An experimental study of a vane controlled jet flap gust alleviation system

Abstract

An experimental effort to demonstrate the feasibility of an active gust alleviator using a fluidically actuated jet flap control system was undertaken. The wing model had a variable deflection jet at the trailing edge and was free to move in pitch only. A vane mounted ahead of the wing served as gust sensor and provided the signal which controlled the jet angle. Experimental results showed the system capable to alleviating up to 92% of the motion caused by a sinusoidal gust at constant amplitude. RMS vales of wing rotation angle were found to be 0.68 degrees with control off and 0.29 degrees with control on when excited by a random two-dimensional gust.