A system for inerting at least one volume in an aircraft includes at least one generator of inert gas fed with compressed air originating from a passenger cabin, and means for distributing the inert gas into the volume to be rendered inert, which are connected to the generator of inert gas. According to the invention, the generator of inert gas comprises a fuel cell including an outlet of oxygen-depleted gas connected to means for drying said gas.

A generator of inert gas from an airflow, in an inerting system for at least one aircraft fuel tank is disclosed. The generator includes a system with an air inlet and means for distributing the airflow to a plurality of air separation modules arranged in parallel on the air system to deplete oxygen in the air and generate a nitrogen-enriched inert gas at the outlet. The generator also includes a programed control unit for the distribution means to selectively supply air to a single, a portion or all of the air separation modules, depending on the flight phase of the aircraft.

A vehicle oxygen indication system that includes at least one oxygen source, and a plurality of oxygen assemblies. Each oxygen assembly includes a hose, a switch, a mask, and a flow indicator. The hose includes a lumen through which oxygen can flow from the oxygen source to the mask. The switch is switchable between a normal state when oxygen is not flowing from the oxygen source to the mask and a flow state where oxygen flows to the mask. When the switch is in the flow state, the flow indicator is switched from a static state to an indication state.

Described herein are methods which involve minimizing or eliminating the occurrence of delayed negative effects that may arise from exposure to reduced oxygen partial pressure. An amount of supplemental oxygen, which substantially mimics a target oxygen partial pressure, is administered to an individual that is exposed to a reduced oxygen partial pressure environment, to compensate for the reduced oxygen partial pressure. The target partial pressure may be selected such that the individual experiences substantially no change in the oxygen partial pressure. Individuals receiving the supplemental oxygen may be healthy, have special sensitivities, or have a pre-existing neurological condition.

An environmental control system (ECS) includes an air conditioning pack that receives outside air; a regenerative treatment subsystem, wherein the treatment subsystem includes a treatment bed configured to cycle between an adsorption phase and a desorption phase; and a fan that receives recirculated air from the environment and moves the recirculated air to a mixing manifold.

An emergency oxygen system for aircraft comprising: a breathing gas supply circuit to be connected upstream to a source of breathing gas and downstream to at least one mask, a flow control valve configured to adjust the flow of breathing gas supplied to the mask, an electronics board configured to control the flow control valve, a power source, a switching device interposed between the power source and the electronics board, the switching device comprising a switch configured to have a first state in which power from the power source is supplied to the electronics board and a second state in which the electronics board is not supplied with power from the power source.

A cryogenic cooling system for an aircraft includes a first air cycle machine, a second air cycle machine, and a means for collecting liquid air. The first air cycle machine is operable to output a cooling air stream based on a first air source. The second air cycle machine is operable to output a chilled air stream at a cryogenic temperature based on a second air source cooled by the cooling air stream of the first air cycle machine. An output of the second air cycle machine is provided to the means for collecting liquid air.

A system for an aircraft includes an engine bleed source of a gas turbine engine. The system also includes a means for chilling an engine bleed air flow from the engine bleed source to produce a chilled working fluid. The system further includes a means for providing the chilled working fluid for an aircraft use.

A propulsion system includes an electric fan propulsion motor with a plurality of propulsion motor windings. The propulsion system also includes a means for controlling a flow rate of a working fluid through a cryogenic working fluid flow control assembly to the propulsion motor windings.

Described herein are a system for providing oxygen to oxygen masks in an aircraft, and an associated method for regulating the oxygen flow in an efficient manner. The system has an oxygen tank, oxygen masks, first and second oxygen lines, and an electrically controllable valve. The valve is coupled to the oxygen tank and the two oxygen lines. The oxygen masks are coupled to the oxygen lines downstream of the valve to accommodate the transfer of oxygen from the oxygen tank via the valve. In a working state when an electrical signal is applied the valve produces a connection between the oxygen tank and the first oxygen line when required, and permanently prevents a connection between the oxygen tank and the second oxygen line. When in a rest state, the valve produces a permanent connection between the oxygen tank and the second oxygen line.