**figure screen shot attached** A composite component (such as shown in Fig.2) is required for an aerospace application. The specification for the component stipulates that it must have an Elastic Modulus in the fibre direction of at least 320 GN/m2, and the transverse direction modulus must not be less than 8 GN/m2, but with a maximum permissible density of 1650 kg/m3. In order to determine if such a composite is possible:
i) Plot (preferably using excel), the composite modulus (Ec) versus fibre volume fraction (Vf) showing upper (isostrain model – parallel to the fibres) and lower (isostress model - perpendicular to the fibres) bounds for the Epoxy/Carbon-fibre composite (data are provided in Table 2);

ii) Estimate the carbon fibre volume fraction required to achieve the above specification.
(Hint from the plot in part i) find the Vf for the required modulus [320 GPa] in the fibre direction – upper bound line, then check if the lower limit is okay, finally workout the density of the composite to see if it is within the spec – also check your answer with calculations)