1、Designation: D5448/D5448M 16Standard Test Method forInplane Shear Properties of Hoop Wound Polymer MatrixComposite Cylinders1This standard is issued under the fixed designation D5448/D5448M; the number immediately following the designation indicates theyear of original adoption or, in the case of re
2、vision, the year of last revision. A number in parentheses indicates the year of lastreapproval. 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. Scope1.1 This test me
3、thod determines the inplane shear propertiesof wound polymer matrix composites reinforced by high-modulus continuous fibers. It describes testing of hoop wound(90) cylinders in torsion for determination of inplane shearproperties.1.2 The technical content of this standard has been stablesince 1993 w
4、ithout significant objection from its stakeholders.As there is limited technical support for the maintenance of thisstandard, changes since that date have been limited to itemsrequired to retain consistency with other ASTM D30 Commit-tee standards, including editorial changes and incorporation ofupd
5、ated guidance on specimen preconditioning and environ-mental testing. The standard, therefore, should not be consid-ered to include any significant changes in approach andpractice since 1993. Future maintenance of the standard willonly be in response to specific requests and performed only astechnic
6、al support allows.1.3 The values stated in either SI units or inch-pound unitsare to be regarded separately as standard. The values stated ineach system may not be exact equivalents; therefore, eachsystem shall be used independently of the other. Combiningvalues from the two systems may result in no
7、n-conformancewith the standard.1.3.1 Within the text the inch-pound units are shown inbrackets.1.4 This standard does not purport to address all of thesafety concerns, if any, associated with its use. It is theresponsibility of the user of this standard to establish appro-priate safety and health pr
8、actices and determine the applica-bility of regulatory limitations prior to use.2. Referenced Documents2.1 ASTM Standards:2D792 Test Methods for Density and Specific Gravity (Rela-tive Density) of Plastics by DisplacementD883 Terminology Relating to PlasticsD2584 Test Method for Ignition Loss of Cur
9、ed ReinforcedResinsD2734 Test Methods for Void Content of Reinforced PlasticsD3171 Test Methods for Constituent Content of CompositeMaterialsD3878 Terminology for Composite MaterialsD5229/D5229M Test Method for MoistureAbsorption Prop-erties and Equilibrium Conditioning of Polymer MatrixComposite Ma
10、terialsD5449/D5449M Test Method for Transverse CompressiveProperties of Hoop Wound Polymer Matrix CompositeCylindersD5450/D5450M Test Method for Transverse Tensile Prop-erties of Hoop Wound Polymer Matrix Composite Cylin-dersE6 Terminology Relating to Methods of Mechanical TestingE111 Test Method fo
11、r Youngs Modulus, Tangent Modulus,and Chord ModulusE122 Practice for Calculating Sample Size to Estimate, WithSpecified Precision, the Average for a Characteristic of aLot or ProcessE177 Practice for Use of the Terms Precision and Bias inASTM Test MethodsE251 Test Methods for Performance Characteris
12、tics of Me-tallic Bonded Resistance Strain GagesE456 Terminology Relating to Quality and StatisticsE691 Practice for Conducting an Interlaboratory Study toDetermine the Precision of a Test MethodE1237 Guide for Installing Bonded Resistance Strain Gages1This test method is under the jurisdiction of A
13、STM Committee D30 onComposite Materials and is the direct responsibility of Subcommittee D30.04 onLamina and Laminate Test Methods.Current edition approved July 1, 2016. Published July 2016. Originally approvedin 1993. Last previous edition approved in 2011 as D5448/D5448M 11. DOI:10.1520/D5448_D544
14、8M-16.2For referenced ASTM standards, visit the ASTM website, www.astm.org, orcontact ASTM Customer Service at serviceastm.org. For Annual Book of ASTMStandards volume information, refer to the standards Document Summary page onthe ASTM website.Copyright ASTM International, 100 Barr Harbor Drive, PO
15、 Box C700, West Conshohocken, PA 19428-2959. United States13. Terminology3.1 DefinitionsTerminology D3878 defines terms relatingto high-modulus fibers and their composites. TerminologyD883 defines terms relating to plastics.Terminology E6 definesterms relating to mechanical testing. Terminology E456
16、 andPractice E177 define terms relating to statistics. In the event ofa conflict between terms, Terminology D3878 shall haveprecedence over other standards.NOTE 1If the term represents a physical quantity, its analyticaldimensions are stated immediately following the term (or letter symbol) infundam
17、ental dimension form, using the following ASTM standard sym-bology for fundamental dimensions, shown within square brackets: Mfor mass, L for length, T for time, for thermodynamic temperature,and nd for non-dimensional quantities. Use of these symbols is restrictedto analytical dimensions when used
18、with square brackets, as the symbolsmay have other definitions when used without the brackets.3.2 Description of Terms Specific to This Standard:33.2.1 hoop wound, na winding of a cylindrical componentwhere the filaments are circumferentially oriented.3.2.2 inplane shear modulus, G12ML1T2, ntheelast
19、ic shear modulus of a unidirectional material in the planedefined by axes parallel and perpendicular to the reinforcingfibers.3.2.3 inplane shear strain at failure, 12und, nthe valueof inplane shear strain at failure when an inplane shear force isapplied to the material.3.2.4 inplane shear strength,
20、 12,ML1T2, nthestrength of a unidirectional material when an inplane shearforce is applied to the material.3.2.5 specimena single part cut from a winding that meetsthe specifications of Fig. 1. Each winding may yield severalspecimens.3.2.6 windingan entire part completed by one windingoperation and
21、then cured.4. Summary of Test Method4.1 A thin walled hoop wound cylinder nominally 100 mm4 in. in diameter and 140 mm 512 in. in length is bondedinto two end fixtures. The specimen/fixture assembly ismounted in the testing machine and monotonically loaded ininplane shear while recording force. The
22、inplane shear strengthcan be determined from the maximum force carried prior tofailure. If the cylinder strain is monitored with strain gaugesthen the stress-strain response, the inplane shear strain atfailure, and the inplane shear modulus can be derived.5. Significance and Use5.1 This test method
23、is designed to produce inplane shearproperty data for material specifications, research anddevelopment, quality assurance, and structural design andanalysis. Factors that influence the inplane shear response andshould therefore be reported are material, method of materialpreparation, specimen prepar
24、ation, specimen conditioning, en-vironment of testing, specimen alignment and gripping, speedof testing, void content, and fiber volume fraction. Properties,in the test direction, that may be obtained from this test methodare as follows:5.1.1 Inplane Shear Strength, 12u,5.1.2 Inplane Shear Strain at
25、 Failure, 12u, and5.1.3 Inplane Shear Modulus, G12.6. Interferences6.1 Material and Specimen PreparationPoor material fab-rication practices, lack of control of fiber alignment, anddamage induced by improper specimen machining are knowncauses of high material data scatter in composites.6.2 Bonding S
26、pecimens to Test FixturesA high percentageof failures in or near the bond between the test specimen andthe test fixture, especially when combined with high materialdata scatter, is an indicator of specimen bonding problems.Specimen-to-fixture bonding is discussed in 11.5.6.3 System AlignmentExcessiv
27、e bending or axial loadingwill cause premature failure, as well as highly inaccurate shearmodulus determination. Every effort should be made to elimi-nate excess bending and axial loading from the test system.Bending and axial loading may occur due to misaligned grips,misaligned specimens in the tes
28、t fixtures, or from departures ofthe specimens from tolerance requirements. The alignmentshould always be checked as discussed in 13.2.7. Apparatus7.1 Micrometer and CalipersA micrometer witha4to7 mm 0.16 to 0.28 in. nominal diameter ball-interface or a flatanvil interface shall be used to measure t
29、he specimen wallthickness, inner diameter, and outer diameter. A ball interfaceis recommended for these measurements when at least onesurface is irregular (e.g. a course peel ply surface, which isneither smooth nor flat). A micrometer or caliper with a flat3If the term represents a physical quantity
30、, its analytical dimensions are statedimmediately following the term (or letter symbol) in fundamental dimension form,using the followingASTM standard symbology for fundamental dimensions, shownwithin square brackets: M for mass, L for length, T for time, forthermodynamic temperature, and nd for non
31、dimensional quantities. Use of thesesymbols is restricted to analytical dimensions when used with square brackets, as thesymbols may have other definitions when used without the brackets.FIG. 1 Assembly Drawing for the Shear Fixture and SpecimenD5448/D5448M 162anvil interface shall be used for measu
32、ring the overall speci-men length, the gauge length (the free length between thefixtures) and other machined surface dimensions. The use ofalternative measurement devices is permitted if specified (oragreed to) by the test requestor and reported by the testinglaboratory.The accuracy of the instrumen
33、ts shall be suitable forreading to within1%ofthesample dimensions. For typicalspecimen geometries, an instrument with an accuracy of60.0025 mm 60.0001 in. is adequate for wall thicknessmeasurements, while an instrument with an accuracy of60.025 mm 60.001 in. is adequate for measurement of theinner d
34、iameter, outer diameter, overall specimen length, gaugelength, and other machined surface dimensions.7.2 Inplane Shear FixtureThe inplane shear fixture con-sists of a steel outer shell, insert, and adaptor. An assemblydrawing for these components and the test fixture is shown inFig. 1.7.2.1 Outer Sh
35、ellThe outer shell (SI units, see Fig. 2;inch-pound units, see Fig. 3) is circular with a concentriccircular hollow in one face, a groove along the diameter of theother face, and a center hole through the thickness. Along thediameter perpendicular to the groove, three pairs of smalleccentric holes a
36、re placed at three radial distances. The twoouter pairs of holes are threaded. Four additional threadedholes are placed at the same radial distance as the innermostFIG. 2 Outer Shell of the Shear Fixture in SI UnitsD5448/D5448M 163pair of holes at 90 intervals starting 45 from the diameter thatpasse
37、s through the center groove.7.2.2 InsertThe fixture insert is circular with a center holethrough the thickness (SI units, see Fig. 4; inch-pound units,see Fig. 5). Two sets of holes are placed along a concentriccenterline. These holes align with the innermost set of holes inthe outer shell. The set
38、of 4 holes at 90 intervals arecounterbored. The insert is fastened inside the hollow of theouter shell to form the concentric groove used to put thespecimen in the fixture.7.2.3 AdaptorThe adaptor is circular with a square centraltorque nut raising out of one face, a flange along a diameter onthe ot
39、her face, and a central hole (SI units, see Fig. 6;inch-pound units, see Fig. 7). Two bolt holes are placedequidistant from the adaptor center on a diameter perpendicularto the centerline of the flange. The adaptor is fastened to theouter shell. The flange of the adaptor fits into the groove of theo
40、uter shell. The complete inplane shear specimen/fixture as-sembly is seen in Fig. 1.NOTE 2The outer shell and insert for the compression fixture are thesame outer shell and insert used for the fixtures in Test MethodsD5449/D5449M and D5450/D5450M.7.3 Testing Machine, comprised of the following:7.3.1
41、 Fixed MemberA fixed or essentially stationarymember, with respect to rotation, to which one end of thetorsion specimen/fixture/adaptor assembly, shown in Fig. 1,can be attached.7.3.2 Rotational MemberA rotational member to whichthe opposite end of the torsion specimen/fixture/adaptorassembly, shown
42、 in Fig. 1, can be attached. Either therotational member or the fixed member shall be free to moveFIG. 3 Outer Shell for the Shear Fixture in Inch-Pound UnitsD5448/D5448M 164axially to prevent the application of axial forces, or the axialforce shall be limited to 5 % of the axial strength of themate
43、rial.7.3.3 Drive Mechanism, for imparting to the movable mem-ber a uniform controlled angular velocity with respect to thefixed member. This angular velocity is to be regulated asspecified in section 11.6.7.3.4 Force IndicatorA suitable force-indicating mecha-nism capable of showing the total torsio
44、nal force carried by thetest specimen. This mechanism shall be essentially free ofinertia-lag at the specified rate of testing and shall indicate theforce within an accuracy of 61 % of the actual value, or better.7.3.5 Construction MaterialsThe fixed member, movablemember, drive mechanism, fixtures,
45、 and adaptors shall beconstructed of such materials and in such proportions that thetotal rotational deformation of the system contributed by theseparts is minimized.7.4 Strain-Indicating DeviceForce versus strain data shallbe determined by means of bonded resistance strain gauges.Each strain gauge
46、shall be 6.3 mm 0.25 in. in length. Straingauge rosettes (0/45/90) shall be used to correct for gaugemisalignment. Gauge calibration certification shall complywith Test Method E251. Some guidelines on the use of straingauges on composites are presented in 7.4.1 7.4.4. A generalreference on the subje
47、ct is Tuttle and Brinson.47.4.1 Surface PreparationThe surface preparation offiber-reinforced composites discussed in Guide E1237 canpenetrate the matrix material and cause damage to the rein-forcing fibers, resulting in improper specimen failures. Rein-forcing fibers should not be exposed or damage
48、d during thesurface preparation process. The strain gauge manufacturershould be consulted regarding surface preparation guidelinesand recommended bonding agents for composites, pending the4Tuttle, M. E. and Brinson, H. F., “Resistance-Foil Strain-Gage Technology asApplied to Composite Materials,” Ex
49、perimental Mechanics, Vol 24, No. 1, March1984, pp. 5464; errata noted in Vol 26, No. 2, January 1986, pp. 153154.FIG. 4 Insert of the Shear Fixture in SI UnitsD5448/D5448M 165development of a set of standard practices for strain gaugeinstallation surface preparation of fiber-reinforced compositematerials.7.4.2 Gauge ResistanceConsideration should be given tothe selection of gauges having larger resistance to reduceheating effects on low-conductivity materials. Resistances of350 or higher
