| 摘要 |
The present invention discloses an aircraft capable of vertical take-off and landing. The aircraft comprises a single constant speed variable pitch propeller ( 3 ), a fuselage ( 2 ), an empennage ( 21, 22 ) and main wings ( 6 ) fixed to the fuselage ( 2 ); arranged similar to a conventional aircraft, but sized and positioned for vertical flight. A stator is positioned a minimal distance behind the propeller so as to compensate the torque caused by the propeller. The aircraft comprises high lift and high drag devices such as flaps ( 19 ) and a leading edge slat ( 7 ) on the main wings ( 6 ), and a fuselage spoiler ( 18 ). The positioning of the center of gravity ( 23 ) allows for a stable nose-up take-off and landing, NUTOL, position. The propeller generated airflow (PGA) over the main wings ( 6 ) and high lift and drag devices ( 7, 18, 19 ) creates lift and drag forces. Due to the NUTOL position, the sum of the propeller thrust, the lift forces and the drag forces on the aircraft results in a vertical force and no forward (horizontal) force, thus enabling vertical flight. Roll, pitch and yaw control is achieved by aerodynamic surfaces positioned inside and outside of the PGA.
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