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2.3 Fibre orientation It is rare for fibres in a composite laminate to be perfectly aligned. Woven fabrics in- troduce a crimp to fibres which causes misalignment of load paths. Even non woven fabrics can suffer from some crimping around stitch points. The misalignment of fibres causes dramatic loss of mechanical properties, particularly in compression, due to increased likelihood of buckling. When using unidirectional fabrics, tapes or tows, it becomes critical to ensure accurate alignment of fibres during component manufacture to ensure loads are transferred efficiently and to maximize the advantages of utilizing composite materials. 2.4 Fatigue Resistance Generally composites show excellent fatigue resistance when compared with most metals. However, since fatigue failure tends to result from the gradual accumulation of small amounts of damage, the fatigue behaviour of any composite will be influenced by the toughness of the resin, its resistance to microcracking, and the quantity of voids and other defects which occur during manufacture. As a result, epoxy-based laminates tend to show very good fatigue resistance when compared with both polyester and vinylester, this being one of the main reasons for their use in aircraft structures. 3. Monolithic laminates Most composite structures are built up into useful sections by stacking plies of fibre or fabric onto each other. Since the orientation of the fibres can be varied, the properties of the laminate are not consistent through the thickness of the part, and are considered highly anisotropic in all 3 planes. 3.1 Rule of mixtures Whilst deformation of homogeneous, isotropic materials can be described relatively simply by use ofYoungs and Shear moduli, which are bulk properties of the raw material simple properties of composite materials can be estimated based on the contribution of each part of the composite. This method is referred to as the rule of mixtures (RoM). For a 2 component composite: Vf + Vm =1 where Vf = Volume fraction fibre Vm = Volume fraction matrix 10 - GTC-6-0417PDF Image | GUIDE TO COMPOSITES
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