Structural optimization coupled to fluid-structure interaction of an UAV aircraft wing
The main goal of the UAV aircraft is to carry the maximum payload with safety and with a minimum amount of resources and costs. Structural optimization helps reach this goal allowing the reduction of the aircraft empty weight by maximizing the payload without putting at risk the flight safety.
The main objective of this paper is to study and to propose a methodology in order to obtain an optimized internal wing structure of the UAV aircraft. Such optimization takes into account the static aeroelastic effects of Fluid-Structure Interaction (FSI) through Computation Fluid Dynamics (CFD) techniques coupled with the Finite Element Method (FEM).
Three optimization cases have been assessed: parametric, topology without FSI loop and topology with FSI loop. Parametric optimization was performed in the modeFRONTIER environment by means of the SOBOL algorithm in order to maximize the wing aerodynamic efficiency based on a fixed structure topology. The topology optimization used a Matlab code that obtained a solution on the basis of Optimality Criteria and using a sensitivity filter. For the non-FSI case the aerodynamic loads were held constant (calculated from the CFD analysis) and for the FSI case the loads were calculated from a FSI two-way analysis.