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: A fuel tank with a venting system includes a flap for closing and opening a vent made in the tank. The flap is coupled to a float. The flap includes a valve coupled to a second float mounted in a hinged manner in the tank so that the valve adopts a closed position, being pushed by the second float when the level of fuel in the tank reaches a certain threshold, and an open venting position in order to prevent overpressure within the tank, being driven by the second float when the level of fuel is below the threshold and the force exerted by the internal pressure on the valve is less than the sum of the forces exerted on the valve by the atmospheric pressure and by the weight of the second float.

Abstract: 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.

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 data transmission system including an emitting device, a receiving device and a communication link, wherein the emitting device includes: a radio frequency emitter connected to the communication link; a power line connected to the communication link at a connection point, wherein the power line is brought to a supply voltage; and a capacitive coupling component connected between the radio frequency emitter and the connection point, wherein the receiving device includes: a radio frequency receiver connected to the communication link for receiving the radio frequency signal; a power line connected to the communication link at a connection point; and a capacitive coupling component connected between the connection point and the radio frequency receiver, wherein the capacitive coupling components transmit the radio frequency signal and block the supply voltage.

Abstract: An emitting device includes: an oscillator configured for generating at least one carrier wave; an emitter including: at least one input connected to the oscillator; an activation input configured for receiving a signal representative of data to be transmitted; at least one output configured to generate a carrier wave modulated by the signal representative of the data to be transmitted; a communication link connected to the output of the emitter; a power line connected to the communication link at a connection point; a capacitive coupling component connected between the output of the emitter and the connection point. A receiving device and a system for transmission are also described.

Abstract: Breathing mask comprising a shell and a harness, wherein: the breathing mask also comprises a folding system adapted to make the harness move from an extended position to a folded position, the folding system also comprises a pulling device and a guide device, the pulling device has a connecting portion connected to the harness and a gripping portion, the guide device is connected to the shell, the pulling device is free to move between a first position and a second position, and the guide device cooperates with the pulling device to guide the pulling device between the extended position and the folded position.

Abstract: Method for circulating fuel in a filling line (2) of a tank of an aircraft. The method according to the invention involves automatically and mechanically varying the cross-section for passage of the fuel until the fuel reaches a threshold maximum speed. A valve (1) connected to a filling line (2) of an aircraft fuel tank, for implementing said method. According to the invention, it comprises a device (7) for restricting the cross-section for passage of the fluid, capable, when the fuel circulates in the line (2), of automatically varying the cross-section for passage of the fuel, until the speed of the fuel reaches a threshold maximum value.

Abstract: The invention relates to a fluid nonreturn device (1) comprising a body (2) defining a chamber (5) intended to receive a fluid and having at least one opening (3), the chamber (5) has an internal wall (6) extended by an elastic return member (8) which forms an integral part of said internal wall (6), said elastic return member (8) is extended by a valve shutter (9) forming an integral part of said elastic return member (8), the elastic return member (8) pushes the valve shutter (9) into a position in which it closes off the opening (3) so as to prevent the fluid in the chamber (5) from leaving via the opening (3).

Abstract: The invention relates to a method of sequencing commands to execute N sets of instructions, where N is a natural number greater than or equal to two, said method being implemented by a control unit suitable for periodically receiving time interrupts and for generating commands to execute the sets of instructions to be executed, said control unit comprising at least a main counter. The method comprises the steps of: a) initializing the main counter; b) incrementing the main counter upon receipt of a time interrupt; c) generating a command to execute a set of instructions to be executed, said set of instructions being selected based on an instantaneous value p of the main counter; d) repeating steps a) to d).

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 for determining the water content in the atmosphere by image processing comprises: determining the number of particles contained in a size range; measuring the mass of particles having a size in the size range from the determined number of particles; determining the number of particles having a size equal to a threshold size; evaluating the number of particles outside of the given size range from the determined number of particles and from the threshold size; estimating the mass of particles outside of the size range from the evaluated number of particles; and determining the water content by addition of the estimated mass and the measured mass.

Abstract: A device for determining the water content in the atmosphere comprising: a laser transmitter suitable for transmitting a laser beam for illuminating particles of water and/or ice present in the atmosphere, a first out-of-focus imager having a first collection angle suitable for capturing at least one first representative image of the particles, and processing unit in communication connection with the first image. The device further comprises a second out-of-focus imager having a second collection angle suitable for capturing at least one second image. The processing unit is in communication connection with the second imager, the processing unit being suitable for processing the first and second images in order to determine the water content in the atmosphere.

Abstract: Embodiments of the present disclosure relate generally to the use of the fuel cell systems on board aircraft and other passenger transportation vehicles and to methods of using heat, air, and water generated by such fuel cell systems. The heat may be used to address condensation within the aircraft. The heat may be used to help evaporate excess water that would otherwise condense in the aircraft skin. The excess water collected may be used to create humidification for cabin air. In other examples, the heat, warmed air, or warmed water may be delivered to other locations or heating systems for beneficial use.

Abstract: Embodiments of the present disclosure relate generally to systems and methods for providing improved aircraft fuel cell systems. In one embodiment, the system provides separate zones, maintaining various equipment components in separate controlled hydrogen concentration zones. In one embodiment, the fuel cell system provided may be simpler such that it functions without a power converter and autonomous such that it functions without need for power from any aircraft supply.

Abstract: Assembly intended in particular to be arranged in a cockpit of an aircraft, said assembly comprising a respiratory mask and a stowage device, wherein: the respiratory mask has a face cover and a harness, the stowage device comprises a base and a platform, the platform is adapted to receive the respiratory mask in a stowage position where the harness forms a loop extending around the platform, the platform comprises a main element movable relative to the base between a retracted position and a protruding position, and the platform further comprises auxiliary elements, the auxiliary elements movable with respect to the main element between a flattened configuration and an expanded configuration of the platform.

Abstract: Assembly intended to be arranged in an aircraft cockpit having a pressurized cabin, in order to supply a breathing gas to a crew member, said assembly comprising a respiratory mask having an oronasal face cover and a harness, the oronasal face cover having a respiratory cavity and being suitable for applying on the face of the crew member around the mouth and nose, the harness forming a loop adapted to be extended around the head of the user on a side opposite from the oronasal face cover so as to hold the oronasal face cover on the face of the user, and a storage device, said storage device comprising a base and a platform, the platform being mounted so as to be movable relative to the base between a retracted position and an extended position, the platform having a receiving surface, the receiving surface of the platform being adapted to receive the respiratory mask in a storage position where the harness holds the oronasal face cover against the receiving surface of the platform by encircling the platform

Abstract: Embodiments provide methods for storing a respiratory mask. In one embodiment, the respiratory equipment may include a respiratory mask having a front side and a rear side and a cavity having an opening in the rear side. There may also be provided an inflatable harness adapted to maintain the respiratory mask against the user face, and a storage element comprising a housing. In one embodiment, the method may include pulling on the harness on the front side of the respiratory mask in order to place the harness on the respiratory mask in an storage position outside said cavity, and maintaining the harness on the respiratory mask in the storage position and inserting the respiratory mask into the housing of the storage element.

Abstract: A stowage device of emergency equipment for aircraft crewmember, the stowage device comprising a housing, the housing extends along a longitudinal direction and has side walls, a back wall and an opening opposite to the back wall, the side walls and the back wall define an internal space adapted to stow a respiratory mask in a stowage position, the side walls extend along the longitudinal direction up to a front edge delimiting the opening. One of the side walls is an adjustable wall. The housing comprises a frame and a movable element. The movable element is mounted on the frame and is movable between a retracted position and a protruding position. The movable element comprises a main movable panel and the adjustable wall includes the main movable panel.

Abstract: The invention relates to a method for detecting the presence of ice crystals in an environment, implemented by a detection device in relative motion with respect to said environment, said method comprising at least: an emission step, in which at least one optical radiation is emitted by the detection device into the environment; a reception step, in which at least a portion of the emitted optical radiation is received, a step of calculating a comparison signal, and a step of calculating the noise of the comparison signal, a thresholding step, in which the noise is compared to a defined threshold, a communication step, in which a signal indicating detection of the presence of ice crystals in the environment is transmitted when the noise is greater than the defined threshold.