Abstract: A support device for an aircraft cabin interior layout assembly comprises a fixed frame extending according to a longitudinal direction; and a table comprising a tray deployable relative to the frame between a retracted configuration and a deployed configuration. The tray extends horizontally in the retracted configuration and in the deployed configuration and is displaceable in rotation about a first axis of rotation, substantially parallel, while remaining horizontal between the retracted configuration and the deployed configuration. The tray is displaceable in translation relative to the frame in the longitudinal direction between a first position of use and a second position of use when the tray is in the deployed configuration, while being fixed in rotation about the first rotation axis.

Abstract: A piloting device for piloting an aircraft includes a first and a second control stick movably mounted on a support, a detection system for detecting the positions of the first and second control sticks, an elastic mechanism configured to apply a restoring force to the second control stick, first and second actuation systems configured to apply respective first and second position adjustment forces to the respective first and second control sticks, and a control module configured to control the second adjustment force so that the positions of the first and second control sticks are identical. The control module is configured to control the first adjustment force based on the second adjustment force and the restoring force.

Abstract: An aircraft rudder pedal includes a frame, a pair of pedals, an output shaft and a mechanical kinematic chain for transmitting to the output shaft a displacement of at least one of the pedals relative to the frame. The mechanical kinematic chain comprises a central transmission part able to be rotated relative to the frame by a displacement of one of the pedals relative to the frame. The mechanical kinematic chain also includes a transmission mechanism joining the central transmission part to the output shaft. The transmission mechanism includes a homokinetic association of two universal joints between said central transmission part and the output shaft.

Abstract: A device for holding objects in an aircraft cabin includes at least one interface, intended for being attached to a wall of the cabin, or for being formed in a wall of the cabin, the interface defining an attachment region for the object, the object being suitable for being placed in contact with the attachment region. The object can be rotated over the attachment region between a position for placing the object on the attachment region, wherein the object can be moved away from the attachment region, and an attachment position of the object on the attachment region, wherein the object is held on the attachment region.

Abstract: A virtualized aircraft control architecture includes a human-machine interface configured for generating a main command for arranging a functional element into a target configuration among a plurality of configurations; a procedure management module configured for generating a suggested command depending upon a current step of a flight procedure; a command confirmation module generating a safety command associated with the main command when the latter corresponds to the suggested command; and an interface module configured for sending the main and safety commands to a control module. The control module arranges the functional element into the target configuration when the main command and the safety command, respectively, correspond to the expected main and safety commands for arranging the functional element into the target configuration.

Abstract: An aircraft portion includes a piece of equipment including an outer wall delimiting an enclosure and a door facing an aisle. The equipment door is displaceable between a closed configuration and an open configuration. The aisle has a maximum width when the door is in the closed configuration and a minimum width when the door is in the open configuration. When the door is in the closed configuration and in case of depressurization, the door is displaced and kept into an emergency configuration. The aisle has an optimum width which corresponds to a width sufficient for simultaneously letting air escape from the enclosure and enabling passengers to walk down the aisle past the piece of equipment.

Abstract: An aircraft mission calculation system is for indicating a risk of loss of optimality of the trajectory actually flown by the aircraft. The system includes a first trajectory calculation module, configured to calculate an optimal mission trajectory between a geographical point of origin and a geographical point of destination. The first calculation module is configured to calculate a plurality of iso-displacement curves from the geographical point of origin to the geographical point of destination. The system comprises a module for determining a level of risk of loss of optimality of the trajectory actually taken by the aircraft, associated with a modification of the trajectory of the aircraft with respect to the calculated mission trajectory, the display manager displaying on the display, in addition to the calculated trajectory, an indicator of the determined level of risk.

Abstract: A system for calculating a mission of an aircraft by combination of algorithms includes a first path calculation module, configured for calculating an optimal mission path between a geographical point of origin and a geographical destination point as a function of airplane performance, operational mission specifications and a weather context. The first calculation module is configured to determine the optimal path in a manner non constrained by a network of waypoints and/or imposed paths between the waypoints. The system includes a definition module, around the optimal path, an optimization region of the path and a second path calculating module, configured to calculate an optimized path of the aircraft in the optimization region in a manner constrained by a network of waypoints and/or imposed paths between the waypoints.

Abstract: An manufacturing installation for manufacturing a manufactured object by additive friction stir deposition includes a manufacturing system configured to manufacture a manufactured object by additive friction stir deposition from a manufacturing material, and a feed system configured to feed the manufacturing system with manufacturing material. The feed system includes a spool of a manufacturing material wire wound about a spool axis; an unwinding device configured to unwind the wire, to drive the spool in rotation about a principal axis of rotation and to drive the wire in rotation about its neutral fiber; and a device for guiding the unwound wire to the manufacturing system.

Abstract: An aircraft rudder pedal comprising a frame and at least one pedal side system. The or each pedal side system includes a pedal and an articulated support structure of the pedal connecting the pedal to the frame. The articulated support structure of said pedal comprises a crank, a lever and a support link. The crank presents a first pivotal articulation connection to the frame and a second pivotal articulation connection with the support link. The lever presents a first pivotal articulation connection with the frame and a second pivotal articulation connection with the support link.

Abstract: A system for monitoring the operational status of an aircraft between successive missions of the aircraft includes a computer able to determine at least one operational impact measurement on at least one future mission of the aircraft related to the aircraft and/or to an aircraft equipment and/or to a consumable and/or to the aircraft crew, the operational impact measurement being determined as a function of the flight logbook and/or technical logbook data of at least one already completed mission of the aircraft and/or a context of the future mission. The system includes a display and a display manager on the display, able to display on the display at least one operational impact indicator related to the aircraft and/or to the equipment and/or to the consumable and/or to the crew, as a function of the operational impact measurement determined by the computer.

Abstract: A secure transfer system for digital aircraft data includes a data producer system configured to generate a data capsule at each data production and a data consumer system. The consumer system is configured to retrieve each capsule to extract an identifier, a refresh indicator, a functional data packet, and an integrity control result. It is configured to check the integrity of the data in the capsule by establishing a new integrity check result from the identifier, the refresh indicator, and the functional data packet retrieved from the capsule and comparing the new integrity check result to the integrity check result of the capsule. The data capsule is in an integrity state when the new integrity check result matches the integrity check result retrieved from the capsule.

Abstract: A system is (10) for determining a flight rest scenario for an aircraft crew (12) comprising at least two pilots able to fly the aircraft (12) during a flight. The system (10) comprises a display device (16) comprising a screen (20), a module (32) for acquiring flight context and constraints inputs, and a module (34) for determining at least one crew rest scenario for the flight from the acquired inputs. The determination module (34) is able to determine the rest scenario from at least one simulation by a biomathematical fatigue model having at least one of the acquired inputs as variables. The system also includes a display management module (36) configured to display the determined rest scenario on the screen (20) of the display device (16).

Abstract: A system for piloting an aircraft includes a throttle, a flight parameter sensor system, and an engine calculator controlling thrust parameters of an engine of the aircraft. The piloting system includes a flight control unit connected to the engine calculator, the sensors and the throttle. The flight control unit generates a thrust control vector from a flight control law and sends a digital signal including the generated thrust control vector to the engine calculator. The engine calculator controlling said thrust parameters of the engine depending on the generated thrust control vector received.