A.3 ALTERNATIVE EQUATIONS FOR THE ELASTIC AND THERMAL PROPERTIES OF A LAMINA Property Chamis [1] Tsai-Hahn [2] Eu Same as Equation 3.36 Same as Equation 3.36 E22 ErEm (Vr+m2vm)ErEm Er-VVi(Er -Em) (EmnVr +722VmEr) GGm G12 (Vr+m2Vm)GrGm Gr-VVE(Gr-Gm) (GmV:+712VmGr) 12 Same as Equation 3.37 Same as Equation 3.37 11 Same as Equation 3.58 a2 an Vi (1-V)(1+Eul) E K陆 Krve+Km(1-vr) Kz ViKr Km (1-)Km+K(K:-Ka) Note:In Tsai-Hahn equations for E22 and Gi2,n22 and n2 are called stress-partitioning parameters.They can be determined by fitting these equations to respective experimental data. Typical values of nz2 and m2 for epoxy matrix composites are: Fiber Type Carbon Glass Kevlar-49 722 0.5 0.516 0.516 12 0.4 0.316 0.4 Thermal conductivity. REFERENCES 1.C.C.Chamis,Simplified composite micromechanics equations for hygral,thermal and mechanical properties,SAMPE Quarterly.15:14(1984). 2.S.M.Tsai and H.T.Hahn,Introduction to Composite Materials,Technomic Publish- ing Co.,Lancaster,PA (1980). 2007 by Taylor Francis Group,LLC.REFERENCES 1. C.C. Chamis, Simplified composite micromechanics equations for hygral, thermal and mechanical properties, SAMPE Quarterly, 15:14 (1984). 2. S.M. Tsai and H.T. Hahn, Introduction to Composite Materials, Technomic Publish￾ing Co., Lancaster, PA (1980). A.3 ALTERNATIVE EQUATIONS FOR THE ELASTIC AND THERMAL PROPERTIES OF A LAMINA Property Chamis [1] Tsai–Hahn [2] E11 Same as Equation 3.36 Same as Equation 3.36 E22 EfEm Ef
ffiffiffiffi vf p (Ef
Em) (vf þ h22vm)EfEm (Emvf þ h22vmEf) G12 GfGm Gf
ffiffiffiffi vf p (Gf
Gm) (vf þ h12vm)GfGm (Gmvf þ h12vmGf) n12 Same as Equation 3.37 Same as Equation 3.37 a11 Same as Equation 3.58 a22 afT ffiffiffiffi vf p þ(1
ffiffiffiffi vf p ) 1 þ vfnm Ef E11
am K* 11 Kfvf þ Km(1
vf) K22 (1
ffiffiffiffi vf p )Km þ ffiffiffiffi vf p KfKm Kf
ffiffiffiffi vf p (Kf
Km) Note: In Tsai–Hahn equations for E22 and G12, h22 and h12 are called stress-partitioning parameters. They can be determined by fitting these equations to respective experimental data. Typical values of h22 and h12 for epoxy matrix composites are: Fiber Type Carbon Glass Kevlar-49 h22 0.5 0.516 0.516 h12 0.4 0.316 0.4 * Thermal conductivity.
2007 by Taylor & Francis Group, LLC.