IMPROVED PROPULSIVE ASSEMBLY FOR A MULTI-ENGINE HYBRID AIRCRAFT

Abstract: a propulsive assembly including a first and a second gas turbine each having a gas generator and a free power turbine, a main rotor coupled to the free power turbine of a first and a second main coupling, a first and a second reversible electric machine each coupled to the gas generator, by way of a first deactivatable coupling, and each coupled to the main rotor by way of a second deactivatable coupling, the first deactivatable coupling being activated when the electric machines are rotating in a first direction of rotation, and the second deactivatable coupling being activated when the electric machines are rotating in a second direction of rotation opposite to the first direction of rotation.

Inventor(s): Benjamin Nicolas FULLERINGER, Antoine Pascal MOUTAUX, Romain Jean Gilbert THIRIET

CPC Classification: B64D27/33 (EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT)

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