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U.S. Patent Specifications

Aircraft Engineering and Aerospace Technology

ISSN: 0002-2667

Article publication date: 1 December 1945



In combination with an aeroplane having a wing for sustaining purposes, an aileron pivotally supported adjacent the wing and adapted to float freely, and a hinged tab associated with the aileron and adapted in response to tilting relatively to the aileron during flight of the aeroplane to control the angular position of said aileron with respect to the air stream, a system for controlling the tab comprising a cam mounted to rotate about the pivot axis of the aileron, pilot actuated means for turning the cam relatively to the wing, a cam follower in operative engagement with the cam, and an operating connexion extending between the cam follower and the tab and operative to tilt the tab relatively to the aileron in response either to turning of the cam relatively to the wing or to relative turning of the cam and aileron, said cam being so designed that when it is in a neutral stationary position with respect to the wing and said wing is caused in connexion with flight to change its angle of attack from zero to stall it effects tilting of the tab into a position wherein it causes the aileron to assume substantially the same angle of attack as the wing and being also so designed that when it is in its said neutral stationary position with respect to the wing and such wing is caused to increase its angle of attack above the stall angle it positively maintains the tab in a fixed tilted position with respect to the aileron.


(1945), "U.S. Patent Specifications", Aircraft Engineering and Aerospace Technology, Vol. 17 No. 12, pp. 371-372.




Copyright © 1945, MCB UP Limited

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