Ratier Figeac

Ratier-figeac Sas

Eric Delbos

Hélène Bergonnier

Bertrand Prouzet

Frédéric Vermande

Jean De La Bardonnie

Adil Sardi

Sébastien Caminade

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.

Brake assembly with thermal fuse

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.

Gearbox assembly

A device according to the present invention comprises:

Device for assisting the operation of an aircraft door

A device and a control method are described for a swinging aircraft door (), mobile around a swinging axis () substantially parallel to the longitudinal axis of the aircraft via a motorized mechanism and having integrated boarding stairs (). The method includes the capture of electromagnetic or ultrasonic radiation using at least one sensor (); 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.

Control method and device for aircraft door and aircraft door incorporating same

Device for emergency actuation especially intended for an aircraft opening

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.

Motorized device for opening and/or closing an aircraft door

Door actuator comprising means for setting to atmospheric pressure in a rapid manner at the end of opening the door

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.

Actuator for gas-operated emergency opening of an openable element of an aircraft, having means for venting the gas

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:

Aircraft hatch emergency opening actuator including opening delay means

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 B, B, a cylinder, a wallclosing off the endof the cylinder, a pistondelimiting a chamberwith variable volume, a cylinderwith an external section at most equal to the internal section of the cylinder, a mounting unit for mounting the cylinderin cooperation with the pistonso that the latter closes off the endof this cylinder, a pistondelimiting a chamberwith variable volume, a first fluid Li filling the two chambers, a communicating unitfor communication under pressure loss between the chambers, an abutmentmounted in cooperation with the pistonso that this abutmenthas a movement correlative with that of the piston, and a connecting unitfor connecting the cylinderto the body Co. Application notably to the control for opening and closing an aircraft door.

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Lacapelle-Marival, France

Eric Delbos