Patent ID: 6899298
Filing Date: 2005-05-31
Classification: B64C,Y02T

Abstract:
1. An aircraft structure adapted for short takeoff and landing performance comprising: a fuselage with a longitudinal axis; a wing extending transversely of the fuselage and attached thereto, having a normal flight position and an area, the fuselage and the wing in the normal flight position having a stall angle; thrust means attached to one of the fuselage and the wing, operable to move the fuselage generally in the direction of the longitudinal axis; a deployable wing with a wing axis, operably connected to the fuselage so that an angle of attack defined between the longitudinal axis and wing axis can be adjusted in the range from 0° to a predetermined angle substantially exceeding the stall angle; means for regulating the angle of attack of the deployable wing, operably connected between the deployable wing and the fuselage; and means for changing the area of the deployable wing between a fully retracted value and a fully deployed value.