Abstract: The system according to the invention comprises: an electrical network, and a regulating assembly. The regulating assembly includes a secondary electric power source, a conversion assembly for an additional electric power injected on the electrical network, the conversion assembly being able, in a first configuration, to consume the additional electric power present on the network to create a supply fluid of the secondary source. The assembly includes a reservoir for each supply fluid, to collect the supply fluid produced by the conversion assembly.

Abstract: An aircraft fuel storage device having at least one main reservoir designed to contain a first batch of fuel and at least one feed line for supplying a propulsion engine of the aircraft with the first batch of fuel contained in the main reservoir and having at least one auxiliary reservoir, designed to contain a second batch of fuel separate from the first batch of fuel, and wherein the auxiliary reservoir is connected to the main reservoir. The device also having an intake line for bringing the second batch of fuel contained in the auxiliary reservoir toward a combustion chamber of the aircraft independent of the propulsion engine of the aircraft.

Abstract: This assembly (24) includes an emergency electricity generator (60). The electricity generator assembly (24) is controllable between an inactive rest configuration and an active configuration for producing energy in which the emergency electricity generator (60) delivers emergency electric energy to the electric network (20), without being electrically powered by the electric network (20). The emergency electric power generation assembly (24) is able to be placed in an intermediate standby configuration, in which the emergency electric power generation assembly (24) is electrically powered by the electric network (20) so that the emergency electricity generator (60) produces standby electric energy of lower power than the power delivered by the emergency electricity generator (60) in the active configuration.

Abstract: An environmental control system including an upstream assembly supplying outside air to a rotary system of an aircraft, the air not having passed through a propulsion engine of the aircraft, and wherein the rotary system includes a rotary shaft, a power turbine, a compressor and a cold turbine, and wherein the upstream supply assembly is connected to an inlet of the compressor mounted with the rotary shaft that is rotated by the power turbine and wherein the shaft is supplied with compressed gas from the compressor toward the cold turbine.

Abstract: The system according to the invention comprises: an electrical network (20), and a regulating assembly (24). The regulating assembly (24) includes a secondary electric power source (58), a conversion assembly (60) for an additional electric power injected on the electrical network (20), the conversion assembly (60) being able, in a first configuration, to consume the additional electric power present on the network (20) to create a supply fluid of the secondary source (58). The assembly (60) includes a reservoir (62A, 62B) for each supply fluid, to collect the supply fluid produced by the conversion assembly (60).

Abstract: The device according to the invention comprises at least one main reservoir (130A, 130B), the or each main reservoir (130A, 130B) being designed to contain a first batch of fuel. It comprises at least one feed line (144C, 144D) for supplying a propulsion engine (16A, 16B) of the aircraft with the first batch of fuel contained in the main reservoir (130A, 130B). The device (18) comprises at least one auxiliary reservoir (132), designed to contain a second batch of fuel separate from the first batch of fuel, the auxiliary reservoir (132) being connected to the main reservoir (130A, 130B). The device (18) comprises an intake line (160) for bringing the second batch of fuel contained in the auxiliary reservoir (132) toward a combustion chamber of the aircraft independent of the or each engine (16A, 16B) of the aircraft.

Abstract: The system according to the invention comprises a rotary shaft (50), a compressor (54) mounted integral with the rotary shaft (50), a power turbine (52) capable of rotating the rotary shaft (50), a cold expansion turbine (56) rotated by the rotary shaft (50) and supplied with a compressed gas from the compressor (54) toward the cold turbine (56). The system (22) comprises an upstream assembly (42) supplying outside air to the aircraft not having passed through a propulsion engine (16A, 16B) of the aircraft, the upstream supply assembly (42) being connected to an inlet of the compressor (54).