15 April 2016 High-fidelity simulation and reduced-order modelling of integrally-actuated membrane wings with feedback control
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Abstract
This work presents a numerical framework for the simulation and design of integrally actuated membrane wings with feedback control. The performance of the aeroelastic system are evaluated using a high-fidelity model. It consists in a fluid solver based on the direct numerical integration of the unsteady Navier-Stokes equations implicitly coupled with a geometrically non-linear dynamic structural model which has been calibrated using experimental data. The rate-dependent constitutive law for the dielectric elastomer considered for the integral wing actuation is based on a non-linear formulation. The framework also includes a methodology for the model reduction of the fully-coupled system. The resulting low-order description showed to retain the main system dynamics, and can therefore be used for the design of the control scheme for the wing. Results highlights the potential to achieve on-demand aerodynamics using the actuation concept proposed. In particular, it is shown that the wing aerodynamic performance is noticeably enhanced through the actuation and the disturbances on the lift in case of gusts can be reduced up to 60%.
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Stefano Buoso, Stefano Buoso, Rafael Palacios, Rafael Palacios, } "High-fidelity simulation and reduced-order modelling of integrally-actuated membrane wings with feedback control", Proc. SPIE 9799, Active and Passive Smart Structures and Integrated Systems 2016, 979928 (15 April 2016); doi: 10.1117/12.2218348; https://doi.org/10.1117/12.2218348
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