Patent ID: 8336811
Filing Date: 2012-12-25
Classification: B64C,Y02T

Abstract:
1. An aircraft comprising: a reference system determined by a longitudinal X axis oriented positively toward a front of the aircraft, a vertical Z axis perpendicular to the X axis and oriented positively toward a bottom of the aircraft and a lateral Y axis perpendicular to the plane defined by the X and Z axes and oriented positively toward a right side of the aircraft; a wing affixed to an upper central part of the fuselage along the longitudinal X axis; a set of rear airfoils situated behind the wing; and propulsion engines mounted on the wing, wherein the wing, the set of rear airfoils and the propulsion engines are parts of an aero-propulsive unit, said aero-propulsive unit being a structure independent of the fuselage; and wherein the aero-propulsive unit is connected to the fuselage by a six degrees of freedom connection system using arms the lengths of which are modified to control a position of the aero-propulsive unit relative to the fuselage along the X, Y and Z axes of the reference system of the aircraft and in rotation about the three axes X, Y and Z, during flight.