Aircraft having a hybrid power source

An aircraft having a hybrid power source comprising:

• at least two horizontal drive thrusters each powered by a respective first electric motor, forming at least two respective horizontal drive units,
• at least four pairs of vertical take-off/landing rotors each powered by a respective second electric motor, and at least four power sources each connected to the respective second electric motor of one of the pairs of vertical take-off/landing rotors, each pair of rotors forming with the respective second electric motors and power source a vertical drive unit, each vertical drive unit comprising a power supply bus whose output can be connected to a single one of the horizontal drive units, the number of vertical drive units being such that each horizontal drive unit is connectable to at least two of the vertical drive units via a respective switch disposed at an input of the horizontal drive unit,
• at least two power generation sources, each connected on the one hand to each of the power supply buses by a respective input of the corresponding vertical drive unit, and on the other hand to each horizontal drive unit via the respective output of each vertical drive unit,
• at least one power supply command configured to send a power command to the power generation sources according to power requirements of the vertical drive units and/or of the horizontal drive units, the power sources supplying electricity according to a difference between the power requirements of the vertical drive units and/or of the horizontal drive units and power emitted by the power generation sources based on the power command, the power generation sources being further configured for recharging the power sources, such that the power sources are passively controlled.