Wing Structural Optimization for Electric Distributed Propulsion Aircraft using Genetic Algorithm

Resumo

The search for less polluting means of transport has been stimulating the development of batteries
with higher energy densities and electric motors that are more efficient. These advances have made possible the
emergence of several all-electric aircraft, which make use of multiple rotors. In this sense, there was a need to
create a methodology to be followed in the conceptual design phase, focused on aerodynamic and structural issues
that change in this type of aircraft. These changes, such as the lack of a Gravity Center shift and the need for a
greater number of engines and rotors, alters the spar, the aerodynamic flow, the number of ribs and the stiffness of
the wing itself. In this study, the engines are distributed along the wing, aiming greater traction and less variation
in the angle of attack along the wingspan. An aerodynamic model was created with these requirements, based on
the lift line theory, in order to calculate the flight load. Finally, using these values, employing routines of genetic
algorithms, the structure was optimized, adopting the spar geometry and thickness as design variables, with the
objective of minimizing weight, following the Tsai-Wu criterion and the impossibility of buckling.