Levy Flight Equilibrium Optimizer–Based Wing Design Optimization Using Functional Constraints

Abstract

This paper presents wing design optimization with functional constraints using the proposed method. The proposed method is an equilibrium optimizer (EO), and it is motivated by controlling the volume mass balance method to calculate both equilibrium and dynamic states. A well-defined generation rate term is verified to strengthen the capability of the EO at exploitation and exploration. Here, the EO’s updating behavior is enhanced by Levy flight. Hence, it is named as Levy flight–based equilibrium optimizer (LFEO). The analysis device of aerodynamics is intended by combining the numerical nonlinear lifting-line method to attain the coefficients of lift and drag of the baseline wing. The proposed method is utilized for solving restricted optimization problems, and three various optimization problems are solved. The functional restrictions are connected to wing weight, wing plan form area, and root bending moment, which is included in the first optimization issue, and then the second optimization issue is created. The third optimization issue is attained by including to the second issue the state of level flight and minimum speed of the baseline unmanned air vehicle (UAV) at the maximum speed of level flight and obtainable power restrictions. It shows that describing the moment of root bending, wing area, and obtainable power restrictions at aerodynamic optimization issues may lead to various realistic wing-plane and airfoil shapes. Finally, the proposed method is implemented using MATLAB or Simulink and it is compared with existing techniques such as EO and genetic algorithm (GA).