Patent ID: 8474747
Filing Date: 2013-07-02
Classification: B64C,Y02T

Abstract:
1. An aircraft horizontal stabilizer, located at a tail of the aircraft, configured to vary its sweep angle by rotating around an essentially vertical axis with respect to the direction of flight of the aircraft when the aircraft is in flight at high speeds, close to the speed of sound, the vertical axis being contained in the plane of symmetry of the aircraft, wherein the horizontal stabilizer is a single piece and structurally continuous such that it does not transmit a bending moment to the fuselage structure of the aircraft, which permits the horizontal stabilizer to be of reduced weight, such that the horizontal stabilizer rotates in a single way and a single direction around the vertical axis to achieve the sweep angle required for high-speed flight, the horizontal stabilizer is also configured to rotate around a longitudinal reference axis, the longitudinal reference axis is essentially horizontal and perpendicular to both the plane of symmetry of the aircraft and the vertical axis, and a middle portion of the horizontal stabilizer is completely surrounded by the fuselage.