1、Designation:D650711Standard 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 revision.
2、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 Thispracticeestablishesorientationcodesforcontinuous-fiber-reinforced composite materials.Orientationcodes are explicitly provided for tw
3、o-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:2D3518/D3518M Test Method for In-Plane She
4、ar Responseof Polymer Matrix Composite Materials by Tensile Test ofa 645 LaminateD3878 Terminology for Composite MaterialsE1309 GuideforIdentificationofFiber-ReinforcedPolymer-Matrix Composite Materials in Databases2.2 Other Documents:MIL-HDBK-17-2F,Polymer Matrix Composites,Vol 2Materials Propertie
5、s,Section 1.6.13ISO 1268-1 Fibre-reinforced PlasticsMethods of Produc-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 lam
6、inate orientation code is to providea simple,easily understood method 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-17-2F,and ISO 1268-1.4.2 The br
7、aiding orientation code provides similar informa-tion for a two-dimensional 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 la
8、yer for the laminate orientation code.Forlaminates symmetric about 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
9、three-axis of the laminate.The reference direction(0)is somewhat 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 specim
10、en configuration for which the loadingdirection is selected 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:1m1b1/2m2b2.
11、#nsbnotes(1)1This practice is under the jurisdiction of ASTM Committee D30 on CompositeMaterials and is the direct responsibility of Subcommittee D30.01 on Editorial andResource Standards.Current edition approved March 1,2011.Published April 2011.Originallyapproved in 2000.Last previous edition appr
12、oved in 2005 as D6507 00(2005).DOI:10.1520/D6507-11.2For 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.3Available fro
13、m DOD Single Stock Point,700 Robbins Ave.,Building 4D,Philadelphia,PA 19111-5094,http:/www.dodssp.daps.mil/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
14、Wright Aeronautical Laboratories,Day,OH,prepared by Rockwell Interna-tional Corp.,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
15、Conshohocken,PA 19428-2959.United States1 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,
16、2,.(see 6.1.5),n=number of 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 listed 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
