Propulsive assembly for a multi-engine hybrid aircraft

A propulsive assembly for a hybrid aircraft, particularly a multi-engine helicopter, comprising:

• at least a first gas turbine and a second gas turbine each having a gas generator and a free power turbine rotationally driven by a stream of gas generated by the gas generator,
• a main rotor coupled to the free power turbine of the first gas turbine and of the second gas turbine by way of a first and a second main coupling means respectively,
• a first reversible electric machine and a second reversible electric machine each coupled to the gas generator of the first gas turbine and of the second gas turbine respectively, by way of a first deactivatable coupling means, and each coupled to the main rotor by way of a second deactivatable coupling means, the first deactivatable coupling means being each configured to be activated when the first and the second electric machine are rotating in a first direction of rotation, and the second deactivatable coupling means being configured to be activated when the first and the second electric machine are rotating in a second direction of rotation opposite to the first direction of rotation.