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Desionation: D303e/D30seM - 14
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,NTERNAfIONAL
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Standard Test Method for
Tensile Properties of Polymer Matrix Composite Materialsl
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thc tlxecl clesignation D3019/D30i9M: the nurnbcr immediately tirlloling the designrtion inclicaLes the
yelr of origiral adoption or, in the case of revisiorr. thc year of last re\ision. A number in parentheses indicares tlre )ear of last
reapproval. A superscript epsilon (r:) irdicates an eclitorirl change sincc the last rerisiol or reapproval.
o
n.
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Tlris stancl*'d is issued
rLnder
This sttuulttnl lws been upproted./or u.sc h ogtttti<'s nl tlu' U.S. Deportruot o1'DeJbn,sc.
1.
erlies and Equilibrium Conditioning of Polymer Matrix
Scope
UCornposite Materials
HO
VE-l Practices for Folce Verification of Testing Machines
E6 Terminology Relating to Methods of Mechanical Testing
1a
E83 Practice fbr Verilication and Classi{ication of Exten>Y
someter Systerns
F),
El l1 Test Method for Young's Modulus, Tangent Modulus,
and Chord Modulus
E 121 Practice for Calculating Sarnple Size to Estimate, With tsE
Specified Precision, the Average for a Characteristic of a
1.1 This test rnethod determines the in-plane tensile properties of polyrner matrix composite matedals reinforced by
high-rlodulus fibers. The composite material forms are limited
to continuous fiber or discontinuous fiber-reintbrced composites in which the laminate is balanced and symntelric with
respect to the test direttion.
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1.2 The values stated in either SI units or inch-pound units
are to be regarded separately as standard. Within the text, the
inch-pound units are shown in brackets. The values stated in
each systenr are nol exact equivalents; therefore. each system
must be used independently ol the other. Combining values
tiom the two systems may result in noncontormance with the
FX
ASTM Test Methods
(/!F
I Test Methods fbr Perlbnnance Characteristics of Me- mo
E25
tallic Bonded Resistance Strain
Gauges
F=
9;
1D
Terminology Relating to Quality and Statistics
Practice for Verification of Testing Frame and Speci- :lo
men Alignment Under Tensile and Compressive Axial
HU
Force Application
>C
E1237 Guide for Installing Bonded Resistance Strain Gages ? (t)
E.156
E
priute sofett tttrl ltealtlt practices cmd detennine the applical,i lit.t t'.1 ti,?rtldtt)t-\'littrittttiotts prior t,t tt.sc.
2. Referenced Documents
l0l2
as
;P
2 1 ASTM Stuntlurds:)
D792 Test Methods lor Density and Specific Gravity (Rela-
3. Terminology
*g
E
3.1 Defnitions-Terminology D3878 defines terms relating
A='
to high-modulus fibers and their composites. Terminology >=.
D883 defines terms relating to plastics. Tenninology E6 defines 2a
terrns relating to mechanical testing. Terminology E.l-56 and 6):
ob
Praclice E 177 define terrns relating to statistics. In the event of
a conflict between terrrs, Terminology D3878 shall have >o
3E
precedence over the other standards.
>J
(aE
iUl
3.2 Definitions of Terms SpeciJic to This Standard:
tive Density) ol' Plastics by Displacement
D88-3 Terminology Relating to Plastics
D258'+ Test Method fbr Ignition Loss of Cured Reinforced
Resins
D213,1Test Methods fbr Void Content of Reinforced Plastics
D3l7l Test Methods for Constituent Content of Cornposite
Materials
D3878 Terrninology for Composite Materials
D5229/D5229N{ Test Method for Moisture Absorption Prop-
>z
3.2.1 Note-If the term represents a physical quantity, its zd
o-'
ts(t
analytical dimensions are stated imrnediately fbllowing the @o
{<
(or
fbrm,
using
in
fundamental
dimension
letter
symbol)
terrn
vD
the following ASTM standard symbology for fundamental
dimensions, shown within square brackets: lMl for mass, [L]
=
o
o
ibr length, [I] fbr tirne, [@] fbr therrnodynamic temperalure,
9,
and I nril for nondimensional quantities. Use of these symbols
is restricted to analytical dimensions when used with square
o
'This test rnethod is Ltnder the juriscliction ol ASTM Committee D30 on
Conrposite \'luterids and is the direct responsibility of Subcommittee D30.0:l on
Lamina ancl LiLnrinate Tcst Methods.
CLLrrent edition approved May 15. 201:1. Publishecl NIay 201;1. Originally
approred in 1971. Last prtvious eclition approved in 2008 as D3039-08. DOI:
-520/D-1039_D30.19M-
s9
>9Method for Poisson's Ratio at Room Temperature ai
El77 Practice tbr Use of the Tenns Precision and Bias in rni
E 132 Test
1.3 This stutdard tloes not purport to atltlress all oJ the
sufett trnrcems, if any, ossociated vvith its use. It is the
respottsibilin' of the user of this standard to estttblish oppro-
I
fo
Lot or Process
standard.
10.
=o
torE
1,1.
: fjor reterenced ASTN'I standards. visit thc ASTM lvebsite, lvww.astn].org. or
contact ASTM C'ustomer Sen,ice at service@rashn.org. For Anntutl Book oJ ASTill
brackets, as the symbols may have other deijnitions when used
without the brackets.
Starulartl.s volurne infbrmation. refcr to the stanrlarcl's Docurncnt Summary page on
the ASTN{ rebsite.
3
o
Copyright O ASTM lnternational, 100 Barr Harbor Drive. PO Box C700, West Conshoh@ken. PA 19428'2959 United States
I
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([Jp oeoss/D3o3eM 3.2.2 nornirnl ralue, n-a r,,alue. existing in narne onlv,
assigned to a measurable properly for the purpose of convenienl designation. Tolerances r.na) be applied to a nominal
l'alue to define an acceptable range lor the property.
3.2.3 transition regiort, rr-a sLrain region of a stless-str.rin
or strain-strain curve ovel rvhich a significant cl-range in the
slope of the curve occurs 'nl,ithin a small strain range.
3.2.1 trctnsitiott stroitt, ttl'ttt\i.i"t, Intl], n-the strain value at
the mid range ol the transitiort re_tion betr,veen the two
essentially linear portions of a bilinear stress-straiu oI srrainstrain cun,e.
3.2.1.1 Discusslon-Many {ilamentary composite materials
shorv essentially bilinear behavior during force application,
such as seen in plots of either longitLrdinal stress versus
longitudinal slrain or transvel'se slrain versus long longitudinal
strain. There are varying physical reasons lor the existence of
a lransition region. Common examples include: matrix cracking under tensile fbrce application and ply delantination.
3.3 .S.r'nrbols:
A-minimum cross-sectional area of a coupoll.
B_,.-percent bending for a uniaxial coupon of rectangular
cross section about -y axis ol' the specirnen (about the narrow
direction ).
B.--percent bending tor a uniaxial coupon ol rectangular
cross section about i axis of the specimen (about the wide
direction).
CV-coeflrcient of variation statistic of a sample populalion
for a given property (in percent).
E-modulus of elasticity in the test direction.
in the test direction.
prrr-gl1imn1s shear strength in the test direction.
f'I1-1111im31s tensile strength
Ir-coupon
Lr-extensometer gage length.
f,,,,,-minimum required bonded tab length.
n-number of coupons per sarnple population.
P-fbrce carried by test coupon.
P/-fbrce carried by test coupon at failure.
quality assurance, and structural design and analysis. Factors
that influence the lensile response and should therefore be
reported include the fbllowing: ntaterial, nterhods of ntaterial !
preparation and lay-up. specimen stackiltg sequence, specimen ;{
preparalion, specirnen conditioning, environrnent of testing, 0
F
specimen alignment and glipping, speed of tesring, rinle lr 6)
temperature, voicl content, and volume percent reinforcement. z
Properties, in the test direction, which may be obtained from
F
this test method include the fbllowing:
5.1.1 Ultimate tensile strength,
5.l.l
Ultinrate tensile srltin.
5.1.3 Tensile chord modulus of elasticity,
5.1.4 Poisson's ratio. and
5.
I
.5 Transition stlain.
6.1 Material
z
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z
m
a
!
6. Interferences
rn
F
Preltartttiort-Poor material fab- (,
m
control of fiber alignment, and v
cutd Specintetr
rication practices, lack of
damage induced by improper colrpon machinins are known
causes of high material data scatter in composites.
f
sarnple
population for a given property.
,r--mean ot' average (estimate of mean) of a sample population fbr a given property.
d-extensional di splacement.
e general symbol fbr strain. whether normal strain or shear
strain.
e-indicated normal strain fiom slrain transducer or extensometer.
stress.
o
I
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Test Method
4.1 A thin flat strip of marerial having a constant rectangular
cross section is mounted in the grips of a ntechanical lesting
machine and monotonically loaded in tension wl.rile recording
the force. The ultirnate strength of the material can
be
.tI
I
x
elasticity determination. Every effor1 should be rnade to elirninate excess bending frorn the test system. Bending may occur
z
as a result of misaligned grips or li'om specin'rens themselves if 6)
improperly installed in the grips or out-ol-tolerance caused by o
o
poor specimen preparation. If there is any doubt as to the
alignment inherent in a given test rnachine, then the alignrnent
=
should be cl.recked as discussed in 7.2.5.
tn
6.4 Edge Effects
in Angle Ply Lcuninate.i-Premature failure
and lower stilfnesses are observed as a result ol edge softening
-t
z,
ol
in laminales containing offaxis plies. Because of this, the lrl
6l
strength and modulus fbr angle ply laminales can be drastically \fl
underestimated. For quasi-isotropic laminates containing significant 0' plies. the efl-ect is nor as significant.
7. Apparatus
r,-Poisson's ratio.
4. Summary of
5. Significance and Use
5.1 This test nrethod is designecl lo produce tensile proper.ty
data for rnaterial specifications. research and developrnent,
6.3 System Alignnrcnt-Excessive bending will cause premature ailure, as well as highly inaccurate modulus ol
p/r/"t-1111i11um fbrce carried by test coupon before failure.
s,, ,-standard deviation statislic of a sample population fbr
a given property.
x,-coupon width.
o-nonnal
detelrninecl fionr the nta.riutum fbrce carried belble failur-e. Il
the coupon strain is monitored rvith strain ol displacernent
tlansducers then the stress-strain l'esponse ol' tl're malerial can
be deternrined, from rvliich the ultirnate tensile strain, tensile
modulus ol elasticity. Poisson's ratio. and transition strain can
be derived.
6.2 Gripping-A high percentage ol grip-induced failures, F
o
especially when cornbined with high rnaterial data scatter, is an o
indicator of specimen gripping problems. Specimen grippin-q D
3
methods are discussed l'urther in 1.2.1,8.2, and 11.5.
thickness.
-rr-test result for an individual coupon l'rom the
14
J.l Mir:rcnrcters and Calipers-A micrometer with a 4 to 7
mrn [0.16 to 0.28 inl nominal diameter ball inter{ace shall be
used to measure the specimen thickness rvhen at least one
surfhce is irregular (such as the bag-side of a laminate). A
rnicrometer with a 4 to 7 mm [0. 16 to 0.28 in.l nominal
dianreter ball interface or with a flat anvil intertace shall be
(NJp osose/D3ossM
to measule the specimen thickness rvhen both sutfaces are
smooth (such as tooled surlhces). A rnicrometer or caliper, with
a llat anvil interface. shall be used to measttre the width of the
specimen. The accuracy of lhe instruments shall be suitable for
reading to within I 7a of the sample dimensions. For typical
specimen geometries, an instrumetrt with an accuracy of
-f0.0025 mm [-10.0001 in.l is adequate fbr thickness
rneasurement, rvhile an instrument with an accuracy of +0.025
used
mm [+0.001 in.l is aclequate for rvidth nteasurement.
7.2 Testirrg Macltine-The testing machine shall be in conformance with Practices 8,1 and shall satisty the lbllowing
requirements:
7.2.1 Testing Machine Heads-The testing machine shall
have both an essenlially stationary head and a movable head.
1.2.2 Drive Meclrunisrn--:lhe testing machine drive mecha-
nism shall be capable of imparting to the rnovable head a
controlled velocity with respect to the stationary head. The
velocity of the movable head shall be capable of being
regulated as specifled
in
I 1.3.
I .2.3 Force Indicator --The testing machine force-sensing
device shall be capable of indicating the total force being
carried by the test specimen. This device shall be essentially
fiee from inertia lag at the specified rate of testing and shall
indicate the force with an accuracy over the force range(s) of
interest of within + I 7c of the indicated value. The fbrce
range(s) oi interest may be fairly low for rnodulus evaluation,
much higher for strength evaluation, or both, as required.
Nore l - {btaining precision tbrce data over a large range of interest in
the same test. such as *hen both elastic modulus and ultimate f-otce are
bein-g determined. place extreme requitements on the load cell and its
calibration. For some equipment, a special calibration may be required.
For some combinations of material and load cell, simultuneous precision
measurement of both elastic modulus and ultimate strength may not be
possible and rneasurement of modulus and strength may have to be
performed in separate tests using a different load cell range for each test.
7.2.4 Grips-Each head of the testing machine shall carry
one grip fbr holdin-e the iest specimen so that the direction of
force applied to the specimen is coincident with the longitudinal axis of the specin.ren. The grips shall apply suffrcient lateral
pressure to prevent slippage between the grip face and the
coupon. If tabs are used the grips should be long enough that
they overhang the beveled portion of the tab by approximately
10 to 15 mm [0.5 in.].It is highly desirable to use grips that are
-
14
OJ
n
7.2.5.1 A rectangular alignment coupon. pref'erably sirnilar P
in size and stilTness to the test specimen of interest. is I
instrurnented with a minimum of three longitudinal strain A
gages of similtrr type, two on the front lace across the width
and one on the back lace ol the specirnen, as shown in Fig. 1. f=
Any difference in indicated strain between these gages during f
loading provides a rleasure of the amount ol bending in the
thicknesi plane (8,,) and rviclth plane (8.) of the coup-on. The +
=
strain gage location should normally be located in tlre rniddle :
of the coupon gage section (if moclulus determinaiion is a 6 3concern), near a grip (if prernature grip failures are a problem ). A E
or any combination of these areas.
+o
7 .2.5.2 When evaluating system alignment, it is advisable to C S
perform the alignment check with the same coupon inserted in li I
each of the fbur possible installation permutations (described I $
relative
to the initial position): initial (top-front lacing fl 3
f. I !
observer), rotated back to front only (top back facing obselr, er
lotated end for end only (bottom liont facing observer), and f j
rotated both front to back and end to end (bottorn back facing i j.
observer). These fbur dala sets provide an indication
"f :0
whether the bending is due to the system itself or to tolerunce ! {
in the alignment check coupon or gaging.
EI
1 .2.5.3 The zero strain point may be taken either before f 6
gripping or after gripping. The strain response of the alignment gl g
coupon is subsequently monitored during the gripping pro..sr. | 3
the tensile loading process, or both. Eq I and Eq I use these fi 3
indicated strains to calculate the ratio of the percentage of fl H
bencting strain to average extensional strain for each bending [ fi
plane of the alignment coupon. Plotting percent bending uersus fi i
axial average strain is useful in understanding trends in the ] #
bending behavior of the system
pE
1.2.5.4 Problems with failures during gripping would U. 5 3
reason to examine bending strains during the gripping process
I3c
in the location near the grip. Concem over modulus data scatter b E
would be reason to evaluate bending strains over the modulus I B
evaluation force range for the typical transducer location. 1,.
Excessive failures near the grips would be reason to evaluate x $
bending strains near the grip at high loading levels. While ,h"
^:.
>1.
2a
a=
6):
-lwr-
oil
rotationally self-aligning to minimize bending stresses in the
S
S
SGI
coupon.
G
G
2
SG2
Nole 2 {rip surfaces that are lightly serrated, approximately
1
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OEE
&
iUl
2z
B
o-.
ts(r
I
serration/mm 125 ser-ralions/in.l, have been tound satisfactory lbr use in
wedge-action grips when kept clean and sharp; coarse setutions tnal'
produce grip-induced failu'es in untabbed coupons. Smooth gripping
surfaces have been used successfully with either hydraulic grips or an
emery cloth intertace, or both.
0,
00
\l<
vil
5:
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J.2.5 St'stem Alignntent-Poor system alignment can be a
major contributor to premature failure, to elastic property data
scatter, or both. Practice El0l2 describes bending evaluation
guidelines and describes potential sources of misalignment
during tensile testing. In addition to Practice E1012, the degree
of bending in a tensile system can also be evaluated using the
following related procedure. Specimen bending is considered
separately
in
I 1.6.1.
9.
w18
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3
(rYP 2PL)
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FlG.
1
Front
Sidc
Gage Locations for System Alignment Check Coupon
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f.
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,{$Jp osose/D3o3eM
rutaxirrr-rr.t-t
acli'isable arlloLlnt ()l s-\'stenl rtrisalignntent is urete-
rial and location clependent, goocl testing practice is generall-y
able to limit percent bending to a ranse ol'3 to 5 Ct at nrodelate
strain levels (> 1000 pre ). A sl,stenr shorving excessile benclil-s
lirr the given application should be reacljusted or niorti{iecl.
l, - !-r-jti.:
-:
)/l lt:.
x
r:,)
'
11,,,
tog
100
(t)
rlr
"
rvhele:
B,
-
B.
-
t",, t:r, dtttl
t,.i
=
percent bencling about syslem r. axis (abor.rt
the narrorv plane), as calculated by Eq 1. 9i;
perceut bending aboLtl svstent : a.xis (about
the wicle plane). as calculated by I:c1 l. 9L:
indicated longitudinal srraills displayed by
1,2. and 3, respectively, o1'Fir. l, pe;
Ga_ses
c,,,"
Nor
=
L,
and
(({rr + t'..112+ t.112
3-'txperimental
error- rraY be introduced bY sorLr-ces such as poor'
st'stem alignnrent. specimen preparalion and strain gage precision ancl
calibration. These sorLrces of error r.nay result in an uverale calcr"rlated
strain (r:,,.) of 0. car:sing B, and B- (Eq I and l:tg 1) to approach infinity
as the averase calculalecl strain is the denorninator. To rninirnize the
potential fbr this occurrence during svstem alignn.rent evaluation. it is
recomrrended that lblce be applied to the alignntent coupon until all three
strain gages measure positive strain of no less than -500 prs u,ilh an r:,,. of
no less than 1000 pu;. ll these conditions can not be met. the tesl
configulation should be atljusted prior to perfirrrring futlher systenl
aliErnrent evaluation.
7 .3 Strain-lndi<'utirtg Det,icc-Folce-strain clata, ii required,
shall be determined by nreans of either a strain transducer or an
extensolreter. Attachment of the strain-indicating device to the
coupou shall not cause danrage to the specinteu surfhce. If
Poisson's ratio is to be determined. the specimen shalt be
instrunrentecl Io measure strain in both longitudinal and lateral
directions. If the modulus of elaslicity is to be deterntined, the
longitudinal strain should be sinrultaneously measulecl on
opposite laces of the specinren to allow lbr a correction as o
result ol'any bending of the specimen (see ll.(t lor llrther
guidance).
7
.3.1 Bondctl Rcsisttutce Stroin Gagc Sclecrron-Strain
gage selection is a compromise based on the i-Vpe ol- material.
_sage Iength ol'6 mrn [0.25 in.] is recontnrended for
nrost matel'ials. Active ga-ce lengths should not be less than 3
An active
nrm
[0.
125 in.].3 Gage calibration cerlilicalion shall corlply
rvith Test Methods El5l. When testin_u rvoven l'abric laminates,
gage selectiou should consider the use ol'an aclive gage length
that is at least as great as lhe characteristic repeatin-c unit ol'the
weave. Sorne guidelines on lhe use o1- strain gages on con'lposites fbllor.v. A general rel'ercnce on the subject is Tuttle and
Brinson.r
7.3.1.1 Sudace preparation of llber-r'einlorced compt'rsites
in accordance rvith Practice Ir1ll7 can penetl'ate the ntatrix
'A tr,picrl gagc uould harc a 0.25-in. actire sage Icngth. i5t) (l r.\i'tiutcc. J
strnin rrting of l',i or bett.'r. ancl the ilppropriate c.nrirrtnntc'ntrl rc\i\tiulcd ind
thcrrnrl coefticient.
''futtle. \'1. tl. iurd l.lrinson. H. I-.. "Resistilnc. Ftril Strtin-G roe-li'chnirlotr ii'
Applied to C'onrposite NIrLterirls." E.rparitnefiol Lleclrurtir'.s. Vrl l-{. \o. I. \lrrch
l98J: pp.5,1 65: crratr notc'd in Vtrl 26. \o. l. Junc 1936. pp. l5-l l5-1.
-
14
rnaterial ilutl cause darnage
Lo thc reinliircin_r libcrs lesulting in
iurproper coupon lailures. Reinlbrcing llbers should not [rt,
exposed or dalnaced durinc the suLfnce prepar.rtion process.
The strrrin cage uanufiictul'er shoulcl be consultecl regarcling
surl'ace preparatiorl _suidelines anri recon.rnrended bonclinc
agents tbr contposites pendin_e the clevelclprnent of a set of
staudal'd practices fbl strain gage install.ttion sulface prepal'ation ol' hber'-reinlbrcecl contposite rnatel'ials.
7.3.1 .2 Consicleralion shoLrld be given to rhe selection ttf'
gtges hal'ing larser resistances to reduce healing elI'ects on c
lorv-conductir itv rnaterials. Rc.sistances ol 350 O trr higher ure l
preferred. Aclclitional consicleration should bc giren to the ure !
ol' the mininrurn possible -sage excitation vohage eonsislr-nt t
with the ctesired accuracy ( I to 2 V is recomrnencled) to reduce J
lirrther the por,ver consulned by the gage. Heating ol the !
coupon by the eage rnay afl'ect the perl'orrnance of the material
clirectly, or it rnay aff'ect the indicated strain as a resulr ol a
difl'erence betrveen the ga-ue temperalure cornpensurion lacttlr
and the coefllcient ol' thermal expansion ol- llre coLrpor", ,ru,"ri
il
!
i
i
al.
7.3.1 .3 Consideration o1'some fbrrn of teniperature coltlpensation is recommended, even when testiltg at stancllrcl labora- E
=
tory atrnosphere. TemperatLlre cornpensation is requirecl when fr
testin-q in nonambient ternperature
1.3.1
envitontnenis.
.4 Considelation sl.rould be given Lo the transvelse
I
I
sensitivity ol the seleclecl strain gage. The strain gage manu- H
facturer should be consLrlted fbr reconrmenclations on tl'ans- E
verse sensitivity con'ections ancl efl'ects on cornposites. This is f,
particularly irriportant fbl a transversely rnountecl gage ,re.l t,., !
deterrnine Poisson's ratio. as discussed in Note ll
I
J.3.2 E.rtensotneter.s-For lnost purposes, the extensonleter !
ga-ee length shoulil be in the lan,ee of t0 to 50 mm t0.5 to 2.t) f;
in.l. Extensorneters shall satisl)i, at a minimum, Praclice E8f ,
P
Class B- l requirernents lor the strain range of interest and shall D
be calibratecl clver that strain range in acCordance with Practice ]
Eiii. For extremely stiff rnaterials, or fbr measurement o1' T
transverse strains, the tixed error allowed by Class B- t x
extensonreters nray be signilicant, in which case Class A
extensorreters should be consiclerecl. The extensonreter shall be B
essentially ll'ee of inertia lag at the speciliecl speed ol testing. fr
and the weight of the extensorneler should noi induce bending
$
strains greater than those allorved in 6..1.
Norc
4-lt
i
is generallv less dillicult to perti)nn \lrrin calibration
of longer gaue length as lesi precirion in displacenrenf
requiretl ol the exlensorneter calibration
extensometers
clerice.
on 3
is fi
il
7.1 Conditiorting ()ltuntber'-When conditionin.q materiuls Z
at nonlaborillory environmeltts. a tetlperature/i'lporIevel- 3
controllecl erlvil'onntenlal conclitioning charnber is requiled thar S
shall be capable ol' ntaintaining the requirecl ternperature to within +3'C [*5"F] ancl the required relatii,e vapor level to
u,ithin +3 7r, Chamber conclitions shall be ntonitorecl eitlrer on
an autolnated continuous basis o| on a r.nanual basis at resular
intervals.
7.5 Enyixtuntental Test Cluttnbcr-An environrnental
test
chamber is lecluired for test environr.nenls other than ambient
testing laboratory conditions. This chantbel shall be capatrle ol
lraintaining the gage section
of the test specirnen at the
recluirecl test environrnent during the n.rechanical test.
$p osose/DsoseM - 14
8. Sampling and Test Specimens
8.1 Santpling-Test at least five
specimens per test condition unless valicl results can be gair.red through the use of fewer
specimens, such as in the case ol a designed experiment. For
statistically significant data, the proceclures outlined in Practice
E,122 should be consulted. Report the rnethod of sampling.
Nore 5-lf specimens are to under-eo environmental conditioning to
equilibrium. and are of such type or geometry that the rveight change of
the material cannot be properly mezrsured by rveighint the specirnen itself
(such as a tabbed mechanical coupon). then use antxher traveler coupon of
the same nominal thickness afid appropriate size (but without tabs) Io
detemine uhen equilibrium has been reached for- the specimens being
conditioned.
8.2 Gaontetrt'-Design of mechanical test coupons, especially those using end tabs, remaitrs to a large extent an art
rather than a science, rvith no industry consensus on how to
approach the engineering of the gripping interface. Each major
composite testing labortrtory has developed gripping methods
for the specilic material systems and environments commonly
encountered within that laboratory. Cornparison of these methods shor.vs them to differ widely, making it extremely difltcult
10 recommend a universally useful approach or set of approaches. Because of this dilficulty, definition of the geometry
of the test coupoll is broken down into the following three
levels, which are discussed further in each appropriate section:
Purpose
Degree of Geometry Definition
l\ilandatory Shape and Tolerances
8.2.1 General Requirements
8.2.2 SpecificRecommendations NonmandatorySuggestedDimensions
Nonmandatory Typical Practices
8.2.3 Detailed Examples
8.2.1 General Requirenrcrts :
.l
Shape, Dintensiorts, and Tolerances-The complete
requirements for specimetr shape, dimensions, and
tolerances is shown in Table l.
8.2.1 .2 IJse of Tabs-Tabs are not required. The key factor
in the selection of specimen tolerances and gripping methods is
the successful introduction of force into the specimen and the
prevention of premature failure as a result of a signiflcant
discontinuity. Therefore, determine the need to use tabs, and
specilication of the major tab design parameters, by the end
result: acceptable failure mode and location. If acceptable
8.2.1
list of
TABLE 1 Tensile Specimen Geometry Requirements
Bequirement
Parameter
Coupon Requirements:
shape
minimum length
specimen width
specimen width tolerance
specimen thickness
specimen thickness tolerance
specimen flatness
Tab Requirements (if used):
tab material
fiber orientation (composite tabs)
tab thickness
tab thickness varialion between
tabs
tab bevel angle
tab step at bevel to specimen
A
constant rectangular cross-section
gripping + 2 times width + gage length
as neededA
11 % of width
as needed
14 % of thickness
flat with light {inger pressure
as needed
as needed
as needed
a1 % tab thickness
5 to 90", inclusive
feathered without damaging specimen
See 8.2.2 or Table 2 for recommendations
!,
failure modes occur rvith reasonable fiequency, then tl.rere is
reason to change a given gripping rnethcld.
no P
o
8.2.2 Spet:ifit Recontnrt:nclrttiotts:
E
8.2.2.lWdttl'Thickness,ttnc!Length-Selectthespecimen<
ancl
fibers
bulk ;
5
wiclth and thickness to promote failure in the gage section
q
assure that the specimen contains a sull'icient nuirb.. of
in the cross section to be statistically representative of the
material. The specinren length should normally be substantially 3'
longer than the minirnum requirement
to minimize bending
$
stresses caused by minor grip eccenlricities. Keep the gage
section as far fiom the grips as reasonably possible arrd prol'ide
a significant amount of material under stress and theretble
ri
fr b
I
produce a more statistically significant result. The mininrum f {
requirernents for specimen design shown in Tuble I ale by o ]
themselves insufficient to create a properly dimensioned and [ fl
toleranced coupon drarving. Therefore, recommendations on Q $
other irnportant dimensions are proviclerl for typical material E E
confrgurations in Table 2. These -eeometries have been lound I p
by a number of testing laboratories to produce acceprable f, i'
failure modes on a wide variety of rnalerial systems, but use of rr l"
then'r cloes not guarantee success lbr every existing o. trtur" fr f
marerial
system.
9n
8.2.2.2 Gripping/tlse oJ Tabs-There are many mrteri.l fi g
configurations, such as multidirectional laminates. fabric-based t d
rnaterials, clr ranclomly reinforcecl sheet-molding compounds, 6 d
which can be successfully tested without tabs. However', tabs I i
are strongly recommendecl when testing unic'lilectional materi- fi !
als (or strongly unidirectionally dominated laminates.l to tailure ! I
in the fiber direction. Tabs may also be required when testing I L
unidirectional rnaterials in the matrix direction to p..u"ri I f,
gripping darnage.
i E
8.2.2.3 Tab Geontetrt-Recommendations on important di- H H
mensions are provided lor typical material conflgurations in f;
Table 2. These dimensions have been found by a number of 3 $
testing laboratories to produce acceptable failure modes on a f, '
wide variety of material systems, but use of thern does not j< 8
guarantee success for every existing or future material system. €
The selection of a tab configuration that can successfully ! i'
produce a gage section tensile failure is dependent upon the 2 6.
couporl material, coupon ply orientation, and the type of grips [i g
being used. When pressure-operated nonwedge grips are ur.d $ I
with care, squzred-off 90" tabs have been used successfully. > o
Wedge-operated grips have been used most successlully wittr f, I
tabs having low bevel angles (7 to 10") and a leathered smooth 4 E
transition into the .oupor. For alignment purposes, l, ir
! I
essential that the tabs be of matched tl.rickness.
8.2.2.4 Friction Tabs-Tabs need not always be bondecl tu S S
the material under test ro be eff-ective in introducing the fbrce J $
into the specimen. Friction tabs, essentially nonbonded tabs :f
held in place by the pressure of the grip, and ol'ten used with d
emery cloth or some other light abra.sive between the tab and 9
the coupon, have been successfully used in some
applications. 3
In specific cases, lightly serrated wedge grips (see Note l) have
been successfully used with only emery cloth as the interlace
between the grip and the coupon. However, the abrasive used
g
i
5
Sorne f
in this i
must be able to withstand significant compressive fbrces.
types
of
ernery cloth have been fbund ineffective
application because of clisintegration of the
abrasive.
*)
g
($ip oooss/D3o3eM -
14
TABLE 2 Tensile Specimen Geometry FlecommendationsA
widrh.
Fiber
Orientat:on
A
mm Iin.l
Overah
Lenglh.
mm [in.j
0'unidirectional
90'unidirectional
balanced and syrnmetric
15 [0.s]
250
[1
0 0]
2s
2s
11.01
175
I
7.01
l1 .01
250 [10.0]
random-d iscontinuous
25 [1.0]
250 I10.01
Tnickness
mm [in.]
Tab Length
mm lin.l
[0.040]
[0.080]
2.5 [0.100]
2.5 [0.100]
56 [2 25]
25 11.01
emery clcth
emery cloth
1.0
2.0
Tab
Thickness.
[in.]
mm
Tab Bevel
Angle,'
7 or90
1.5 [0.062]
1.5 [0.062]
90
Dimensions in this table and the tolerances ol Fig 2 or Fr.t 3 are recommendaiions only and may be varied so long as the requirements of Tai[rle 1 are met.
8.1.2.-5 Ttb 14utcriul-The rnost consistentlv usecl bonded
!as been continuous E-glass {lber-reinfbrcecl
polyn.rer nratlix ntatelials (rvoven or unwoven.) in a [()/90lns
laminate con{i_suration. The tab malerial is cornrnonly appliecl
at;15'to the fbrce clirection to provicle i1 sol-t interf'ace. Other
trotches, undercuts. rough or uneveu surl aces, or clelanrinations
8.2.2.6 Bottderl Tub Lertgth-When using bondec[ tabs. estimate the minirnunr suggested tab length firr bonclecl tabs by the
causecl by inappropriate rnachining ntelho(ls. Obtain final
dinrensions lrv u,ater-lubr-icatecl plecision sau'ins. rnilling, or
grinclin-u. The r-rse o1'clianroncl tooling has been tbund to be
extrernely e{i-ective lirr ntany nratelial s-ystents. E,clges should
be flat and parallel rvitl.rin the specifiecl tolet'ances.
8.3.3 kbeliti.q-Label the coupons so that the1, will be
distinct lrorr each other and traceable back to the ra',v material
ancl in a milnner that u'ill both be r.rnaft-ected by tlre test and not
inUuence the test.
fbllorving sinrple equation. As this equation does no1 itccount
lbr the pealiing stresses that are known to exist tlt the ends ot
9. Calibration
bonded .joints. The ta[] len_cth calculated by this eLluation
should normally be increased by some l-actor to leduce the
chances of joint lailure:
equipnrent.
1ab nraterial
conligulations that have reportedl)' been successfully
usecl
have incorporatecl steel tabs clr tabs rilacle ol the sanre malerial
as is bein-c tested.
L*": F"'ltl2F"'
(3)
r.l,here:
I
Lrrirr
FU
It
FU
minirnurn recluired bonded tab length, nrm Iin.]:
ultirnate tensile strengtl.r of coupon rnaterial. MPa
Ipsi];
coupon thickness. rnm Iin.]; ancl
ultimate shear strength ol- adhesive. coupolr rnaterial,
or tab nraterial (whichever is lowest), MPa [psi].
8.2.2.7 Brtrdei Tul; Atlltesiya-Any high-elon_qation (tough)
adhesive systenr that rneets the environrllental requirenrerrts
may be used rvhen bonding tabs to the rnaterial under test. A
uniforrn bondline of r.ninimurn thickness is desirable to reduce
undesirable stresses in the assenrbly.
8.2.3 Detailed E.rtutrplcs-The minimurn requirements lirr
specimen design cliscussed in 8.2.1 are by thenrselves insufficient to create a properly dinrensioned and toleranced coupon
drawing. Dimensionally toleranced specinren drawings fbr
both tabbed and untabbed lbrms ale shown as exanrples in Fig.
2 (SI.1 and lrig..3 tinch-pouncl). The tolelances on these
drawings are hxecl, but satisly the recluirernents of hbb I lor
all ol the reconrrnended configurations of Table 2. For a
specific conliguration, the tolerances on Fig. I and l-'ig. .j rniglit
be able to be relaxed.
8.-j 5/,c, irtcr Prcp(trLtti()n:
8.3.1 Pancl Fultricution-Control of llber alignnrent is critical. Irnproper fiber alignment will reduce the nreasured properties. Erratic fiber ali-snment will also increase the coeflicient
of variation. The specirnen preparation nrethod shall bc repolted.
8.3.2 Mttcltitting Metlnds-Specirnen preparirtion is ertrenrely inrporlant lbl this specimen. Mold the specirrens
individually to avoid edge and cutting eftects or cut theui lronr
plates. Il-they are cut lionr plates, take precautions to aroiti
9. I The accuracy of all measurir.rg ecluipment shall have
certified calibrations that ure cul'rent at the time o1'use ol'the
10. Conditioning
10. I The recornnrendecl pre-test condition is efl'ective n.roisture equilibrium at a specilic relative hurniclity as established
by Test Method D5ll9/D-5129\.'1; however, il the test requestor
does not explicitly specity a pre-test conclitioning errvironmeut.
no conditioning is recluired and the test specirnens ntay
be
tested as prepared.
10.2 The pre-test specinren conditioning process. to include
specified environnlenlal expclsure Ievels and resulting moisture
coutent, shall be repol'ted with the test clata.
Notr. 6rThe tenn moisture. as used in Test Method D.1129/l)-ill9\1.
inclucles not only the vapor o[ a Iiquid anrl its condensate. but the liqLLid
itsell'in large quantities. u: lol intnrersiorr.
10.3 Il no explicit conclitioning process is perlbnned, the
specimen conditioning plocess shall be reported as "unconclitioned" and the rnoisture content as "unknorvn."
11. Procedure
ll.l Puruttteters To Be Speci.fiel Befttre Tcst:
I l.l.l The tension specimen sampling rnethod,
coupon type
required).
tensile properties ancl clata reporting tbrrnat
and georletry, and conditioning travelers
ll.l.2 The
(il
des ired.
Norr T Determine specilic material propert),. accunlcv. and dala
reporting requirements belirre test fbr propel selection of inrtrunrentation
ancl data-recorclint equiprnent. Estimate operating stress and strain levels
to arcl in tlansducer selection. calibration ol equipment. ancl cleterr.nination
ol equipment setdngs.
.1.3 The environnrenlal conditioning test paralneters.
.4 lf perl'orrned, the sampliltg ntethocl, coupoll
seonletry. and test parameters used to deternrine density and
rein lbrcemen[ \'olunte.
I
I
I I .l
I l .) Gtrrt'nr
l
I
rt.st
t'trr'l
it,tt.t.
:
a
{Np
-
osose/Dso3eM
J
qJ
14
Q.
DRAWIIIC NOTES:
I INTERpRET DRAWING tru ecconoeruie wlrH ANSI yr4.sM r9i2, suaJEcr ro rHE FoLLowlNG:
2, ALL DIMENSIONS IN MILLIMETRES \ryITH DECIMAL TOLERANCES AS FOLLOWS
NoDFcrMAi I
o
i I xx
+3 ltr l+:
3 ALL ANGLES PAVE IOLERANCE OF + ,5O
4. ply oRTENTATToN DrREcrroN ToLERANcE RELATTvE ro @ wtrutru + .s".
5, FIN SH ON MACHINED EDGES NOT TO EXCEED 1.6/ (SYMBOLOGY IN ACCORDANCE
o
3
WITH ASA 846,I, WITH ROUGHNESS
HEIGHT IN MICROMETRES,)
6.
7
VALUES TO BE PROVIDED FOR THE FOLLOWING, SUBJECT
LAy-up, ply oRTENTATToN REFERENcE RELATTvE ro
To ANY RANGES SHoWN ON THE FIELD OF DRAWING: L4ATERIAL.
o
@. ovrnaul LENGTH. GAGE LENGTH. coupoN THTcKNESS, TAB
MATERIAL TAB THICKNESS, TAB LENGTH, TAB BEVEL ANGLE. TAB ADHESIVE.
NO ADHFSIVF BTJILDUP ALLOWED IN TH S AREA,
_45.90'
A,
n
o
+45"
'.,1\u+0o
,:
sil Nort+
4. sEENorE5,
__l
r-
OJ
r1
DTIoTAl
I
t
SEE NOTE
5
I
l*_
2x
sre ruore
t4l
=o
!olE
gl{o
E;^ El.
s
SEE NOTE 5
>:
z\
I+IojEcE
ilg
F),
t l!
t
>;
ze
I
lr
E
tsE
COUPON WITH TABS
+l' 99' ++s'
\t400
SEE NOTE
uDo
=,;
>q
H5
4
i
f/fosT.Al
SEE NO'TE
at^
o
:.,:,1
5
-I-q
UtIilo
FE
.g;
;D
AA
=E
HU
>C
COUPON \A/ITHOUT TABS
FlG.2
Tension Test Specimen Drawing (Sl)
11.2.1 Report any deviations from this test method, whether
intentional or inadvertent.
11.2.2 If specific gravity, density, reinfbrcement volume, or
void volume are 1tl be reported, then obtain these samples fiom
the same panels being tension tested. Specific gravity and
density may be evaluated by means of Test Methods D792.
Volume percent of the constiluents may be evaluated by one of
the matrix digestion procedures of Test Method D3 171, or, for
cefiain reinforcement materials such as glass and ceramics, by
the matrix burn-off technique of Test Method D258,+. The void
content equations of Test Methods D2731 are applicable to
both Test Method D2584 and the matrix digestion procedures.
Following final specimen machining and any
conditioning, but before the tension testing, determine the
I 1.2.3
specimen area as A = w' x /i, at three places in the gage section,
and report the area as the average of these three determinations
to the accuracy in 7.1. Record the average area in units of
,,,rt 1in.';.
ll.3 Speed of Testing Set the speed ol testing to effect a
nearly constant strain rate in the gage section. If strain control
=p
*g
t,
^='
>=.
a=
6.)9
is not available on the testing machine, this may be approxi- 2a
mated by repeated monitoring and adjusting of the rate of force
application to maintain a nearly constant strain rate, as measured by strain transducer response versus time. The strain rate
should be selected so as to produce failure within 1 to l0 rnin.
If the ultimate strain of the material cannot be reasonably
estimated, initial trials should be conducted using starldard
speeds until the ultimate strain of tl.re material and the
compliance of the system are known, and the strain rate can be
adjusted. The suggested standard speeds are:
ll.3.l Strain-Controlled Tests-A standard strain rate of
0.01 rnin I.
11.3.2 Cutstant Head-Speed Tests-A standard head displacement rate of 2 mm/min [0.05 in./minl.
NorE 8 Use of a fixed head speed in testing machine systems with a
high compliance may result in a strain rate that is much lower than
required. Use of wedge grips can cause extreme compliance in the system.
especially when using compliant tab materials. In some such cases, actual
strain rates l0 to -50 times lowerthan estimated by head speeds have been
obserr,ed.
ob
DO
3E
>J
(aE
iut
>z
zd
o-.
HE
@o
\l<
vi
=
o
o
J
9,
o
=
o
o
n.
o
I
{$p
-
osose/D3oseM
14
ORAWING NOTES:
INTERPRET DRAWING IN ACCORDANCE WITH ANSI YI4,5M.1982, SUB]ECT TO THE FOLLOWING:
ALL DIMENSIONS IN INCHES WITH OECIMAL TOLERANCES AS FOLLOWS:
1.
2,
l.xxx
.r.x l,xx
l +ol | +ot
3, ALL AN6LE5 HAVE TOTERANCE OF *,5'.
4. pty oRTENTATToN DrREcroN ToLEFANcE RELATTvE ro i-! wtrutru +.s".
5. FrNrsH oN MAcHTNED EDGEs Nor ro ExcEED 64/ (svtrrebi-o-cv rN AccoRDANcE wrrH ASA 846,I, wrrH Rou6H5.
6.
NESS HEIGHT rN MTCROTNCHES.)
VATUES TO BE PROVIOED FOR THE FOLLOWING, 5UBJECT TO ANJ ]TA NGES SHOWN ON TH E FIELO OF DRAWING I
MATERTAL, LAy-up, ply oRrENTATrorl REFERENcE Reulrtve ro l -I--]. ovERALL LENGTH, GAGE LENGTH, coupoN
THICKNESS, TAB INATERIAL, TAB THICKNESS, TAB IENGTH, TAB BEVEL ANGLE, TA8 AOHESIVE.
NO AOHESIVE BUILDUP ALLOWED IN THIS AREA,
9o'
-45"t.iz'
+15"
.
\Z+
4x
l'-
l-
0"
SEE NOTE 4
SEE
+
NOTEI
.010
I
l'-_-=-
----------.-1-.]ll.
'
l//loo3lAi
5E€ NOTE
n
{
d
H
d
5
lf,l
+
SEE NOTE
6t
z{
I t2
t-
D)
>1
ri
2
d
o
1
nt
4x.010 MAX
BONDLINE THICKNESS
COUPON WITH TABS
_ou.
9!"
\ v+l,/
tfl
H
+r5"
DI
'rl
ln
oo
SEE NOTE 4
SEE NOTE
l*_
sEE NorE
_l
5
A
ti
ill
!i
5
I
--E1
ol
ri
!l
E]
ol
5
o
-T-rB:l
3r
sEE NOTE
7'
I
a
*l
TI
x
laloo:l
FlG.
3
COUPON WITHOUT TABS
Tension Test Specimen Drawing (inch-pound)
11.4 Test Ertyironntent-Cclndition the specinren to the desired rnoislure profile and. if possible, test under the same
cortditioning fluid exposure level. However, cases such as
elevated tentperature testing of a ntoist specimen place unre-
alistic requirenrents on the capabilities of corrrnon
testing
machine environmentul chambers. In such cases, the mechanical test environrnent may need to be rnodified, lbr example, by
testin_u at elevated ten'lperaturc rvitlr no fluid exposure control.
but with a specilied limit on tir.ne to lailure fion.r rvithdrawal
lrorn the conditioning chamber. Modifications 1o the resr
environnrenl shall be recordecl. [n the case where lhere is no
fluid exposure control, the pel'centage nroisture loss of the
specimen prior to test completion may be eslilnated by placing
a conditioned traveler coupon ol- known weight wilhin the test
clrarnber a1 the sanle tirne as the specirnen is placed in the
charnber. Upon corr.rpletion ol the test, the traveler couplrn is
removed from the chamber. ',veighecl. ancl the percentage
weight calculated and reportecl.
I1.4.1 Store the specin.ren in the conclitioned environment
until test tiure, il'the testing area environrnetlt is diff'erent than
the conditioning environment.
ll.5
Specinten lttsertion-Place the specitnen in the grips
ol
the testin_e machine. taking care 1o align the long axis oi the
gripped specimen with the test direclion. Ti-ehten the grips.
recording the pressure used on pressure conlrollable (hydraulic
or pneumatic) grips.
NrrrE 9-The ends of the glip.jau s on rveclge-tvpe grips shoulcl be even
rvith each other-lirllowin,s insertion to avoicl inducin_rl a bending moment
that results in prcmature lailure of tlre specimen al the grip. When using
untabbed specimens. a lblded strip of mediunt grade (80 ro 150 grit)
ernerl, cloth betu'een the specirnen faces and the grip .jau,s (-urit-side
loward specirnen) provides a nonslip grip t.rn the specimen without jalr
serralion damage to the surface ol' the specimen. When usin_q tabbed
jarvs extencl approxinratelr
specimens. insert the coupon so that the
-urip
1() to I5 rnrn 10.5 ir.l past the beginning olthe tapeled portion o1'rhe trb.
Ctrupons haring tabs that extend beyond the grips itre prone to lailure irt
the tab ends because of excessive interlaminar stresses.
z
o
o
o
3
o
-{
z
o
c0
,([p
11.6 Trtmsducer lnstullution-Il' strain l'esponse is to be
deterrnined attiich the strain-indication trausducer(s) to the
specimen, svnrntetrically aboul the micl-span, rnid-rvidlh location. Attach the stl'ain-recording instlumentation to the transLlur'crs olr llte specirnen.
1L6.1 When cleterminin-[ modulus o{-elasticiti. it is rectrmn'rended that at least one specimen per
like sample be evaluated
rvith back-to-back axial transducers to evaluate the percent
bendin-e. using Ec1 4. at the average axial strain checkpoint
value (the rlid range of the appropriate chord n-rodulus strain
range) shorvn in Tahle 3. Asingle transclucer can be used if the
percent bencling is no more than 3 7c. When bending is _ereater
than 3 Tr averaged strains tiom back-to-back transducers of
like kind are recommended.
B
l.-,-l
rt'-------:l'/
-
osose/DsoseM
rlt
'hl
fla,"v constitutes a variable being studiecl. RetesLs shall be
I
perlbrmed fbr any specimen on rvhich values aLe not ellcu- 3
Iated.
B
12.2 Grip/Tab Failures-Reexarnine the means of force
introducLion into the material il a signitrcant fiacrion of failures
in a sample population occur within one specimen lvidth of the
tab or grip. Factors considerecl should include the tab
3
5
q
13.
Calculation
= indicated strain from fiont transducer, pe:
= indicated strain from back transducer, pre; and
8,, - percenl bending in specinten.
ll.7 Loucling-Apply the lorce ro the specimen at
13.l
Tensilc Stre.ss/Ten.sile Strengtlt-Calculate
5 and ieport the resulrs ro three a S
tf the tensile modulus is to be calculated. ] ]
the tensile stress at each requirecl data point using Eq E i
'tr-
significant fi-eures.
determine
o
lA
o, P/A
el
rhe
specified rate until lailure. while recording data.
11.8 Data Recnrding-Record force versus crosshead displacement (and lorce versus strail'I, if extensometers are u1ilized) continuously or at lrequent regular intervals. For this test
method, a sampling rate of 2 to 3 data recordings per second,
and a target minirnum of 100 data points per test are recommended. If a transition region or initial ply failures are no1ed,
record the force, strain. and rnode of damage at such points.
Record the rnethocl used to deten'nine the initial failure (visual,
acoustic ernission, etc.). Il-the specimen is to be lailed, record
the maximum fbrce, the failure force, and the strain (or
transducer displacement) at, or as near as possible to, the
moment of rupture.
NorE 10-Other valuable data that can be useful in understanding
testing anomalies and gripping or specimen slipping problenrs includes
lbrce versus head displacement data and fbrce velsus time data.
Failure Mode-Record the mode and location of lhil-
ure ofthe specirnen. Choose, ilpossible, a standard descriplion
using the three-part failure rnode code that is shown in Fig,
L
12. Validation
12.1 Values for ultirnate properties shall not be calculated
for any specimen that breaks at some obvious flaw, unless such
Point
frrA _
Start
iooo'
Calculation
Range
End Point
pri
3oooT
Longitudinal Strain
Checkpoint lor
Bending
pa;
a ,1000 pa 0.001
absolute strain.
=
I This strain range is to be contained in the lower half of the
stress/strain curve. For
materials that fail below 6000 pe, a strain range of 25 to 50% of ultjmate
recommended.
P-"
gg
i i
rr, I I Y
:.t'
r.sr
where:
Ftu = ultimate tensile strength, Mpa [psi];
Pmax = maximum lbrce beloie failure, N ilUfl:
o; = tensile stress at ith data point, MPa [psi];
Pi = force ar lrh clata point, Ni Ubfl; and
A = average cross-rectioral area f-rom I 1.2.-1, mmr Li, .l
3F
9n
fi O
gE
X3
13.2 Tensile Strain/Ultinrute Tensile Struin-.If tensile i 3
rnodulus or ultimate tensile strain is to be calculated. ,na 6 *
material response is being cletermined by an extenso,r.,"., I I
determine the tensile strain from the indicated disolacement ar I L
each required data point using Ec1 7 ancl report tire results ,o
I X
three significant iigures.
; I
r.,
6,/1,.
(7,88
>c
where:
f
si = tensile strain at ith clata point, ;-re;
E, = extensometer displacement at lth data point, mm tin.l; jt; [t
and
Le = extensotneter gage length, rnm [in.l.
^ -:.
13.3 Tensile Mocltrltr.s oJ Elasticitl-:
i
O=
NorE I I To minimize potential efi'ects of bending it is recommend.d
that the strain clata usecl tir modulus of elasticity dlterminadon U. tn.
average of the indicated strains I'rom each sidi of the specimen. o.
di:cussed irr 7..1 and I 1.r,.
13.3.1 Tensile Chord Modulus
o.f Elasricitt-select the
=
RE
Y*
D9
; I
I ff
2
I
appropriate chord modulus strain range lrorn Table -1. Calculate !
the tensile chord n'rodulus of elasticity frclm the srress-strain I
data using Eq 8. if data is no1 available ar the exact strain range $
end points (as ofien occurs with digital data), use the closest J
available data point. Reporl the tensile chord modulus of
elasticity to three significant ligures. Also report the strain
TABLE 3 Specimen Alignment and Chord Modulus Calculation
Strain Ranges
Tensile Chord Modulus
Longitudinal Strain
;
grip f.
_I
5L
the ultimate i'fbo
tensile strensth using L,q
r" -
€t,
is
-l
alignment, tab rntrterial, tab angle. tab adhesive, grip type,
pressure. and grip alignment.
rvhere:
ll.9
ql
14
$
$
r
f
range used in the calculation. A graphical example of chorri
f;
modulus is shown in Fig. 5.
I 3.3. l. I The tabulated strain ranges should only be usecl for
A
materials that do not exhibit a tran.sition region ia significant
change in the slope of the stress-strain curve) within the given
I=
strain range. If a transilion region occurs within the recom- f
mended strain range, then a more suitable strain range shall be j
used
rntl
reported.
B.
o
i
J
ffi
oaoee/D3o3eM
-
14
trt
ffi
YW
ill
ilt
M
LIT
GAT
!
i
m7l
///
I
6
!
\W
2
I
Vt
z
c
z
t!
M
U,
iiy
AGM(I)
LGM
AcM(2)
XGM
!
rl1
First Character
v
at
m
Third Chatacier
Second Character
re Location Code
v
A
edge Delarlination
Giip/iab
Lateral
Multi-nrode
long. Splitting
eXplosive
D
G
L
At grip/tab
A
<1W Irom grip/tab
w
M(xyz)
Multiple
S
Various
rop
Le{t
Right
Middle
Vatious
Unknown
Cage
x
M
areas
Unknown
U
o
Other
o
t
L
R
M
V
I
!
v
o
a
I
U
D
FlG.
4
3
Tensile Test Failure Codesffypical Modes
.t1
I
Fcr.'d: nrlAl
(8)
x
where:
Echord
Ao
Ae
z
= tensile chorcl modulus ol elasticity, GPa [psi];
6)
cliff'erence
in applied tensile stress between the two 6
=
o
strain points of Table i, MPa [psi]; ancl
= diff'erence between the two strain points of Table .l
3
D
13.3.2 Tensile Motlulus of Elasticitt' (Other De.finitiotts)- q
Dt
Other detinitions of elastic rnodulus may be evaluatecl and
reported at the user's discretion. If such data is generated and
(nominally 0.002).
repofiec1, report also the deltnition used, the strain range used.
and the resulls to three significant llgures. Test Method Elll
provides additional guidance in the determination of rnodulus
of elasticity.
Norr I2 An example of another modulus definition is the secondarl
chord modulus of elasticity for materials that exhibit essentially bilinear'
slress-strain behavior. An example of seconclary chord modulus is shown
in Fig. 5.
I
5000
FlG.
5
Sr.i. (r()
J.-l Poissorr's Rutit,:
!0000
NorE l3-11'bonded resistance strain gages are being used. the errorproduced by the transl'erse sensitit,ity effect on the transverse gare rvill
Typical Tensile Stress-Strain Curves
l0
a
,(p osose/D3ossM - 14
tr
-
generally be rnuch liuger fbr composites than tbl rretals. An accurare
mersurement of Poisson's ratio requires correction lor this e1lec1.
inlo".ation .n the
rnaximum extelt applicable (repor.ting of iterns bevond tl,re
The control of a given tesling laboratory. such as might oicur with &
g
rnaterial
paner
derairs
or
pararnere.r.
rabrication
,nuri-rr."J;
A
:'i:T;ii:"l,'illtjii.:',i1;li':i:.';':Ii'ffilt"r
resPonsibilirv of the lequestor):
13.4.1 Polsso rt's Rotio Bt' Cltortl Metlnd-select the approI I The revision level or date of issue of this test melhod'
5
=
pliate chorcl rnodulus longitudinal srrain range ti"", r.irri :
lil-1 I ' 2 The date(s) and localion(s)
of the test'
f
(by
betermine
plorring or otheru,ise) rhe rrans'err. .rr*in
l'1.1.3 The name(s) of the test operator(s).
(measured perpendicular to the applied tor..), r,,'.il;;;il
;
t'"i,o longitudinal strains (nteasured parallel to the applied 14.1.4 Any variatiotrs to this test method, anomalies noticed 3.
tolce). r;,, sirain range encl points. If data is not available it the during testing, or equiprnent problerr.rs occurring during testing. !
l'1.1.5 Identiltcation of the material tested including: mate- $ -exact striiirt range end points (as often occurs lvith digital clata),
use the closest available ilata point. Calculate PoisJon's ratio rial specification, material type, material designation. ! B
by Eq 9 and reporl lo three signilicant fi_eures. Also report the manufacturer, manufacturer's lot or balch nurnber, source (if = ;
not fiom manul'acturer). date of certification. expiration of I E
slrain ran_ee used.
use
\
- a:,1.,
(e) ffi:ffH,?,xiLHll1illill';tl:niiTii:,T'xl"illl#ii
q
x
where:
prepreg matrix content, and prepreg volatiles content.
0B
v = Poisson's ratio;
14.1.6 Description of the fabrication steps used ro p,.prr" 2 E
Ac, = diil'erence in lateral strain between the two lon-titudi- the laminate including: labrication start date. fabrication enA >i 9
nal strain points of Table -i, prc; ancl
date, process specilication, cure cycle, consoliclation rnethoO. f;
fr'
Ler = difference between the lrvo longitudinal strain points and a description of the equipment used.
H i(nominally
of Table 3
either 0.001, 0.002, or O.OOS). l1.l .7 ply orientation stacking sequence of the laminare.
EF
14.1.8 Il requestecl, report density, volume p..."n, ! !
13.4.2 Tensile Poissort's Ratio (Other DeJinitions) Other
definitions of Poisson's ratio may be evaluated and rcported at reinforcement, and void content test methods, specirnin .r*- fi 5l
the user's direction. 11' such data is generated and reported, pling rnethod and geometries, test parameters, ancl test results. I il
leport also the clefinition used, the strain range used, and the
14.1.9 Average ply thickness of the material.
C d.
results to three significant figures. Test Method El32 provides lzl.l.l0 Results of any nondestructive evaluation tests.
Hi
additional guidance in the determination of Poisson's ratio.
14.1.11 Method of preparing the lesl specimen, including S f
13.5 T'ansition Strttin-Where applicable, determine the specimen labeling scheme an<l method, specimen geornetry. IF
transition strain from either the bilinear longitutlinal stress sampling method, coupon cutting method, identiflcation of tab
] E
versus longitudinal strain curve or the bilinear transverse strain geometry, tab material, and tab adhesive used.
o !i
versus longitudinal strain culve. Create a best linear fit or chord
14.1 .12 Calibration dates and methods fbr all rneasurement I E
line for each of the two linear regions and extend the lines until and test equipment.
EU
they intersect. Determine to tlx'ee significant digits the longi14. 1.13 Type of tesl rnachine, grips, jaws, grip pr...rr., Ei
tudinal strain that corresponds to the inlersection point and alignment results, ancl data acquisitior.r rorrpiing iat" una 3 B
record this value as the transition strain. Report also the equipment type.
I
method of linear fit (if used) and rhe strain ranges over which
14.1 .14 Results of system alignment evaluations, if any x$
thelinearIrtorchordlinesweredetermined'Agraphicalsuchweredone.<
example of transition stlain is shown in Fig.5.
l4.l.l5 Dimensions ol-each tesr specimen
E
13.6 Sttttistics-For each series of tesls calculate the averl4.l.l6 Conditioning parameters antl results, use of tlauet- E =:
!
age value, stanclard deviation and coellcient of variation (in
ers and traveler geometry, an<I the procedure usecl if other rhan
$ f,
percent) for each property determined:
that specified in the test method.
i f
l4.l.l1
.-/i.),,,
\,=, I
//T,r;'ttt'l/ttt\
Vt4
CY : 100 X ,i,, ,/r
(
lt
=
=
=
=
=
the test machine environmental
used) and soak time at environmenr.
14.1.19 Nurnber of specimens tested.
chamber
tllt
(if
t4.1.20 Speed of
(12)
testing.
l1.l.2l
3 6>J
3E
=;
F;
S
3
facLors
ts
Transducer placement on the specirnen and rrans- +
ducer type fbr each transducer used.
d
14.1.22 If strain gages were used, the type, resistance, size. E
gage tactor, temperature compensation method, trallsverse 2,
where:
.1
s,, r
CV
n
,ri
Relative hurnidity and temperature ol- the testing
laboratory.
14. l.l8 E,nvironment ol
l0)
sample mean (average):
s&mPle stanclard deviation;
sample coelficient of variation, in percent;
number of specimens; and
measured or derived proper0/.
sensitivity, lead-wire resistance, and any correction
used.
l4.l .23 Stress-strain curves and tabulated data
14. Report
\
14.1 Report the following information. or relelences poinring to other documentation containing this infonnation, to the
of stress !i
=
ersus strain for each specimen.
14.1 .24 Percent bending results for each specirnen so
ated.
d,
evalu- j
*
3
ll
':
([Jp ososs/DsoseM TABLE 4 Precision Statistics
Material *
B
c
F
G
8.52
156.37
66.]8
121 .52
B
C
23.57
1.30
'12.38
F
3.95
G
9.47
B
U
u.bb
F
2.04
G
127
t.Jo
s,
S.
S,'.'
SF
0.52 0.85 0.92
3.84 10.85 10.85
3.20 1.52 3.48
1.59 3.92 3.92
Modulus. Msi
0.86
0.06
0.44
0.09
0.20
0.1 6
Failure Strain.9'o
0.08
0.09
0.06
0.16
0
0.05
0.65
0.05
0.29
0.08
0.06
0.04
0.03
0.15
03
9.94
6.94
2.30
3.23
0.63
0.04
0.37
0.04
o.12
0.07
0.08
0.06
0.07
0.0s
6.94
5.26
3.23
1.29
2.06
dqq
b. t5
13.02
12.47
5.25
3.19
15.1.2 Mechanical factors that can all'ect the test lesults
include: the physical cliaracteristics ot' the testing nrachine
10.84
1.01
2.98
N4ethod D-i039/D3039Mand are influencecl by rnecl'ranical and
material tactors. specinren preparation. and rneasurernellt errors.
S^/X''
3.66
4.57
3.54
2.28
3.1 2
(stiflness, damping, and mass). accurac\ of tbrce application
and displacernent/strain nreasLrrenlent. :peed of lorce
application. alignrnent of test specirren uith applied lorce,
parallelism of the grips, glip pressure. ancl tr pe of' force control
(displacement, straill, or tbrce).
15.1.3 N,{aterial factors that can aff'ect test results inclr.rde:
rnaterial quality rind represenlativeness. sampling scheme, tind
specimen preparation (dimensional accuracy. tab rnaterial, tab
taper. tab adhesive. and so forth).
15.1.-1 The mean tensile stren-eth lbr ti strairr rate seusiti\ e^
glass/epox1 tape courposite testing in the fiber direction was
founcl to increase br approximately trvo standard deviations
with decreasins time to failure tested at the limits of the
recommended time to failule prescribed in Test Method
D3039iD3039M. Tliis result su-s-eesl thal caution rnust be used
when comparing test data oblained for slrtrin rate sensiti\e
composite materials tested in accordance rvith this standard.
l5.l.5 Measurenlent errors arise lronr the use ol specialized
rneasuring instruments such as load cells. extensornetels ancl
strain gages, micrometers, data acquisition devices, aud so
forth.
15.1.6 Data obtained fiom specimens that fl'acture outsicle
the gage are should be used with caution as this data may not
be representative o1' the material. Failure in the grip region
indicates the stress concentration at the tab is greater than the
natural strength variation of the material in the gage section. A
tapered tab, bonded with a ductile low-modulus adhesive has a
relatively low-stress concentration and should result in the
lowest fiequency of grip failures. Low-strength bias increases
with the frequency of grip ftrilures by an amount proportional
to the stress concentration at the tab.
l5. I .7 An interlaboratory test program was conducted
where an average of five specimens each, of six diII'erent
5.27
8.03
4.13
11.l .25 Individual strengths and average value, starldard
deviation, and coefficient of variation (in percent) fbr the
population. Note il the failure force was less than the maxi-
murn force before lailure.
14.1.26 Individual strains at failure and the average value,
standard deviation, and coefllcient of variation (in percent) for
the population.
14.1 .21 Strain range used for chord modulus and Poisson's
ratio determination.
14.l .28 If another delinition of modulus of elasticity is used
in addition to chord rnodulus, describe the rnethod used, the
resulting conelation coeffrcient (if applicable), and the strain
ranee used krr the evlluation.
14.1 .29 Individual values of modulus of elaslicity, and the
average value, standard deviation, and coel'ficient of variation
(in percent) for the population.
14.1.30 [f another definition of Poisson's ratio is used in
addition to the chordwise definition, describe the method used,
the resulting correlation coefficient (if applicable), and the
strain range used fbr the evaluation.
14.1.31 Individual values of Poisson's ratio, and the average
value, standard deviation, and coeflicient of variation (in
per(ent t l'or the poprrlation.
14.1.32 If transition slrain is determined, the method of
linear ht (if used) and the slrain ranges over which the linear fit
or chord lines were determined.
14.1.33 Individual values of transition strain (if applicable),
and the average value, standard deviation, and coetficient of
variation (in percent) for the population.
11.1.34 Failure mode
and location
ol
lailure fbr
14
rnalerials and lay-up configurations, were tested
different laboratories.6Table
-tr
by
nine
presents the precision statistius
generated frorn this study as detlned in Practice E69 I lor
tensile strength, modulus, and failure strain. All data except
that fbr Material B (90' lay-up) was normalized with respect to
an average thickness. The rnaterials listed in Table ,1
are
deflned as:
A
B
C
F
each
lM-6/3501-O uni-tape (0)n
llv-6/3501-6 uni-tape (90)n
ll\,'l-6/3501-6 uni-tape (90/0)n
Glass/epoxy tabric (7781
glass/Ciba R 7376 Epoxy)-
specimen.
"
15. Precision and Biass
15.1.8 The averages ol the coellicients of variation are in
Table 5. The values of S,.iX and S^/X represent the repeatabilitr
l5.l
Precision:
l5.l.l The precision and bias of tension test strength and
rnodulus measurements depend on strict adherence to the Test
i
(ooroa
"ffiffil:[labric
carbon/Ciba R 6376)
and the reproducibility coeflrcients of variation. respeiiirelr.
\lrt;ri-,i. I)h.,..' I : Hrrtnrrnization
.rl7.i. Irinril Relrrrt. .\ST\1 Lr\titute tirr
" lnternational Hrrnronization of Contptr'ite
ol'ASTM
A research rcport is available frrxr AST\'1 lntemrtional Herclcluarters. Request
D3039/D3039N1and ISO
St:rnd:u'ds Reseiuch,
RR:D.30.1003.
1)
April
1997.
a
,qg7m
D3039/D3039M
Average ol
s/x,7;
5.11
Strenglh
Modulus
Failure strain
2.22
5.94
Average of
s"lx,
- 14
Q,
measuled while nrodulLrs was fclund to plovide the highest
repeatability and reproducibility of the parameters measured.
15.1.9 The consistency of agreet.nent fbr repeated tests of
the same material is dependent on lay-up configuration, material and specinren preparation techniques, test conditions, and
meaisuremeuts of the tension test parameters.
TABLE 5 Averages of the Coefticients of Variation
Parameter
+
g,
%
6.00
3.22
s
I
o
15.2 Bias-Bias cannot be deterrnined tor this test method
These arerages permit a relative comparison of the repeatabil-
as no acceptable ref-erence standard exists.
ity tri'ithin laboratorl, precision) and reproducibility (betlveen
laboratoll prccision) ol- the tension test parameters. Overall,
16. Keywords
this indicates that the failure strain rneasurements exhibit the
least repealabilit,r and reproducibility of all the parameters
16.1 composite materials; modulus of elasticity; Poisson's
ratio; tensile properties; tensile strength
A,
s.
o
o
E
=o
T'
O'
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in this standard. LJsers of this standard are expressly advised that determination of the validity of any such patent rights, and the risk
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9I
t{o
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ig
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COPYRIGHT,O,
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