Power Engineering, Harbin University of Science and Technology,
Harbin, China
b Composite Research and Structure Centre, Harbin Institute of Technology, Harbin, China
1 songxin121@sina.com
Because of good crack growth resistance owe to the fibers between the aluminum layers, fiber metal
laminates (FML) offer significant improvements compared to currently applied materials for aircraft
structures. The crack resistance of different reinforced fibers, glass fiber, and carbon fiber, under
stress ratio R ��1, 0.1, and 0.5, respectively, are analyzed through test data. The results showed
significant scatter in the positive stress ratio and obvious difference between two outer aluminum
layers. So, the failure criterions of metal materials specified in the test standard are unsuitable for
the FMLs fatigue test, and it is a problem to determine the failure criterion according to the
engineering applications. This study is an experimental investigations with respect to the FMLs crack
resistance and a qualitative conclusions have been drawn from the data analysis.
Keywords: fiber metal laminates, glass fiber, carbon fiber, crack resistance, failure criterion.
Introduction. Fiber metal laminates (FML), as an interplay hybrid composite, is
composed of metal lamina and reinforced fibers that are sticked layer by layer, and then,
solidified under proper temperature and pressure [1]. FMLs has the characteristics of metal
and fiber composite materials, especially, the high resistance against crack growth.
Furthermore, with the emergence of high strength alloy and new composite materials, the
study of FMLs properties, which are composed of different new materials, have been
developed [2]. New style FMLs will be studied for remarkable properties improvements,
such as, light weight, high anti-fatigue properties and vibrations resistance, high specific
strength and specific stiffness, good toughness, and machinability, etc. [3]. These superior
properties make it very suitable for the new generation airplane structures [4]. So, the crack
resistance of new style FMLs must be studied deeply especially. There are some finite
element research to analyze mechanical and crack resistance of FMLs [5, 6]. In the earlier
studies, fracture behavior of FMLs have been simulated by FE method [7, 8]. In this paper,
the crack resistance of FMLs with different reinforced fiber, glass fiber and carbon fiber,
under stress ratio R ��1, 0.1, and 0.5, are analyzed by test data. For the reason of
significant scatter in the positive stress ratio, and obvious difference between two outer
aluminum layers, a qualitative analysis is implemented.
1. FMLs Specimen Preparation. Composed materials of FMLs specimens are, in
this paper, LY12M aluminum alloy layers with 1 mm thickness, HS2 glass fiber prepreg
layers (GFML) and T700 carbon fiber prepreg layers (CFML), and sticked by J272
middle-temperature-setting-glue. The interlayes of aluminum alloy are bonded with fiber
on the double side; outer layers of aluminum alloy are bonded on the single side. The
surface of aluminum alloy layers should be treated by the method of phosphoric acid
anodizing, according to the standard HB/Z197-91. Ambient temperature of specimen
preparation is 25 5� �C relative humidity �65%. Solidification temperature is 120–125�C,
pressure is 0.2–0.4 MPa. After solidification process, the quality of FMLs must be checked
by the nondestructive testing (NDT) technology. Figure 1 shown the NDT results of
different solidified process with ultrasonic C-scan system. Light colour area is defective
© X. SONG, Z. Y. LI, Y. SHEN, Y. L. CHEN, J. Z. ZHANG, 2016
138 ISSN 0556-171X. Ïðîáëåìû ïðî÷íîñòè, 2016, ¹ 1
region (Fig. 1a) and deep colour area is the qualified solidifying portion of FMLs (Fig. 1b).
Figure 2 showed the fractography analysis of FMLs with weak and good solidifying
quality, respectively. In the defective region, delaminating (Fig. 2a) and bubbles (Fig. 2b)
may exist. Fractography analysis of good solidifying quality is presented in Fig. 2c.
2. Fatigue Test of FMLs Specimen. Fatigue crack propagation rate test have done
according to ASTM E-647, figuration of specimen shown in Fig. 3, fatigue crack prepare
and fatigue crack propagation test implemented by PLG-100C high-cycle fatigue-testing
machine (Fig. 4), loading orientation of uniaxial constant amplitude load along the fiber
lay-up direction, stress ratios R are �1, 0.1, and 0.5, respectively. Normally, stiffness
failure criterion is used in fatigue test of composite material. During the fatigue test, with
the damage accumulation rising, resonance frequency of the system comprised by fatigue
test machine and specimen together is descending gradually. In this study, test is finished
a b
Fig. 1. Different results of FMLs with different thermo-compression solidification process [(a) have
more defects than (b)].
a b
c
Fig. 2. Fractography analysis of differnet solidifying quality: (a) delaminating in �200 magnifying;
(b) the composites bubbles in �100 magnifying; (c) fractography in �500 magnifying.
ISSN 0556-171X. Ïðîáëåìû ïðî÷íîñòè, 2016, ¹ 1 139
Comparative Analysis of Crack Resistance of Fiber Metal Laminates ...
when the first machine halt occurred which is triggered by the insufficient stiffness of
specimen. Crack propagation data are acquired by the specimen photograph after assigned
loading cycle, measured by image processing software programmed in Adobe Flash.
For the metal material specimen, test data are invalid if crack sizes measured on front
and back surfaces differ by more than 0.25B (B is the width of specimen). As a kind of
composite material, fatigue damage forms of FMLs are different from other metal. Not only
the performance are different between each layer of FMLs, but also there are residual stress
will exist in specimen after solidification and machining process [9], as a result, it makes a
significant difference between two outer metal laminates in fatigue crack growth, as shown
in Fig. 5. Nowadays, there are no reasonable ways to determine the crack length of FMLs
specimen when the large diversity occurred. In this paper, crack lengths of two outer metal
laminates, at the same time, are all recorded. Because during the test, there has emerged
through crack of one side, the other not, while the test still go on. Therefore, the numbers of
records two of outer surfaces are different. The number of specimen tested and test data
recorded for different test are listed in Table 1.
3. Fatigue Test Results Analysis. In the Paris law, da dN C K m
� ( )� , fatigue crack
growth rate da dN is the function of stress intensity factor range �K (or maximum stress
intensity factor K max when stress ratio R is negative.). The relationship is usually shown
with empirical curve fitting curves. Take logarithm on both sides of the Paris formula,
log( ) log log( ),da dN C m K� � in the double logarithmic coordinates, with a set of
log( )�K and log( ),da dN material constant C and m can be determined by the test data
linear fitting curve. Value of �K is calculated by the method specified in the ASTM
E647.
Fig. 3. LY12M aluminum alloy specimen configuration.
Fig. 4. PLG-100C high-cycle fatigue-testing machine.
140 ISSN 0556-171X. Ïðîáëåìû ïðî÷íîñòè, 2016, ¹ 1
X. Song, Z. Y. Li, Y. Shen, et al.
When the linear correlation factors, R 2, approaches 1, it means the test data exhibit a
linear correlation in present coordinate system, otherwise, it is implied that the test data
scattered broadly. It can be seen that in Table 2, R 2 of FMLs are very low, compared to
reference specimens which are made from the identical material, LY12M aluminum alloy,
so, it indicates that the FMLs test data are dispersed in a wide range.
T a b l e 1
Number of Specimes Tested and Test Data Recorded for Different Test
Stress
ratio
R
Material
CFML GFML LY12M
NST TDRF TDRB NST TDRF TDRB NST TDR
�1 8 70 107 7 61 47 9 100
0.1 5 39 67 7 66 66 7 58
0.5 7 91 96 6 39 39 9 68
Note: NST correspond to number of specimens tested; TDRF – test data recorded of front surface;
TDRB – test data recorded of back surface.
a b
c d
Fig. 5. Different fatigue crack propagation performance of two outer metal layers: front (a) and back
(b) of glass fiber reinforced metal laminates; front (c) and back (d) of carbon fiber reinforced metal
laminates.
ISSN 0556-171X. Ïðîáëåìû ïðî÷íîñòè, 2016, ¹ 1 141
Comparative Analysis of Crack Resistance of Fiber Metal Laminates ...
A qualitative analysis of fatigue crack growth tendency of different fiber reinforced
FMLs has been done. In Fig. 6, under different stress ratio R, LY12M specimen test results
are presented, while the FMLs fitting curves are derived from arithmetic average of fatigue
crack growth rate of FMLs specimen front and back surface. So, there is a big deviation in
this simplified method.
From Fig. 6a, it can be seen that in the initial stage of crack propagation,
da dN
�10 5 mm/cycle, because of more defects in FMLs than that in identical material
specimen, the effect of compressive stress promote damage increasingly more in composites
T a b l e 2
Correlation Factor R
2 for Different Test Data
Stress
ratio
R
Material
CFML GFML LY12M
Front Back Front Back
�1 0.13 0.07 0.45 0.17 0.80
0.1 0.47 0.44 0.35 0.54 0.87
0.5 0.26 0.36 0.59 0.44 0.86
a b
c
Fig. 6. Comparison of different fatigue crack propagation performance under different stress ratio R.
Stress intensity factor range �K , MPa m
Stress intensity factor range �K , MPa m
Stress intensity factor range �K , MPa mF
at
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142 ISSN 0556-171X. Ïðîáëåìû ïðî÷íîñòè, 2016, ¹ 1
X. Song, Z. Y. Li, Y. Shen, et al.
than in metal, consequently, da dN of FMLs are higher than which of LY12M specimen.
However, in high crack growth rate region, da dN �
�10 4 mm/cycle, because of the bridge
linkage of reinforced fiber, da dN of FMLs are lower than which of LY12M specimen.
This feature is also shown in the case of positive R, Fig. 6b and 6c. With the stress range
decreasing, as listed in Table 3, different tension strength of components, � b of T700 is
about 4900 MPa and of HS2 is about 4278 MPa, effects on crack growth differently. When
R � 0.5, T700 carbon fiber FMLs specimen have lowest crack growth rate, LY12M
specimen have fastest rate, accordingly, carbon fiber FMLs specimen have the largest
tension strength, and LY12M specimen have least strength.
4. Concluding Remarks. It is unreasonable in FMLs fatigue test when the strength
failure criterions are used as identical metal material test or nonmetal composites test.
Because the defects and residual stress are inevitable after specimen preparation, and
fatigue crack growth behavior between two outer metal laminates of FMLs specimen is
different, it is proper to record all these two fatigue data and analyze respectively. It is
suitable to determine the test end condition according to stiffness failure criterion,that is test
finished when the first machine halt occurred because of the insufficient stiffness of
specimen.
In the select-reinforced materials study, tension strength of different reinforced fiber
affect fatigue cracks propagation rate for the main reason of bridge linkage phenomenon
around crack tip zone, especially, in the case of small stress amplitude range applied. For
fiber reinforced composites specimen the compressive stress will promote crack propagation,
so, when stress ratio R is negative, compressive stress in fatigue loading has more effect
on da dN of FMLs specimens in the initial stage of crack propagation.
Acknowledgments. The work was supported by the National Nature Science
Foundation of China under the Contract No. 51271067.
1. X. R. Wu and Y. J. Guo, “Fatigue life prediction of fiber reinforced metal laminates
under variable amplitude loading,” Eng. Sci., 1, No. 3, 36–39 (1999).
2. M. Boscolo, G. Allegri, and X. Zhang, “Design and modeling of selective
reinforcements for integral aircraft structure,” AIAA J., 46, No. 9, 2323–2331 (2008).
3. J. Bienias, B. Surowska, and P. Jakubczak, “The comparison of low velocity impact
resistance of aluminum/carbon and glass fiber metal laminates,” Polym. Compos.,
Doi: 10.1002/pc.23266 (2014).
4. J. F. Laliberté, C. Poon, P. V. Straznicky, and A. Fahr, “Applications of fiber-metal
laminates,” Polym. Compos., 21, No. 4, 558–567 (2000).
5. M. Grassi and X. Zhang, “Finite element analyses of mode I interlaminar delamination
in z-fibre reinforced composite laminates,” Compos. Sci. Technol., 63, 1815–1832
(2003).
T a b l e 3
Test Load for Different Stress Ratio
Stress
ratio
R
Material
CFML GFML LY12M
Pm , kN �P, kN Pm , kN �P, kN Pm , kN �P, kN
0.1 0.47 0.44 0.35 0.54 3.51 2.87
0.5 0.26 0.36 0.59 0.44 7.50 2.50
ISSN 0556-171X. Ïðîáëåìû ïðî÷íîñòè, 2016, ¹ 1 143
Comparative Analysis of Crack Resistance of Fiber Metal Laminates ...
6. Y.-Q. Liao, J.-H. Su, and S.-L. Ke, “Application of ANSYS in composite simulation
analyses,” Fiber Compos., 23, No. 4, 63–66 (2006).
7. X. Song and J. Z. Zhang, “Analysis of a finite element model of 2-D elastic-plastic
crack,” J. Harbin Univ. Sci. Tech., 13, No. 5, 9–13 (2008).
8. X. Song, Z. Liu, and J. Z. Zhang, “Simulation study of fracture behavior in a FMLs
specimen by 3D elastic-plastic finite element model,” Polym. Polym. Compos., 19,
No. 2-3, 209–212 (2011).
9. G. T. Zhang, W. G. Chen, and B. Yang, “Testing research on mechanical properties of
T700 carbon fiber/epoxy composites,” Fiber Compos., 49, No. 2, 49–52 (2009).
Received 03. 08. 2015
144 ISSN 0556-171X. Ïðîáëåìû ïðî÷íîñòè, 2016, ¹ 1
X. Song, Z. Y. Li, Y. Shen, et al.
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/NLD (Gebruik deze instellingen om Adobe PDF-documenten te maken die zijn geoptimaliseerd voor prepress-afdrukken van hoge kwaliteit. De gemaakte PDF-documenten kunnen worden geopend met Acrobat en Adobe Reader 5.0 en hoger.)
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/ENU (Use these settings to create Adobe PDF documents best suited for high-quality prepress printing. Created PDF documents can be opened with Acrobat and Adobe Reader 5.0 and later.)
>>
/Namespace [
(Adobe)
(Common)
(1.0)
]
/OtherNamespaces [
<<
/AsReaderSpreads false
/CropImagesToFrames true
/ErrorControl /WarnAndContinue
/FlattenerIgnoreSpreadOverrides false
/IncludeGuidesGrids false
/IncludeNonPrinting false
/IncludeSlug false
/Namespace [
(Adobe)
(InDesign)
(4.0)
]
/OmitPlacedBitmaps false
/OmitPlacedEPS false
/OmitPlacedPDF false
/SimulateOverprint /Legacy
>>
<<
/AddBleedMarks false
/AddColorBars false
/AddCropMarks false
/AddPageInfo false
/AddRegMarks false
/ConvertColors /ConvertToCMYK
/DestinationProfileName ()
/DestinationProfileSelector /DocumentCMYK
/Downsample16BitImages true
/FlattenerPreset <<
/PresetSelector /MediumResolution
>>
/FormElements false
/GenerateStructure false
/IncludeBookmarks false
/IncludeHyperlinks false
/IncludeInteractive false
/IncludeLayers false
/IncludeProfiles false
/MultimediaHandling /UseObjectSettings
/Namespace [
(Adobe)
(CreativeSuite)
(2.0)
]
/PDFXOutputIntentProfileSelector /DocumentCMYK
/PreserveEditing true
/UntaggedCMYKHandling /LeaveUntagged
/UntaggedRGBHandling /UseDocumentProfile
/UseDocumentBleed false
>>
]
>> setdistillerparams
<<
/HWResolution [2400 2400]
/PageSize [612.000 792.000]
>> setpagedevice
|