1、Designation: D6507 16Standard Practice forFiber Reinforcement Orientation Codes for CompositeMaterials1This standard is issued under the fixed designation D6507; the number immediately following the designation indicates the year oforiginal adoption or, in the case of revision, the year of last revi
2、sion. A number in parentheses indicates the year of last reapproval. Asuperscript epsilon () indicates an editorial change since the last revision or reapproval.1. Scope1.1 This practice establishes orientation codes forcontinuous-fiber-reinforced composite materials. Orientationcodes are explicitly
3、 provided for two-dimensional laminatesand braids. The laminate code may also be used for filament-wound materials. A method is included for presenting subscriptinformation in computerized formats that do not permit sub-script notation.2. Referenced Documents2.1 ASTM Standards:2D3518/D3518M Test Met
4、hod for In-Plane Shear Responseof Polymer Matrix Composite Materials by Tensile Test ofa 645 LaminateD3878 Terminology for Composite Materials2.2 Other Documents:CMH-17-2G, Polymer Matrix Composites, Volume 2 Ma-terials Properties, Section 1.6.13ISO 1268-1 Fibre-reinforced PlasticsMethods of Produc-
5、ing Test PlatesPart 1: General Conditions, AnnexStacking Designation Systems43. Terminology3.1 DefinitionsDefinitions in accordance with Terminol-ogy D3878 shall be used where applicable.4. Significance and Use4.1 The purpose of a laminate orientation code is to providea simple, easily understood me
6、thod of describing the lay-up ofa laminate. The laminate orientation code is based largely on acombination of industry practice and the codes used in theNASA/DOD Advanced Composites Design Guide,5CMH-17-2G, and ISO 1268-1.4.2 The braiding orientation code provides similar informa-tion for a two-dime
7、nsional braid, based largely on StandardTest Methods for Textile Composites.65. Reference System5.1 A reference plane and direction are selected beforewriting the orientation code. The reference plane is selected asthe bottom or top layer for the laminate orientation code. Forlaminates symmetric abo
8、ut their midplane, the orientation codeusing the top layer as the reference plane is identical to theorientation code using the bottom layer as the reference plane;selection of the reference plane effectively determines thepositive z- or three-axis of the laminate. The reference direction(0) is some
9、what arbitrarily selected for convenience andrelevance to the application. Often, a dominant fiber directionis defined to be 0. An example in which relevance to testingdetermines the reference direction is the D3518/D3518Min-plane shear specimen configuration for which the loadingdirection is select
10、ed as 0.6. Laminate Orientation (Lay-up) Code6.1 The following information and the examples in Fig. 1describe the laminate orientation code. Ply directions andnumber of layers are indicated using the laminate orientationcode as follows:1This practice is under the jurisdiction of ASTM Committee D30 o
11、n CompositeMaterials and is the direct responsibility of Subcommittee D30.01 on Editorial andResource Standards.Current edition approved July 1, 2016. Published July 2016. Originally approvedin 2000. Last previous edition approved in 2011 as D6507 11. DOI: 10.1520/D6507-16.2For referenced ASTM stand
12、ards, 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.3Available from SAE International (SAE), 400 Commonwealth Dr., Warrendale,PA 15096, htt
13、p:/www.sae.org.4Available from American National Standards Institute (ANSI), 25 W. 43rd St.,4th Floor, New York, NY 10036, http:/www.ansi.org.5NASA/DOD Advanced Composites Design Guide, Vol. 4, Section 4.0.5, AirForce Wright Aeronautical Laboratories, Day, OH, prepared by Rockwell Interna-tional Cor
14、p., 1983(distribution limited).6Masters, J. E., and Portanova, M. A., Standard Test Methods for TextileComposites, NASA CR-4751, NASA Langley Research Center, 1996Copyright ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959. United States11m1b1/2m2b2.#nsbnotes (
15、1)where:1, 2= ply orientations (degrees) of the laminate stackingsequence (see 6.1.2),m1,m2= number of plies at each particular orientation 1,2,.(not used for a single ply) (see 6.1.3),b1,b2= material type and form, or both, (if required) ateach particular orientation 1, 2,.(see 6.1.5),n = number of
16、 repetitions of the bracketed group ofplies (see 6.1.4),s = indication of geometric symmetry (see 6.1.6), andb = indicator of material type and form, or both, (ifrequired) for an abbreviated group of plies.All subscripts are lowercase with the exception of T fortotal (see 6.1.6).6.1.1 Laminae are li
17、sted in order from the reference plane tothe opposite side of the laminate. Square brackets are used toindicate the beginning and the end of the code.6.1.2 The orientation of each lamina with respect to thereference direction is indicated by the angle between theprincipal fiber direction of that lam
18、ina and the referencedirection. When indicating the lay-up of a weave, the angle ismeasured between the warp direction and the reference direc-tion. Positive angles are measured counter-clockwise from thereference direction when looking toward the lay-up surface(right-hand rule). A consistent range
19、of angles is used with allangles in the range 90 90. Orientations of successivelaminae with different values are separated by a virgule (/).Pairs of plies of equal and opposite angle may be indicated byplus-minus (6) and minus-plus 1! symbols, where the top ofthe symbol indicates the direction of th
20、e first ply. For example,+45/45/45/+45 is the same as 645/145#.6.1.3 Ply symbols for two or more adjacent laminae with thesame orientation and material system can be condensed bywriting the common angle (and material form, if necessary)followed by a subscript equal to the number of identical plies.S
21、ee Example 4 in Fig. 1.6.1.4 When a laminate contains repeated and adjacentsubsets of laminae, the code can be shortened by enclosingeach subset in parentheses with the closing parentheses fol-lowed by n, s, and b subscripts that apply to the entire subset,as appropriate. As many subsets as necessar
22、y to describe thelaminate may be used within the square brackets. The entire setof laminae within the square brackets may be repeated asFIG. 1 Examples of Laminate Orientation CodeD6507 162indicated by an optional final set of subscripts outside theclosing bracket. For example:Full: 0/60/-60/0/90/0/
23、90/0/60/-60/0/90/0/90/90/0/90/0/-60/60/0/90/0/90/0/-60/60/0Condensed: 0/60/(0/90)22s6.1.5 The convention used for indicating materials with theb subscript is no subscript for a tape ply and a subscript of “f”for a weave (fabric). If the entire lay-up contains one type oflamina, the appropriate subsc
24、ript (for example, “f”) may followthe closing square bracket. The laminate code for an interplyhybrid has the different materials contained in the laminateindicated by unique subscripts on the laminae. The relationbetween subscript and material type must be identified in thenotes at the end of the c
25、ode.6.1.6 All symmetry considered in this document is about themidplane of the laminate. A subscript of “s” is used if the firsthalf of the lay-up is indicated and the second half is symmetricwith the first. When a symmetric lay-up with an odd number oflaminae is shown, the layer bisected by the mid
26、plane isindicated by overlining the angle of that lamina. The strictinterpretation of this notation is that half of that lamina lieswithin each of the two parts of the symmetric laminate. Wherethe subscript s is not used, a subscript T (for total) may beused to indicate that the entire lay-up is ind
27、icated.6.1.7 Additional notes to describe orientation of ply faces,identification of materials used in the laminate, and so on, mayappear at the end of the orientation code.6.2 Since many computer programs do not permit the use ofsubscripts and superscripts, the following modifications arerecommende
28、d. This form is included in Fig. 1, except forlaminate orientation codes that require no modification.6.2.1 Subscript information is preceded by a colon (:), forexample, 90/0:2/45:s.6.2.2 A bar over a ply (designating a nonrepeated ply in asymmetric laminate) is indicated by a backslash () after the
29、ply, for example, 0/45/90:s.6.2.3 Plus-minus (6) and minus-plus (+) symbols are re-placed by “+ ” or “ +.”6.3 This lay-up code may also be used for filament-woundmaterials in which the 0 direction is usually the winding axisof symmetry, and the reference plane is usually the toolsurface.7. Braiding
30、Orientation Codes7.1 The following information describes the two-dimensional braiding orientation code.7.1.1 Fiber direction, yarn size, and number of layers areindicated using the following braiding orientation code:0m1/6m2.#nN notes (2)where: = braid angle,m1= number of fibers in the axial yarn bu
31、ndles (k used forthousands),m2= number of fibers in the braided yarn bundles (k usedfor thousands),n = number of braided layers in a laminate, andN = volume percentage of axial yarns in the preform.7.1.2 Volume percentage of axial yarns in the preformprovides an indication of the relative modulus of
32、 a preform inthe principal axial directions. The volume percentage is calcu-lated from information about the braider yarns and the axialyarn. In a two-dimensional triaxial braid, there are two braideryarns and one axial yarn in a unit. Choosing a unit volume, thetotal (combined) length of the two br
33、aider yarns is calculatedfrom the axial yarn length (lA) and the braid angle (BA)asfollows:lB5 2lA/cosBA! (3)The total braider yarn content (assuming unit thickness) isthe total braider yarn length times the cross-sectional area ofthe braider yarn (AB). The total axial yarn content is the axialyarn
34、length (l) times the cross-sectional area of the axial yarn(AA). The total yarn content is the sum of these two computa-tions. The percentage of axial yarn in the preform is then thetotal axial yarn content divided by the total yarn content (thesum of the total axial and total braider yarn contents)
35、 asfollows:N 5 AA/$2 AB/cosBA!#1AA% (4)If the same fiber (that is, AS4, IM6, and so forth) is used inthe axial and braider yarns, the cross-sectional areas areproportional to the number of fibers in the yarns. Given thissimplification, the equation to compute the axial yarn contentsis as follows:N 5
36、 nA/$2 nB/cosBA!#1nA% (5)Note, this computation ignores yarn crimp and jamming ofthe yarn bundles.7.1.3 Examples in Table 1 illustrate the use of the braidingorientation code.8. Keywords8.1 composite materials; continuous-fiber-reinforced com-posite materials; orientation codesTABLE 1 Examples of Br
37、aiding Orientation CodeBraid CodeAxial YarnSize, kBraidAngle, BraidedYarn Size, kNumber ofLayersAxial YarnContent, %030k/706k363 % 30 70 6 3 63012k/606k533 % 12 60 6 5 33D6507 163ASTM International takes no position respecting the validity of any patent rights asserted in connection with any item me
38、ntionedin this standard. Users of this standard are expressly advised that determination of the validity of any such patent rights, and the riskof infringement of such rights, are entirely their own responsibility.This standard is subject to revision at any time by the responsible technical committe
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