| 摘要 |
<p>The invention relates to a vertical take-off and landing lenticular aircraft with blades. According to the invention, the aircraft is built on a structure (A) consisting of some spars (1), an engine-supporting platform (2), a central platform (3) supporting the main rotor and the mobile control plates, which is, in its turn, made integral with the main structure by some radial spars (4) which, at the same time, support some segments (5) bearing the adjustable steering blades, a lower platform (6) supporting the lower spars and a cabin structure (7), the aircraft structure being skirted by an envelope (B) which, on the one hand, ensures the aerodynamic shape thereof and, on the other hand, through some openings (a) ensures the intake of lifting air flow through an air inlet (b) and the intake of air for the engine through a piping (8), the lifting air flow being discharged through some openings (c) cut into the bottom part of the aircraft, together with the exhaust gases from the engine, a crew cabin (C) containing the control and navigation systems, a propelling system provided with a turbo engine (D) supported by the platform (2) and some fittings (9) discharging the pressurized exhaust gases into the lifting air flow, which is coupled with a rotor (E) provided with 5 blades, by means of a reducing gear (10) whose outlet is connected to the hub (11) of the rotor which entrains the rotor (E) generating the lifting air flow entering through 6 triangular openings (a) in the aircraft skirting, further on, said flow passing through the network of adjustable steering blades (F+G) and, after being mixed with the exhaust gases from the engine, being discharged through the openings (c), producing the reaction lifting force, the steering of the aircraft being achieved by means of the adjustable blades (F+G) grouped into two functional sub-systems: the blades (F) for the control of forward/backward and right/left movements and the blades (G) for the control of gyration and anti-torque.</p> |
