ABSTRACT
The structural response equations of composite lamina (thin single layer) of Chapter 3 are the basis to establish the behavior of thin composite laminates, which are a combination or stack of several laminae. In general, the FRP structural members are made from multilayers of a single thin composite lamina. Different fiber orientations, materials (fiber/fabric types), and stacking sequences for a laminate formulation are a few of the many parameters necessary to obtain the required properties of structural elements (flanges and webs) or complete cross sections such as wide flange, circular, hollow rectangular, or other shapes. The FRP structural element or member properties vary with several parameters, as stated previously. To study the structural response influence from these parameters, the classical lamination theory (CLT) was developed (Jones, 1975). Technical details of CLT relating to strength and stiffness equations as functions of constituent material properties, and associated examples for different elements and members are presented in this chapter.
