1、Designation: D7332/D7332M 09D7332/D7332M 15Standard Test Method forMeasuring the Fastener Pull-Through Resistance of aFiber-Reinforced Polymer Matrix Composite1This standard is issued under the fixed designation D7332/D7332M; the number immediately following the designation indicates theyear of orig
2、inal adoption or, in the case of revision, 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.1. Scope1.1 This test method determines the fastener pull-through resistanc
3、e of multidirectional polymer matrix composites reinforcedby high-modulus fibers. Fastener pull-through resistance is characterized by the force-versus-displacement response exhibitedwhen a mechanical fastener is pulled through a composite plate, with the force applied perpendicular to the plane of
4、the plate. Thecomposite material forms are limited to continuous-fiber or discontinuous-fiber (tape or fabric, or both) reinforced composites forwhich the laminate is symmetric and balanced with respect to the test direction. The range of acceptable test laminates andthicknesses is defined in 8.2.1.
5、2 Two test procedures and configurations are provided. The first, Procedure A, is suitable for screening and fastenerdevelopment purposes. The second, Procedure B, is configuration-dependent and is suitable for establishing design values. Bothprocedures can be used to perform comparative evaluations
6、 of candidate fasteners/fastener system designs.1.3 The specimens described herein may not be representative of actual joints which may contain one or more free edgesadjacent to the fastener, or may contain multiple fasteners that can change the actual boundary conditions.1.4 This test method is con
7、sistent with the recommendations of CMH-17, which describes the desirable attributes of a fastenerpull-through test method.1.5 The values stated in either SI units or inch-pound units are to be regarded separately as standard. Within the text theinch-pound units are shown in brackets. The values sta
8、ted in each system are not exact equivalents; therefore, each system mustbe used independently of the other. Combining values from the two systems may result in nonconformance with the standard.1.6 This standard does not purport to address all of the safety concerns, if any, associated with its use.
9、 It is the responsibilityof the user of this standard to establish appropriate safety and health practices and determine the applicability of regulatorylimitations prior to use.2. Referenced Documents2.1 ASTM Standards:2D792 Test Methods for Density and Specific Gravity (Relative Density) of Plastic
10、s by DisplacementD883 Terminology Relating to PlasticsD3171 Test Methods for Constituent Content of Composite MaterialsD3410/D3410M Test Method for Compressive Properties of Polymer Matrix Composite Materials with Unsupported GageSection by Shear LoadingD3878 Terminology for Composite MaterialsD5229
11、/D5229M Test Method for Moisture Absorption Properties and Equilibrium Conditioning of Polymer Matrix CompositeMaterialsD5687/D5687M Guide for Preparation of Flat Composite Panels with Processing Guidelines for Specimen PreparationE4 Practices for Force Verification of Testing MachinesE6 Terminology
12、 Relating to Methods of Mechanical TestingE18 Test Methods for Rockwell Hardness of Metallic Materials1 This test method is under the jurisdiction of ASTM Committee D30 on Composite Materials and is the direct responsibility of Subcommittee D30.05 on Structural TestMethods.Current edition approved S
13、ept. 1, 2009April 1, 2015. Published October 2009May 2015. Originally approved in 2007. Last previous edition approved in 20072009 asD7332/D7332M07D7332/D7332M09. 1. DOI: 10.1520/D7332_D7332M-09.10.1520/D7332_D7332M-15.2 For referencedASTM standards, visit theASTM website, www.astm.org, or contactAS
14、TM Customer Service at serviceastm.org. For Annual Book of ASTM Standardsvolume information, refer to the standards Document Summary page on the ASTM website.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 mad
15、e to the previous version. Becauseit 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 versionof the standard as published by ASTM is to be considered the official document.Copy
16、right ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959. United States1E122 Practice for Calculating Sample Size to Estimate, With Specified Precision, the Average for a Characteristic of a Lot orProcessE177 Practice for Use of the Terms Precision and Bias in A
17、STM Test MethodsE456 Terminology Relating to Quality and StatisticsE1309 Guide for Identification of Fiber-Reinforced Polymer-Matrix Composite Materials in DatabasesE1434 Guide for Recording Mechanical Test Data of Fiber-Reinforced Composite Materials in Databases2.2 Industry Documents:CMH-17-1FCMH-
18、17-1G Composite Materials Handbook, Volume 1Polymer Matrix Composites Guidelines for Character-ization of Structural Materials33. Terminology3.1 DefinitionsTerminology D3878 defines terms relating to composite materials. Terminology D883 defines terms relatingto plastics. Terminology E6 defines term
19、s relating to mechanical testing. Terminology E456 and Practice E177 define terms relatingto statistics. In the event of a conflict between terms, Terminology D3878 shall have precedence over the other standards.NOTE 1If the term represents a physical quantity, its analytical dimensions are stated i
20、mmediately following the term (or letter symbol) infundamental dimension form, using the following ASTM standard symbology for fundamental dimensions, shown within square brackets: M for mass,L for length, T for time, for thermodynamic temperature, and nd for non-dimensional quantities. Use of these
21、 symbols is restricted to analyticaldimensions when used with square brackets, as the symbols may have other definitions when used without the brackets.3.2 Definitions of Terms Specific to This Standard:3.2.1 diameter-to-thickness ratio, D/h nd, nthe ratio of the hole diameter to the specimen thickn
22、ess.3.2.1.1 DiscussionThe diameter-to-thickness ratio may be either a nominal value determined from nominal dimensions or an actual value determinedfrom measured dimensions.3.2.2 failure force, nthe maximum force magnitude achieved prior to the first significant (greater than 10 %) drop in appliedfo
23、rce, as observed in force versus displacement data.3.2.3 initial sub-critical failure, ndiscontinuity observed in force versus displacement data prior to attaining the failure force.Sub-critical failures are characterized by minor (less than 10 %) drops in applied force, or by compliance changes (gr
24、eater than10 % change in slope), prior to attaining the failure force.3.2.4 nominal value, na value, existing in name only, assigned to a measurable property for the purpose of convenientdesignation. Tolerances may be applied to a nominal value to define an acceptable range for the property.3.2.5 pr
25、incipal material coordinate system, na coordinate system with axes that are normal to the planes of symmetry inherentto a material.3.2.5.1 DiscussionCommon usage, at least for Cartesian axes (123, xyz, and so forth), generally assigns the coordinate system axes to the normaldirections of planes of s
26、ymmetry in order that the highest property value in a normal direction (for elastic properties, the axis ofgreatest stiffness) would be 1 or x, and the lowest (if applicable) would be 3 or z. Anisotropic materials do not have a principalmaterial coordinate system due to the total lack of symmetry, w
27、hile, for isotropic materials, any coordinate system is a principalmaterial coordinate system. In laminated composites, the principal material coordinate system has meaning only with respect toan individual orthotropic lamina. The related term for laminated composites is “reference coordinate system
28、.”3.2.6 reference coordinate system, na coordinate system for laminated composites used to define ply orientations. One of thereference coordinate system axes (normally the Cartesian x-axis) is designated the reference axis, assigned a position, and the plyprincipal axis of each ply in the laminate
29、is referenced relative to the reference axis to define the ply orientation for that ply.3.2.7 rupture, nseparation of the fastener and test laminate, caused by failure of the fastener, the composite plate, or both.Rupture is characterized by an extreme force drop, such that the specimen is incapable
30、 of carrying significant applied force.3.2.8 specially orthotropic, adja description of an orthotropic material as viewed in its principal material coordinate system.In laminated composites, a specially orthotropic laminate is a balanced and symmetric laminate of the 0i/90jns family as viewedfrom th
31、e reference coordinate system, such that the membrane-bending coupling terms of the laminate constitutive relation arezero.3 Available from U.S. Army Research Laboratory, Materials Directorate, Aberdeen Proving Ground, MD 21001.SAE International (SAE), 400 Commonwealth Dr.,Warrendale, PA 15096, http
32、:/www.sae.orgD7332/D7332M 1523.3 Symbols:A = cross-sectional area of a specimenCV = coefficient of variation statistic of a sample population for a given property (in percent)d = fastener or pin shank diameterdcsk = countersink depthD = specimen hole diameterh = specimen thicknessl = specimen length
33、n = number of specimens per sample populationN = number of plies in laminate under testPf = failure forcePi = force carried by test specimen at initial failurePm = maximum force carried by test specimen during testsn-1 = standard deviation statistic of a sample population for a given propertyw = spe
34、cimen widthxi = test result for an individual specimen from the sample population for a given propertyx5x5 mean or average (estimate of mean) of a sample population for a given propertyi = displacement at initial failurer = displacement at rupture4. Summary of Test Method4.1 Procedure A, Compressive
35、-Loaded Fixture:4.1.1 Two flat square, constant rectangular cross-section composite plates, each containing a centrally located fastener hole, areplaced in a multi- piece multi-piece fixture that has been aligned to minimize loading eccentricities. Each plate contains fouradditional holes on the per
36、iphery to accommodate the test fixture components. The two plates are joined together by the fastener,with one plate being rotated 45 with respect to the second plate.4.1.2 The plates are pried apart by the application of compressive force transmitted through the fixture, producing a tensileloading
37、through the fastener and a compressive loading through the composite plates. Force is applied until failure of the compositespecimen, the fastener, or both occurs. Applied force and crosshead displacement are recorded while loading.4.2 Procedure B, Tensile-Loaded Fixture:4.2.1 A flat square, constan
38、t rectangular cross-section composite plate containing a centrally located fastener hole is placed ina multi-piece fixture that has been aligned to minimize loading eccentricities. The plate is joined by the fastener to a yoke, whichis designed to rotate as to avoid imparting a moment to the fastene
39、r.4.2.2 Auniaxial tensile force is applied to the yoke, imparting a tensile loading on the fastener and an out-of-plane compressiveloading on the composite plate. Force is applied until failure of the composite specimen, the fastener, or both occurs.Applied forceand crosshead displacement are record
40、ed while loading.4.3 For both procedures, preferred failure modes are those associated with failure of the composite at the fastener hole.Unacceptable failure modes include those associated with the fastener (such as head, shank, or thread failure) or failure of thecomposite away from the fastener h
41、ole.5. Significance and Use5.1 This test method is designed to produce fastener pull-through resistance data for structural design allowables, research anddevelopment. The procedures may be used to assess pull-through resistance for a variety of composite laminate thicknesses,fastener diameters, and
42、 fastener head styles. However, the flexibility of test parameters allowed by the variants makes meaningfulcomparison between datasets difficult if the datasets were not generated using identical test parameters.5.2 Early composite pull-through tests using fasteners common to metal structures led to
43、 premature joint failures, and resultedin the development of fasteners specific for composite applications. These fasteners have larger heads and tails to reducethrough-thickness compression stresses on the composite laminate.5.3 General factors that influence the mechanical response of composite la
44、minates and should therefore be reported include thefollowing: material, methods of material preparation and lay-up, specimen stacking sequence, specimen preparation, specimenconditioning, environment of testing, specimen alignment, speed of testing, time at temperature, void content, and volume per
45、centreinforcement.5.4 Specific factors that influence the pull-through resistance of composite laminates and should therefore be reported includethe following: hole diameter, fastener diameter, fastener head diameter, loading bar spacing to fastener hole diameter ratio(Procedure A), clearance hole d
46、iameter to fastener hole diameter ratio (Procedure B), diameter to thickness ratio, fastener torque,fastener or pin material, fastener or pin clearance, countersink angle and depth of countersink, type of grommet (if used), and typeD7332/D7332M 153of support fixture. Fastener pull-through resistance
47、 properties which may be determined from this test method include initialsub-critical failure force/displacement, failure force, maximum force, and rupture displacement.6. Interferences6.1 Material and Specimen PreparationPoor material fabrication practices, lack of control of fiber alignment, and d
48、amageinduced by improper specimen machining are known causes of high material data scatter in composites in general. Importantaspects of specimen preparation that contribute to data scatter include thickness variation, out-of-plane curvature, surfaceroughness, and failure to meet the dimensional tol
49、erances specified in 8.2.2.6.2 Hole PreparationBecause of the dominating presence of the filled hole, results from this test method are relativelyinsensitive to parameters that would be of concern in an unnotched tensile, compressive or flexural property test. However, sincethe filled hole dominates the strength, consistent preparation of the hole, without damage to the laminate, is important tomeaningful results. Damage caused by hole preparation will affect strength results and can reduce the calculated strength.6.3 Fastener Head Style and
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