초록

A system and a method according to the invention reduce wake turbulence of an aircraft in that a component affixed to the extremity of the wing of an aircraft disturbs the rolling action of the air in the region of the outer wing by periodic hingeing movements.

대표청구항 ▼

What is claimed is: 1. A system for reducing wake turbulence of an aircraft during flight along a flight direction, the aircraft having a wing including an outer wing portion, an extremity and a top, the system comprising:a component configured to be attached to the top of the wing at the extremity

What is claimed is: 1. A system for reducing wake turbulence of an aircraft during flight along a flight direction, the aircraft having a wing including an outer wing portion, an extremity and a top, the system comprising:a component configured to be attached to the top of the wing at the extremity of the wing of the aircraft so as to disturb a rolling action of air at the outer wing portion, the component comprising:a fixed element;a first hingeable wing element having a first inner surface and a second hingeable wing element having a second inner surface,wherein the first and second hingeable wing elements are configured to be hingedly positionable to a first position in which the first inner surface is positioned side-by-side with the second inner surface and downstream of the fixed element, and configured to be hingedly positionable to a second position in which the first and second hingeable elements are folded out relative to each other in the flight direction; anda central aircraft control system configured to control rotary movement of the first and second hingeable wing elements between an outer end position and an inner end position, such that in the outer end position the first wing element is folded outward at a first predetermined deflection angle in relation to an axis in the flight direction and the second wing element extends parallel to the flight direction, and such that in the inner end position the second wing element is folded inward at a second predetermined deflection angle in relation to the axis in the flight direction and the first wing element extends parallel to the flight direction.