Finite element analysis of fluid–structure interaction for the design of MAV aerodynamic shape

In the study of micro aircraft flexible aerodynamic shape, the flexible structure interface deforms due to the air pressure, and this deformation simultaneously in turn affects the flow distribution around it, which is called a fluid–structure interaction problem. This paper discusses the general approach to such a fluid–structure interaction and further presents a detailed comparison between two representative materials used as aircraft surfaces. Two structure surfaces are respectively composed of natural rubber with high elasticity and steel alloy 1020 with high stiffness. In the test environment, the experimental model has a velocity of 8 m/s relative to the airflow, and the Reynolds number is higher than 5.44 × 104. The simulations of the two aerodynamic models using the two materials were performed in ANSYS CFX. The simulation results have shown that the aerodynamic shape with flexible rubber material has greater deformation and smaller force peak amplitude than the rigid material aerodynamic shape, which is a good factor to maintain flight stability. It is concluded that the flexible material with higher flexibility and shock-absorbing capability used as micro aircraft shape can play a buffer role especially in the aerodynamic disturbance.

► The numerical simulations of a micro air vehicle model have been performed.
► We studied the fluid–structure interaction performances based on two materials.
► The aerodynamic shape with flexible material has greater deformation.
► Flexible models undergo thrust/drag forces but rigid models remain in thrust force.
► The rigid material model has a larger initial force generated in vertical direction.