| 摘要 |
The present invention relates to a system for the transformation of a traditional self-sustained horizontal take-off and landing aircraft into hybrid, integrated, self-sustained vertical take-off and landing and horizontal flight comprising, besides the propulsion system already provided in the aircraft, a hydraulic propulsion system, activating at least a blade rotor (1), to be used during the vertical take-off and landing and transition phases, said hydraulic system being powered by the engines of the aircraft, and at least an auxiliary engine (2), provided in a rear position and/or under the aircraft, said at least an auxiliary engine being progressively tiltable and swingable between two limit positions, respectively vertical position and horizontal position, said standard propulsion means of the aircraft being deactivated during the vertical take-off and landing and the transition and activated during the self-sustained horizontal flight, and said at least an auxiliary engine and said at least one auxiliary engine being operating during the vertical take-off and landing and the transition and deactivated during the self-sustained horizontal flight. |
