Non-linear aeroelastic response and control of supersonic flapped 2-D lifting surfaces

This paper concerns the linear and non-linear aeroelastic control ol a 2-D wing-flap system operating in supersonic/hypersonic flight speed regimes. Open and closed-loop aeroelastic response, flutter, and post-flutter of 2-D supersonic lifting surfaces are investigated. The following problems are addressed: i) the implications of aerodynamic and structural aonlinearities on the aeroelastic response in the post-flutter range, and ii) development of a comprehensive control methodology to control the flutter boundary. A linear and non-linear combined active proportional and velocity control strategy is implemented. The control's effectiveness in reducing the oscillation amplitude in the subcritical flight speed range, in suppressing flutter, and in preventing the catastrophic failure in the post-flutter range is demonstrated. Simulations were carried out using a time marching integration with the non-linear Mathematica® solver.