U.S. Patent Specifications

Abstract

In combination with an aeroplane having a wing with an aileron hinged to the rear portion thereof to swing up or down from a neutral position to either an ordinary or extreme deflected position and back again, a control for the aileron comprising an actuating element in the pilot's compartment of the aeroplane, a sleeve connected pivotally to the front portion of the aileron and adapted in response to axial shift thereof to swing said aileron, a plunger having one end thereof fitting within the sleeve and its other end mounted in the wing so that said plunger is rotatable without axial displacement, means between the actuating element and said other end of the plunger for effecting rotation of the plunger in response to control movement of said element, and a roller and cam slot motion imparting connection between the plunger and sleeve operative in response to rotation of said plunger to shift the sleeve axially and thus effect swinging of the aileron, the slot of said connection being of helical design and formed in the sleeve and having the intermediate part thereof adapted to receive the roller when the aileron is in or near its neutral position and arranged so that when the roller is disposed therein the aileron is locked against swinging movement except by rotation of the plunger, and also having one end part thereof adapted to receive the roller when said plunger is rotated in one direction in order to swing upwards the aileron into its ordinary or extreme deflected position and curved and of such pitch that when the roller is therein the aileron is free so that it tends in response to flow of air there‐against during flight of the aeroplane to return downwards to its neutral position, and its other end adapted to receive the roller when the plunger is rotated in the reverse direction in order to swing the aileron downwards into an ordinary or extreme deflected position and curved and of such pitch that when the roller is therein the aileron is free so that it tends in response to flow of air there‐against during flight of the aeroplane to return upwards to its neutral position.

Citation

(1939), "U.S. Patent Specifications", Aircraft Engineering and Aerospace Technology, Vol. 11 No. 8, pp. 334-334. https://doi.org/10.1108/eb030534