ASTM D5448/D5448M-22

Standard Test Method for Inplane Shear Properties of Hoop Wound Polymer Matrix Composite Cylinders

SIGNIFICANCE AND USE
5.1 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 technical content of this test method has been stable since 1993 without significant objection from its stakeholders. As there is limited technical support for the maintenance of this test method, changes since that date have been limited to items required to retain consistency with other ASTM D30 Committee standards, including editorial changes and incorporation of updated guidance on specimen preconditioning and environmental testing. The test method, therefore, should not be considered to include any significant changes in approach and practice since 1993. Future maintenance of the test method will only be in response to specific requests and performed only as technical support allows.  
1.3 Units—The values stated in either SI units or inch-pound units are to be regarded separately as standard. The values stated in each system are not necessarily exact equivalents; therefore, to ensure conformance with the standard, each system shall be used independently of the other, and values from the two systems shall not be combined.  
1.3.1 Within the text, the inch-pound units are shown in brackets.  
1.4 This standard does not purport to address all of the safety concerns, if any, associated with its use. It is the responsibility of the user of this standard to establish appropriate safety, health, and environmental practices and determine the applicability of regulatory limitations prior to use.  
1.5 This international standard was developed in accordance with internationally recognized principles on standardization established in the Decision on Principles for the Development of International Standards, Guides and Recommendations issued by the World Trade Organization Technical Barriers to Trade (TBT) Committee.

General Information

• Status: Published
• Publication Date: 30-Apr-2022
• ICS: 83.120 - Reinforced plastics
• Technical Committee: D30 - Composite Materials
• Drafting Committee: D30.04 - Lamina and Laminate Test Methods

Relations

• Refers: ASTM D883-24 - Standard Terminology Relating to Plastics
• Effective Date: 01-Feb-2024
• Refers: ASTM D883-23 - Standard Terminology Relating to Plastics
• Effective Date: 01-Nov-2023
• Refers: ASTM D2734-23 - Standard Test Methods for Void Content of Reinforced Plastics
• Effective Date: 01-Oct-2023
• Refers: ASTM E456-13a(2022)e1 - Standard Terminology Relating to Quality and Statistics
• Effective Date: 01-Apr-2022
• Refers: ASTM E1237-20 - Standard Guide for Installing Bonded Resistance Strain Gages
• Effective Date: 15-Aug-2020
• Refers: ASTM E251-20a - Standard Test Methods for Performance Characteristics of Metallic Bonded Resistance Strain Gages
• Effective Date: 01-Jun-2020
• Refers: ASTM E251-20 - Standard Test Methods for Performance Characteristics of Metallic Bonded Resistance Strain Gages
• Effective Date: 01-May-2020
• Refers: ASTM D5229/D5229M-20 - Standard Test Method for Moisture Absorption Properties and Equilibrium Conditioning of Polymer Matrix Composite Materials
• Effective Date: 01-Mar-2020
• Refers: ASTM D883-20 - Standard Terminology Relating to Plastics
• Effective Date: 01-Jan-2020
• Refers: ASTM D3878-19a - Standard Terminology for Composite Materials
• Effective Date: 15-Oct-2019
• Refers: ASTM D883-19c - Standard Terminology Relating to Plastics
• Effective Date: 01-Aug-2019
• Refers: ASTM D3878-19 - Standard Terminology for Composite Materials
• Effective Date: 15-Apr-2019
• Refers: ASTM D883-19a - Standard Terminology Relating to Plastics
• Effective Date: 15-Apr-2019
• Refers: ASTM D883-19 - Standard Terminology Relating to Plastics
• Effective Date: 01-Feb-2019
• Refers: ASTM D883-18a - Standard Terminology Relating to Plastics
• Effective Date: 01-Dec-2018

Overview

ASTM D5448/D5448M-22 is an internationally recognized standard test method developed by ASTM International for determining the inplane shear properties of hoop wound polymer matrix composite cylinders. This standard is indispensable for professionals involved in material specifications, research and development, quality assurance, and structural analysis of composite materials. It focuses on high-modulus continuous fiber-reinforced polymer matrix composites, examining the torsional response of hoop wound (90°) cylindrical specimens.

This test method provides valuable data on the inplane shear strength, inplane shear strain at failure, and inplane shear modulus of composite materials, supporting optimization and safety in engineering applications.

Key Topics

• Shear Properties Measurement: The method estimates:
  • Inplane shear strength (τ12u)
  • Inplane shear strain at failure (γ12u)
  • Inplane shear modulus (G12)
• Applicability: Specifically designed for hoop wound composite cylinders, typically fabricated using high-modulus, continuous fiber reinforcement.
• Test Procedure Highlights:
  • Cylindrical specimens are loaded in torsion using specialized fixtures to produce and measure inplane shear properties.
  • Measurements utilize resistance strain gauges, with correction for transverse sensitivity and temperature effects.
  • Specimen and fixture preparation, system alignment, and environmental conditioning are essential to achieving accurate results.
• Reporting Factors: Key factors affecting test results include material type, method of manufacture, specimen preparation, test environment, conditioning, alignment, gripping method, testing speed, void content, and fiber volume fraction.
• Data Analysis: Results are calculated per specimen and require statistical treatment (mean, standard deviation, coefficient of variation) for series of tests.

Applications

ASTM D5448/D5448M-22 is widely used in industries where advanced composite materials are critical, including:

• Aerospace Engineering: Ensures reliable material performance in load-bearing components of aircraft and spacecraft, especially in pressurized cylinders and tanks.
• Automotive and Transport: Supports the structural design and quality control of composite drive shafts and pressure vessels.
• Civil Infrastructure: Utilized for composite piping and pressure containment systems in construction and utilities.
• Material R&D: Facilitates comparison of new composite formulations, supporting material innovation by delivering standardized strength and modulus data.
• Quality Control: Assists manufacturers and suppliers in meeting material specifications and maintaining consistent production quality.

Related Standards

ASTM D5448/D5448M-22 references several key ASTM standards for composite material testing and data analysis:

• ASTM D792: Test Methods for Density and Specific Gravity of Plastics
• ASTM D883: Terminology Relating to Plastics
• ASTM D2584: Test Method for Ignition Loss of Cured Reinforced Resins
• ASTM D2734: Test Methods for Void Content of Reinforced Plastics
• ASTM D3171: Test Methods for Constituent Content of Composite Materials
• ASTM D3878: Terminology for Composite Materials
• ASTM D5229/D5229M: Moisture Absorption and Conditioning of Composite Materials
• ASTM D5449/D5449M, D5450/D5450M: Related test methods for transverse properties of hoop wound cylinders
• ASTM E6, E111: Mechanical testing terminology and modulus of elasticity determination

For effective use of ASTM D5448/D5448M-22, it is important to apply consistent terminology and supporting test methods within the broader context of ASTM composite testing standards.

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Keywords: ASTM D5448/D5448M-22, inplane shear properties, hoop wound polymer matrix composite cylinders, composite material testing, shear strength, shear modulus, quality assurance, structural analysis, fiber-reinforced composites, material standards, ASTM composite test methods.

Standards Content (Sample)

This international standard was developed in accordance with internationally recognized principles on standardization established in the Decision on Principles for the
Development of International Standards, Guides and Recommendations issued by the World Trade Organization Technical Barriers to Trade (TBT) Committee.
Designation: D5448/D5448M − 22
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 U.S. Department of Defense.
1. Scope Development of International Standards, Guides and Recom-
mendations issued by the World Trade Organization Technical
1.1 Thistestmethoddeterminestheinplaneshearproperties
Barriers to Trade (TBT) Committee.
of wound polymer matrix composites reinforced by high-
modulus continuous fibers. It describes testing of hoop wound
2. Referenced Documents
(90°) cylinders in torsion for determination of inplane shear
2.1 ASTM Standards:
properties.
D792Test Methods for Density and Specific Gravity (Rela-
1.2 Thetechnicalcontentofthistestmethodhasbeenstable
tive Density) of Plastics by Displacement
since 1993 without significant objection from its stakeholders.
D883Terminology Relating to Plastics
Asthereislimitedtechnicalsupportforthemaintenanceofthis
D2584Test Method for Ignition Loss of Cured Reinforced
test method, changes since that date have been limited to items
Resins
required to retain consistency with otherASTM D30 Commit-
D2734TestMethodsforVoidContentofReinforcedPlastics
tee standards, including editorial changes and incorporation of
D3171Test Methods for Constituent Content of Composite
updated guidance on specimen preconditioning and environ-
Materials
mental testing. The test method, therefore, should not be
D3878Terminology for Composite Materials
considered to include any significant changes in approach and
D5229/D5229MTestMethodforMoistureAbsorptionProp-
practicesince1993.Futuremaintenanceofthetestmethodwill
erties and Equilibrium Conditioning of Polymer Matrix
only be in response to specific requests and performed only as
Composite Materials
technical support allows.
D5449/D5449MTest Method for Transverse Compressive
1.3 Units—The values stated in either SI units or inch-
Properties of Hoop Wound Polymer Matrix Composite
pound units are to be regarded separately as standard. The
Cylinders
values stated in each system are not necessarily exact equiva-
D5450/D5450MTest Method for Transverse Tensile Prop-
lents; therefore, to ensure conformance with the standard, each
erties of Hoop Wound Polymer Matrix Composite Cylin-
system shall be used independently of the other, and values
ders
from the two systems shall not be combined.
E6Terminology Relating to Methods of Mechanical Testing
1.3.1 Within the text, the inch-pound units are shown in
E111Test Method for Young’s Modulus, Tangent Modulus,
brackets.
and Chord Modulus
1.4 This standard does not purport to address all of the E122PracticeforCalculatingSampleSizetoEstimate,With
Specified Precision, the Average for a Characteristic of a
safety concerns, if any, associated with its use. It is the
responsibility of the user of this standard to establish appro- Lot or Process
E177Practice for Use of the Terms Precision and Bias in
priate safety, health, and environmental practices and deter-
mine the applicability of regulatory limitations prior to use. ASTM Test Methods
E251Test Methods for Performance Characteristics of Me-
1.5 This international standard was developed in accor-
dance with internationally recognized principles on standard- tallic Bonded Resistance Strain Gages
E456Terminology Relating to Quality and Statistics
ization established in the Decision on Principles for the
E691Practice for Conducting an Interlaboratory Study to
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. For referenced ASTM standards, visit the ASTM website, www.astm.org, or
Current edition approved May 1, 2022. Published May 2022. Originally contact ASTM Customer Service at [e-mail]. For Annual Book of ASTM
approved in 1993. Last previous edition approved in 2016 as D5448/D5448M–16. Standards volume information, refer to the standard’s Document Summary page on
DOI: 10.1520/D5448_D5448M-22. the ASTM website.
Copyright © ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959. United States
D5448/D5448M − 22
Determine the Precision of a Test Method
E1237Guide for Installing Bonded Resistance Strain Gages
3. Terminology
3.1 Definitions—Terminology D3878 defines terms relating
to high-modulus fibers and their composites. Terminology
D883definestermsrelatingtoplastics.TerminologyE6defines
terms relating to mechanical testing. Terminology E456 and
Practice E177 define terms relating to statistics. In the event of
a conflict between terms, Terminology D3878 shall have
precedence over other standards.
NOTE 1—If the term represents a physical quantity, its analytical
dimensionsarestatedimmediatelyfollowingtheterm(orlettersymbol)in
fundamental dimension form, using the following ASTM standard sym-
bology for fundamental dimensions, shown within square brackets: [M]
for mass, [L] for length, [T] for time, [θ] for thermodynamic temperature,
and[nd]fornon-dimensionalquantities.Useofthesesymbolsisrestricted
FIG. 1 Assembly Drawing for the Shear Fixture and Specimen
to analytical dimensions when used with square brackets, as the symbols
may have other definitions when used without the brackets.
3.2 Description of Terms Specific to This Standard:
5. Significance and Use
3.2.1 hoop wound, n—awindingofacylindricalcomponent
5.1 This test method is designed to produce inplane shear
where the filaments are circumferentially oriented.
property data for material specifications, research and
−1 −2
3.2.2 inplane shear modulus, G [ML T ], n—the
development, quality assurance, and structural design and
elastic shear modulus of a unidirectional material in the plane
analysis. Factors that influence the inplane shear response and
defined by axes parallel and perpendicular to the reinforcing
should therefore be reported are material, method of material
fibers.
preparation, specimen preparation, specimen conditioning, en-
u
vironment of testing, specimen alignment and gripping, speed
3.2.3 inplane shear strain at failure, γ [nd], n—the value
of testing, void content, and fiber volume fraction. Properties,
of inplane shear strain at failure when an inplane shear force is
inthetestdirection,thatmaybeobtainedfromthistestmethod
applied to the material.
are as follows:
−1 −2
3.2.4 inplane shear strength, τ ,[ML T ], n—the
u
5.1.1 Inplane Shear Strength, τ ,
strength of a unidirectional material when an inplane shear
u
5.1.2 Inplane Shear Strain at Failure, γ , and
force is applied to the material.
5.1.3 Inplane Shear Modulus, G .
3.2.5 specimen, n—a single part cut from a winding that
6. Interferences
meets the specifications of Fig. 1; each winding may yield
several specimens.
6.1 Material and Specimen Preparation—Poormaterialfab-
rication practices, lack of control of fiber alignment, and
3.2.6 winding, n—an entire part completed by one winding
damage induced by improper specimen machining are known
operation and then cured.
causes of high material data scatter in composites.
4. Summary of Test Method
6.2 Bonding Specimens to Test Fixtures—Ahigh percentage
of failures in or near the bond between the test specimen and
4.1 A thin walled hoop wound cylinder nominally 100 mm
the test fixture, especially when combined with high material
[4 in.] in diameter and 140 mm [5 ⁄2in.] in length is bonded
data scatter, is an indicator of specimen bonding problems.
into two end fixtures. The specimen/fixture assembly is
Specimen-to-fixture bonding is discussed in 11.5.
mounted in the testing machine and monotonically loaded in
inplaneshearwhilerecordingforce.Theinplaneshearstrength 6.3 System Alignment—Excessive bending or axial loading
will cause premature failure, as well as highly inaccurate shear
can be determined from the maximum force carried prior to
failure. If the cylinder strain is monitored with strain gages, modulus determination. Every effort should be made to elimi-
nate excess bending and axial loading from the test system.
then the stress-strain response, the inplane shear strain at
failure, and the inplane shear modulus can be derived. Bending and axial loading may occur due to misaligned grips,
misalignedspecimensinthetestfixtures,orfromdeparturesof
the specimens from tolerance requirements. The alignment
should always be checked as discussed in 13.2.
If the term represents a physical quantity, its analytical dimensions are stated
immediately following the term (or letter symbol) in fundamental dimension form,
7. Apparatus
usingthefollowingASTMstandardsymbologyforfundamentaldimensions,shown
within square brackets: [M] for mass, [L] for length, [T] for time, [θ] for
7.1 Micrometer and Calipers—A micrometer witha4to
thermodynamic temperature, and [nd] for nondimensional quantities. Use of these
8mm[0.16to0.32in.]nominaldiameterball-interfaceoraflat
symbolsisrestrictedtoanalyticaldimensionswhenusedwithsquarebrackets,asthe
symbols may have other definitions when used without the brackets. anvil interface shall be used to measure the specimen wall
D5448/D5448M − 22
thickness, inner diameter, and outer diameter. A ball interface inner diameter, outer diameter, overall specimen length, gage
is recommended for these measurements when at least one length, and other machined surface dimensions.
surface is irregular (for example, a coarse peel ply surface,
7.2 Inplane Shear Fixture—The inplane shear fixture con-
which is neither smooth nor flat).Amicrometer or caliper with
sists of a steel outer shell, insert, and adaptor. An assembly
a flat anvil interface shall be used for measuring the overall
drawing for these components and the test fixture is shown in
specimen length, the gage length (the free length between the
Fig. 1.
fixtures), and other machined surface dimensions. The use of
7.2.1 Outer Shell—The outer shell (SI units, see Fig. 2;
alternative measurement devices is permitted if specified (or
inch-pound units, see Fig. 3) is circular with a concentric
agreed to) by the test requestor and reported by the testing
circular hollow in one face, a groove along the diameter of the
laboratory.Theaccuracyoftheinstrumentsshallbesuitablefor
other face, and a center hole through the thickness. Along the
reading to within 1% of the sample dimensions. For typical
diameter perpendicular to the groove, three pairs of small
specimen geometries, an instrument with an accuracy of
60.0025 mm [60.0001 in.] is adequate for wall thickness eccentric holes are placed at three radial distances. The two
outer pairs of holes are threaded. Four additional threaded
measurements, while an instrument with an accuracy of
60.025 mm [60.001 in.] is adequate for measurement of the holes are placed at the same radial distance as the innermost
FIG. 2 Outer Shell of the Shear Fixture in SI Units
D5448/D5448M − 22
FIG. 3 Outer Shell for the Shear Fixture in Inch-Pound Units
pairofholesat90°intervalsstarting45°fromthediameterthat outer shell.The flange of the adaptor fits into the groove of the
passes through the center groove. outer shell. The complete inplane shear specimen/fixture as-
7.2.2 Insert—Thefixtureinsertiscircularwithacenterhole sembly is seen in Fig. 1.
through the thickness (SI units, see Fig. 4; inch-pound units,
NOTE 2—The outer shell and insert for the compression fixture are the
see Fig. 5). Two sets of holes are placed along a concentric
same outer shell and insert used for the fixtures in Test Methods
centerline.These holes align with the innermost set of holes in
D5449/D5449M and D5450/D5450M.
the outer shell. The set of 4 holes at 90° intervals are
7.3 Testing Machine, comprised of the following:
counterbored. The insert is fastened inside the hollow of the
7.3.1 Fixed Member—A fixed or essentially stationary
outer shell to form the concentric groove used to put the
member, with respect to rotation, to which one end of the
specimen in the fixture.
torsion specimen/fixture/adaptor assembly, shown in Fig. 1,
7.2.3 Adaptor—Theadaptoriscircularwithasquarecentral
can be attached.
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; 7.3.2 Rotational Member—A rotational member to which
inch-pound units, see Fig. 7). Two bolt holes are placed the opposite end of the torsion specimen/fixture/adaptor
equidistantfromtheadaptorcenteronadiameterperpendicular assembly, shown in Fig. 1, can be attached. Either the
to the centerline of the flange. The adaptor is fastened to the rotational member or the fixed member shall be free to move
D5448/D5448M − 22
FIG. 4 Insert of the Shear Fixture in SI Units
axially to prevent the application of axial forces, or the axial Each strain gage shall be 6.3 mm [0.25 in.] in length. Strain
force shall be limited to 5% of the axial strength of the gage rosettes (0°/45°/90°) shall be used to correct for gage
material.
misalignment. Gage calibration certification shall comply with
7.3.3 Drive Mechanism,forimpartingtothemovablemem-
Test Method E251. Some guidelines on the use of strain gages
ber a uniform controlled angular velocity with respect to the
on composites are presented in 7.4.1 – 7.4.4. A general
fixed member. This angular velocity is to be regulated as
reference on the subject is Tuttle and Brinson.
specified in section 11.6.
7.4.1 Surface Preparation—The surface preparation of
7.3.4 Force Indicator—A suitable force-indicating mecha-
fiber-reinforced composites discussed in Guide E1237 can
nismcapableofshowingthetotaltorsionalforcecarriedbythe
penetrate the matrix material and cause damage to the rein-
test specimen. This mechanism shall be essentially free of
forcing fibers, resulting in improper specimen failures. Rein-
inertia-lag at the specified rate of testing and shall indicate the
forcing fibers should not be exposed or damaged during the
forcewithinanaccuracyof 61%oftheactualvalue,orbetter.
surface preparation process. The strain gage manufacturer
7.3.5 Construction Materials—The fixed member, movable
should be consulted regarding surface preparation guidelines
member, drive mechanism, fixtures, and adaptors shall be
and recommended bonding agents for composites, pending the
constructed of such materials and in such proportions that the
total rotational deformation of the system contributed by these
parts is minimized.
Tuttle, M. E., and Brinson, H. F., “Resistance-Foil Strain-Gage Technology as
7.4 Strain-Indicating Device—Force versus strain data shall
Applied to Composite Materials,” Experimental Mechanics, Vol 24, No. 1, March
be determined by means of bonded resistance strain gages. 1984, pp. 54–64; errata noted in Vol 26, No. 2, January 1986, pp. 153–154.
D5448/D5448M − 22
FIG. 5 Insert for the Shear Fixture in Inch-Pound Units
development of a set of standard practices for strain gage 7.4.4 Transverse Sensitivity—Considerationshouldbegiven
installation surface preparation of fiber-reinforced composite to the transverse sensitivity of the selected strain gage. The
materials. strain gage manufacturer should be consulted for recommen-
7.4.2 Gage Resistance—Consideration should be given to dations on transverse sensitivity corrections and effects on
the selection of gages having larger resistance to reduce composites.
heating effects on low-conductivity materials. Resistances of
7.5 Conditioning Chamber—When conditioning materials
350Ωorhigherarepreferred.Additionalconsiderationsshould
at non-laboratory environments, a temperature/vapor-level
be given to the use of the minimum possible gage excitation
controlled environment conditioning chamber is required that
voltage consistent with the desired accuracy (1 to 2V is
shall be capable of maintaining the required temperature to
recommended) to further reduce the power consumed by the
within 63°C[65°F] and the required relative humidity level
gage. Heating of the specimen by the gage may affect the
to within 63% RH. Chamber conditions shall be monitored
performance of the material directly, or it may affect the
either on an automated continuous basis or on a manual basis
indicated strain due to a difference between the gage tempera-
at regular intervals.
ture compensation factor and the coefficient of thermal expan-
sion of the specimen 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. The
ture environments. test temperature shall be maintained within 63°C[65°F] of
D5448/D5448M − 22
FIG. 6 Adaptor for the Shear Fixture in SI Units
the required temperature, and the relative humidity level shall Specimens may be fabricated on a tapered mandrel yielding a
be maintained to within 63% RH of the required humidity maximum taper over the specimen length of 0.0005mm⁄mm
level. on the diameter. The specimens shall have a nominal wall
thickness of 2mm [0.08in.], the actual thickness to be speci-
8. Sampling and Test Specimens
fied by the winding parameters and shall be maintained as the
test specimen is wound and cured.
8.1 Sampling—At least five specimens per test condition
should be tested, unless valid results can be gained through the
8.3 Winding—All specimens shall be hoop wound (approxi-
use of fewer specimens, such as in the case of a designed
mately 90°) with a single tow and with enough layers to meet
experiment. For statistically significant data, the procedures
the thickness criterion described in 8.2.
outlined in Practice E122 should be consulted. The method of
8.4 Unless otherwise directed, determine specific gravity
sampling shall be reported.
and reinforcement and void volume percentages for each
NOTE 3—If specimens are to undergo environmental conditioning to
winding. The material used for the determination of these
equilibrium, and are of such type or geometry that the weight change of
properties should be extracted from the center of the winding
thematerialcannotbeproperlymeasuredbyweighingthespecimenitself,
if multiple specimens are extracted from one winding or from
then another traveler of the same nominal thickness and appropriate size
shall be used to determine when equilibrium has been reached for the
one of the ends of the winding if only one specimen is
specimens being conditioned.
extracted from the winding. Determine and report specific
8.2 Geometry—The test specimen shall be as shown in Fig. gravity and density in accordance with Test Methods D792.
8. The length of all specimens shall be 140mm [5.5in.]. This Determine and report volume percent of the constituents by
will provide a 102mm [4.0in.] gage length. The inner diam- one of the matrix digestion procedures of Test Method D3171,
eterofallspecimensshallbe100 64mm[4.000 60.015in.]. or, for certain reinforcement materials such as glass and
D5448/D5448M − 22
FIG. 7 Adaptor for the Shear Fixture in Inch-Pound Units
ceramics, by the matrix burn-off technique of Test Method doesnotexplicitlyspecifyapre-testconditioningenvironment,
D2584.ThevoidcontentequationsofTestMethodsD2734are no conditioning is required and the test specimens may be
applicabletobothTestMethodD2584andthematrixdigestion
tested as prepared.
procedures.
10.2 The pre-test speci
...

This document is not an ASTM standard and is intended only to provide the user of an ASTM standard an indication of what changes have been made to the previous version. Because
it may not be technically possible to adequately depict all changes accurately, ASTM recommends that users consult prior editions as appropriate. In all cases only the current version
of the standard as published by ASTM is to be considered the official document.
Designation: D5448/D5448M − 16 D5448/D5448M − 22
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 U.S. Department of Defense.
1. 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 technical content of this standard test method has been stable since 1993 without significant objection from its
stakeholders. As there is limited technical support for the maintenance of this standard, test method, changes since that date have
been limited to items required to retain consistency with other ASTM D30 Committee standards, including editorial changes and
incorporation of updated guidance on specimen preconditioning and environmental testing. The standard, test method, therefore,
should not be considered to include any significant changes in approach and practice since 1993. Future maintenance of the
standard test method will only be in response to specific requests and performed only as technical support allows.
1.3 Units—The values stated in either SI units or inch-pound units are to be regarded separately as standard. The values stated in
each system mayare not benecessarily exact equivalents; therefore, to ensure conformance with the standard, each system shall be
used independently of the other. Combiningother, and values from the two systems may result in non-conformance with the
standard.shall not be combined.
1.3.1 Within the text, the inch-pound units are shown in brackets.
1.4 This standard does not purport to address all of the safety concerns, if any, associated with its use. It is the responsibility
of the user of this standard to establish appropriate safety safety, health, and healthenvironmental practices and determine the
applicability of regulatory limitations prior to use.
1.5 This international standard was developed in accordance with internationally recognized principles on standardization
established in the Decision on Principles for the Development of International Standards, Guides and Recommendations issued
by the World Trade Organization Technical Barriers to Trade (TBT) Committee.
2. Referenced Documents
2.1 ASTM Standards:
D792 Test Methods for Density and Specific Gravity (Relative Density) of Plastics by Displacement
D883 Terminology Relating to Plastics
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 July 1, 2016May 1, 2022. Published July 2016May 2022. Originally approved in 1993. Last previous edition approved in 20112016 as
D5448/D5448M – 11.D5448/D5448M – 16. DOI: 10.1520/D5448_D5448M-16.10.1520/D5448_D5448M-22.
For referenced ASTM standards, visit the ASTM website, www.astm.org, or contact ASTM Customer Service at [e-mail]. For Annual Book of ASTM Standards
volume information, refer to the standard’s Document Summary page on the ASTM website.
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D5448/D5448M − 22
D2584 Test Method for Ignition Loss of Cured Reinforced Resins
D2734 Test Methods for Void Content of Reinforced Plastics
D3171 Test Methods for Constituent Content of Composite Materials
D3878 Terminology for Composite Materials
D5229/D5229M Test Method for Moisture Absorption Properties and Equilibrium Conditioning of Polymer Matrix Composite
Materials
D5449/D5449M Test Method for Transverse Compressive Properties of Hoop Wound Polymer Matrix Composite Cylinders
D5450/D5450M Test Method for Transverse Tensile Properties of Hoop Wound Polymer Matrix Composite Cylinders
E6 Terminology Relating to Methods of Mechanical Testing
E111 Test Method for Young’s Modulus, Tangent Modulus, and Chord Modulus
E122 Practice for Calculating Sample Size to Estimate, With Specified Precision, the Average for a Characteristic of a Lot or
Process
E177 Practice for Use of the Terms Precision and Bias in ASTM Test Methods
E251 Test Methods for Performance Characteristics of Metallic Bonded Resistance Strain Gages
E456 Terminology Relating to Quality and Statistics
E691 Practice for Conducting an Interlaboratory Study to Determine the Precision of a Test Method
E1237 Guide for Installing Bonded Resistance Strain Gages
3. Terminology
3.1 Definitions—Terminology D3878 defines terms relating to high-modulus fibers and their composites. Terminology D883
defines terms relating to plastics. Terminology E6 defines terms relating to mechanical testing. Terminology E456 and Practice
E177 define terms relating to statistics. In the event of a conflict between terms, Terminology D3878 shall have precedence over
other standards.
NOTE 1—If the term represents a physical quantity, its analytical dimensions are stated immediately following the term (or letter symbol) in fundamental
dimension form, using the following ASTM standard symbology for fundamental dimensions, shown within square brackets: [M][M] for mass, [L][L]
for length, [T][T] for time, [θ] for thermodynamic temperature, and [nd][nd] for non-dimensional quantities. Use of these symbols is restricted to
analytical dimensions when used with square brackets, as the symbols may have other definitions when used without the brackets.
3.2 Description of Terms Specific to This Standard:
3.2.1 hoop wound, n—a winding of a cylindrical component where the filaments are circumferentially oriented.
−1 −2
3.2.2 inplane shear modulus, G [ ML T ], n—the elastic shear modulus of a unidirectional material in the plane defined by
axes parallel and perpendicular to the reinforcing fibers.
u
3.2.3 inplane shear strain at failure, γ [nd], n—the value of inplane shear strain at failure when an inplane shear force is applied
to the material.
−1 −2
3.2.4 inplane shear strength, τ , [ ML T ], n—the strength of a unidirectional material when an inplane shear force is applied
to the material.
3.2.5 specimen—specimen, n—a single part cut from a winding that meets the specifications of Fig. 1. Each; each winding may
yield several specimens.
3.2.6 winding—winding, n—an entire part completed by one winding operation and then cured.
4. Summary of Test Method
4.1 A thin walled hoop wound cylinder nominally 100 mm [4 in.] in diameter and 140 mm [5 ⁄2 in.] in.] in length is bonded into
two end fixtures. The specimen/fixture assembly is mounted in the testing machine and monotonically loaded in inplane shear
If the term represents a physical quantity, its analytical dimensions are stated immediately following the term (or letter symbol) in fundamental dimension form, using
the following ASTM standard symbology for fundamental dimensions, shown within square brackets: [M] for mass, [L] for length, [T] for time, [θ] for thermodynamic
temperature, and [nd] for nondimensional quantities. Use of these symbols is restricted to analytical dimensions when used with square brackets, as the symbols may have
other definitions when used without the brackets.
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FIG. 1 Assembly Drawing for the Shear Fixture and Specimen
while recording force. The inplane shear strength can be determined from the maximum force carried prior to failure. If the cylinder
strain is monitored with strain gaugesgages, then the stress-strain response, the inplane shear strain at failure, and the inplane shear
modulus can be derived.
5. Significance and Use
5.1 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:
u
5.1.1 Inplane Shear Strength, τ ,
u
5.1.2 Inplane Shear Strain at Failure, γ , and
5.1.3 Inplane Shear Modulus, G .
6. Interferences
6.1 Material and Specimen Preparation—Poor material fabrication practices, lack of control of fiber alignment, and damage
induced by improper specimen machining are known causes of high material data scatter in composites.
6.2 Bonding Specimens to Test Fixtures—A high percentage of failures in or near the bond between the test specimen and the test
fixture, especially when combined with high material data scatter, is an indicator of specimen bonding problems. Specimen-to-
fixture bonding is discussed in 11.5.
6.3 System Alignment—Excessive bending or axial loading will cause premature failure, as well as highly inaccurate shear
modulus determination. Every effort should be made to eliminate excess bending and axial loading from the test system. Bending
and axial loading may occur due to misaligned grips, misaligned specimens in the test fixtures, or from departures of the specimens
from tolerance requirements. The alignment should always be checked as discussed in 13.2.
7. Apparatus
7.1 Micrometer and Calipers—A micrometer with a 4 to 7 mm8 mm [0.16 to 0.280.32 in.] nominal diameter ball-interface or a
flat anvil interface shall be used to measure the specimen wall thickness, inner diameter, and outer diameter. A ball interface is
recommended for these measurements when at least one surface is irregular (e.g. (for example, a coursecoarse peel ply surface,
which is neither smooth nor flat). A micrometer or caliper with a flat anvil interface shall be used for measuring the overall
D5448/D5448M − 22
specimen length, the gaugegage length (the free length between the fixtures)fixtures), and other machined surface dimensions. The
use of alternative measurement devices is permitted if specified (or agreed to) by the test requestor and reported by the testing
laboratory. The accuracy of the instruments shall be suitable for reading to within 1 % 1 % of the sample dimensions. For typical
specimen geometries, an instrument with an accuracy of 60.0025 mm [60.0001 in.] is adequate for wall thickness measurements,
while an instrument with an accuracy of 60.025 mm [60.001 in.] is adequate for measurement of the inner diameter, outer
diameter, overall specimen length, gaugegage length, and other machined surface dimensions.
7.2 Inplane Shear Fixture—The inplane shear fixture consists of a steel outer shell, insert, and adaptor. An assembly drawing for
these components and the test fixture is shown in Fig. 1.
7.2.1 Outer Shell—The outer shell (SI units, see Fig. 2; inch-pound units, see Fig. 3) is circular with a concentric circular hollow
in one face, a groove along the diameter of the other face, and a center hole through the thickness. Along the diameter perpendicular
to the groove, three pairs of small eccentric holes are placed at three radial distances. The two outer pairs of holes are threaded.
FIG. 2 Outer Shell of the Shear Fixture in SI Units
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FIG. 3 Outer Shell for the Shear Fixture in Inch-Pound Units
Four additional threaded holes are placed at the same radial distance as the innermost pair of holes at 90° intervals starting 45°
from the diameter that passes through the center groove.
7.2.2 Insert—The fixture insert is circular with a center hole 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—The adaptor is circular with a square central 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 equidistant from the
adaptor center on a diameter perpendicular 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 assembly is seen in Fig. 1.
NOTE 2—The outer shell and insert for the compression fixture are the same outer shell and insert used for the fixtures in Test Methods D5449/D5449M
and D5450/D5450M.
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FIG. 4 Insert of the Shear Fixture in SI Units
7.3 Testing Machine, comprised of the following:
7.3.1 Fixed Member—A fixed or essentially stationary member, with respect to rotation, to which one end of the torsion
specimen/fixture/adaptor assembly, shown in Fig. 1, can be attached.
7.3.2 Rotational Member—A rotational member to which the opposite end of the torsion specimen/fixture/adaptor assembly,
shown in Fig. 1, can be attached. Either the rotational member or the fixed member shall be free to move axially to prevent the
application of axial forces, or the axial force shall be limited to 5 % of the axial strength of the material.
7.3.3 Drive Mechanism, for imparting to the movable member a uniform controlled angular velocity with respect to the fixed
member. This angular velocity is to be regulated as specified in section 11.6.
7.3.4 Force Indicator—A suitable force-indicating mechanism capable of showing the total torsional force carried by the test
specimen. This mechanism shall be essentially free of inertia-lag at the specified rate of testing and shall indicate the force within
an accuracy of 61 % of the actual value, or better.
7.3.5 Construction Materials—The fixed member, movable member, drive mechanism, fixtures, and adaptors shall be constructed
of such materials and in such proportions that the total rotational deformation of the system contributed by these parts is minimized.
D5448/D5448M − 22
FIG. 5 Insert for the Shear Fixture in Inch-Pound Units
7.4 Strain-Indicating Device—Force versus strain data shall be determined by means of bonded resistance strain gauges.gages.
Each strain gaugegage shall be 6.3 mm [0.25 in.] in length. Strain gaugegage rosettes (0°/45°/90°) shall be used to correct for
gaugegage misalignment. GaugeGage calibration certification shall comply with Test Method E251. Some guidelines on the use
of strain gaugesgages on composites are presented in 7.4.1 – 7.4.4. A general reference on the subject is Tuttle and Brinson.
7.4.1 Surface Preparation—The surface preparation of fiber-reinforced composites discussed in Guide E1237 can penetrate the
matrix material and cause damage to the reinforcing fibers, resulting in improper specimen failures. Reinforcing fibers should not
be exposed or damaged during the surface preparation process. The strain gaugegage manufacturer should be consulted regarding
surface preparation guidelines and recommended bonding agents for composites, pending the development of a set of standard
practices for strain gaugegage installation surface preparation of fiber-reinforced composite materials.
7.4.2 GaugeGage Resistance—Consideration should be given to the selection of gaugesgages having larger resistance to reduce
heating effects on low-conductivity materials. Resistances of 350Ω or higher are preferred. Additional considerations should be
given to the use of the minimum possible gaugegage excitation voltage consistent with the desired accuracy (1 to 2 V 2 V is
recommended) to further reduce the power consumed by the gauge.gage. Heating of the specimen by the gaugegage may affect
Tuttle, M. E.E., and Brinson, H. F., “Resistance-Foil Strain-Gage Technology as 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.
D5448/D5448M − 22
FIG. 6 Adaptor for the Shear Fixture in SI Units
the performance of the material directly, or it may affect the indicated strain due to a difference between the gaugegage temperature
compensation factor and the coefficient of thermal expansion of the specimen material.
7.4.3 Temperature Considerations—Consideration of some form of temperature compensation is recommended, even when testing
at standard laboratory atmosphere. Temperature compensation is required when testing in nonambient temperature environments.
7.4.4 Transverse Sensitivity—Consideration should be given to the transverse sensitivity of the selected strain gauge.gage. The
strain gaugegage manufacturer should be consulted for recommendations on transverse sensitivity corrections and effects on
composites.
7.5 Conditioning Chamber—When conditioning materials at nonlaboratorynon-laboratory environments, a temperature/vapor-
level controlled environment conditioning chamber is required whichthat shall be capable of maintaining the required temperature
to within 63°C [65°F]63 °C [65 °F] and the required relative vaporhumidity level to within 63 %. 63 % RH. Chamber
conditions shall be monitored either on an automated continuous basis or on a manual basis at regular intervals.
7.6 Environmental Test Chamber—An environmental test chamber is required for testing environments other than ambient testing
laboratory conditions. This chamber shall be capable of maintaining the gaugegage section of the test specimen at the required test
environment during the mechanical test. The test temperature shall be maintained within 63 °C [65 °F] of the required
temperature, and the relative humidity level shall be maintained to within 63 % RH of the required humidity level.
D5448/D5448M − 22
FIG. 7 Adaptor for the Shear Fixture in Inch-Pound Units
8. Sampling and Test Specimens
8.1 Sampling—At least five specimens per test condition should be tested, unless valid results can be gained through the use of
fewer specimens, such as in the case of a designed experiment. For statistically significant data, the procedures outlined in Practice
E122 should be consulted. The method of sampling shall be reported.
NOTE 3—If specimens are to undergo environmental conditioning to equilibrium, and are of such type or geometry that the weight change of the material
cannot be properly measured by weighing the specimen itself, then another traveler of the same nominal thickness and appropriate size shall be used to
determine when equilibrium has been reached for the specimens being conditioned.
8.2 Geometry—The test specimen shall be as shown in Fig. 8. The length of all specimens shall be 140 mm [5.5 in.]. 140 mm
[5.5 in.]. This will provide a 102 mm [4.0 in.] gauge 102 mm [4.0 in.] gage length. The inner diameter of all specimens shall be
100 6 4 mm 4 mm [4.000 6 0.015 in.]. 0.015 in.]. Specimens may be fabricated on a tapered mandrel yielding a maximum taper
over the specimen length of 0.00050.0005 mm mm/mm ⁄mm on the diameter. The specimens shall have a nominal wall thickness
of 2 mm [0.08 in.], 2 mm [0.08 in.], the actual thickness to be specified by the winding parameters and shall be maintained as the
test specimen is wound and cured.
8.3 Winding—All specimens shall be hoop wound (approximately 90°) with a single tow and with enough layers to meet the
thickness criterion described in 8.2.
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FIG. 8 Test Specimen Shown With Strain GaugeGage Configuration
8.4 Unless otherwise directed, determine specific gravity and reinforcement and void volume percentages for each winding. The
material used for the determination of these properties should be extracted from the center of the winding if multiple specimens
are extracted from one winding or from one of the ends of the winding if only one specimen is extracted from the winding.
Determine and report specific gravity and density in accordance with Test Methods D792. Determine and report volume percent
of the constituents by one of the matrix digestion procedures of Test Method D3171, or, for certain reinforcement materials such
as glass and ceramics, by the matrix burn-off technique of Test Method D2584. The void content equations of Test Methods D2734
are applicable to both Test Method D2584 and the matrix digestion procedures.
8.5 Labeling—Label the specimens so that they will be distinct from each other and traceable back to the raw material, and will
neither influence the test nor be affected by it.
9. Calibration
9.1 The accuracy of all measurement equipment shall have certified calibrations that are current at the time of use of the
equipment.
10. Conditioning
10.1 The recommended pre-test condition is effective moisture equilibrium at a specific relative humidity as established by Test
Method D5229/D5229M; however, if the test requestor does not explicitly specify a pre-test conditioning environm
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