| 摘要 |
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.
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