An Experimental Study of a Vane Controlled Jet Flap Gust Alleviation System.
NAVAL POSTGRADUATE SCHOOL MONTEREY CALIF
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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 jet angle. Experimental results showed the system capable of alleviating up to 92 of the motion caused by a sinusodial gust at constant amplitude. RMS values 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. Author