Abstract: A method for synchronizing a first time domain with a second time domain of a system on chip includes a detection of at least one periodic trigger event generated in the first time domain, the second time domain or in a third time domain; acquisitions, made at the instants of the at least one trigger event, of the current timestamp values representative of the instantaneous states of the time domain(s) other than the trigger time domain; a comparison, made in the third time domain, between differential durations between current timestamp values which are respectively acquired successively; and a synchronization of the second time domain with the first time domain, on the basis of the comparison.

Abstract: Method for manufacturing a casing of an aircraft turbomachine, the casing including an annular shell extending about an axis A and made of a composite material including fibres that are woven and immersed in a resin, the annular layer including an abradable material arranged inside the shell, and covering a first inner annular surface of an intermediate section of the shell, the method including a step of gluing the layer on the first surface, during which the casing is heated and compressed by a system that is present at least partially inside the casing, wherein, prior to the heating and compression of the casing, a forming tool is mounted inside the casing and is made of two rings.

Abstract: A fan casing for an aircraft turbomachine, the casing including a one-piece annular body, the one piece annular body including a radially internal annular surface, a first annular portion of which is made of an abradable material, wherein a second annular portion of the internal surface comprises blind holes conferring acoustic properties to the second portion.

Abstract: A first input node receives a first input signal and a second input node receives a second input signal. The first and second input signals are in phase quadrature. An edge detector circuit senses the first input signal and produces a pulsed signal indicative of edges detected in the first input signal. A pulse skip and reset circuit senses the pulsed signal and the second input signal, and produces a reset signal indicative of pulses detected in the pulsed signal while the second input signal is de-asserted. A sampling circuit senses the second input signal and the reset signal, and produces an output signal that is deasserted in response to assertion of the second input signal and is asserted in response to a pulse being detected in the reset signal.

Abstract: A gas turbine fan casing made of composite material with a fibrous reinforcement includes a plurality of superimposed turns of a strip-shaped fibrous texture having a three-dimensional weaving between a plurality of layers of warp yarns and a plurality of layers of weft yarns, the fibrous reinforcement being densified by a matrix. The fibrous texture includes at least one lateral section of variable thickness in which the weft yarns have a size or a count different from the size or the count of the weft yarns of the plurality of layers of weft yarns present in the remainder of the fibrous texture.

Abstract: A method for synchronizing a first time domain with a second time domain of a system on chip includes a detection of at least one periodic trigger event generated in the first time domain, the second time domain or in a third time domain; acquisitions, made at the instants of the at least one trigger event, of the current timestamp values representative of the instantaneous states of the time domain(s) other than the trigger time domain; a comparison, made in the third time domain, between differential durations between current timestamp values which are respectively acquired successively; and a synchronization of the second time domain with the first time domain, on the basis of the comparison.

Abstract: A method of moving a door of a well for an aircraft undercarriage during sequences of deploying or retracting the undercarriage includes: using a temporary mechanical connection between the door and the undercarriage that is effective when the undercarriage is close to its retracted position, causing the door to be opened by the undercarriage while the undercarriage is being deployed and causing the door to be closed by the undercarriage while the undercarriage is being retracted, but releasing the door from the undercarriage when the undercarriage is close to its deployed position, and using a door actuator acting on the door to close and open the door when the undercarriage is in its deployed position and the temporary mechanical connection is interrupted.

Abstract: In an embodiment a method includes generating a low-frequency clock signal having a first frequency, in a standby mode and in a run mode of the CPU, generating a high-frequency clock signal having a second frequency higher than the first frequency, in the run mode, updating a value of the reference time base at each period of the low-frequency clock signal in the standby mode, and accessing the counter register with the high-frequency clock signal in the run mode.

Abstract: A housing for an aircraft turbine engine includes an annular body extending around an axis A. The body includes a securing flange extending radially outwards at each of the axial ends thereof, and an abradable layer arranged inside the body. A method for manufacturing the housing includes a step b) of bonding the layer to the first surface, during which the housing is heated and compressed by a system present at least partially inside the housing. The method further includes, prior to step b), a step a) of mounting at least two tools between the flanges, each of the tools being located in a circumferential area outside the body so as to exert bearing forces in opposite axial directions on the flanges.

Abstract: Method for manufacturing a casing of an aircraft turbomachine, the casing including an annular shell extending about an axis A and made of a composite material including fibres that are woven and immersed in a resin, the annular layer including an abradable material arranged inside the shell, and covering a first inner annular surface of an intermediate section of the shell, the method including a step of gluing the layer on the first surface, during which the casing is heated and compressed by a system that is present at least partially inside the casing, wherein, prior to the heating and compression of the casing, a forming tool is mounted inside the casing and is made of two rings.

Abstract: A ring assembly has a housing made of woven composite material carrying on its radially inner face an acoustic panel with a cellular structure covered with a composite material. The housing includes at least one radial recess in which is engaged at least one radially outwardly projecting part of the radially outer face of the acoustic panel.

Abstract: A gas turbine fan casing made of composite material with a fibrous reinforcement includes a plurality of superimposed turns of a strip-shaped fibrous texture having a three-dimensional weaving between a plurality of layers of warp yarns and a plurality of layers of weft yarns, the fibrous reinforcement being densified by a matrix. The fibrous texture includes at least one lateral section of variable thickness in which the weft yarns have a size or a count different from the size or the count of the weft yarns of the plurality of layers of weft yarns present in the remainder of the fibrous texture.

Abstract: A fan casing for an aircraft turbomachine includes an annular body extending around an axis and equipped with an annular attachment flange at each of its axial ends. The casing further includes an annular coating made from abradable material, wherein the body is made from a composite material, and further includes an annular stiffener that is arranged inside the body and that carries the coating. The stiffener includes an annular ring, a radially outer face of which is separated radially from the body and a radially inner face of which receives the coating. The stiffener further includes annular attachment tabs configured to the wall to the body.

Abstract: An emergency extension system for extending at least one aircraft undercarriage, the emergency extension system comprising both electromechanical actuators, each electromechanical actuator having an identification component arranged to allocate an identifier to said electromechanical actuator, which identifier depends in particular on a function performed by said electromechanical actuator, and also an electrical card having a delay component arranged to delay actuation of a the electromechanical actuator by an actuation delay that depends on the identifier allocated to the electromechanical actuator, the electromechanical actuators of the emergency extension system thus being arranged to be actuated in succession in an actuation sequence that is defined by the actuation delays.

Abstract: The invention relates to a fan casing (200) for an aircraft turbomachine, such as a jet engine, said casing having a one-piece annular body (202), said body having a radially internal annular surface (206), a first annular portion (208) of which is made of abradable material, characterized in that a second annular portion (210) of said internal surface comprises blind holes (212) that confer acoustic properties on said second portion.

Abstract: A method for manufacturing a composite-material casing for a gas turbine, includes producing by three-dimensional weaving a fiber texture in the form of a strip, winding of the fiber texture around several superimposed turns on a mandrel with a profile corresponding to that of the casing to be manufactured in order to obtain a fiber preform of a shape corresponding to that of the casing to be manufactured, and densifying the fiber preform by a matrix. During the winding of the last turn of the fiber texture on the mandrel, at least one stiffening element is interposed between the before-last turn and the last turn of the fiber texture. The stiffening element projects over the outer surface of the before-last turn of the fiber texture. The stiffening element has an axial section of omega-type shape.

Abstract: A device (1) for connecting an end of a first shaft to an end of a second shaft, the end of the first shaft having a radial groove. The device includes a body (2) having a bore (21) into which the end of the first shaft can be introduced, a locking pin (3) movable with respect to the body (2) between a locked position, in which the pin (3) projects into the bore (21) such that, when the end of the first shaft is received inside the bore (21), the locking pin (3) is engaged in the radial groove in the end of the first shaft, and an unlocked position. In the unlocked position, the locking pin (3) is disengaged from the radial groove in the end of the first shaft, and an elastic return member (4) urges the locking pin (3) into the locked position.

Abstract: The invention relates to a device (1) for connecting an end of a first shaft to an end of a second shaft, the end of the first shaft having a radial groove, the device comprising:—a body (2) having a bore (21) into which the end of the first shaft can be introduced,—a locking pin (3) mounted so as to be movable with respect to the body (2) between a locked position, in which the pin (3) projects into the bore (21) such that, when the end of the first shaft is received inside the bore (21), the locking pin (3) is engaged in the radial groove in the end of the first shaft in order to prevent the end of the first shaft from being removed from the bore (21), and an unlocked position, in which the locking pin (3) is disengaged from the radial groove in the end of the first shaft so as to allow the end of the first shaft to be introduced into the bore (21) or to allow the end of the first shaft to be removed from the bore (21), and—an elastic return member (4) for urging the locking pin (3) into the locked position

Abstract: A method of moving a door of a well for an aircraft undercarriage during sequences of deploying or retracting the undercarriage includes: using a temporary mechanical connection between the door and the undercarriage that is effective when the undercarriage is close to its retracted position, causing the door to be opened by the undercarriage while the undercarriage is being deployed and causing the door to be closed by the undercarriage while the undercarriage is being retracted, but releasing the door from the undercarriage when the undercarriage is close to its deployed position, and using a door actuator acting on the door to close and open the door when the undercarriage is in its deployed position and the temporary mechanical connection is interrupted.

Abstract: An emergency extension system for extending at least one aircraft undercarriage, the emergency extension system comprising both electromechanical actuators, each electromechanical actuator having an identification component arranged to allocate an identifier to said electromechanical actuator, which identifier depends in particular on a function performed by said electromechanical actuator, and also an electrical card having a delay component arranged to delay actuation of a the electromechanical actuator by an actuation delay that depends on the identifier allocated to the electromechanical actuator, the electromechanical actuators of the emergency extension system thus being arranged to be actuated in succession in an actuation sequence that is defined by the actuation delays.