Vertical take-off aircraft - P

Abstract

A vertical take-off aircraft is disclosed. Looking at the aircraft it can be seen that the aircraft comprises a main rotor assembly 1 at the top of the aircraft which consists of an assembly of blades 2, 3 and a rotor 4 . Rotation of the main rotor assembly 1 is achieved by means of a main power plant 5 . The main power plant is connected to the main body 6 of the aircraft by a tilt enabling joint 7 . The tilt enabling joint 7 allows tilting of the main power plant 5 relative to the main body 6 of the aircraft to occur in a controlled manner during flight. A universal joint 8 is used to allow tilting to occur. The tilt enabling joint 7 is fitted with a combination of hydraulic actuators 9, 10 and springs 11, 12 and 13 that allow the tilting of the tilt enabling joint 7 to be controlled. When the main power plant 5 is tilted, the main rotor assembly 1 is tilted with it. Tilting of the main power plant 5 thus initiates changes in the direction of travel of the aircraft without the need to change the pitch angles of the blades 2 and 3 . To counter the rotational force exerted on the main body 6 of the aircraft by the rotation of the main rotor assembly 1 , an additional power plant 15 is attached to the upper section of the tilt enabling joint 14 , which rotates a secondary rotor assembly 16 . The secondary rotor assembly comprises blades 17 and 18 , and a rotor 19 . Rotation of the additional rotor assembly pushes air in a primarily horizontal direction by means of the pitch of the blades 17 and 18.

1 . A vertical take-off aircraft, comprising a main rotor assembly at the top of the aircraft, which said main rotor assembly comprises an assembly of blades and a rotor, and such that the said main rotor assembly is above a main body of the aircraft, with vertical lift being achieved by means of at least one power plant rotating the main rotor assembly thereby forcing air in a downward direction by way of the blades in the main rotor assembly, and which said blades are above the at least one power plant, and which said at least one power plant is connected to the main body of the aircraft by a tilt enabling joint, such that the main rotor assembly and the at least one power plant 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 of tilt of the at least one power plant relative to the main body of the aircraft, and which said tilt enabling joint is connected to the main body of the aircraft, with a secondary rotor assembly, comprising 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 at least one additional power plant, such that by forcing air to travel in a horizontal direction, relative to the main body of the aircraft, a rotational force exerted on the main body of the aircraft by the rotation of the main rotor assembly can be countered.  
     
     
         2 . The vertical take-off aircraft of  claim 1 , wherein the at least one power plant comprises at least one engine.  
     
     
         3 . The vertical take-off aircraft of  claim 1 , wherein the at least one additional power plant comprises at least one engine.  
     
     
         4 . The vertical take-off aircraft of  claim 2 , wherein the at least one additional power plant comprises at least one engine.