Abstract: A turbofan having a fixed structure, a fan, a fan casing surrounding the fan, an outer cowl disposed around the fan casing and mounted so as to be articulated on the fixed structure, and a deployment system that moves the outer cowl from a closed position to an open position. The deployment system has a guide rail fastened around the fan casing, a slider that is able to move along the guide rail and has a shoe. An activation system of the deployment system moves the slider and the shoe alternately in one direction or the other along the guide rail. One end of an arm of the deployment system is mounted to be articulated on the shoe and another end is mounted to be articulated on the outer cowl. Such a motorized deployment system makes it possible to save space and mass in the turbofan.

Abstract: A turbofan having a fixed structure, a fan, a fan casing surrounding the fan, an outer cowl disposed around the fan casing and mounted so as to be articulated on the fixed structure, and a deployment system that moves the outer cowl from a closed position to an open position. The deployment system has a guide rail fastened around the fan casing, a slider that is able to move along the guide rail and has a shoe. An activation system of the deployment system moves the slider and the shoe alternately in one direction or the other along the guide rail. One end of an arm of the deployment system is mounted to be articulated on the shoe and another end is mounted to be articulated on the outer cowl. Such a motorized deployment system makes it possible to save space and mass in the turbofan.

Abstract: A turbofan having a nacelle comprising a slider translatable between an advanced position and a retracted position to open a window between a duct and the exterior, a plurality of blades, each one rotatable on the slider between a stowed position and a deployed position, and a maneuvering system that moves each blade and comprises, for each blade, a shaft rotatable on the slider and on which the blade is fixed, and a toothed sector fixed to the shaft, and a toothed arc rotatable on the slider about a longitudinal axis, where the teeth of the toothed arc mesh with the teeth of each toothed sector, a cam, as one with the toothed arc, and a groove, as one with a fixed structure, which receives the cam and where, when the slider moves, the cam follows the groove and rotates the toothed arc.

Abstract: A turbofan having a nacelle comprising a slider translatable between an advanced position and a retracted position to open a window between a duct and the exterior, a plurality of blades, each one rotatable on the slider between a stowed position and a deployed position, and a maneuvering system that moves each blade and comprises, for each blade, a shaft rotatable on the slider and on which the blade is fixed, and a toothed sector fixed to the shaft, and a toothed arc rotatable on the slider about a longitudinal axis, where the teeth of the toothed arc mesh with the teeth of each toothed sector, a cam, as one with the toothed arc, and a groove, as one with a fixed structure, which receives the cam and where, when the slider moves, the cam follows the groove and rotates the toothed arc.

Abstract: The present disclosure describes systems and methods for operating an event-driven spiking neural network. The neural network is based on a pipelined comparator tree used to find the next neuron to fire (as per the event-driven simulation strategy), with each neuron having a firing time associated therewith. The neuron's discharge is then processed by updating the post-synaptic neurons affected by the firing event. The architecture can be duplicated or otherwise scaled to increase the performance of the system.

Abstract: An engine assembly for aircraft including a turboshaft engine, an attachment strut, and a plurality of engine mounts interposed between the attachment strut and the turboshaft engine. The plurality of engine mounts include two forward mounts arranged in a staggered manner in relation to each other in a vertical direction of the turboshaft engine, the first forward mount configured to assure uniquely taking up of stresses brought to bear along the transversal direction of the turboshaft engine, and the second forward mount configured to assure uniquely taking up of stresses brought to bear along the transversal and vertical directions.

Abstract: The invention relates to an engine assembly for an aircraft comprising a turbojet, a engine mount pylon, and a plurality of engine mounts inserted between the engine mount pylon and the turbojet. According to the invention, the plurality of engine mounts comprises a engine mount (6a) designed so as to uniquely resist forces applied along a direction (Y) transverse to the turbojet, this engine mount (6a) comprising an intermediate fitting (46) assembled onto a first fitting (40) fixed to the pylon through two swivel axes (48) oriented parallel along a vertical direction (Z), and a pin (56) oriented along a longitudinal direction (X) and fixed to the intermediate fitting, the pin being installed on a second fitting (58) fixed to the turbojet, with clearance along the longitudinal direction (X).

Abstract: The invention relates to an engine assembly for an aircraft comprising a turbojet, a engine mount pylon, and a plurality of engine mounts inserted between the engine mount pylon and the turbojet. According to the invention, the plurality of engine mounts comprises a engine mount (6a) designed so as to uniquely resist forces applied along a direction (Y) transverse to the turbojet, this engine mount (6a) comprising an intermediate fitting (46) assembled onto a first fitting (40) fixed to the pylon through two swivel axes (48) oriented parallel along a vertical direction (Z), and a pin (56) oriented along a longitudinal direction (X) and fixed to the intermediate fitting, the pin being installed on a second fitting (58) fixed to the turbojet, with clearance along the longitudinal direction (X).

Abstract: An engine assembly for aircraft including a turboshaft engine, an attachment strut, and a plurality of engine mounts interposed between the attachment strut and the turboshaft engine. The plurality of engine mounts include two forward mounts arranged in a staggered manner in relation to each other in a vertical direction of the turboshaft engine, the first forward mount configured to assure uniquely taking up of stresses brought to bear along the transversal direction of the turboshaft engine, and the second forward mount configured to assure uniquely taking up of stresses brought to bear along the transversal and vertical directions.