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 aircraft includes at least one wall delimiting a first zone (I) of the aircraft which is thermally insulated from the outside of the aircraft and a second zone (E) contained within the aircraft which is not thermally insulated with respect to the outside of the aircraft and a heat exchanger inside which a heat transfer fluid circulates, wherein the wall includes at least one duct inside which the heat transfer fluid circulates so as to act as a heat exchanger.

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 leaktight nose cone backplate for an aircraft having a first side oriented towards a radome zone intended to house a mobile antenna, and a second side opposite the first side and oriented towards a cockpit of the aircraft. The second side has at least one recess intended to receive at least one piece of cockpit equipment, each recess being partly delimited by a backplate structure forming a protrusion on the first side.

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: An electrical and electronics bay of an aircraft has at least two rows of systems elements, each row being separated by a single corridor extending an entire longitudinal length of the electrical and electronics bay and being devoid of the systems elements. Each row has at least one set of systems elements and at least one electrical power center, wherein the systems elements are arranged in cabinets. At least one of the cabinets includes at least one removable mobile shelf for allowing access from a front to the back of the cabinets. Bottom edges of back faces of the cabinet are arranged against the fuselage to remove an additional corridor at the back of the cabinet, and front faces of the cabinet are directly accessible from the single corridor.

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: A method for dynamically controlling throughput set points from sources to targets in a network on a chip including a plurality of nodes and a plurality of links between these nodes for transmission of data packets, including for each link of the network solicited by the transmission of data packets, estimation of an available throughput margin that includes the estimation of a first margin calculated based on a maximum throughput capacity of the link; and for each emitting source of at least one data packet, the calculation and the application of an update of its throughput set point according to the estimated available throughput margins. Estimation of available throughput margin for each link includes estimation of a second margin calculated based on a maximum local absorption capacity of possible sporadic overflows of the throughput set points and its value is determined according to the first and second calculated margins.

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 ventilation system for an avionics bay has two strut assemblies for stiffening the floor of the cockpit, each strut assembly being arranged symmetrically regarding to the central plane of the aircraft, and means of distribution of the blowing air in the cabinets of the bay from the strut assemblies. The extraction circuit includes exhaust ducts integrated in the cabinets and couples together by tight inter-cabinets junctions in an overall configuration of maximized compactness.

Abstract: A keel beam connected to a central wing box of an aircraft and ensuring the connection between a front structure and a rear structure of an aircraft is characterized in that it includes, on the one hand, a U-shaped body with a horizontal base and two solid lateral walls, and on the other hand, a cover which has a U shape oriented in the same manner as the body, with a base in the lower portion and curved edges, the ends of which are oriented upward so that each curved edge includes an outer surface flattened against and fixed to the inner surface of the lateral walls in order to define, with the body, a closed section, the cover including openings for accessing the inside of the keel beam.

Abstract: The invention relates to an access controller which comprises a module (24) for managing writing in a circular buffer (16), means (38) for storing a first read pointer (PL) and a second write pointer (PE), a module (30) for managing reading in the circular buffer (16), means (24, 30, 40) for blocking reading, respectively writing, means (38) for storing a read or write work pointer (PT) which is different from the first and second pointers (PL; PE), and means (24, 30, 40) for updating the wo: pointer (PT) according to a predetermined update logic. The predetermined update logic comprises forward or backward movements of the work pointer (PT) inside the circular buffer (16), and the controller includes means for blocking the read or write work pointer if the read work pointer (PT) points outside a memory space reserved for reading or, respectively, if the write work pointer (PT) points outside a free memory space for writing.

Abstract: A system for transmitting concurrent data flows on a network includes a memory containing the data of the data flows; a plurality of queues assigned respectively to the data flows, organized to receive the data as atomic transmission units; a flow regulator configured to poll the queues in sequence and, if the polled queue contains a full transmission unit, transmitting the unit on the network at a nominal flow-rate of the network; a queue management circuit configured to individually fill each queue from the data contained in the memory, at a nominal speed of the system, up to a threshold common to all queues; a configuration circuit configurable to provide the common threshold of the queues; and a processor programmed to produce the data flows and manage their assignment to the queues, and connected to the configuration circuit to dynamically adjust the threshold according to the largest transmission unit used in the flows being transmitted.

Abstract: A credit-based data flow control method between a consumer device and a producer device. The method includes the steps of decrementing a credit counter for each transmission of a sequence of data by the producer device, arresting data transmission when the credit counter reaches zero, sending a credit each time the consumer device has consumed a data sequence and incrementing the credit counter upon receipt of each credit.

Abstract: A system for transmitting concurrent data flows on a network, includes a memory containing data of data flows; a plurality of queues assigned respectively to the data flows, organized to receive the data as atomic transmission units; a flow regulator to poll the queues in sequence and, if the polled queue contains a full transmission unit, transmitting the unit on the network at a nominal flow-rate of the network; a sequencer to poll the queues in a round-robin manner and enable a data request signal when the filling level of the polled queue is below a threshold common to all queues, which threshold is greater than the size of the largest transmission unit; and a direct memory access configured to receive the data request signal and respond thereto by transferring data from the memory to the corresponding queue at a nominal speed of the system, up to the common threshold.

Abstract: A forward part of an aircraft comprising a fuselage and a landing gear well housing a forward landing gear comprising a breaker strut designed to adopt an extended configuration when the landing gear is extended, configuration in which said breaker strut lies in a strut plane parallel to the transverse direction of the forward part. The forward part comprises a transverse beam resisting strut reactions located above the landing gear well and mounted on the fuselage at its two ends, the beam having a globally rectangular cross-section, in which the median plane parallel to the length of the rectangle is coincident with said strut plane.

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: 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: A leaktight nose cone backplate for an aircraft having a first side oriented towards a radome zone intended to house a mobile antenna, and a second side opposite the first side and oriented towards a cockpit of the aircraft. The second side has at least one recess intended to receive at least one piece of cockpit equipment, each recess being partly delimited by a backplate structure forming a protrusion on the first side.

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.