Optimization of Light Weight Aircraft Wing Structure


In this paper, the static analysis for finding the optimum design of wing structure has been performed. The two types of wings for unmanned airplanes were chosen; the first wing was the taper designed at (M=0.71) and the other wing was rectangular designed at (M=0.21).
The research covers both the aerodynamic and structural design. The aerodynamic
study was achieved by using the vortex lattice method and the structural analysis was
achieved by using the Ansys 5.4 package where isotropic and composite materials were
From results the mass saving of (32%) when composite material is used instead of isotropic material for the taper wing and (23%) for the rectangle wing. The optimum design for each wing was obtained according to the mass, stress and displacement.