Abstract
Structural topology optimization (STO) has emerged a thriving technique to determine the optimal concept design of mechanically loaded structures. Optimized configuration can be evolved by meeting the objective of optimal material distribution in allocated design domains under strength and stiffness constraints. In this paper, STO technique is emphasized by addressing its imperative material interpolation schemes and a general mathematical formulation for maximizing the structural stiffness under static loading. Potential application of this technique is explored by developing weight optimized configuration of an operative unarmed aerial vehicle wing ribs. Analytical study is carried out to evaluate the performance of different sections of optimized configuration. Weight to strength factor of each section is estimated by determining its shape and inertia factors. Finite element analysis and analytical outcomes of optimized configuration validate its enhanced performance as compared to operative ribs.