Experimental Trapped Vorticity Flight Control Using An Augmenting Error Minimization Adaptive Law

摘要: Closed-loop feedback control is used in a series of wind tunnel experiments to efiect commanded 2-DOF maneuvers (pitch and plunge) free airfoil without moving surfaces. The objective achieve bandwidths that are beyond those achievable with mechanical Bi-directional changes the pitching moment over range angles attack efiected by controllable, nominally-symmetric, trapped vorticity concentrations on both suction pressure surfaces near trailing edge. Actuation applied hybrid actuators each comprised miniature obstruction integrated synthetic jet actuator manipulate regulate concentrations. In present work, model trimmed using position attitude loops actuated servo motors ball screw mechanism plunge axis. Once trimmed, loop axis opened controlled force mode. Force mode allows simulation ∞ight tunnel. It can maintain static trim model, alter its efiective mass, change dynamic characteristics introduce disturbances. Attitude stabilization achieved closing through ∞ow reference adaptive controller designed specifled level tracking performance presence disturbances, parametric uncertainties unmodeled dynamics associated ∞ow. law employs neural network element which adaptation based novel error minimization scheme. augments linear law, closed system be shown uniformly ultimately bounded Lyapunov-like stability analysis.