ASTM D6507-00(2005)

Standard Practice for Fiber Reinforcement Orientation Codes for Composite Materials

SIGNIFICANCE AND USE
The purpose of a laminate orientation code is to provide a simple, easily understood method of describing the lay-up of a laminate. The laminate orientation code is based largely on a combination of industry practice and the codes used in the NASA/DOD Advanced Composites Design Guide,5 MIL-HDBK-17, and ISO 1268-1.
The braiding orientation code provides similar information for a two-dimensional braid, based largely on Standard Test Methods for Textile Composites.6
SCOPE
1.1 This practice establishes orientation codes for continuous-fiber-reinforced composite materials. Orientation codes are explicitly provided for two-dimensional laminates and braids. The laminate code may also be used for filament-wound materials. A method is included for presenting subscript information in computerized formats that do not permit subscript notation.

General Information

• Status: Historical
• Publication Date: 30-Sep-2005
• ICS: 65.020.20 - Plant growing
• Technical Committee: D30 - Composite Materials
• Drafting Committee: D30.01 - Editorial and Resource Standards

Relations

• Replaces: ASTM D6507-00 - Standard Practice for Fiber Reinforcement Orientation Codes for Composite Materials
• Effective Date: 01-Oct-2005
• Replaced By: ASTM D6507-11 - Standard Practice for Fiber Reinforcement Orientation Codes for Composite Materials
• Effective Date: 01-Mar-2011
• Referred By: ASTM C1793-15 - Standard Guide for Development of Specifications for Fiber Reinforced Silicon Carbide-Silicon Carbide Composite Structures for Nuclear Applications
• Effective Date: 01-Oct-2005
• Referred By: ASTM D7750-23 - Standard Test Method for Cure Behavior of Thermosetting Resins by Dynamic Mechanical Procedures using an Encapsulated Specimen Rheometer
• Effective Date: 01-Oct-2005
• Referred By: ASTM C1783-15 - Standard Guide for Development of Specifications for Fiber Reinforced Carbon-Carbon Composite Structures for Nuclear Applications
• Effective Date: 01-Oct-2005
• Referred By: ASTM D8335-20 - Standard Guide for Identification of Fiber-Reinforced Polymer-Matrix Composite Materials
• Effective Date: 01-Oct-2005
• Referred By: ASTM D4762-18 - Standard Guide for Testing Polymer Matrix Composite Materials
• Effective Date: 01-Oct-2005
• Referred By: ASTM C1835-16(2023) - Standard Classification for Fiber Reinforced Silicon Carbide-Silicon Carbide (SiC-SiC) Composite Structures
• Effective Date: 01-Oct-2005
• Referred By: ASTM C1836-16(2023) - Standard Classification for Fiber Reinforced Carbon-Carbon Composite Structures
• Effective Date: 01-Oct-2005
• Referred By: ASTM D8066/D8066M-23 - Standard Practice Unnotched Compression Testing of Polymer Matrix Composite Laminates
• Effective Date: 01-Oct-2005

Standards Content (Sample)

NOTICE: This standard has either been superseded and replaced by a new version or withdrawn.
Contact ASTM International (www.astm.org) for the latest information
Designation:D6507–00 (Reapproved 2005)
Standard Practice for
Fiber Reinforcement Orientation Codes for Composite
Materials
This standard is issued under the fixed designation D6507; the number immediately following the designation indicates the year of
original adoption or, in the case of revision, the year of last revision. A number in parentheses indicates the year of last reapproval. A
superscript epsilon (´) indicates an editorial change since the last revision or reapproval.
1. Scope 4. Significance and Use
1.1 This practice establishes orientation codes for 4.1 The purpose of a laminate orientation code is to provide
continuous-fiber-reinforced composite materials. Orientation a simple, easily understood method of describing the lay-up of
codes are explicitly provided for two-dimensional laminates a laminate. The laminate orientation code is based largely on a
and braids. The laminate code may also be used for filament- combination of industry practice and the codes used in the
wound materials.Amethod is included for presenting subscript NASA/DOD Advanced Composites Design Guide, MIL-
information in computerized formats that do not permit sub- HDBK-17, and ISO 1268-1.
script notation. 4.2 The braiding orientation code provides similar informa-
tion for a two-dimensional braid, based largely on Standard
2. Referenced Documents 6
Test Methods for Textile Composites.
2.1 ASTM Standards:
5. Reference System
D3878 Terminology for Composite Materials
E1309 Guide for Identification of Fiber-Reinforced 5.1 A reference plane and direction are selected before
Polymer-Matrix Composite Materials in Databases writing the orientation code. The reference plane is selected as
2.2 Other Documents: the bottom or top layer for the laminate orientation code. For
MIL-HDBK-17-2D, Polymer Matrix Composites,Vol 2 laminates symmetric about their midplane, the orientation code
Materials Properties, Section 1.6.1 using the top layer as the reference plane is identical to the
ISO 1268-1 Fibre-reinforced Plastics—Methods of Produc- orientation code using the bottom layer as the reference plane;
ing Test Plates—Part 1: General Conditions, Annex selection of the reference plane effectively determines the
Stacking Designation Systems positive z-orthree-axisofthelaminate.Thereferencedirection
(0°) is somewhat arbitrarily selected for convenience and
3. Terminology
relevance to the application. Often, a dominant fiber direction
3.1 Definitions—Definitions in accordance with Terminol-
is defined to be 0°. An example in which relevance to testing
ogy D3878 shall be used where applicable. determines the reference direction is in-plane shear specimens
in which the loading direction is selected as 0°.
This practice is under the jurisdiction ofASTM Committee D30 on Composite
6. Laminate Orientation (Lay-up) Code
Materials and is the direct responsibility of Subcommittee D30.01 on Editorial and
6.1 The following information and the examples in Fig. 1
Reference Standards.
Current edition approved Oct. 1, 2005. Published October 2005. Originally
describe the laminate orientation code. Ply directions and
approved in 2000. Last previous edition approved in 2000 as D6507 – 00. DOI:
number of layers are indicated using the laminate orientation
10.1520/D6507-00R05.
2 code as follows:
For referenced ASTM standards, visit the ASTM website, www.astm.org, or
contact ASTM Customer Service at [e-mail]. For Annual Book of ASTM
Standards volume information, refer to the standard’s Document Summary page on
the ASTM website. NASA/DOD Advanced Composites Design Guide, Vol 4, Section 4.0.5, Air
Available from DOD Single Stock Point, 700 Robbins Ave., Building 4D, Force Wright Aeronautical Laboratories, Day, OH, prepared by Rockwell Interna-
Philadelphia, PA 19111-5094, http://www.dodssp.daps.mil/ tional Corp., 1983 (distribution limited).
4 6
Available from American National Standards Institute (ANSI), 25 W. 43rd St., Masters, J. E., and Portanova, M. A., Standard Test Methods for Textile
4th Floor, New York, NY 10036. Composites, NASA CR-4751, NASA Langley Research Center, 1996.
Copyright © ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959, United States.
D6507–00 (2005)
FIG. 1 Examples of Laminate Orientation Code
@u m b /u m b .] notes (1)
measured between the warp direction and the reference direc-
1 1 1 2 2 2 nsb
tion. Positive angles are measured counter-clockwise from the
where:
reference direction when looking toward the lay-up surface
u , u = ply orientations (degrees) of the laminate stack-
1 2
(right-hand rule). A consistent range of angles is used with all
ing sequence (see 6.1.2),
angles in the range 90$ u > –90. Orientations of successive
m ,m = number of plies at each particular orientation u ,
1 2 1
laminae with different values are separated by a virgule (/).
u,. (not used for a single ply) (see 6.1.3),
Pairs of plies of equal and opposite angle may be indicated by
b ,b = material type and form, or both, (if required) at
1 2
plus-minus (6) and minus-plus ~1! symbols, where the top of
each particular orientation u , u ,. (see 6.1.5),
1 2
n = number of repetitions of the bracketed group of the symbol indicates the direction of the first ply. For example,
plies (see 6.1.4),
[+45/–45/–45/+45] is the same as @ 6 45/145].
s = indication of geometric symmetry (see 6.1.6),
6.1.3 Plysymbolsfortwoormoreadjacentlaminaewiththe
and
same orientation and material system can be condensed by
b = indicator of material type and form, or both, (if
writing the common angle (and material form, if necessary)
required) for an abbreviated group of plies.
followed by a subscript equal to the number of identical plies.
All subscripts are lowercase with the exception of ‘T’ for
See Example 4 in Fig. 1.
total (see 6.1.6).
6.1.4 When a laminate contains repeated and adjacent
6.1.1 Laminae are listed in order from the reference plane to
subsets of laminae, the code can be shortened by enclosing
the opposite side of the laminate. Square brackets are used to
each subset in parentheses with the closing parentheses fol-
indicate the beginning and the end of the code.
lowed by n, s, and b subscripts that apply to the entire subset,
6.1.2 The orientation of each lamina with respect to the
as appropriate
...