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: 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: 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: 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: 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: 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: 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: 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.

Abstract: A method for manufacturing a strainer, such as a strainer of an ejector used to transfer fuel between two tanks of an aircraft or to supply fuel to an engine is provided. The strainer includes a conduit whereof a first end is intended to be connected to an inlet of the ejector, and whereof a second end is located within a housing including an open face for the passage of fuel, the open face being closed off by a grate acting as a filter. The method includes the step of manufacturing the conduit, the housing and the grate of the strainer as a single monobloc part.

Abstract: A fluid gauging system includes a set of fuel level probes and two computation modules adapted for inferring fluid level information based on measurement signals which originate from the probes. In a refuelling operation mode, the probes are distributed into two dynamically configurable subsets, which are separate and assigned respectively to the computation modules for deriving two results for the fluid level independently from each other. Such system has special interests for fuel tank equipment designed for aircraft. A major advantage is a reduction in the total number of fuel level probes which are necessary to obtain reliable results whatever the fuel level and the aircraft attitude and acceleration.

Abstract: A capacitor fuel probe comprises a plurality of capacitor segments which are superposed on one another along a probe axis. The capacitor segments are distributed into three sets and connected electrically in parallel within each set separately. A capacity measurement which is performed for all the sets allows determining a fuel level while taking into account a possible variation of a dielectric constant of the fuel parallel to the probe axis. Top height values hn of the capacitor segments are selected so that hn?1<hn·(Kmin?1)/(Kmax?1), for any integer n-value from 2 to N, N being the number of capacitor segments, n varying according a superposition order of the capacitor segments, and Kmin and Kmax being minimum and maximum values for a fuel dielectric constant which are prescribed for the capacitor fuel probe.

Abstract: A breathing system for an aircraft crew member or passenger may include a face-fitting device, a storage area added to a seat headrest for retaining the face-fitting device in a storage position apart from the head, and a back portion for retaining the face-fitting device on the user's head when the breathing system is used. The back portion is retained on the headrest by a removable fixing mechanism when the face-fitting device is in the storage position, and the removable fixing mechanism is released upon the tightening the face-fitting device on the user's head.

Abstract: Described are inerting systems that may be used on board an aircraft or other passenger transportation vehicle to reduce a risk of fire due to electronic components or to other elements in a compartment and to assist in preventing or extinguishing any fire or hazardous condition that may occur. The systems include a source of inert gas such as oxygen depleted air generated from a fuel cell on board the aircraft. The oxygen depleted air or other inert gas is conveyed through ducts to compartments that house the electronics, thus changing the conditions in the compartment to be less conducive to fire.

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 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.