A Computational Aeroelastic Framework for Studying Non-conventional Aeronautical Systems

A computational co-simulation framework to study the aeroelastic behavior of a variety of aeronautical systems characterized by highly flexible structures undergoing complex motions in space and immersed in a low-subsonic flow is presented. The authors combine a non-linear aerodynamic model based on an extended version of the unsteady vortex-lattice method with a non-linear structural model based on a segregated formulation of Lagrange’s equations obtained with the Floating Frame of Reference formalism. The structural model construction allows for hybrid combinations of different models typically used with multi-body systems, such as models based on rigid-body dynamics, assumed-modes techniques, and finite-element methods. The governing equations are numerically integrated in the time domain to obtain the structural response and the consistent flowfield around it. The integration is based on the fourth-order predictor-corrector method of Hamming. The findings are found to capture known non-linear behavior of these non-conventional flight systems. The developed framework should be relevant for conducting aeroelastic studies on a wide variety of aeronautical systems such as: micro-air-vehicles (MAVs) inspired by biology, morphing wings, and joined-wing aircrafts, among others.

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