Search

This paper demonstrates design of a commercial aircraft at the conceptual design stage by considering 2 objective functions i.e. minimization of aircraft maximum takeoff weight and maximization of lift-to-drag ratio multi-objective evolutionary algorithms (MOEAs). Dynamic stability is taken as a design constraint while design variables include geometrical properties of the plane, consisting of the wing, empennage and fuselage. The aerodynamic coefficients of flight were calculated by using SUAVE (Aerospace Conceptual Design Environment) whereas dynamic stability analysis was achieved through using Athena vortex lattice (AVL) software. Pareto front obtained from various MOEAs are compared by Hypervolume. MOEAs are contained as MOEA / D, Two-Arch2, RPBILDE, PICEA-g, KnEA/A-ENS and KnEA. The obtained solutions for aircraft can be used for further design in the preliminary design stage. [ABSTRACT FROM AUTHOR]