An oxygen supply device for an aircraft has a reaction tank for chemical oxygen generation and a pressurized tank filled with oxygen. The oxygen supply device also has an energy converter for converting thermal energy into electrical energy and also a control unit for setting a first amount of oxygen, provided by the reaction tank to a consumer unit, and a second amount of oxygen, provided by the pressurized tank to the consumer unit. The energy converter is designed to convert a thermal energy, generated by the chemical oxygen generation in the reaction tank, into electrical energy and to provide the electrical energy. The control unit is designed to set the second amount of oxygen, provided by the pressurized tank to the consumer unit, by using the electrical energy provided by the energy converter. The invention also relates to a method for supplying a passenger cabin of an aircraft with oxygen.

A method for monitoring breathing air of a person breathing via a face mask (8). In the method pressure of inhaled air and partial pressure of oxygen before oxygen enters in the face mask (8) are measured. A partial pressure of oxygen in lungs of the person is estimated on the basis of the measured pressure of inhaled air and the measured partial pressure of oxygen. Also at least one physical characteristics of lungs is taken into account. The estimated partial pressure of oxygen in lungs is compared with a threshold. An indication of impending hypoxia is provided to the person, if the comparison indicates that the estimated partial pressure of oxygen in lungs is at a level lower than the threshold. The present disclosure also relates to an apparatus (6) for implementing the method.

An air separation module includes a cylindrical canister and a separator. The cylindrical canister has a longitudinal axis, an inlet, an oxygen-depleted air outlet, and a drain portion with an oxygen-enriched air outlet. The separator is arranged within the cylindrical canister to separate a compressed air flow into an oxygen-depleted air flow fraction and an oxygen-enriched air flow fraction, the oxygen-depleted air flow fraction provided to the oxygen-depleted air outlet and the oxygen-enriched air flow fraction to the drain portion of the canister. The drain portion extends tangentially from the cylindrical canister to issue the oxygen-enriched air flow fraction with entrained condensate from the oxygen-enriched air outlet with a tangential flow component. Nitrogen generation systems and methods of removing condensate from air separation modules are also described.

A fuel tank inerting system of an aircraft includes a first air flow provided from a first source having a first temperature and a second air flow including cabin outflow air having a second temperature. The first temperature is greater than the second temperature. A fuel tank inerting heat exchanger is arranged in fluid communication with both the first air flow and the second air flow. At least one air separating module is configured to separate an inert gas from the first air flow output from the fuel tank inerting heat exchanger.

Disclosed is an aircraft environmental control and fuel tank inerting coupling system based on a membrane separation method. The dehumidification of gas in an aircraft environmental control system and the separation of oxygen and nitrogen in a fuel tank inerting system are realized respectively, based on the selective permeability of a membrane to water vapour/air and oxygen/nitrogen. In the coupling system, part of drying gas passing through a membrane dehumidification heat exchanger (5) enters a membrane air separator (9), and the other part thereof is cooled through a large expansion turbine (8) and then directed into a cockpit for refrigeration; and nitrogen-rich gas generated by the membrane air separator (9) is directed into a fuel tank for inerting. Oxygen-rich gas is mixed with gas supplied by the environmental control system, thus increasing the oxygen content of gas supplied by the aircraft cockpit.

The present invention relates to flying scooter comprising a base made of fibreglass, 20 fans with 20 motors connected to a power system with components comprising capacitors, batteries, photovoltaic solar cells, an oxygen generator, a regulator, electronic sensors, and electronic chips. The scooter has a circular front part that includes a display that gives operational levels of the components, and the base has a cavity for the passenger's legs, and a rubber strap for securing the passenger. Manual controls are provided as well as a grip for the controls. The controls are connected to the sensors and electronic chips wirelessly.

A thermal sensor and a method of making a thermal sensor is disclosed. The thermal sensor includes a first electrode, a second electrode, and a composition between the first and second electrodes. The composition includes solid particles of a state-changing material that transitions at a threshold temperature between solid and liquid states having different electrical conductivities.

A system is disclosed for aircraft life support and generating inert gas. The system includes an electrochemical cell with a cathode and an anode separated by a proton transfer medium. A cathode supply fluid flow path is between an air source and a cathode fluid flow path inlet, and an inerting gas flow path is in operative fluid communication with a cathode fluid flow path outlet and a protected space. An anode supply fluid flow path is between a water source and an anode fluid flow path inlet, and an oxygen gas flow path is in operative fluid communication with an anode fluid flow path outlet and an aircraft occupant breathing device. An electrical connection is between a power source and the electrochemical cell.

Aircrafts and methods for reusing oxygen enriched air. In one embodiment, an aircraft includes an oxygen supply subsystem configured to supply oxygen to a cabin of the aircraft, and an air separator configured to receive a pressurized air stream, to separate the pressurized air stream into oxygen enriched air and an inert gas, and to feed the oxygen enriched air to the oxygen supply subsystem.

A fuel system is provided for an aircraft having a fuel source. The fuel system includes a fuel oxygen reduction unit defining a liquid fuel supply path, a stripping gas supply path, a liquid fuel outlet path, and a stripping gas return path, wherein the stripping gas return path is in airflow communication with the fuel source.