Page 284 - Mechanics Analysis Composite Materials

Chapter 5. Mechanics of laminates 269
0 in unidirectional plies of a hoop layer (4 = go"),

Finally, the stresses can be obtained with the aid of Eqs. (5.72). For the cylinder
under study, we get:
0 in the angle-ply layer,

T T T
GI' = f0.41-, r~f= ~0.068-, = 0.025- ;
R2h R2h R2h
0 in the hoop layer,

-
YO -
,,90 , - G., - 0, q; =0.082- T ,
R2h
where h = 1.22 mm is the total thickness of the laminate.

5.12. References
Aleksandrov, A.Ya., Brukker, L.E., Kurshin, L.M. and Prusakov, A.P. (1960). Analysis of Sundwich
Plates. Mashinostroenie, Moscow (in Russian).
Ashton, J.E. (1 969). Approximate solutions for unsymmetrically laminated plates. J. Composite Mater.
189-191.
Chen. H.-J. and Tsai, S.W. (1996). Three-dimensional effective moduli of symmetric laminates.
J. Composite Mater. 30(8).
Karmishin, A.V. (1 974). Equations for nonhomogeneous thin-walled elements based on minimum
stiffnesses. App. Mech. (Prikladnaya Mekhanika), 10(6), 34-42 (in Russian).
Vasiliev. V.V. (1993). Mechanics of Composite Structures. Taylor & Francis, Washington.
Verchery, G. (1999). Designing with anisotropy. Part 1: Methods and general results for laminates. In
Proc. 12th International Conference on Composite Materials (ICCM-12),Paris, France, 5-9 July 1999.
ICCMIZ/TCA (CD-ROM), 1 Ip.
Whitney. J.M. (1987). Structural Ana1ysi.s of Laminated Anisotropic Plates. Technomic Publishing Co.,
Inc.. Lancaster. PA, USA.