LAUSR

Abstract The paper presents a technique for cost-effective and safe study of conventional and critical flight regimes and control validation using an autonomous dynamically scaled aircraft model mounted in a three-degree-of-freedom gimbal in a wind tunnel. The similarity of the dynamics of the model in gimbal and in free flight at high angles of attack is shown. To suppress large amplitude self-sustained pitch oscillations and prevent stalling, several control laws are developed using recent control design techniques based on structured H∞-optimization. The control laws are tested and compared in a dynamic rig with three degrees of freedom in a wind tunnel.