Abstract: A gear assembly for a side stick on an aircraft. The gear assembly includes a first gear, a second gear configured to engage with the first gear, and a viscoelastic material provided in the first gear.

Abstract: The brake assembly includes a housing, a rotor disc. The rotor disc includes at least one internal cavity. The at least one internal cavity includes a pawl and a thermal fuse. In use, the thermal fuse is configured to maintain the position of the pawl in the at least one internal cavity when a temperature is below a predetermined threshold, and wherein the thermal fuse is configured to melt when a predetermined threshold of temperature is reached during braking to release the pawl out of the at least one internal cavity towards the housing. The housing includes at least one recess configured to receive the pawl.

Abstract: A method of calculating and outputting pressure information about the status of an actual pressure of a gas bottle of a door damper at 200 C, performed on a smart device. The method includes receiving, from a non-compensated pressure gauge, a pressure input indicating an actual pressure of said gas bottle of said door damper at ambient temperature, receiving a temperature input indicating an actual temperature of said gas bottle of said door damper, and using said inputs to calculate and convert said actual pressure of said gas bottle of said door damper at ambient temperature to a pressure at a temperature of 200 C, and further comprising outputting pressure information about the status of the gas bottle of said door damper based on said converted pressure at 200 C.

Abstract: A gearbox assembly comprising a plurality of component parts in torque transmission connection via gear, shaft and/or housing components; the assembly further comprising means for providing redundancy at selected locations where failure can lead to loss of torque transmission between component parts of the assembly.

Abstract: A gearbox assembly comprising a plurality of component parts in torque transmission connection via gear, shaft and/or housing components; the assembly further comprising means for providing redundancy at selected locations where failure can lead to loss of torque transmission between component parts of the assembly.

Abstract: A device according to the present invention comprises: a tubular body (2) and a first attachment means (6), a piston (30) provided with a rod (12) connected to a second attachment means (10), the piston (30) sliding inside the tubular body (2) and defining inside said body a working chamber filled with hydraulic fluid, an accumulator comprising a rigid shell (20) inside of which a separation means (40) is located, defining a compensation chamber (42) that is filled with hydraulic fluid and is in communication with the working chamber, and a chamber (47) filled with pressurized gas, the rigid shell (20) being a metal shell produced by means of welded assembly and the accumulator being made such as to obtain an entirely welded enclosure (47) containing the gas.

Abstract: A gearbox assembly comprising a plurality of component parts in torque transmission connection via gear, shaft and/or housing components; the assembly further comprising means for providing redundancy at selected locations where failure can lead to loss of torque transmission between component parts of the assembly.

Abstract: A device and a control method are described for a swinging aircraft door (3), mobile around a swinging axis (21) substantially parallel to the longitudinal axis of the aircraft via a motorized mechanism and having integrated boarding stairs (31). The method includes the capture of electromagnetic or ultrasonic radiation using at least one sensor (401, 501); the detection of something on the stairs on the basis of captured electromagnetic or ultrasonic radiation, in order to deduce therefrom whether a detection condition is satisfied or not; and, driving of the motorized mechanism in order to control the closure of the door in response to a closure command except in case of detection of something on the stairway.

Abstract: This device comprises: a pneumatic cylinder (34), a gas generator (36), a chamber (6, 8) for atmospheric venting, with: an inlet with a connection to the gas generator (36), a first outlet, a second outlet, a valve (16) having a first side (24) and a second side (26) which can change position under the effect of a gas generated by the gas generator and comprising a passage (22) between the two sides (24, 26) obstructed by means which are clearable based on the pressure, where said shuttle-valve (16) is mobile between: a first position allowing connection to the first outlet and the second outlet and isolating the inlet from the first outlet and the second outlet; and a second position allowing connection of the inlet with the first outlet and isolating the second outlet from the inlet and the first outlet.

Abstract: A device for opening or closing an aircraft door includes an electric motor; a connector to connect the motor, and a driver. The driver includes a screw and nut system having a screw rotationally driven by the motor. The driver is configured to drive continuously and in sequence the connector with the door in a translational movement along one preset direction and then in rotational movement.

Abstract: This device comprises: a pneumatic cylinder (34), a gas generator (36), a chamber (6, 8) for atmospheric venting, with: an inlet with a connection to the gas generator (36), a first outlet, a second outlet, a valve (16) having a first side (24) and a second side (26) which can change position under the effect of a gas generated by the gas generator and comprising a passage (22) between the two sides (24, 26) obstructed by means which are clearable based on the pressure, where said shuttle-valve (16) is mobile between: a first position allowing connection to the first outlet and the second outlet and isolating the inlet from the first outlet and the second outlet; and a second position allowing connection of the inlet with the first outlet and isolating the second outlet from the inlet and the first outlet.

Abstract: A device and a control method are described for a swinging aircraft door (3), mobile around a swinging axis (21) substantially parallel to the longitudinal axis of the aircraft via a motorized mechanism and having integrated boarding stairs (31). The method includes the capture of electromagnetic or ultrasonic radiation using at least one sensor (401, 501); the detection of something on the stairs on the basis of captured electromagnetic or ultrasonic radiation, in order to deduce therefrom whether a detection condition is satisfied or not; and, driving of the motorized mechanism in order to control the closure of the door in response to a closure command except in case of detection of something on the stairway.

Abstract: This device comprises: a pneumatic cylinder (34), a gas generator (36), a chamber (6, 8) for atmospheric venting, with: an inlet with a connection to the gas generator (36), a first outlet, a second outlet, a valve (16) having a first side (24) and a second side (26) which can change position under the effect of a gas generated by the gas generator and comprising a passage (22) between the two sides (24, 26) obstructed by means which are clearable based on the pressure, where said shuttle-valve (16) is mobile between: a first position allowing connection to the first outlet and the second outlet and isolating the inlet from the first outlet and the second outlet; and a second position allowing connection of the inlet with the first outlet and isolating the second outlet from the inlet and the first outlet.

Abstract: A device according to the present invention comprises: a tubular body (2) and a first attachment means (6), a piston (30) provided with a rod (12) connected to a second attachment means (10), the piston (30) sliding inside the tubular body (2) and defining inside said body a working chamber filled with hydraulic fluid, an accumulator comprising a rigid shell (20) inside of which a separation means (40) is located, defining a compensation chamber (42) that is filled with hydraulic fluid and is in communication with the working chamber, and a chamber (47) filled with pressurized gas, the rigid shell (20) being a metal shell produced by means of welded assembly and the accumulator being made such as to obtain an entirely welded enclosure (47) containing the gas.

Abstract: An aircraft door actuator, including: a pneumatic cylinder for the opening of the door including a chamber into which a pressurized gas is injected via a first port, means for supplying the chamber of the cylinder with pressurized gas, via a supply pipe and said first port, means for setting the chamber to atmospheric pressure when the piston is in the position for opening the door, so as to allow said door to be moved into the closing position, including: a pressurized gas exhaust pipe a gate-valve means for guiding the opening of the gate-valve via the pressurized fluid located in the chamber when the door is in the opening position, so as to open the exhaust pipe in order to set said chamber of the cylinder to atmospheric pressure in a rapid manner once the door is open.

Abstract: Actuator for gas-operated emergency opening of an openable element of an aircraft, having the ability to vent the gas. The actuator for emergency opening of an openable element of an aircraft includes a thrustor, a pressurised-gas reservoir where the gas reservoir having a membrane capable of being perforated in order to actuate said thrustor, a movable perforator arranged to perforate said membrane of said reservoir in order to release the gas into the thrustor via a first fluid circuit, and a venting circuit that vents, away from the thrustor, the gas contained in the reservoir, in the event of accidental rupture of said membrane, via a second fluid circuit which does not actuate said thrustor.

Abstract: This device comprises: an electric motor (4), means for connection with the door, and means for driving comprising a screw/nut system with a screw (12) rotationally driven by the motor (4) where said drive means are suited for driving continuously and in sequence the means for connection with the door in a translational movement along . one preset direction and then in rotational movement.

Abstract: An aircraft hatch emergency opening actuator, includes, a cylinder connected to the hatch at one end to a reference frame at the other end to which the hatch is connected, fluid means feeding the cylinder for emergency opening of the hatch, means for injection of the fluid means at a point of a fluid circuit feeding the cylinder for emergency opening of the hatch, said injection means configured to adopt: a rest position, in which the fluid means are isolated from the cylinder, and an active position, in which the fluid means are injected at the point of the fluid circuit, means for delaying the injection of the fluid means into the cylinder including a mobile element in the fluid circuit, delaying opening of the circuit when the injection means are in the active position, the injection delay being determined by a time of movement of the mobile element.

Abstract: The present invention relates to devices for damping the movement of a body Co between two positions at the end of travel. The device according to the invention is essentially characterized in that it comprises two abutments B1, B2, a cylinder 10, a wall 11 closing off the end 12 of the cylinder 10, a piston 14 delimiting a chamber 16 with variable volume, a cylinder 20 with an external section at most equal to the internal section of the cylinder 10, a mounting unit for mounting the cylinder 20 in cooperation with the piston 14 so that the latter closes off the end 21 of this cylinder 20, a piston 24 delimiting a chamber 26 with variable volume, a first fluid Li filling the two chambers 16, 26, a communicating unit 30 for communication under pressure loss between the chambers 16, 26, an abutment 40 mounted in cooperation with the piston 24 so that this abutment 40 has a movement correlative with that of the piston 24, and a connecting unit 50 for connecting the cylinder 20 to the body Co.

Abstract: The present invention relates to devices for damping the movement of a body Co between two positions at the end of travel. The device according to the invention is essentially characterized in that it comprises two abutments B1, B2, a cylinder 10, a wall 11 closing off the end 12 of the cylinder 10, a piston 14 delimiting a chamber 16 with variable volume, a cylinder 20 with an external section at most equal to the internal section of the cylinder 10, means for mounting the cylinder 20 in cooperation with the piston 14 so that the latter closes off the end 21 of this cylinder 20, a piston 24 delimiting a chamber 26 with variable volume, a first fluid Li filling the two chambers 16, 26, means 30 for communication under pressure loss between the chambers 16, 26, an abutment 40 mounted in cooperation with the piston 24 so that this abutment 40 has a movement correlative with that of the piston 24, and means 50 for connecting the cylinder 20 to the body Co.