This method for controlling the operation of a coupling device for an aircraft turbomachine comprises the steps of: a first comparison of the determined rotational speed of an electric machine with a time evolution profile, the first comparison being carried out to determine an operating deviation; a second comparison of the operating deviation with a detection threshold; and according to the result of the second comparison step, identifying the existence or absence of a failure of the coupling device; the second comparison step comprising determining the value of the detection threshold from at least one control parameter, the operating deviation and the rotational speed of the electric machine.

Hybrid propulsion integral systems for a fixed wing aircraft, and a V/STOL aircraft. A core of the jet engine rotates an integral generator, that provides current to charge batteries located in various locations on an aircraft. The batteries and generator are selectively used to power electric motor(s) that provide the sole source of torque (power) to fans, propellers, or rotors that propel the aircraft, along with a fuel operated gas turbine. In addition, for a V/STOL air vehicle, a hybrid propulsion system fixed to a wing or split between wing and empennage, with moving integral submodules, such as a multifunctional thrust vectoring exhaust nozzle and electrically operated tiltable propeller(s). These differ from the prior configurations by provisioning integrated architectures as delineated.

Hybrid propulsion integral systems for a fixed wing aircraft, and a V/STOL aircraft. A core of the jet engine rotates an integral generator, that provides current to charge batteries located in various locations on an aircraft. The batteries and generator are selectively used to power electric motor(s) that provide the sole source of torque (power) to fans, propellers, or rotors that propel the aircraft, along with a fuel operated gas turbine. In addition, for a V/STOL air vehicle, a hybrid propulsion system fixed to a wing or split between wing and empennage, with moving integral submodules, such as a multifunctional thrust vectoring exhaust nozzle and electrically operated tiltable propeller(s). These differ from the prior configurations by provisioning integrated architectures as delineated.