Abstract: A connection system comprising: a dispensing member; a receiving member; first sealing means and second sealing means arranged at the interface between the dispensing member and the receiving member to enable redundant leak-tight engagement between the dispensing member and the receiving member; a control chamber defined between the first sealing means and the second sealing means; and means for measuring the current pressure in the control chamber so as to detect a gas leak.

Abstract: A fuel cell, in particular for an aeronautical application, comprising a central module comprising a plurality of cells for generating electricity, a first end plate and a second end plate, at least one of the end plates comprising at least one outlet pipe. The fuel cell comprises a pressure-regulating device fluidly connected to the outlet pipe, the pressure-regulating device comprising at least one arm fluidly connected to the outlet pipe, at least one member for opening/closing the arm, at least one member for measuring the pressure in the outlet pipe and at least one member for controlling the opening/closing member according to the measured pressure.

Abstract: An electrical power supply device in an aircraft, the device including an enclosure, the enclosure containing at least: a fuel cell; a dihydrogen generator; a gas feed circuit connecting the dihydrogen generator to the anode of the fuel cell; an oxygen feed device feeding the cathode of the fuel cell; and a cooling circuit of the fuel cell associated with at least one heat exchanger; wherein the enclosure is mounted on an actuator system, the actuator system being configured to move the enclosure from a first position in which the enclosure is housed inside an outer wall of the aircraft, to a second position in which the enclosure projects from the outer wall.

Abstract: A mobile system for generating electricity, in particular for an aircraft, said generator system comprising a dioxygen source, a dihydrogen source and a fuel cell generating electricity from dioxygen and dihydrogen. The generator system comprises an aircraft container that is configured to be carried in an aircraft and in which the sources and said fuel cell are mounted, the generator system including an electrical connection module electrically connected to the fuel cell and including an electrical connection output port that is configured to be electrically connected to an aircraft so as to supply it with electricity.

Abstract: A fuel cell, in particular for an aeronautical application, comprising a central module comprising a plurality of cells for generating electricity, a first end plate and a second end plate, at least one of the end plates comprising at least one outlet pipe. The fuel cell comprises a pressure-regulating device fluidly connected to the outlet pipe, the pressure-regulating device comprising at least one arm fluidly connected to the outlet pipe, at least one member for opening/closing the arm, at least one member for measuring the pressure in the outlet pipe and at least one member for controlling the opening/closing member according to the measured pressure.

Abstract: A connection system comprising: a dispensing member; a receiving member; first sealing means and second sealing means arranged at the interface between the dispensing member and the receiving member to enable redundant leak-tight engagement between the dispensing member and the receiving member; a control chamber defined between the first sealing means and the second sealing means; and means for measuring the current pressure in the control chamber so as to detect a gas leak.

Abstract: An electrical power supply device in an aircraft, the device including an enclosure, the enclosure containing at least: a fuel cell; a dihydrogen generator; a gas feed circuit connecting the dihydrogen generator to the anode of the fuel cell; an oxygen feed device feeding the cathode of the fuel cell; and a cooling circuit of the fuel cell associated with at least one heat exchanger; wherein the enclosure is mounted on an actuator system, the actuator system being configured to move the enclosure from a first position in which the enclosure is housed inside an outer wall of the aircraft, to a second position in which the enclosure projects from the outer wall.