Vertical take-off and landing aircraft using hybrid electric propulsion system

Abstract

A vertical take-off and landing aircraft using a hybrid electric propulsion system, according to an embodiment of the present invention, includes: a first control step (S) of changing a destination when an engine (), a power generator (), an engine control unit (), a power management device (), a control unit (), a battery management system (), a main battery () and the like malfunction, thereby causing a normal flight to be difficult; a second control step (S) of performing control so that an aerial vehicle () glides to a point (T), at which same has entered a first space (CEP-) required for landing or a wider second space (CEP-) considered safe, and maintains lift and has minimized flight air resistance after passing through the point (T); a third control step (S) of performing control so that lift is increased and performing control so that a nose cone is switched into an upward direction; and a fourth control step (S) of performing control so that lift is gradually reduced, and controlling a second variable-pitch control device () so that thrust does not act on the aerial vehicle at the moment the aerial vehicle lands, and thus the present invention can vertically land while minimizing impact to be applied to the aerial vehicle.