Abstract: The aircraft passenger seat headrest (20) includes a carrier (21) and a helmet (22) for at least partially housing the head of the passenger. The helmet is attached to the carrier and is movably mounted in relation to the carrier (21). Said helmet includes a body and at least one portion (32, 34) that is movably mounted onto the body to extend the latter.

Abstract: An integration method and module aims at simplifying the electrical connections between equipment and an electrical power center to be supplied electricity, while enabling a good accessibility of each piece of equipment for easier maintenance. To do so, a particular integration of this equipment is carried out so as to be able to connect the equipment in a direct extension of the electrical power center. According to one embodiment, an integration module includes a frame and a cover, the frame having a substantially parallelepipedic shape adapted to be able to extend longitudinally along a main axis in parallel with a longitudinal main side of the electrical power center. Cells, which define a constant cross section and an adjustable width enabled by movable intermediary walls, extend perpendicularly to the main longitudinal axis. Such cells are adapted to receive formatted electrical equipment.

Abstract: An electrical core of an aircraft is provided. The electrical core includes at least one shelf on which is disposed at least one module containing components and comprising at least one input able to be linked to at least one power supply cable and at least one output able to be linked to at least one output cable. In the module, the output cable or cables travel under or in the shelf disposed under the module.

Abstract: An electrical cabinet of an aircraft is provided. The electrical cabinet includes at least one motherboard including on a first face sockets into which are plugged PCB boards ensuring one or more electrical functions, the said electrical cabinet being linked to the electrical circuit of the aircraft organized as various electrical harnesses by way of an electrical connection system, characterized in that the electrical connection system comprises at the level of the second face of the motherboard at least one additional layer, the free face of the last additional layer comprising sockets each ensuring electrical connection with an electrical harness of the aircraft, the additional layer or layers comprising tracks which make it possible to reorganize the electrical circuits emanating from the sockets intended for the PCB boards so as to render them compliant with the sockets intended for the harnesses of the aircraft.

Abstract: A device for mixing at least two separate streams of components which, when mixed, form a combined fluid stream. The device comprises a conduit with at least two separate passageways leading to exit openings at an end face of the conduit. Each passageway communicates with a separate component stream and is arranged to direct the separate component stream in a downstream direction. The exit openings each have a predetermined cross-sectional flow area. A separate channel is located at a downstream end of each passageway exit opening. The channels are arranged to redirect the flow from each passageway to an axial direction. A single mixing chamber communicates with all of the separate channels, the mixing chamber being arranged to receive each of the component streams at an upstream end thereof and to permit a mixing of the component streams. An outlet is arranged downstream of the mixing chamber through which the combined fluid stream is dispensed.

Abstract: A cockpit for an aircraft nose, the cockpit having a floor that acts solely as a floor for the crew to walk on and that is lower than the height of the cabin floor situated behind the cockpit. The cockpit also has a stair connected to the floor in order to enter and leave the cockpit. This arrangement enlarges the volume of the cockpit and enables equipment to be housed therein that previously used to be housed in the zone that is difficult to access that is situated under the cockpit and that also contains the bay for storing landing gear.

Abstract: An aircraft nose comprising a primary fuselage structure, and housed inside said structure, a cockpit, and an avionics bay containing a plurality of avionics racks designed to receive electrical and/or electronic equipment. The cockpit and the avionics bay are each made in the form of a distinct module that is suitable for being installed in a single operation inside the primary fuselage structure. The use of modules for integrating in the aircraft nose makes it possible to reduce considerably the time required for fitting out the nose on the final assembly line of the aircraft.

Abstract: An aircraft hold including a device for automated processing of luggage is provided. The device includes at least one automated arm for handling the luggage. The automated arm, which is mounted so as to be able to move in translation along the longitudinal axis of the hold of the aircraft includes a head for grasping an item of luggage. A wrapper for packaging an item of luggage for the automated processing of the item of luggage is also provided. The wrapper is in the form of a protective film and includes a grasping surface separate from but secured to the protective film. A method for automated processing of luggage in an aircraft is provided.

Abstract: An aircraft front portion in which the landing gear storage bay is arranged under a cockpit floor. The landing gear bay is mechanically connected to the fuselage frames of the aircraft front portion in order to perform the function of taking up the mechanical forces acting on the fuselage frames under the effect of pressurization. The cockpit floor is thus simplified since it serves solely as a plane for the crew to walk on and it can be lowered so as to release space in the cockpit.

Abstract: An air extraction unit taking the form of a body, the geometric shape of which makes it easier to incorporate into an avionics bay of an aircraft. The air extraction unit derives from a multipurpose approach to the operational components of the avionics bay of an aircraft aimed at achieving weight and cost savings. All of the elements of the air extraction circuit are arranged in a compact housing of the body and are protected by the structure thereof. The air extraction unit can be used as a floor of an avionics bay that can be walked on, with a lateral organization.

Abstract: The present invention relates to an aircraft cockpit with a double flight deck in which a central pane of a windscreen can be removed in order to at least partially clear an opening in order to constitute an emergency exit and ensure natural ventilation of the cockpit. Moreover, a central portion of a glare shield and of a flight station instrument panel are optionally moveable in order to facilitate access to the opening in the event of the need for emergency evacuation.

Abstract: A method for automated processing of luggage in an aircraft is provided. The hold of the aircraft includes a device for automated processing of the luggage. The method includes the device for automated processing operating in an autonomous manner to load the luggage into the hold of the aircraft, with each item of luggage being packaged to this end in a packaging wrapper comprising visual markers. The method includes the device for automated processing viewing these visual markers.

Abstract: An electrical and electronics bay of an aircraft comprising two rows of elements, each row being separated by a single corridor and comprising at least one set of systems elements and at least one electrical power center, the systems elements being arranged in cabinets. At least one of the cabinets comprises mobile shelves for allowing access to the back of the cabinets by crossing it. This architecture makes it possible to increase the density of the elements present in the bay while observing the principles of redundancy and segregation.

Abstract: An integral avionics bay module. The module has a structure that has an integral cabin floor on top that closes the structure. Installing such an integral avionics bay structure in a single operation inside a primary fuselage structure considerably reduces the integration time on the final assembly line for the aircraft.

Abstract: The invention relates to an overhead panel able to be positioned in an aircraft cockpit, which includes an assembly of independent submodules (67), each of which is associated with a particular system or a particular function of the aeroplane, incorporated in a rigid self-supporting module (60), including a front face (65) to which the submodules (67) are attached, and two side faces fitted with peripheral electrical connectors (63) intended to be connected to different systems of the aeroplane. The invention also relates to a method of manufacture of such a panel.

Abstract: A piece of furniture for an aircraft, including a plurality of carriages a first section forming an interface of use for a user with which at least one carriage may be taken and/or deposited in the piece of furniture and a second section allowing the said carriages to be circulated along at least first and second main directions substantially perpendicular to each other, at least in a plane of the aircraft for storing and/or delivering to the user at least one carriage, the first section and/or the second section including an arrangement for distributing at least one carriage from the second section towards the first section and vice versa.

Abstract: A toilet area for an aircraft cabin comprising an access door and housing a toilet bowl. The toilet area also comprises an evacuation exit, the access door occupying a closed position in the toilet area in a toilet configuration and a folded position in the toilet area in an evacuation configuration. Usage in particular in a flying wing aircraft is provided.

Abstract: A seating device with reduced bulk, for example for an aircraft. This seating device comprises a backrest which describes a circular translational movement towards the front and upwards of the device when the seating device is brought to the retracted configuration. A seating structure is provided comprising a bearing piece on which are fixed, side by side, a plurality of seating devices with reduced bulk. An aircraft is provided comprising a seating device with reduced bulk mounted in its cabin.

Abstract: The invention relates to a seat back for an aircraft comprising a structural column bearing a plurality of devices for supporting an occupant of the seat, these devices being distributed along the structural column and oriented transversely relatively to the structural column so as to each protrude on either side of this column. This solution can reduce the mass and dimensions, while providing satisfactory comfort for the occupant.

Abstract: In an electrical cabinet (110) for an electrical power unit that carries out electrical power switching for at least multiple electrical power switching equipment (50), the electrical power switching equipment (50) is attached to a front of at least a support grid rack (31) arranged as a matrix with n rows and p columns, where n and p are greater than or equal to two. Each piece of equipment (50) is attached to the grid rack at a slot (34) in the grid rack, open to the front of the grid rack (31) and to the rear of the grid rack to allow installation from the front of the equipment and to allow access from the front to the rear of the grid rack through the slots (34).