In order to maintain the hinge moments of a combined pair of aircraft ailerons as low as possible each aileron is constructed so that when it is depressed to increase the camber of the wing its own camber is simultaneously increased. As shown, this is effected by making the aileron in two parts a, b hinged together at e, the leading portion a being adapted to be depressed whenever the aileron as a whole is depressed about the hinges c at the rear ends of brackets d. The dipping of the portion a is effected by a link t connected to a non‐rotatable nut r working on a threaded rod k, at the upper end of which is a pulley m actuated by a cable n that passes into the wing structure at a point in line with the axis c. A cable o which serves to vary the camber of the wing is associated with the cable n through a gearing‐up pulleys p, q.
(1935), "Month in the Patent Office: A Selection of the More Important Aircraft and Engine Specifications Published Recently", Aircraft Engineering and Aerospace Technology, Vol. 7 No. 10, pp. 267-268. https://doi.org/10.1108/eb029982Download as .RIS
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