AICRAFT CONTAINING HYBRID POWER UNITS AND CORRESPONDING CONTROL METHOD Russian patent published in 2023 - IPC B64D27/02 B64D27/24 B64D35/08 

FIELD: aircrafts.

SUBSTANCE: aircraft equipped with a power unit comprising a heat engine unit and an electric motor unit. The aircraft is equipped with a power unit, wherein the power unit comprises: a traction system with blades, a heat engine unit, containing the first heat engine and the second heat engine, configured to actuate the traction system with blades, an electric motor unit, configured to actuate operation of the vane propulsion system, a power supply system comprising a battery capable of supplying power to the electric motor unit, a clutch system configured to engage any or each of the heat engines to drive the vane propulsion system. Moreover, the clutch system is also configured to disengage any of the heat engines or each of the heat engines relative to the traction system with blades. The electric motor unit is positioned in series with the heat engine unit, between the heat engine unit and the traction system with blades. Moreover, the mentioned device contains a control unit for the clutch system of the heat engine unit and the power supply system of the electric motor unit. Further, the control unit is configured to disengage one of the two heat engines in the event of a malfunction of said heat engine. At the same time, the other heat engine remains engaged, and the control of the power supply system is configured for supplying power to the electric motor unit to drive the traction system with blades using said other heat engine, which remains engaged, and the electric motor unit. Moreover, the control unit is also configured to disengage two heat engines and control the power supply system to supply power to the electric motor unit to actuate the traction system with blades by means of only the electric motor unit. The group of inventions is also related to a method for controlling such aircraft.

EFFECT: group of inventions improves the safety and efficiency of the propulsion unit due to the independent use of energy sources.

16 cl, 7 dwg