Hybrid powered aircraft having an electromechanical distribution and protection junction

A hybrid powered aircraft comprising:

• at least two drive units each comprising a propulsion unit and an electric motor,
• a plurality of stored electrical energy sources arranged to provide electrical energy to one or more of the electric motors,
• at least one electrical generation source comprising a fuel-based electrical energy generator and connected to each stored electrical energy source, and
• a power supply control device arranged to output a power command to the at least one electrical generation source according to power requirements of the drive units, the plurality of stored electrical energy sources being arranged to provide electrical energy according to a difference between the power requirements of the drive units and power provided by the at least one electrical generation source, on the basis of the power command, the at least one electrical generation source being further configured to recharge the plurality of stored electrical energy sources such that each stored electrical energy source is treated passively,
• wherein each electrical generation source comprises at least one electrical converter, which is connected to each stored electrical energy source via a respective junction including a first contactor or electromechanical relay, a second contactor or electromechanical relay, and a diode,
• and wherein the power supply control device is arranged to control the operation of each junction according to a set of states consisting of:
• a unidirectional state in which current flows from the electrical converter to the stored electrical energy source, a bidirectional state in which the current flows in both directions, and a blocking state in which the flow of the current is blocked.