1、Designation: D 6507 00 (Reapproved 2005)Standard Practice forFiber Reinforcement Orientation Codes for CompositeMaterials1This standard is issued under the fixed designation D 6507; the number immediately following the designation indicates the year oforiginal adoption or, in the case of revision, t
2、he year of last revision. A number in parentheses indicates the year of last reapproval. Asuperscript epsilon (e) indicates an editorial change since the last revision or reapproval.1. Scope1.1 This practice establishes orientation codes forcontinuous-fiber-reinforced composite materials. Orientatio
3、ncodes are explicitly provided for two-dimensional laminatesand braids. The laminate code may also be used for filament-wound materials.Amethod is included for presenting subscriptinformation in computerized formats that do not permit sub-script notation.2. Referenced Documents2.1 ASTM Standards:2D
4、3878 Terminology for Composite MaterialsE 1309 Guide for Identification of Fiber-Reinforced Poly-mer Matrix Composite Materials in Databases2.2 Other Documents:MIL-HDBK-17-2D, Polymer Matrix Composites,Vol2Materials Properties, Section 1.6.13ISO 1268-1 Fibre-reinforced PlasticsMethods of Produc-ing
5、Test PlatesPart 1: General Conditions, AnnexStacking Designation Systems43. Terminology3.1 DefinitionsDefinitions in accordance with Terminol-ogy D 3878 shall be used where applicable.4. Significance and Use4.1 The purpose of a laminate orientation code is to providea simple, easily understood metho
6、d 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,5MIL-HDBK-17, and ISO 1268-1.4.2 The braiding orientation code provides similar informa-tion for a two-dimen
7、sional 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 abou
8、t 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 somew
9、hat 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 in-plane shear specimensin which the loading direction is selected as 0.6. Laminate Orientation
10、 (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 on CompositeMaterials and is the
11、 direct responsibility of Subcommittee D30.01 on Editorial andReference Standards.Current edition approved Oct. 1, 2005. Published October 2005. Originallyapproved in 2000. Last previous edition approved in 2000 as D 6507 00.2For referenced ASTM standards, visit the ASTM website, www.astm.org, orcon
12、tact 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 DOD Single Stock Point, 700 Robbins Ave., Building 4D,Philadelphia, PA 19111-5094, http:/www.dodssp.daps.mil/4Available
13、from American National Standards Institute (ANSI), 25 W. 43rd St.,4th Floor, New York, NY 10036.5NASA/DOD Advanced Composites Design Guide, Vol 4, Section 4.0.5, AirForce Wright Aeronautical Laboratories, Day, OH, prepared by Rockwell Interna-tional Corp., 1983 (distribution limited).6Masters, J. E.
14、, and Portanova, M. A., Standard Test Methods for TextileComposites, NASA CR-4751, NASA Langley Research Center, 1996.1Copyright ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959, United States.u1m1b1/u2m2b2.nsbnotes (1)where:u1, u2= ply orientations (degrees)
15、of the laminate stack-ing sequence (see 6.1.2),m1,m2= number of plies at each particular orientation u1,u2,.(not used for a single ply) (see 6.1.3),b1,b2= material type and form, or both, (if required) ateach particular orientation u1, u2,.(see 6.1.5),n = number of repetitions of the bracketed group
16、 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 listed in order from the reference pla
17、ne 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 lamina and the referencedirection. When
18、 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 of angles is used with allangles in
19、the range 90 $ u 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 the first ply. For example,+45/45/
20、45/+45 is the same as 6 45/145.6.1.3 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.See Example 4 in Fig. 1.6.1.4 Whe
21、n 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 necessary to describe thelaminate may be
22、 used within the square brackets. The entire setof laminae within the square brackets may be repeated asFIG. 1 Examples of Laminate Orientation CodeD 6507 00 (2005)2indicated by an optional final set of subscripts outside theclosing bracket. For example:Full: 0/60/-60/0/90/0/90/0/60/-60/0/90/0/90/90
23、/0/90/0/-60/60/0/90/0/90/0/-60/60/0Condensed: 0/660)/(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 subscript (for example, “f”
24、) 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 code.6.1.6 All symmetry
25、 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 midplane isindicated by o
26、verlining 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 indicated.6.1.7 Additiona
27、l 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 arerecommended based on Guide E 130
28、9. This form is included inFig. 1, except for laminate orientation codes that require nomodification.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 thep
29、ly, for example, 0/45/90:s.6.2.3 Plus-minus (6) and minus-plus 1! symbols arereplaced 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 Orient
30、ation 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:0m1/6um2.nN notes (2)where:u = braid angle,m1= number of fibers in the axial yarn bundles
31、 (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 a pr
32、eform 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 braider
33、 yarns is calculatedfrom the axial yarn length (lA) and the braid angle (BA)asfollows:lB5 2lA/cos BA! (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 leng
34、th (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) asf
35、ollows:N 5 AA/$2 AB/cos BA!# 1 AA% (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/cos BA!# 1 nA% (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
37、Braiding Orientation CodeBraid CodeAxial YarnSize, kBraidAngle, BraidedYarn Size, kNumber ofLayersAxial YarnContent, %030k/6706k363 % 30 670 6 3 63012k/6606k533 % 12 660 6 5 33D 6507 00 (2005)3ASTM International takes no position respecting the validity of any patent rights asserted in connection wi
38、th any item mentionedin 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 tech
39、nical committee and must be reviewed every five years andif not revised, either reapproved or withdrawn. Your comments are invited either for revision of this standard or for additional standardsand should be addressed to ASTM International Headquarters. Your comments will receive careful considerat
40、ion at a meeting of theresponsible technical committee, which you may attend. If you feel that your comments have not received a fair hearing you shouldmake your views known to the ASTM Committee on Standards, at the address shown below.This standard is copyrighted by ASTM International, 100 Barr Ha
41、rbor Drive, PO Box C700, West Conshohocken, PA 19428-2959,United States. Individual reprints (single or multiple copies) of this standard may be obtained by contacting ASTM at the aboveaddress or at 610-832-9585 (phone), 610-832-9555 (fax), or serviceastm.org (e-mail); or through the ASTM website(www.astm.org).D 6507 00 (2005)4
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