Automatic leading edge slat for aircraft

Abstract

A slat assembly is mounted upon the leading edge of an aircraft wing, and responds automatically to changes in air speed or in the angle of attack of the wing, to increase lift at lower air speeds, and to reduce the stalling speed of the wing. A capability is induced in the aircraft for landing and taking off in short distances. For an aircraft of given size and power, also, there is offered an added safety factor in that the aircraft is permitted to land at slower landing speeds than have heretofore been possible. For the purpose of accomplishing these results, the automatic leading edge slat utilizes a base plate projecting from the leading edge of the aircraft wing, and supporting a slat having airfoil characteristics forwardly of the leading edge of the wing. Connecting the slat to the base plate or strip are flat springs shaped and tensioned to permit slat motion in a plurality of directions as a response to air pressures, according to their magnitude and the directions in which they impinge against the slat surfaces. The construction additionally permits manual operation such that the slats of both wings may be positioned in a drag configuration for glide path control. Or, manual operation of a selected one of the slats can offer roll control instead of through the use of conventional ailerons. The action is superior to ailerons because adverse yaw is eliminated and rudder-controlled turn coordination is no longer necessary. Also, this allows for full span flaps which lowers the stalling speed even further.