An aircraft electrical network comprising: - at least one device for generation of an electric current, called the electrical power current, - at least one variable electric power supply circuit: - adapted to be connected to an electric motor, called the compressor motor, to drive a compressor of a thermal management device (25, 26, 27), - arranged to be able to receive an electric power current and to output an electric power supply current for said compressor motor with a variable power supply determined by a control logic - at least one electrical device (28, 29) providing protection against icing of an external surface of the aircraft, characterised in that: - said at least one electrical icing protection device (28, 29) is adapted so that it can be electrically powered by an electrical power supply current output by at least one of said variable electrical power supply circuits (24b, 24d, 24e), called shared electrical power supply (24b, 24d, 24e), of a compressor motor of a thermal management device (25, 26, 27), - said at least one shared electrical power supply is adapted to be connected to said compressor motor through a switching device to which said at least one electrical icing protection device (28, 29) is also connected, - it also comprises a control unit of said switching device programmed so as, if altitude criteria of the aircraft are satisfied, to place said switching device in a state called the second state, in which the shared electrical power supply (24b, 24d, 24e) is electrically connected to said at least one electrical icing protection device (28, 29) connected to this switching device, the shared electrical power supply (24b, 24d, 24e) then being able to supply an electrical power supply current to this electrical icing protection device (28, 29). - at least one device for generation of an electric current, called the electrical power current, - at least one variable electric power supply circuit: - adapted to be connected to an electric motor, called the compressor motor, to drive a compressor of a thermal management device (25, 26, 27), - arranged to be able to receive an electric power current and to output an electric power supply current for said compressor motor with a variable power supply determined by a control logic - adapted to be connected to an electric motor, called the compressor motor, to drive a compressor of a thermal management device (25, 26, 27), - arranged to be able to receive an electric power current and to output an electric power supply current for said compressor motor with a variable power supply determined by a control logic - at least one electrical device (28, 29) providing protection against icing of an external surface of the aircraft, - said at least one electrical icing protection device (28, 29) is adapted so that it can be electrically powered by an electrical power supply current output by at least one of said variable electrical power supply circuits (24b, 24d, 24e), called shared electrical power supply (24b, 24d, 24e), of a compressor motor of a thermal management device (25, 26, 27), - said at least one shared electrical power supply is adapted to be connected to said compressor motor through a switching device to which said at least one electrical icing protection device (28, 29) is also connected, - it also comprises a control unit of said switching device programmed so as, if altitude criteria of the aircraft are satisfied, to place said switching device in a state called the second state, in which the shared electrical power supply (24b, 24d, 24e) is electrically connected to said at least one electrical icing protection device (28, 29) connected to this switching device, the shared electrical power supply (24b, 24d, 24e) then being able to supply an electrical power supply current to this electrical icing protection device (28, 29).