Composite Material Reference

Free reference guide: Composite Material Reference

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About Composite Material Reference

The Composite Material Reference is a searchable engineering database covering fiber and matrix properties, lamina-level mechanical data, lamination theory, failure criteria, and manufacturing processes. The fiber/matrix section includes property cards for seven reinforcement materials — T300, T700S, and M55J carbon fibers, E-Glass and S-Glass fibers, Kevlar 49 aramid, and Hexcel 3501-6 aerospace epoxy — with tensile strength, modulus, elongation, density, filament diameter, Tg values, and cure conditions.

The prepreg/lamina section provides complete unidirectional lamina properties at 60% fiber volume fraction for T300/3501-6, AS4/3501-6, and E-Glass/Epoxy systems including all nine engineering constants (E1, E2, G12, v12, Xt, Xc, Yt, Yc, S12), ply thickness, and coefficients of thermal expansion. Fabric prepreg data for T300 plain weave is also included with comparisons between plain weave, twill, and satin fabric architectures. The lamination theory section covers layup notation conventions, Classical Lamination Theory (CLT) constitutive equations, ABD matrix engineering interpretation, and effective elastic constant calculation from the ABD inverse.

Six major failure criteria are documented with complete mathematical formulations: Tsai-Wu quadratic interaction criterion with safety factor calculation, Tsai-Hill, Maximum Stress, Maximum Strain, Hashin four-mode criterion (built into ABAQUS), and Puck action-plane criterion (recommended by European aerospace standards). The manufacturing section covers autoclave cure cycles with temperature/pressure profiles, RTM and VARTM processes, and filament winding with optimal winding angles including the 54.7-degree netting analysis result for pressure vessels.

Key Features

Seven fiber/matrix property cards: T300 (3530 MPa, 230 GPa), T700S (4900 MPa, 230 GPa), M55J (4020 MPa, 540 GPa), E-Glass (3450 MPa, 72.4 GPa), S-Glass (4580 MPa, 85.5 GPa), Kevlar 49 (3000 MPa, 112 GPa), and 3501-6 epoxy (Tg 208C dry, 154C wet)
Complete UD lamina data at 60% Vf for T300/3501-6, AS4/3501-6, and E-Glass/Epoxy including all nine constants (E1, E2, G12, v12, Xt, Xc, Yt, Yc, S12) plus ply thickness and CTE values
Fabric prepreg properties for T300 plain weave/epoxy with symmetric warp/fill properties (E1=E2=70 GPa) and comparison of plain weave, twill (2x2), and satin (5H/8H) drapeability characteristics
Laminate stacking notation conventions ([0/90/+45/-45]s, [0/90]2s, subscript T) with CLT constitutive equations from lamina [Q] matrix through rotation [Qbar] to ABD matrix assembly
ABD matrix interpretation: A (extensional), B (coupling, want B=0 for symmetric), D (bending/torsion), with A16=A26=0 balanced layup design principle
Six failure criteria with full equations: Tsai-Wu (quadratic interaction with F12 approximation), Tsai-Hill, Maximum Stress (failure mode identification), Maximum Strain, Hashin (4-mode, ABAQUS built-in), and Puck (action-plane, European aerospace standard)
Autoclave cure cycle: vacuum bagging, 120C dwell, 177C/120min cure at 0.59 MPa, 3C/min cooling rate, plus OOA alternative (MTM45-1 at 130C/180min, vacuum only)
RTM/VARTM process parameters (resin viscosity 100-500 mPa.s, Vf 50-60%) and filament winding optimal angles including 54.7-degree netting analysis for pressure vessels and product-specific layups for CNG/H2 tanks, pipes, and rocket motor cases

Frequently Asked Questions

What carbon fiber types are included?

Three Toray carbon fibers are documented: T300 standard modulus (3530 MPa strength, 230 GPa modulus, 1.5% elongation, 1.76 g/cm3 density), T700S high-strength (4900 MPa, 230 GPa, 2.1% elongation), and M55J high-modulus (4020 MPa, 540 GPa, 0.8% elongation, 1.93 g/cm3). Each includes filament diameter and typical applications from general structures through satellite and launch vehicle components.

What lamina data is available?

Complete unidirectional lamina properties are provided for T300/3501-6, AS4/3501-6, and E-Glass/Epoxy at specified fiber volume fractions. Each dataset includes E1, E2, G12, v12, Xt, Xc, Yt, Yc, S12, and ply thickness. For example, T300/3501-6 at 60% Vf: E1=181 GPa, E2=10.3 GPa, G12=7.17 GPa, Xt=Xc=1500 MPa, Yt=40 MPa, Yc=246 MPa, S12=68 MPa, 0.125 mm/ply.

How is Classical Lamination Theory presented?

CLT is presented in three steps: first the lamina stiffness matrix [Q] calculation from engineering constants, then the rotation transformation to [Qbar] for each ply angle, and finally the ABD matrix assembly through thickness integration. The ABD interpretation entry explains each submatrix: A for extensional stiffness, B for coupling (B=0 means symmetric layup with decoupled in-plane and bending), and D for bending/torsional stiffness.

What failure criteria are documented?

Six criteria are covered with complete equations: Tsai-Wu quadratic interaction criterion with strength coefficient formulas and safety factor calculation, Tsai-Hill adapted from Hill anisotropic yield, Maximum Stress with failure mode identification (fiber tension, fiber compression/microbuckling, matrix tension/transverse cracking, matrix compression, shear), Maximum Strain, Hashin four-mode criterion (built into ABAQUS for CDM integration), and Puck action-plane criterion with slope parameter pt=0.25-0.30.

How is the Hashin criterion explained?

The Hashin criterion is presented with its four separate failure modes: fiber tension ((s1/Xt)^2 + (s6/S12)^2 >= 1), fiber compression (|s1|/Xc >= 1), matrix tension ((s2/Yt)^2 + (s6/S12)^2 >= 1), and matrix compression using S23. Key advantages noted are separate failure mode identification, easy integration with Continuum Damage Mechanics (CDM), and built-in availability in ABAQUS FEA software.

What manufacturing processes are covered?

Three processes are documented: autoclave curing with a detailed 180C epoxy cycle (vacuum bagging, 120C dwell, 177C/120min cure at 0.59 MPa, 3C/min max cooling), plus OOA alternatives; RTM with resin viscosity requirements (100-500 mPa.s) and VARTM for large parts; and filament winding with hoop/helical/polar angle classifications and the netting analysis optimal angle of 54.7 degrees for pressure vessels.

Does it cover layup notation?

Yes. The reference explains the standard notation: [0/90/+45/-45]s for symmetric laminates, subscript 2 for repeated groups, subscript T for total (asymmetric) laminates, and 0-subscript for consecutive same-angle plies. It also explains the role of each angle (0 for longitudinal loads, 90 for transverse, +/-45 for shear) and emphasizes symmetric layup as essential for preventing thermal warping.

What is the effective elastic constant calculation?

For symmetric laminates (B=0), effective engineering constants are calculated from the inverse of the A matrix: Ex = 1/(t*a11), Ey = 1/(t*a22), Gxy = 1/(t*a66), vxy = -a12/a11, where t is total laminate thickness. A worked example for a [0/+45/-45/90]s quasi-isotropic T300/epoxy laminate gives Ex=Ey=55.7 GPa, Gxy=21.1 GPa, vxy=0.31.