Patent ID: 6641089
Filing Date: 2003-11-04
Classification: B64C

Abstract:
An auxiliary flap arrangement for a lift-generating aerodynamic element of an aircraft, wherein the aerodynamic element has opposite first and second aerodynamic surfaces and a trailing edge therebetween, and a central chord line is defined intersecting the trailing edge and extending between the first and second aerodynamic surfaces, and wherein said auxiliary flap arrangement comprises:an auxiliary flap extending longitudinally in a span direction of the aerodynamic element along the trailing edge of the aerodynamic element; and means for movably connecting said auxiliary flap to the trailing edge of the aerodynamic element and for selectively moving said auxiliary flap to at least one of a first position in which said auxiliary flap protrudes outwardly away from the central chord line beyond the first aerodynamic surface and a second position in which said auxiliary flap protrudes outwardly away from the central chord line beyond the second aerodynamic surface, as well as a third position between said first and second positions in which said auxiliary flap does not protrude outwardly away from the central chord line beyond the first aerodynamic surface and does not protrude outwardly away from the central chord line beyond the second aerodynamic surface, wherein said means comprise sliding means for sliding said auxiliary flap along a sliding plane substantially perpendicular Â±10Â° relative to the central chord line, selectively to said first, second and third positions, in each of which said auxiliary flap lies on said sliding plane substantially perpendicular Â±10Â° relative to the central chord line.