Symmetric Cross Ply Laminate

Symmetric cross ply laminated composite plat e using fem manoj narwariya 1 vinod patidar 2 and avadesh k.

Symmetric cross ply laminate. Cross ply laminates are uniquely composed of laminae with fibre orientations of 0 and 90. Thus slow stable crack growth has to be considered. This paper however concentrates on microcracking in symmetric cross ply laminates only with instantaneous unstable crack growth. The closed form solutions of anti symmetric cross ply and.

This is a thick lamina from a mechanics point of view. Unidirectional laminate the fiber angle in any ply is parallel to the fiber angle in every other ply. Since for these orientations both q. Srm 9 was designed specifically for tensile testing a 90 0 ns cross ply laminate a symmetric laminate as indicated by the subscript s with n the number of pairs of 90 and 0 plies on each side of the mid thickness of the laminate typically three pairs which results in a 12 ply laminate and closely follows astm d 3039 5 using a 25 4 mm 1 inch wide specimen.

Figure 1 illustrates the formation of the next microcrack in the. θand θplies then not only is it symmetric b 0 but also a16 a26 d16 d26 æ0 as the number of layers increases for the same laminate thickness. Similar to symmetric cross ply laminates but with higher shear stiffness and shear strength properties. Cross ply laminate the fiber angle in any ply is normal to at least one other ply and parallel to any other ply or plies i e contains only 0 and 90 plies.

For a cross ply laminate the coupling stiffness matrix. A laminate of this type will deform into a saddle shape due to residual thermal stresses as described by the equation z k x 2 y 2 where x and y are the in plane coordinates and k is the curvature. Symmetric laminates are characterized by a specific feature their bending stiffness is higher than the bending stiffness of any asymmetric laminate composed of the same layers. Sharma 3 1 research scholar sir padampat singhania univ ersity bhatewar udaipur 313 601.

Figure 1 10 a shows a typical tensile stress stain curve for a cross ply laminate. For thin transverse plies i e thicknesses typically 0 25 mm the onset strain for matrix cracking can be delayed. An anti symmetric cross ply composite laminate has two layers in which the fibers are aligned perpendicular to one another. For cross ply laminates under quasi static loading fast fracture or crack onset rapid growth of the cracks usually occurs when the applied load or strain is typically 0 4 0 6.

In this paper static and vibration analysis for anti symmetric cross ply and angle ply carbon glass hybrid laminates rectangular composite plate are presented.