An environmental control system for a space vehicle includes an oxygen supply, a nitrogen supply, a first pressure control panel having a first oxygen control board configured to receive an oxygen gas from the oxygen supply and a first nitrogen control board configured to receive a nitrogen gas from the nitrogen supply, and a supervisory controller configured to control the first pressure control panel and thereby to adjust a partial pressure of oxygen and an ambient pressure of an oxygen/nitrogen gas mixture within a first module.

A system for increasing an indoor pressure of an air mobility is provided. The system maintain the indoor pressure of the air mobility using an air conditioner provided in the air mobility without additional equipment and without increasing the weight of an airframe, thereby preventing external harmful gas from being introduced into the indoor space and thus ensuring the safety of a passenger.

A processing system deployed in a carrier transport vehicle may establish a wireless communication session with a mobile device of a user, assign a zone of the carrier transport vehicle to the user, the zone including a plurality of network-connected devices, obtain a user profile from the mobile device of the user, determine at least one biometric sensor accessible via the mobile device of the user, obtain biometric data of the user from the at least one biometric sensor accessible via the mobile device of the user, determine a condition of the user based upon the biometric data, identify at least one adjustment to at least one of the plurality of network-connected devices in response to the condition of the user that is determined and the user profile, and apply the at least one adjustment to the at least one of the plurality of network-connected devices.

An oxygen generator for use in a passenger aircraft comprises an oxygen generating substance for generating oxygen gas after being activated; an activating substance for activating the oxygen generating substance; a pyroelectric igniter for igniting the activating substance upon receiving an electric trigger input; a housing defining a gas-tight chamber, accommodating the oxygen generating substance, the activating substance and the pyroelectric igniter; at least two electric conductors, coupled to the pyroelectric igniter and extending through a passage in the housing between an interior of the gas-tight chamber and an exterior of the gas-tight chamber; and at least one of a gas-tight glass-to-metal sealing and a gas-tight ceramic-to-metal sealing, sealing the at least two electric conductors with respect to the housing at the passage.

An oxygen generator outlet manifold assembly that includes an outlet manifold and an end cover. The outlet manifold includes a main body portion with inner and outer surfaces and at least a first hose connector that includes an outlet defined therein extending from the main body portion. The main body portion defines a main body portion interior that includes a connection opening defined in the inner surface, a ring chamber, a flow space and a distribution chamber. An annular ring is positioned in the main body portion chamber interior and separates the ring chamber from the distribution chamber. The end cover includes a generator outlet portion extending therefrom that is received in the connection opening. The generator outlet portion includes an outlet valve having an open and a closed state and includes an interior chamber that cooperates with the ring chamber to define an outlet chamber. An oxygen flow path is defined through the open valve, to the outlet chamber, through the flow space, through the distribution chamber and to the outlet of the first hose connector.

An engine-driven cryogenic cooling system for an aircraft includes a first air cycle machine, a second air cycle machine, and a means for condensing a chilled air stream into liquid air for an aircraft use. The first air cycle machine includes a plurality of components operably coupled to a gearbox of a gas turbine engine and configured to produce a cooling air stream based on a first engine bleed source of the gas turbine engine. The second air cycle machine is operable to output the chilled air stream at a cryogenic temperature based on a second engine bleed source cooled by the cooling air stream of the first air cycle machine.

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 apparatus is disclosed that includes an aircraft or repurposed aircraft or fuselage having a cabin capable of pressurization, a way to pressurize the cabin whether by built in machinery or external apparatus, a way to deliver oxygen to a plurality of persons in the cabin, a source of hyperbaric oxygen, a pressure gauge or regulator configured to measure or regulate a pressure of the hyperbaric oxygen or the aircraft, a plurality of face or head coverings configured to provide the hyperbaric oxygen to persons or patients in need thereof, and an optional exhaust system configured to remove gas(es) from the face or head coverings without releasing the gas(es) into the cabin. Each of the face or head coverings includes a gas inlet, a gas outlet, and one or more seals adapted to contain oxygen in the face or head covering at a pressure greater than 1 atm. A related kit and a related method of treating persons with hyperbaric oxygen are also disclosed.

An aircraft is capable of passing from the aerial domain to the spatial domain and method for automatically adapting the configuration of same. An additional breathable gas supply is provided to be activated only during a flight phase during which aerobic propulsion is interrupted, and is capable of supplying the control system of the manned cabin environment instead of the system associated with the aerobic propulsion means.

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.