Improvements relating to wing flaps for aircraft

Abstract

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.

Inventors

No inventors recorded.

Bibliographic Details