Abstract: The present disclosure concerns the communication between electronic systems in an aircraft subassembly such as a propulsion unit. This communication is at least partially carried out by light signals transmitted through at least one interior volume of the sub-assembly, this interior volume defining an optical channel. To this end, at least one of these systems includes an emitter arranged to emit a light signal and modulate it depending on data to be transmitted generated by this system, and at least one other of these systems includes at least one receiver capable of receiving this light signal.

Abstract: A method for de-icing or anti-icing an aircraft portion having at least one piezoelectric element fastened on the inner face of the aircraft portion includes, during a design phase of the aircraft portion, placing the piezoelectric element on an area of the aircraft portion to determine frequencies of resonance and increased dynamic coupling, and during the de-icing or anti-icing of the aircraft portion, the same piezoelectric element is excited according to the natural frequencies of the area.

Abstract: An active device for attenuating the acoustic emissions of an aircraft turbojet engine includes circulation conduits for a pressurized air flow rate supplying rotary elements each having a pulsation system for the delivered air. The rotary elements are controlled in amplitude and phase and deliver, to outlet diffusers, a pulsed air flow rate with a pulsation at the frequency of the noise to be attenuated having an amplitude and a phase adjusted according to a local feedback law with microphones to attenuate the radiated acoustic power.

Abstract: An improved thrust reverser for an aircraft propulsion assembly includes redirection of the air flow for performing the thrust reversal by one or more closure membranes, i.e. by thin and flexible structures deployed across the propulsion assembly. The improved thrust reverser includes at least one closure membrane arranged to deflect at least one portion of the air flow in the direction of the evacuation structure when the thrust reverser is in the reverse jet position and an intermediate structure movable in rotation relative to the fixed structure.

Abstract: The invention relates to an air intake lip of an aircraft engine nacelle extending along an axis X, in which an air flow circulates from upstream to downstream, the lip extending annularly about the X-axis and having an inner wall facing the X-axis and an outer wall which is opposite the inner wall, the inner wall and the outer wall being connected by an upstream wall and a partition so as to delimit an annular cavity, in which at least one infrared emission source is housed, wherein at least one wall, selected among the inner wall, the outer wall and the upstream wall, is made of a material configured to transmit on an outer face at least 30% of the infrared received on an inner face.

Abstract: The present disclosure concerns the communication between electronic systems in an aircraft subassembly such as a propulsion unit. This communication is at least partially carried out by light signals transmitted through at least one interior volume of the sub-assembly, this interior volume defining an optical channel. To this end, at least one of these systems includes an emitter arranged to emit a light signal and modulate it depending on data to be transmitted generated by this system, and at least one other of these systems includes at least one receiver capable of receiving this light signal.

Abstract: A method for de-icing or anti-icing an aircraft portion having at least one piezoelectric element fastened on the inner face of the aircraft portion includes, during a design phase of the aircraft portion, placing the piezoelectric element on an area of the aircraft portion to determine frequencies of resonance and increased dynamic coupling, and during the de-icing or anti-icing of the aircraft portion, the same piezoelectric element is excited according to the natural frequencies of the area.

Abstract: An active device for attenuating the acoustic emissions of an aircraft turbojet engine includes circulation conduits for a pressurized air flow rate supplying rotary elements each having a pulsation system for the delivered air. The rotary elements are controlled in amplitude and phase and deliver, to outlet diffusers, a pulsed air flow rate with a pulsation at the frequency of the noise to be attenuated having an amplitude and a phase adjusted according to a local feedback law with microphones to attenuate the radiated acoustic power.

Abstract: An improved thrust reverser for an aircraft propulsion assembly includes redirection of the air flow for performing the thrust reversal by one or more closure membranes, i.e. by thin and flexible structures deployed across the propulsion assembly. The improved thrust reverser includes at least one closure membrane arranged to deflect at least one portion of the air flow in the direction of the evacuation structure when the thrust reverser is in the reverse jet position and an intermediate structure movable in rotation relative to the fixed structure.

Abstract: An acoustic attenuation panel for a turbojet engine nacelle is provided by the present disclosure. The panel includes at least one alveolar core disposed between at least one internal skin and at least one external skin. In one form, the alveolar core includes a plurality of alveoli having a helical-shaped cavity along an axis in a direction normal to at least one internal skin and at least one external skin.

Abstract: The present disclosure provides a device for de-icing an air intake lip of an aircraft turbojet engine nacelle. The de-icing device includes a de-icing circuit in which a heat transfer fluid, working in a two-phase form, circulates. The de-icing circuit includes at least one device for circulating the heat transfer fluid in the de-icing circuit, a system for heating the heat transfer fluid and configured to change the phase of the fluid to a vapor phase, and an inlet conduit that opens into the lip through a rear wall and injects the vapor phase fluid into the lip. The fluid changes phase when it condenses on the front wall of the lip to de-ice the lip.

Abstract: The present disclosure provides a thrust reverser device that is integrated in an aircraft nacelle. Blocking flaps are stored inside a mobile cowl disposed in a downstream section of the nacelle, under deflection cascade assemblies during direct-jet operation of the nacelle. Various devices are provided for executing the passage from direct-jet operation to reverse-jet operation in two stages: the mobile cowl moves in translation towards the downstream end of the nacelle; and each flap is then deployed in the main air flow path.

Abstract: An acoustic attenuation panel for a turbojet engine nacelle is provided by the present disclosure. The panel includes at least one alveolar core disposed between at least one internal skin and at least one external skin. In one form, the alveolar core includes a plurality of alveoli having a helical-shaped cavity along an axis in a direction normal to at least one internal skin and at least one external skin.

Abstract: A method for installing a de-icing system on the skin of an aircraft element is provided, which involves applying to the skin several independent layers of solid and/or fluid materials which are hardened in succession, and which comprise at least one layer of controlled electrical resistivity material, which takes electrodes that conduct an electric current originating from an external source, which is flanked on each side by layers of an electrically insulating material.

Abstract: The present disclosure provides a thrust reverser device that is integrated in an aircraft nacelle. Blocking flaps are stored inside a mobile cowl disposed in a downstream section of the nacelle, under deflection cascade assemblies during direct-jet operation of the nacelle. Various devices are provided for executing the passage from direct-jet operation to reverse-jet operation in two stages: the mobile cowl moves in translation towards the downstream end of the nacelle; and each flap is then deployed in the main air flow path.

Abstract: A lighting unit for use in a luminaire, in particular a luminaire for road and/or street lighting, comprising a plurality of light sources and a reflector unit arranged in front of the light sources to control the distribution of the light emitted by said light sources, wherein he reflector unit comprises a plurality of reflector elements arranged parallel to each other, with at least some of the reflector elements comprising a first portion adapted for total reflection and a second portion adapted for partial reflection.

Abstract: A lighting unit for use in a luminaire, in particular a luminaire for road and/or street lighting, has an adaptable light distribution wherein the lighting unit comprises at least two light sources or groups of light sources, each of the light sources or groups of light sources having an individual light distribution characteristic, wherein the overall light distribution of the lighting unit is adapted by modifying the ratio of the light outputs of the at least two light sources or groups of light sources

Abstract: A lighting unit for use in a luminaire, in particular a luminaire for road and/or street lighting, has an adaptable light distribution wherein he lighting unit comprises at least two light sources or groups of light sources, each of the light sources or groups of light sources having an individual light distribution characteristic, wherein the overall light distribution of the lighting unit is adapted by modifying the ratio of the light outputs of the at least two light sources or groups of light sources

Abstract: A lighting unit for use in a luminaire, in particular a luminaire for road and/or street lighting, has an adaptable light distribution wherein the lighting unit comprises at least two light sources or groups of light sources, each of the light sources or groups of light sources having an individual light distribution characteristic, wherein the overall light distribution of the lighting unit is adapted by modifying the ratio of the light outputs of the at least two light sources or groups of light sources