| 摘要 |
A telescopic vertical take-off aircraft is disclosed. The aircraft comprises a main rotor assembly 2 at the top of the aircraft which consists of an assembly of blades 3a, 3b and a rotor 4. Rotation of the main rotor assembly 2 is achieved by means of a main engine assembly 5. The main engine assembly 5 is connected to the main body 6 of the aircraft by a tilt enabling joint 7. The tilt enabling joint 7 enables tilting of the main engine assembly 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 hydraulic actuators 9, 10 and 11, that allow the tilting of the tilt enabling joint 7 to be controlled. When the main engine assembly 5 is tilted, the main rotor assembly 2 is tilted with it. Tilting of the main engine assembly 5 thus initiates changes in the direction of travel of the aircraft without the need to change the pitch angles of the rotor blades 3a and 3b. To counter the rotational force exerted on the main body 6 of the aircraft by the rotation of the main rotor assembly 2, an additional engine assembly 15 is attached to the main body of the aircraft, which rotates a secondary rotor assembly 16. The secondary rotor assembly consists of blades 17 and 18, and a rotor 19. Rotation of the secondary rotor assembly pushes air in a primaryliy horizontal direction by way of the pitch of the blades 17 and 18. Telescopic tube assemblies 12 and 13 allow the distance between the base 14b of the tilt enabling 7 and the main body 6 of the aircraft to be varied.
|
