Modelling Continuously Morphing Aircraft for Flight Control

The goal of the present work is to develop a small-scale flying wing with active winglets from its actual discrete surfaces concept, actuated via single torque actuator, to a seamless continuous concept actuated via a distribution of actuators. In order to achieve this goal, a more conceptual approach is needed and a deep understanding of the interaction between aerodynamics, structures and controls is required. A conceptual approach will allow the tailoring of the main parameters influencing the flexibility of the structures, via an efficient optimisation routine based on a certain actuation power requirement. The efficiency is guaranteed by the implementation of equivalent continuum models for the structure rather than a discrete finite element approach, while the aerodynamic loads are provided by the implementation of a vortex lattice code. The paper describes and validates the tools for an static aeroelastic code which predicts the interaction of the actuated morphing wing and the flow field, in preparation for the optimisation.

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