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2、5448M 93 (Reapproved 2000)Standard Test Method forInplane Shear Properties of Hoop Wound Polymer MatrixComposite Cylinders1This standard is issued under the fixed designation D 5448/D 5448M; the number immediately following the designation indicates the year of original adoption or, in the case of r
3、evision, the year of last revision. A number in parentheses indicates the year of last reapproval. A superscript epsilon (e) indicates an editorial change since the last revision or reapproval.1. Scope1.1 This test method determines the inplane shear properties of wound polymer matrix composites rei
4、nforced 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
5、 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,
6、if any, associated with its use. It is the responsibility of the user of this standard to establish appro- priate safety and health practices and determine the applica- bility of regulatory limitations prior to use.2. Referenced Documents2.1 ASTM Standards:D 792 Test Methods for Density and Specific
7、 Gravity (Rela- tive Density) of Plastics by Displacement2D 883 Terminology Relating to Plastics2D 2584 Test Method for Ignition Loss of Cured ReinforcedResins3D 2734 Test Method for Void Content of Reinforced Plas- tics3D 3171 Test Method for Constituent Content of CompositeMaterials4D 3878 Termino
8、logy for Composite Materials4D 5229/D 5229MTest Method for Moisture Absorption Properties and Equilibrium Conditioning of Polymer Ma- trix Composite Materials4D 5449/D 5449M Test Method for Transverse CompressiveProperties of Hoop Wound Polymer Matrix CompositeCylinders4D 5450/D 5450MTest Method for
9、 Transverse Tensile Properties of Hoop Wound Polymer Matrix Composite Cylinders4E 4 Practices for Force Verification of Testing Machines5E 6 Terminology Relating to Methods of Mechanical Test- ing5E 111 Test Method for Youngs Modulus, Tangent Modulus, and Chord Modulus5E 122 Practice for Calculating
10、 Sample Size to Estimate witha Specified Tolerable Error, the Average for a Characteris- tic of a Lot or Process6E 177 Practice for Use of the Terms Precision and Bias inASTM Test Methods6E 251 Test Methods for Performance Characteristics ofMetallic Bonded Resistance Strain Gages5E 456 Terminology R
11、elating to Quality and Statistics6E 691 Practice for Conducting and Interlaboratory Study toDetermine the Precision of a Test Method6E 1237 Guide for Installing Bonded Resistance StrainGages53. Terminology3.1 DefinitionsTerminology D 3878 defines terms relating to high-modulus fibers and their compo
12、sites. Terminology D 883 defines terms relating to plastics. Terminology E 6 defines terms relating to mechanical testing. TerminologyE 456 and Practice E 177 define terms relating to statistics. In the event of a conflict between terms, Terminology D 3878 shall have precedence over other standards.
13、3.2 Description of Terms Specific to This Standard:73.2.1 hoop wound, na winding of a cylindrical component where the filaments are circumferentially oriented.1 This test method is under the jurisdiction of ASTM Committee D30 on High Modulus Fibers and Their Composites and is the direct responsibili
14、ty of Subcom- mittee D30.04 on Lamina and Laminate Test Methods.Current edition approved Aug. 15, 1993. Published October 1993.2 Annual Book of ASTM Standards, Vol 08.01.3 Annual Book of ASTM Standards, Vol 08.02.4 Annual Book of ASTM Standards, Vol 15.03.5 Annual Book of ASTM Standards, Vol 03.01.6
15、 Annual Book of ASTM Standards, Vol 14.02.7 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 br
16、ackets: M for mass, L for length, T for time, u 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.Copyright ASTM Int
17、ernational, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959, United States.1D 5448/D 5448M 93 (2000)3.2.2 inplane shear modulus, G12 MT1 T2, nthe elastic shear modulus of a unidirectional material in the plane defined by axes parallel and perpendicular to the reinforcing fibers.
18、3.2.3 inplane shear strain at failure, g 12u nd, nthe value of inplane shear strain at failure when an inplane shear load is applied to the material.3.2.4 inplane shear strength, t12, MT2 L1, nthe strength of a unidirectional material when an inplane shear loadis applied to the material.3.2.5 specim
19、ena single part cut from a winding that meets the specifications of Fig. 1. Each winding may yield several specimens.3.2.6 windingan entire part completed by one winding operation and then cured.4. Summary of Test Method4.1 A thin walled hoop wound cylinder nominally 100 mm4 in. in diameter and 140
20、mm 512 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 while recording load. The inplane shear strength can be determined from the maximum load carried prior to failure. If the cylinder strain is
21、 monitored with strain gages then the stress-strain response, the inplane shear strain at failure, and the inplane shear modulus can be derived.5. Significance and Use5.1 This test method is designed to produce inplane shear property data for material specifications, research and devel- opment, qual
22、ity assurance, and structural design and analysis. Factors that influence the inplane shear response and should therefore be reported are material, method of material prepa- ration, specimen preparation, specimen conditioning, environ- ment of testing, specimen alignment and gripping, speed of testi
23、ng, 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, t12u,5.1.2 Inplane Shear Strain at Failure, g12u , and5.1.3 Inplane Shear Modulus, G12.FIG. 1Assembly Drawing for the Shear Fixture
24、and Specimen6. Interferences6.1 Material and Specimen PreparationPoor material fabrication practices, lack of control of fiber alignment, and damage induced by improper coupon machining are known causes of high material data scatter in composites.6.2 Bonding Specimens to Test FixturesA high percenta
25、ge 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 AlignmentExcessive bending or axial loading will caus
26、e premature failure, as well as highly inaccurate shear modulus 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 test fixtures, or from departures
27、of the specimens from tolerance requirements. The alignment should always be checked as discussed in 12.2.7. Apparatus7.1 Micrometers, suitable ball type for reading to within0.025 6 0.010 mm 0.001 6 0.0004 in. of the specimen inner and outer diameters. Flat anvil type or micrometer calipers of simi
28、lar resolution may be used for the overall specimen length and the gage length (the free length between the fixtures).7.2 Inplane Shear FixtureThe inplane shear fixture con- sists of a steel outer shell, insert, and adaptor. An assembly drawing for these components and the test fixture is shown in F
29、ig. 1.7.2.1 Outer ShellThe 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 o
30、f small eccentric holes are placed at three radial distances. The two outer pairs of holes are threaded. 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 Inse
31、rtThe 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 cou
32、nterbored. 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 AdaptorThe 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
33、(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
34、 inplane shear specimen/fixture as- sembly is seen in Fig. 1.NOTE 1The outer shell and insert for the compression fixture are the same outer shell and insert used for the fixtures in Test Methods2D 5448/D 5448M 93 (2000)FIG. 2Outer Shell of the Shear Fixture in SI UnitsD 5449/D 5449M and D 5450/D 54
35、50M.7.3 Testing Machine, comprised of the following:7.3.1 Fixed MemberA fixed or essentially stationary member, with respect to rotation, to which one end of the torsion specimen/fixture/adaptor assembly, shown in Fig. 3, can be attached.7.3.2 Rotational MemberA rotational member to which the opposi
36、te end of the torsion specimen/fixture/adaptor assem- bly, 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 load shall be limited to 5 % of the axial strength of the material.7.3.3
37、 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 9.7.3.4 Load IndicatorA suitable load-indicating mecha- nism capable of showing the total torsional load carr
38、ied by the test specimen. This mechanism shall be essentially free of inertia-lag at the specified rate of testing and shall indicate the load within an accuracy of 61 % of the actual value, or better.7.3.5 Construction MaterialsThe fixed member, movable member, drive mechanism, fixtures, and adapto
39、rs shall be constructed of such materials and in such proportions that the total rotational deformation of the system contributed by these parts is minimized.7.4 Strain-Indicating DeviceLoad versus strain data shall be determined by means of bonded resistance strain gages.3D 5448/D 5448M 93 (2000)FI
40、G. 3Outer Shell for the Shear Fixture in Inch-Pound UnitsEach strain gage shall be 6.3 mm 0.25 in. in length. Straingage rosettes (0/45/90) shall be used to correct for gage misalignment. Gage calibration certification shall comply with Test Method E 251. Some guidelines on the use of strain gages o
41、n composites are presented in 7.4.1-7.4.4. A general reference on the subject is Tuttle and Brinson.87.4.1 Surface PreparationThe surface preparation of fiber-reinforced composites discussed in Guide E 1237 can penetrate the matrix material and cause damage to the rein- forcing fibers, resulting in
42、improper coupon failures. Reinforc- ing fibers should not be exposed or damaged during the surface preparation process. The strain gage manufacturer should be8 Tuttle, M. E. and Brinson, H. F., “Resistance-Foil Strain-Gage Technology asApplied to Composite Materials,” Experimental Mechanics, Vol 24,
43、 No. 1, March1984, pp. 5464; errata noted in Vol 26, No. 2, January 1986, pp. 153154.consulted regarding surface preparation guidelines and recom-mended bonding agents for composites, pending the develop- ment of a set of standard practices for strain gage installation surface preparation of fiber-r
44、einforced composite materials.7.4.2 Gage ResistanceConsideration should be given to the selection of gages having larger resistance to reduce heating effects on low-conductivity materials. Resistances of350V or higher are preferred. Additional considerations should be given to the use of the minimum
45、 possible gage excitation voltage consistent with the desired accuracy (1 to 2 V is recommended) to further reduce the power consumed by the gage. Heating of the coupon by the gage may affect the performance of the material directly, or it may affect the indicated strain due to a difference between
46、the gage tempera- ture compensation factor and the coefficient of thermal expan- sion of the coupon material.4D 5448/D 5448M 93 (2000)FIG. 4Insert of the Shear Fixture in SI Units7.4.3 Temperature ConsiderationsConsideration of someform of temperature compensation is recommended, even when testing at standard laboratory atmosphere. Temp