Embodiments described herein relate to a vertical take-off and landing aircraft, specifically an electric or hybrid electric aircraft having a plurality of ducted fans. The aircraft includes a plurality of axially oriented fans, laterally oriented fans, forward air intakes, side exit ports, rear exhaust ports, plenum air chamber and annular inlet. The aircraft achieves flight by capturing air in the intakes and diverting the air through the axially oriented fans or the laterally oriented fans through the channels selectively.

A method for controlling a flying projectile which rotates during flight, comprising: determining an angle of rotation of an inertial mass spinning about an axis during flight, and controlling at least one actuator for altering at least a portion of an aerodynamic structure, selectively in dependence on the determined angle of rotation and a control input, to control aerodynamic forces during flight. An aerodynamic surface may rotate and interact with surrounding air during flight, to produce aerodynamic forces. A sensor determines an angular rotation of the spin during flight. A control system, responsive to the sensor, produces a control signal in dependence on the determined angular rotation. An actuator selectively alters an aerodynamic characteristic of the aerodynamic surface in response to the control signal.

The method of obtaining both, lifting force and thrust, required for horizontal flight of the vertical take-off and landing flying machine while maintaining horizontal flight stability of the machine which is realized due to suction atmospheric air to the inner cavity formed between coaxial mounted, multi-blade turbines (2, 18), the top and the bottom, which are counter-rotating relatively to each other, and remove the air outside under the machine; the conical turbines are mounted with the direction of wider, circular bases facing in front of them and which are mounted on the double-sided fixed bearings (4, 16) alongside the contour edge of the external ring (12), which is mounted using the distance spacers (13) form the inner side to the central housing (6) which is formed with the conical shape and which is the base where the both turbines (2, 18) are mounted using linear drives from the side of their smaller bases. The air which is accumulated under the pressure at such inner cavity is removed outside of the external ring (12) using drive nozzles (15A, 15B, 15C, 15D), which are installed circumferentially at the inner ring, to achieve thrust required for the horizontal flight or stabilization nozzles (14A, 14B), which are used to maintain required rotational stabilization of the central ring (6). The subject of the invention is also the machine used to achieve this way.