Patent ID: 8371520
Filing Date: 2013-02-12
Classification: B60F,B64C,Y02T

Abstract:
1. An aircraft, comprising: a fuselage having a longitudinal axis and a vertical axis perpendicular to the longitudinal axis; a wing having a predetermined dihedral angle, the wing having a first portion and a second portion, the first portion inclined relative to the second portion by the dihedral angle, the wing rotatably attached to a bottom portion of the fuselage at a center point of the wing between the first portion and the second portion, through a rotatable coupling, the wing rotatable from a first, extended position wherein each of the first portion and the second portion are perpendicular to the longitudinal axis of the fuselage to a second, stowed position where the first portion of the wing lies parallel to the longitudinal axis and bottom portion of the fuselage, and the second portion of the wing lies in a plane inclined from the longitudinal axis and bottom portion of the fuselage by the dihedral angle, wherein the rotatable coupling is mounted at an angle skewed from the vertical axis of the fuselage by an amount substantially equal to the dihederal angle of the wing, such that when the wing rotates from the first, extended position to the second, stowed position, the first portion of the wing lies parallel to the longitudinal axis and bottom portion of the fuselage while the second portion of the wing lies in a plane inclined from the longitudinal axis and bottom portion of the fuselage by the dihedral angle.