Patent ID: 7740205

Claim:
An auxiliary wing and flap assembly for an aircraft comprising: an aircraft wing having a leading edge and a trailing edge, said aircraft wing having a top surface and a bottom surface; a split flap hingedly mounted on said bottom surface of said aircraft wing on a first hinge axis on said aircraft wing directly adjacent said trailing edge; said split flap to be movable between a first retracted position and an extended position, said first retracted position locates said split flap against said aircraft wing, said extended position locates said split flap substantially transverse to said aircraft wing extending from said bottom surface of said aircraft wing; an auxiliary wing assembly mounted on said bottom surface of said aircraft wing by a hinge connected to said aircraft wing, said hinge connection located intermediate said leading edge and said first hinge axis, said auxiliary wing assembly defined as an airfoil-shaped member mounted by a bracket assembly to said aircraft wing, said auxiliary wing assembly being movable between a second retracted position and a deployed position, said second retracted position locates said auxiliary wing against said aircraft wing, said deployed position locates said auxiliary wing transversely to said aircraft wing extending from said bottom surface of said aircraft wing, when in said deployed position there being a longitudinal air gap area located between said auxiliary wing and said aircraft wing; wherein said split flap is movable to be able to assume an angle of extension when in said extended position having an angular relationship of approximately sixty degrees relative to said bottom surface of said aircraft wing, said auxiliary wing when in said deployed position capable of assuming a substantially ninety degree position relative to said bottom surface of said aircraft wing; and wherein said aircraft wing has a chord length defined as C, said auxiliary wing having a chord length defined as approximately 0.25 C, the distance of said air gap area between said aircraft wing and said auxiliary wing being approximately 0.1 C, said flap having a chord length of approximately 0.15 C; whereby said split flap and the auxiliary wing when located in the extended position and the deployed position respectively will cause the aircraft when flying to appreciably slow and lift in order to substantially shorten the landing distance when landing of the aircraft and also function to substantially increase lift for a very short takeoff.