Boundary feedback stabilization of a flexible wing model under unsteady aerodynamic loads
For aerospace engineers designing active control systems for flexible wings, this work provides a theoretical stabilization framework, though it is incremental as it applies existing Lyapunov methods to a specific coupled beam model.
The paper proposes a boundary feedback control law that stabilizes bending and twisting displacements of a flexible wing model under unsteady aerodynamic loads, achieving exponential decay of system energy as proven via Lyapunov analysis and validated by simulations.
This paper addresses the boundary stabilization of a flexible wing model, both in bending and twisting displacements, under unsteady aerodynamic loads, and in presence of a store. The wing dynamics is captured by a distributed parameter system as a coupled Euler-Bernoulli and Timoshenko beam model. The problem is tackled in the framework of semigroup theory, and a Lyapunov-based stability analysis is carried out to assess that the system energy, as well as the bending and twisting displacements, decay exponentially to zero. The effectiveness of the proposed boundary control scheme is evaluated based on simulations.