Abstract: A method and a system for inerting an aircraft fuel tank includes at least one inert gas generator. The device includes at least means of determining the inert gas requirement of the aircraft tank(s) in real-time, means of regulating the inert gas flow rate of an inert gas generator, and controlled distribution means of the inert gas in the various fuel tanks and/or various compartments of an aircraft fuel tank. A control unit is capable of real-time determination of an inert gas flow rate setting according to the inert gas requirement of the tank(s) of the aircraft transmitted by the means of determining the inert gas requirement, the settings being transmitted in real time to the inert gas flow rate regulating means, and is also capable of determining the inert gas distribution control settings to the controlled distribution means of inert gas into the various fuel tanks and/or various compartments of a fuel tank.

Abstract: The present disclosure relates to a device for measuring the amount of oxygen present in a gas to be analyze. The device includes at least one member for measuring the amount of oxygen, a first inlet in communication with the measuring member for the supply of gas to be analyzed, and an outlet for the discharge of said analyzed gas. The device also includes a second inlet intended to communicate with the measuring member, allowing said device to be supplied selectively with a calibration gas having a known amount of oxygen, such that the measurement of the amount of oxygen present in the calibration gas makes it possible to determine a potential drift of the measurement of said measuring member relative to the actual known amount of oxygen present in the calibration gas.

Abstract: A method for the inerting of at least one fuel tank of an aircraft, by means of at least one inert gas generation system, remarkable in that the inert gas generation system is started when at least one oxygen sensor within the tank measures an oxygen level that is above a high threshold.

Abstract: 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.

Abstract: An inerting system of a fuel tank of an aircraft includes an air separation module supplied at the inlet with air at a certain pressure to generate at the outlet an inert gas to be injected into the fuel tank comprising a certain flow rate and a certain oxygen concentration. A control method includes, at a given instant and at a constant air temperature and atmospheric pressure, (1) reducing the inert gas flow rate to a determined value, and (2) reducing the air pressure in order to cause an increase in the oxygen concentration from an initial value to a determined value. Decreasing the inert gas flow rate is performed by compensating for a loss of inert gas flow caused by the air pressure reduction, and decreasing the air pressure is performed by compensating for a reduction in the oxygen concentration caused by the inert gas flow rate reduction.

Abstract: The present disclosure relates to a device for measuring the amount of oxygen present in a gas to be analyze. The device includes at least one member for measuring the amount of oxygen, a first inlet in communication with the measuring member for the supply of gas to be analyzed, and an outlet for the discharge of said analyzed gas. The device also includes a second inlet intended to communicate with the measuring member, allowing said device to be supplied selectively with a calibration gas having a known amount of oxygen, such that the measurement of the amount of oxygen present in the calibration gas makes it possible to determine a potential drift of the measurement of said measuring member relative to the actual known amount of oxygen present in the calibration gas.

Abstract: A method for controlling an inerting system designed to inject a flow of inert gas into a fuel tank of an aircraft during a mission. The method includes: determining a value of a parameter of the mission of the aircraft at a given moment; determining the ratio between the determined value of the mission parameter and a value at the given moment of an equivalent parameter of a standard mission profile, and deducing a weight coefficient therefrom; using the weight coefficient to weight a value of the inert gas flow rate recommended by the standard mission profile for the value of the equivalent parameter at the given moment so that an appropriate inert gas flow rate to be injected is determined for the needs of the mission at the given moment; and commanding the inerting system to inject the inert gas flow rate determined at the given moment.

Abstract: An inerting system of a fuel tank of an aircraft includes an air separation module supplied at the inlet with air at a certain pressure to generate at the outlet an inert gas to be injected into the fuel tank comprising a certain flow rate and a certain oxygen concentration. A control method includes, at a given instant and at a constant air temperature and atmospheric pressure, (1) reducing the inert gas flow rate to a determined value, and (2) reducing the air pressure in order to cause an increase in the oxygen concentration from an initial value to a determined value. Decreasing the inert gas flow rate is performed by compensating for a loss of inert gas flow caused by the air pressure reduction, and decreasing the air pressure is performed by compensating for a reduction in the oxygen concentration caused by the inert gas flow rate reduction.

Abstract: A method for controlling an inerting system designed to inject a flow of inert gas into a fuel tank of an aircraft during a mission. The method includes: determining a value of a parameter of the mission of the aircraft at a given moment; determining the ratio between the determined value of the mission parameter and a value at the given moment of an equivalent parameter of a standard mission profile, and deducing a weight coefficient therefrom; using the weight coefficient to weight a value of the inert gas flow rate recommended by the standard mission profile for the value of the equivalent parameter at the given moment so that an appropriate inert gas flow rate to be injected is determined for the needs of the mission at the given moment; and commanding the inerting system to inject the inert gas flow rate determined at the given moment.

Abstract: A method for the inerting of at least one fuel tank of an aircraft, by means of at least one inert gas generation system, remarkable in that the inert gas generation system is started when at least one oxygen sensor within the tank measures an oxygen level that is above a high threshold.

Abstract: A method and a system for inerting an aircraft fuel tank includes at least one inert gas generator. The device includes at least means of determining the inert gas requirement of the aircraft tank(s) in real-time, means of regulating the inert gas flow rate of an inert gas generator, and controlled distribution means of the inert gas in the various fuel tanks and/or various compartments of an aircraft fuel tank. A control unit is capable of real-time determination of an inert gas flow rate setting according to the inert gas requirement of the tank(s) of the aircraft transmitted by the means of determining the inert gas requirement, the settings being transmitted in real time to the inert gas flow rate regulating means, and is also capable of determining the inert gas distribution control settings to the controlled distribution means of inert gas into the various fuel tanks and/or various compartments of a fuel tank.

Abstract: Method for providing power to a passenger seat (10), whereby the passenger seats are individually fitted with removable fuel cells. The seat fitted with a fuel cell can then use fuel cell power, as well as the by-products generated by the fuel cell to supply energy and elements to optional seat functions. The method involves easily removing and replacing a fuel cell source/bottle associated with a passenger seat, such that even passengers can conduct the replacement, rather than crew members, which allows for fast and easy replacement, without any required tools or mechanical knowledge.

Abstract: The invention concerns a self-propelled vehicle, in particular an aircraft, comprising an onboard equipment such as an inerting system, means for vapour pollutant filtering (1) arranged between an air intake (8) connected to a compressed air source and an air outlet (9) connected to the equipment. The invention is characterized in that the vapour pollutant filtering means (1) comprise adsorption filtering means such as molecular sieve and/or activated carbon.

Abstract: The invention concerns a self-propelled vehicle, in particular an aircraft, comprising an onboard equipment such as an inerting system, means for vapour pollutant filtering (1) arranged between an air intake (8) connected to a compressed air source and an air outlet (9) connected to the equipment. The invention is characterized in that the vapour pollutant filtering means (1) comprise adsorption filtering means such as molecular sieve and/or activated carbon.

Abstract: The inventive method for extinguishing fire in an aircraft cargo compartment (3) consists in injecting a substantially pure nitrogen from high-pressure storage cylinders (12), in simultaneously actuating a device (5) for separating air and supplying nitrogen and in continuously introducing the nitrogen produced by said air separation device (5) into the compartment (3).

Abstract: The invention relates to a system for inerting a compartment of a vehicle, typically a fuel tank (1) for supplying the gas turbine (3) of an aircraft with fuel. Said system comprises a filtering device (5) arranged between the compressed air source (3) and the device for separating gas from the air (8), which typically comprises polymer membranes, said filtering device being provided with at least one catalysis section (51) for the heat decomposition of pollutants that may be present in a vapour phase in the compressed air, and at least one HEPA filtering section (52, 53). The inventive system can be especially used to inert a fuel tank for a civil or military aviation aircraft.

Abstract: The invention relates to an installation for producing oxygen of high purity, which is advantageously installed in a transportable container (21), comprising: an upstream pressure-swing-adsorption (PSA) device (A1) containing a zeolite sieve; a downstream PSA device (A2) containing a carbonaceous sieve; in a loop between the two devices, a permeation device (P) capable of separating oxygen form argon; and a medium-pressure oxygen compressor (20). The invention is used for producing oxygen of high purity on-site, typically in isolated locations.

Abstract: Method for protecting a moving motor vehicle against fire, the vehicle comprising at least one confined zone (1) comprising at least one inflammable member or element such as an engine compartment or a fuel tank, comprising a step for generating an inert gas consisting of nitrogen-enriched air and a step for diffusing an inert gas generated in the said inflammable confined zone(s) (1), characterized in that the inert gas generating step and the gas diffusing step are carried out permanently at least during the periods of use of the vehicle.

Abstract: The on-board system comprises: an OBIGGS (2) that supplies, via outlet (6), nitrogen for inerting compartments (15, 16, 17) of an aircraft; a first OBOGS (3) that supplies oxygen to a supply circuit (19) for aircraft occupant masks (20, 21), the OBIGGS (2) and first OBOGS (3) being supplied with compressed air coming from the aircraft engines (13), and; a second solid electrolyte OBOGS (4) that furnishes, via outlet (24), pressurized pure oxygen stored in a pressurized oxygen tank (26) that can be connected to the oxygen supply line (19).

Abstract: According to this process, there is supplied to the passengers a first fraction of air enriched in oxygen from independent supply elements, in particular high pressure cylinders (16), during a descent phase of the aircraft between a normal cruising altitude and an intermediate re-routing altitude. There is moreover compressed air taken from a source of compressed air belonging to the aircraft, to produce (in 2) a second fraction of the air enriched in oxygen which is delivered to the passengers, at least during a phase of stabilized flight of the aircraft, adjacent the re-routing altitude, greater than 5,500 meters.