In the present scenario of aerospace sector,udstructure weight is considered to be major factor inuddeciding the performance, efficiency etc. One of theudpotential major weight reduction contributor is theudstructural airframe. Structure optimization which deals withudthe structural weight reduction without compromisingudstrength is a complicated, time consuming and experienceudbased process.In this paper, optimisation of a criticaludbracket of flying prototype aircraft engine mount isuddemonstrated using a Finite Element(FE) basedudoptimisation software Altairoptistruct. The optimisation isudcarried in two steps. Topology optimisation, which isudanelastic energy based optimisation to search forudanoptimum material distribution followed by a sizeudoptimisationto get a final solution of the product. Theudoptimisation was carried with an objective of weightudreduction satisfying the strength requirements. As anudoutcome of this exercise, the final product ready forudrealisation is lighter in weight by around 20% compared toudthe initial design.
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