Abstract: Disclosed is a process for manufacturing a part, named composite part, formed from at least one composite material including at least one layer of a reinforcing structure impregnated with a polymer matrix within which the reinforcing structure extends, wherein: a composite blank of the composite part is prepared; and a step of curing the polymer matrix of the composite blank is carried out, exerting a pressure on at least one pressed face of the composite blank. The pressure is exerted in the form of a pressure gradient applied to the pressed face of the composite blank so as to cause the gas present within the composite part to flow from a zone of maximum pressurization to a gas evacuation zone. Also disclosed is a device for manufacturing such a part.

Abstract: An actuator of an aircraft includes at least one limit stop in which at least one of the bearing surfaces, named destructible bearing surface (19), has at least one destructible portion which is able to, and is arranged to, be irreversibly deformed under the effect of the co-operation by limit contact between the driving member bearing surface (19) and the driven member bearing surface (20). Each destructible portion of each destructible bearing surface is mounted to be removable with respect to the stop as to be able to be replaced.

Abstract: A method and a device for coupling piloting members (20, 50), wherein saturation values (SCpsat?, SCpsat+, SCcopsat?, SCcopsat+) of at least one force saturator (28, 58) are adapted such that a force-feedback is exerted for each of these saturation values at a force-feedback value, taken at the force application centre of the manoeuvring handle (21, 51), of between 4 daN and 40 daN, with the result that a function of disconnecting is at least in part performed by the at least one force saturator.

Abstract: A de-icing device is provided for at least one surface portion of a rotor blade liable to be covered with a layer of ice. The device includes: at least one first heating device adapted to permit detachment of at least part of the layer of ice, as well as at least one second heating device including heating elements extending facing only part of the surface portion so as to circumscribe at that location closed-contour zones of the surface portion. The heating elements of the second heating device are adapted to cause breaking of the ice through the thickness of the layer of ice, and the first heating device extends at least partly facing the inside of the closed-contour zones.

Abstract: A bearing for guiding a first guided piece includes a first bearing surface with respect to a second bearing surface fixedly attached to a second guided piece. At least one first intermediate piece is interposed between the first bearing surface and the first guided piece and at least one first automatic release assembly for i) in a first assembly state, fixedly attaching the at least one first intermediate piece and the first guided piece for guidance forces which are lower than a triggering value, and ii) in a release state, permitting a relative displacement of the first guided piece with respect to the at least one first intermediate piece, at least in one displacement orientation, for guidance forces which are greater than the triggering value of the first 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 device for supplying electricity to at least one secondary electric load (30) on-board a turbomachine rotor (12) including a main circuit for transmitting main electric power to at least one main on-board electrical load (16), includes a device (15) for rotatably and electrically connecting the stator and the rotor, and at least one secondary circuit for transmitting a secondary electric power including at least one secondary conductor (28) of the stator connected to a secondary electric power source (29) suitable for outputting a secondary power in the form of a power signal with a secondary frequency selected such as to enable selective, interference-free transmission of the secondary power via the rotary electric connection device (15), separately from the main power transmission.

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: A process and device for controlling a synchronous motor driving an operating lever in opposition to a friction brake, including a sensor for sensing the position of the lever, and a control computer include: a first regulator defining a nominal control voltage (U*) as a function of a difference (??) between the speed of rotation (?_feedback) of the motor and a set-point speed (?_cmd); a second regulator determining saturation limits (?Usat; +Usat) of the nominal control voltage as a function of an instantaneous torque provided by the motor; a saturator providing a limited control voltage (U_cmd) on the basis of the nominal control voltage and on the basis of the saturation limits; a converter feeding each winding of the motor with an alternating-voltage signal (U_alim) worked out on the basis of the limited control voltage as a function of the angular position of the motor.

Abstract: A blade includes an aerodynamic portion (21) and an assembly of the aerodynamic portion to a blade shank retaining the aerodynamic portion in a radial direction (23). The blade shank includes at least one passage restriction in at least one retention direction orthogonal to the radial direction, having a restricted width allowing the aerodynamic portion (21) to pass through. The base of the aerodynamic portion (21) has an overall dimension which is strictly greater than the restricted width so that, in the event of rupture of the assembly, the base is able to come into abutment against the passage restriction so as to retain the aerodynamic portion (21) in the blade shank (20).

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: A device for opening and closing according to the invention relates to an aircraft door (2) hinged around an axis (6) substantially parallel to the longitudinal axis the aircraft comprising a motorized mechanism and a driving system combined with a control device comprising a system for acquisition of the angular position of the door (2) relative to the structure (4) the aircraft, where said angular position acquisition system for the door comprises at least one inclinometer (20) combined with the door (2).

Abstract: A device for combining force between two control units includes force feedback, each control unit including a control stick (21, 31) and at least one force sensor (24, 34) suitable for providing a value of the control force (Fp, Fcp) exerted by a pilot, the device being suitable for forming a force feedback value from the sum of the values of the control forces of each control unit. A correction device limits the force feedback value (Fcor_p) according to at least one parameter taken from the absolute value of the control force (Fcp) of the second control unit and the difference between the control force values of each control unit. A control unit including such a device for combining forces, and an aircraft provided with such control units are also described.

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: 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 propeller blade includes an aerodynamic portion and a blade shank, a hub assembly (28, 32) which provides anchoring in a hub, a blade shank assembly of the aerodynamic portion, a safety device including a safety element (24) which extends from a distal assembly in the aerodynamic portion to a proximal assembly (26, 27) in the blade shank and which is adapted to be able to anchor the aerodynamic portion in the blade shank, wherein the blade shank assembly is anchored radially outside the hub assembly, the proximal assembly is anchored to the blade shank radially inside the hub assembly, and the distal assembly and/or the proximal assembly has a strictly positive radial clearance (30).

Abstract: The invention relates to a propeller blade which comprises a hollow casing (1) forming an extrados (5) and an intrados (4) which extend from a blade shank to a free end in the direction of the span, and a framework which is arranged in the hollow casing (1) and comprises a box spar (8), having a plurality of soles (9a, 9b, 10a, 10b) in surface contact with the hollow casing (1) so as to provide structural support for the hollow casing (1), and at least two cavities (15, 16) which are spaced apart in the direction of the chord (25), wherein the propeller blade further comprises at least two reinforcing spars (6, 7) which extend between the framework and the hollow casing.

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.