GB577779A - Improvements relating to wing flaps for aircraft - Google Patents

Abstract

577,779. Controlling aircraft. GENERAL AIRCRAFT, Ltd., and WILLIAMS, L. C. March 30, 1938, No. 9797. [Class 4] An aircraft flap arrangement includes an auxiliary aerofoil housed in its inoperative position in a recess in the upper side of a main aerofoil and connected thereto by mechanism permitting the auxiliary aerofoil to be displaced bodily in a rearward and vertical sense, the angle of incidence of the auxiliary aerofoil being increased during at least part of such displacement. In one form, the flap B is nested normally in the trailing portion of the upper surface of the wing A and is connected to the wing by links 10, 11. The flap is extended by operation of a jack 16 connected to an arm 19 secured to a torque tube 20 carrying the link 10. The flap has a chord 20 per cent to 30 per cent of the wing chard. In a modification, the link 11 is pivoted to a bracket 28, the link 10 is pivoted to an arm 29. On extension of a jack 16 the flap may be adjusted to the position B<3>, Fig. 2A, and on turning the arm 29 to the position B<2>. In a further modication, the link 11 is constituted by a jack and both the jack and the link 10 are pivoted to a bracket beneath the wing. In this form the flap may uncover a wing slot. In another form the link 10 consists of a jack the upper end of which moves in a fixed guide. In further forms the flap is operatively interconnected with a further flap nested normally beneath the trailing leverportion of the wing. In still further forms the flap is adjustable to a position symmetrically above and below the trailing edge of the wing and in one such case the links carrying the flap have a common pivot on a bracket on the wing. According to the Provisional Specification the trailing edge of the flap may be guided rearwardly whilst the leading edge is displaced upwards and rearwardly.