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3.3 Laminate notation Considering a laminate manufactured using unidirectional (UD) plies, the lay up notation is described as shown below : 0o +45o -45o 90o -45o +45o 0o Starting at the top surface (0/+45/-45/90/-45/+45/0) Figure 11 – Stacking sequence example When designing a laminate it is important to consider the stacking sequence of plies and to be aware of SYMMETRY and BALANCE of the stack. The stack above is both symmetric (about the mid plane) which helps to eliminate any tendency to bend or warp, and balanced meaning that there is an equal number of +45° & -45° plies, which reduces shear coupling. 4. Sandwich panels Single skin laminates, made from glass, carbon, aramid, or other fibers may be strong, but they can lack stiffness due to their relatively low thickness. Traditionally the stiffness of these panels has been increased by the addition of multiple frames and stiffeners, adding weight and construction complexity. A sandwich structure consists of two high strength skins separated by a core material. Inserting a core into the laminate is a way of increasing its thickness without incurring the weight penalty that comes from adding extra laminate layers. In effect the core acts like the web in an I-beam, where the web provides the lightweight ‘separator’ between the load-bearing flanges. In an I-beam the flanges carry the main tensile and compres- sive loads and so the web can be relatively lightweight. Core materials in a sandwich structure are similarly low in weight compared to the materials in the skin laminates. Engineering theory shows that the flexural stiffness of any panel is proportional to the cube of its thickness. The purpose of a core in a composite laminate is therefore to increase the laminate’s stiffness by effectively ‘thickening’ it with a low-density core material.This can provide a dramatic increase in stiffness for very little additional weight. GTC-6-0417 - 13PDF Image | GUIDE TO COMPOSITES
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