On the robust control of aeroelastic vehicles

The paper presents a H_∞ flight control system design case of study for an aeroelastic vehicle. This approach has been developed on a six order reduced model considering the most current longitudinal motion steady-state, i.e., the wings-level, zero-side-slip rectilinear flight. Robust stability and performance of the achieved μ-controller are explored in terms of sensitivity and complementary sensitivity functions. The case study resulted in appropriate boundary of the uncertainty and performance weights assuring good robustness properties.