Patent ID: 6598827
Filing Date: 2003-07-29
Classification: B64C,B64D

Abstract:
A vertical take-off aircraft, comprising a main rotor assembly, at the top of the aircraft, which said main rotor assembly is comprised of an assembly of blades and a rotor, and such that the said main rotor assembly is above the main body of the aircraft, with vertical lift being achieved by an engine assembly rotating the main rotor assembly thereby forcing air in a downward direction by way of the blades in the main rotor assembly, which engine assembly is the main engine assembly of the aircraft, and which said main engine assembly is connected to the main body of the aircraft by a tilt enabling joint, such that the main rotor assembly and main engine assembly can be tilted together as a unity in a plurality of directions and angles relative to the main body of the aircraft, in a controlled manner, such that the direction of travel of the aircraft can be altered by altering the direction or angle of tilt of the main engine assembly relative to the main body of the aircraft, and which said tilt enabling joint is connected to the main body of the aircraft such that the distance between the main body of the aircraft and the base of the tilt enabling joint can be varied, with a secondary rotor assembly, consisting of an assembly of blades and a rotor, connected to the aircraft, which said secondary rotor assembly is used to force air to travel in a horizontal direction, for which said secondary rotor assembly rotation is achieved by means of an additional engine assembly, such that by forcing air to travel in a horizontal direction, relative to the main body of the aircraft, the rotational force exerted on the main body of the aircraft by the rotation of the main rotor assembly can be countered.