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A mixed-norm multi-objective robust controller is designed and integrated with a very flexible aircraft. Due to the aircraft high level of flexibility, the aircraft’s aeroservoelastic equations of motion are extremely nonlinear. In a very flexible aircraft, even slight deviation of flight conditions from their nominal values can highly affect the vehicle’s stability. A control architecture is proposed to minimize the adverse effects of trim velocity variation on the stability and performance of the closed-loop system. The linear matrix inequalities technique is used to express the control design process as a convex optimization problem. The performance of the designed controller when applied to a very flexible aircraft trimmed at various cruise velocities is evaluated and compared with a non-robust H2 controller.

Mixed-Norm Multi-Objective Robust Controller Applied to a Very Flexible Aircraft