ASTM D5448/D5448M-93(2006)
(Test Method)Standard Test Method for Inplane Shear Properties of Hoop Wound Polymer Matrix Composite Cylinders
Standard Test Method for Inplane Shear Properties of Hoop Wound Polymer Matrix Composite Cylinders
SIGNIFICANCE AND USE
This test method is designed to produce inplane shear property data for material specifications, research and development, quality assurance, and structural design and analysis. Factors that influence the inplane shear response and should therefore be reported are material, method of material preparation, specimen preparation, specimen conditioning, environment of testing, specimen alignment and gripping, speed of testing, void content, and fiber volume fraction. Properties, in the test direction, that may be obtained from this test method are as follows:
5.1.1 Inplane Shear Strength, τ12u,
5.1.2 Inplane Shear Strain at Failure, γ12u , and
5.1.3 Inplane Shear Modulus, G12.
SCOPE
1.1 This test method determines the inplane shear properties of wound polymer matrix composites reinforced by high-modulus continuous fibers. It describes testing of hoop wound (90°) cylinders in torsion for determination of inplane shear properties.
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 system are not exact equivalents; therefore, each system must be used independently of the other. Combining values from the two systems may result in nonconformance with the test method.
1.3 This standard does not purport to address all of the safety problems, if any, associated with its use. It is the responsibility of the user of this standard to establish appropriate safety and health practices and determine the applicability of regulatory limitations prior to use.
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Standards Content (Sample)
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Designation: D5448/D5448M – 93 (Reapproved 2006)
Standard Test Method for
Inplane Shear Properties of Hoop Wound Polymer Matrix
Composite Cylinders
This standard is issued under the fixed designation D5448/D5448M; the number immediately following the designation indicates the
year of original adoption or, in the case of revision, the year of last revision. A number in parentheses indicates the year of last
reapproval. A superscript epsilon (´) indicates an editorial change since the last revision or reapproval.
This standard has been approved for use by agencies of the Department of Defense.
1. Scope D5229/D5229M Test Method for Moisture Absorption
Properties and Equilibrium Conditioning of Polymer Ma-
1.1 Thistestmethoddeterminestheinplaneshearproperties
trix Composite Materials
of wound polymer matrix composites reinforced by high-
D5449/D5449M Test Method for Transverse Compressive
modulus continuous fibers. It describes testing of hoop wound
Properties of Hoop Wound Polymer Matrix Composite
(90°) cylinders in torsion for determination of inplane shear
Cylinders
properties.
D5450/D5450M Test Method for Transverse Tensile Prop-
1.2 The values stated in either SI units or inch-pound units
erties of Hoop Wound Polymer Matrix Composite Cylin-
are to be regarded separately as standard. Within the text the
ders
inch-pound units are shown in brackets. The values stated in
E6 TerminologyRelatingtoMethodsofMechanicalTesting
each system are not exact equivalents; therefore, each system
E111 Test Method forYoung’s Modulus,Tangent Modulus,
must be used independently of the other. Combining values
and Chord Modulus
from the two systems may result in nonconformance with the
E122 Practice for Calculating Sample Size to Estimate,
test method.
With Specified Precision, the Average for a Characteristic
1.3 This standard does not purport to address all of the
of a Lot or Process
safety concerns, if any, associated with its use. It is the
E177 Practice for Use of the Terms Precision and Bias in
responsibility of the user of this standard to establish appro-
ASTM Test Methods
priate safety and health practices and determine the applica-
E251 Test Methods for Performance Characteristics of Me-
bility of regulatory limitations prior to use.
tallic Bonded Resistance Strain Gauges
2. Referenced Documents
E456 Terminology Relating to Quality and Statistics
E691 Practice for Conducting an Interlaboratory Study to
2.1 ASTM Standards:
Determine the Precision of a Test Method
D792 Test Methods for Density and Specific Gravity (Rela-
E1237 GuideforInstallingBondedResistanceStrainGages
tive Density) of Plastics by Displacement
D883 Terminology Relating to Plastics
3. Terminology
D2584 Test Method for Ignition Loss of Cured Reinforced
3.1 Definitions—Terminology D3878 defines terms relating
Resins
to high-modulus fibers and their composites. Terminology
D2734 Test Methods for Void Content of Reinforced Plas-
D883definestermsrelatingtoplastics.TerminologyE6defines
tics
terms relating to mechanical testing. Terminology E456 and
D3171 Test Methods for Constituent Content of Composite
Practice E177 define terms relating to statistics. In the event of
Materials
a conflict between terms, Terminology D3878 shall have
D3878 Terminology for Composite Materials
precedence over other standards.
3.2 Description of Terms Specific to This Standard:
This test method is under the jurisdiction of ASTM Committee D30 on
Composite Materials and is the direct responsibility of Subcommittee D30.04 on
Lamina and Laminate Test Methods.
Current edition approved Jan. 15, 2006. Published January 2006. Originally If the term represents a physical quantity, its analytical dimensions are stated
approved in 1993. Last previous edition approved in 2000 as D5448/D5448M–93 immediately following the term (or letter symbol) in fundamental dimension form,
(2000). DOI: 10.1520/D5448_D5448M-93R06. usingthefollowingASTMstandardsymbologyforfundamentaldimensions,shown
For referenced ASTM standards, visit the ASTM website, www.astm.org, or within square brackets: [M] for mass, [L] for length, [T] for time, [u] for
contact ASTM Customer Service at service@astm.org. For Annual Book of ASTM thermodynamic temperature, and [ nd] for nondimensional quantities. Use of these
Standards volume information, refer to the standard’s Document Summary page on symbolsisrestrictedtoanalyticaldimensionswhenusedwithsquarebrackets,asthe
the ASTM website. symbols may have other definitions when used without the brackets.
Copyright © ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959, United States.
D5448/D5448M – 93 (2006)
u
3.2.1 hoopwound,n—awindingofacylindricalcomponent 5.1.2 Inplane Shear Strain at Failure, g , and
where the filaments are circumferentially oriented. 5.1.3 Inplane Shear Modulus, G .
−1 −2
3.2.2 inplaneshearmodulus,G [MT T ],n—theelastic
6. Interferences
shear modulus of a unidirectional material in the plane defined
6.1 Material and Specimen Preparation—Poor material
by axes parallel and perpendicular to the reinforcing fibers.
u
fabrication practices, lack of control of fiber alignment, and
3.2.3 inplaneshearstrainatfailure, g [nd],n—thevalue
damage induced by improper coupon machining are known
of inplane shear strain at failure when an inplane shear load is
causes of high material data scatter in composites.
applied to the material.
−2 −1
6.2 BondingSpecimenstoTestFixtures—Ahighpercentage
3.2.4 inplane shear strength, t ,[ MT L ], n—the
of failures in or near the bond between the test specimen and
strengthofaunidirectionalmaterialwhenaninplaneshearload
the test fixture, especially when combined with high material
is applied to the material.
data scatter, is an indicator of specimen bonding problems.
3.2.5 specimen—asinglepartcutfromawindingthatmeets
Specimen-to-fixture bonding is discussed in 11.5.
the specifications of Fig. 1. Each winding may yield several
6.3 System Alignment—Excessive bending or axial loading
specimens.
will cause premature failure, as well as highly inaccurate shear
3.2.6 winding—an entire part completed by one winding
operation and then cured. modulus determination. Every effort should be made to elimi-
nate excess bending and axial loading from the test system.
4. Summary of Test Method
Bending and axial loading may occur due to misaligned grips,
misalignedspecimensinthetestfixtures,orfromdeparturesof
4.1 A thin walled hoop wound cylinder nominally 100 mm
the specimens from tolerance requirements. The alignment
[4 in.] in diameter and 140 mm [5 ⁄2 in.] in length is bonded
should always be checked as discussed in 12.2.
into two end fixtures. The specimen/fixture assembly is
mounted in the testing machine and monotonically loaded in
7. Apparatus
inplane shear while recording load. The inplane shear strength
7.1 Micrometers, suitable ball type for reading to within
can be determined from the maximum load carried prior to
0.025 6 0.010 mm [0.001 6 0.0004 in.] of the specimen inner
failure. If the cylinder strain is monitored with strain gages
and outer diameters. Flat anvil type or micrometer calipers of
then the stress-strain response, the inplane shear strain at
similar resolution may be used for the overall specimen length
failure, and the inplane shear modulus can be derived.
and the gage length (the free length between the fixtures).
5. Significance and Use
7.2 Inplane Shear Fixture—The inplane shear fixture con-
sists of a steel outer shell, insert, and adaptor. An assembly
5.1 This test method is designed to produce inplane shear
drawing for these components and the test fixture is shown in
property data for material specifications, research and devel-
Fig. 1.
opment, quality assurance, and structural design and analysis.
7.2.1 Outer Shell—The outer shell (SI units, see Fig. 2;
Factors that influence the inplane shear response and should
inch-pound units, see Fig. 3) is circular with a concentric
therefore be reported are material, method of material prepa-
circular hollow in one face, a groove along the diameter of the
ration, specimen preparation, specimen conditioning, environ-
other face, and a center hole through the thickness. Along the
ment of testing, specimen alignment and gripping, speed of
diameter perpendicular to the groove, three pairs of small
testing, void content, and fiber volume fraction. Properties, in
eccentric holes are placed at three radial distances. The two
the test direction, that may be obtained from this test method
outer pairs of holes are threaded. Four additional threaded
are as follows:
u
holes are placed at the same radial distance as the innermost
5.1.1 Inplane Shear Strength, t ,
pairofholesat90°intervalsstarting45°fromthediameterthat
passes through the center groove.
7.2.2 Insert—Thefixtureinsertiscircularwithacenterhole
through the thickness (SI units, see Fig. 4; inch-pound units,
see Fig. 5). Two sets of holes are placed along a concentric
centerline.These holes align with the innermost set of holes in
the outer shell. The set of 4 holes at 90° intervals are
counterbored. The insert is fastened inside the hollow of the
outer shell to form the concentric groove used to put the
specimen in the fixture.
7.2.3 Adaptor—Theadaptoriscircularwithasquarecentral
torque nut raising out of one face, a flange along a diameter on
the other face, and a central hole (SI units, see Fig. 6;
inch-pound units, see Fig. 7). Two bolt holes are placed
equidistantfromtheadaptorcenteronadiameterperpendicular
to the centerline of the flange. The adaptor is fastened to the
outer shell.The flange of the adaptor fits into the groove of the
outer shell. The complete inplane shear specimen/fixture as-
FIG. 1 Assembly Drawing for the Shear Fixture and Specimen sembly is seen in Fig. 1.
D5448/D5448M – 93 (2006)
FIG. 2 Outer Shell of the Shear Fixture in SI Units
NOTE 1—The outer shell and insert for the compression fixture are the
7.3.3 Drive Mechanism,forimpartingtothemovablemem-
same outer shell and insert used for the fixtures in Test Methods
ber a uniform controlled angular velocity with respect to the
D5449/D5449M and D5450/D5450M.
fixed member. This angular velocity is to be regulated as
specified in Section 9.
7.3 Testing Machine, comprised of the following:
7.3.4 Load Indicator—A suitable load-indicating mecha-
7.3.1 Fixed Member—A fixed or essentially stationary
member, with respect to rotation, to which one end of the nism capable of showing the total torsional load carried by the
test specimen. This mechanism shall be essentially free of
torsion specimen/fixture/adaptor assembly, shown in Fig. 3,
can be attached. inertia-lag at the specified rate of testing and shall indicate the
load within an accuracy of 61% of the actual value, or better.
7.3.2 Rotational Member—A rotational member to which
theoppositeendofthetorsionspecimen/fixture/adaptorassem- 7.3.5 Construction Materials—The fixed member, movable
bly, shown in Fig. 1, can be attached. Either the rotational member, drive mechanism, fixtures, and adaptors shall be
member or the fixed member shall be free to move axially to constructed of such materials and in such proportions that the
preventtheapplicationofaxialforcesortheaxialloadshallbe total rotational deformation of the system contributed by these
limited to 5% of the axial strength of the material. parts is minimized.
D5448/D5448M – 93 (2006)
FIG. 3 Outer Shell for the Shear Fixture in Inch-Pound Units
7.4 Strain-Indicating Device—Load versus strain data shall forcing fibers, resulting in improper coupon failures. Reinforc-
be determined by means of bonded resistance strain gages. ingfibersshouldnotbeexposedordamagedduringthesurface
Each strain gage shall be 6.3 mm [0.25 in.] in length. Strain preparation process. The strain gage manufacturer should be
gage rosettes (0°/45°/90°) shall be used to correct for gage consulted regarding surface preparation guidelines and recom-
misalignment. Gage calibration certification shall comply with mended bonding agents for composites, pending the develop-
Test Method E251. Some guidelines on the use of strain gages ment of a set of standard practices for strain gage installation
oncompositesarepresentedin7.4.1-7.4.4.Ageneralreference surface preparation of fiber-reinforced composite materials.
on the subject is Tuttle and Brinson.
7.4.2 Gage Resistance—Consideration should be given to
7.4.1 Surface Preparation—The surface preparation of
the selection of gages having larger resistance to reduce
fiber-reinforced composites discussed in Guide E1237 can
heating effects on low-conductivity materials. Resistances of
penetrate the matrix material and cause damage to the rein-
350Vorhigherarepreferred.Additionalconsiderationsshould
be given to the use of the minimum possible gage excitation
voltage consistent with the desired accuracy (1 to 2 V is
Tuttle, M. E. and Brinson, H. F., “Resistance-Foil Strain-Gage Technology as
recommended) to further reduce the power consumed by the
Applied to Composite Materials,” Experimental Mechanics, Vol 24, No. 1, March
1984, pp. 54–64; errata noted in Vol 26, No. 2, January 1986, pp. 153–154. gage. Heating of the coupon by the gage may affect the
D5448/D5448M – 93 (2006)
FIG. 4 Insert of the Shear Fixture in SI Units
performance of the material directly, or it may affect the within 63%.Chamberconditionsshallbemonitoredeitheron
indicated strain due to a difference between the gage tempera- an automated continuous basis or on a manual basis at regular
ture compensation factor and the coefficient of thermal expan- intervals.
sion of the coupon material. 7.6 Environmental Test Chamber—An environmental test
7.4.3 Temperature Considerations—Consideration of some chamber is required for testing environments other than ambi-
form of temperature compensation is recommended, even ent testing laboratory conditions. This chamber shall be ca-
when testing at standard laboratory atmosphere. Temperature pable of maintaining the gage section of the test specimen at
compensationisrequiredwhentestinginnonambienttempera- the required test environment during the mechanical test.
ture environments.
8. Sampling and Test Specimens
7.4.4 Transverse Sensitivity—Consideration should be
given to the transverse sensitivity of the selected strain gage. 8.1 Sampling—At least five specimens per test condition
The strain gage manufacturer should be consulted for recom- should be tested unless valid results can be gained through the
mendations on transverse sensitivity corrections and effects on use of fewer specimens, such as in the case of a designed
composites. experiment.
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