Abstract: An interior layout of an aircraft cabin extends along a longitudinal axis on a floor and comprises a table having at least one leg, at least one base for each leg and at least one flat tabletop. Each base is intended to be fixed to the floor, each leg is mounted on a base, and each flat tabletop is mounted on at least one leg. The table defines at least one main aisle accessible to a passenger of the aircraft. The main aisle extends in the longitudinal axis along a longitudinal edge of the flat tabletop. The interior layout comprises at least one seat arranged opposite the table. The seat has a seating direction oriented transversely to the longitudinal axis.

Abstract: A command device for controlling a mechanical energy reduction assembly of an aircraft, movable between an inactive configuration and a maximum mechanical energy reduction configuration, includes a rocker button, movable between a mechanical energy reduction assembly configuration maintaining position, a first position of incremental movement of the mechanical energy reduction assembly to its maximum mechanical energy reduction configuration and a second position of incremental movement of the mechanical energy reduction assembly to its inactive configuration. The command device further includes at least one return element configured to return the rocker button to its maintaining position.

Abstract: A device is for assisting the piloting in acceleration of an aircraft in taking in order to control its speed. The comprises a control member, adapted to be actuated by a pilot from a neutral position to define a taxiing piloting command for controlling the speed of the aircraft and a central controller, adapted to operate pilot at least one engine of the aircraft to apply the taxiing command defined by the pilot. The taxiing piloting command is an acceleration or deceleration command of the aircraft during taxiing.

Abstract: A system for secure transfer of digital aircraft data comprising redundant data producer systems includes a first data producer, capable of producing first data, at successive moments, and a second data producer, redundant to the first system. The second data producer is capable of producing an integrity check result relating at least to second data which it produces in a manner redundant to the first data, the integrity check result being transmitted to a data consumer. The data consumer is capable of retrieving the first data and the integrity check result produced by the second system, to produce a new integrity check result from the first data and compare the new integrity check result with the integrity check result produced by the second system.

Abstract: A piloting device for piloting an aircraft comprises a first and a second control stick mounted movable on a support. The device comprises a priority selection module configured to switch the first and second control sticks between a piloting configuration and a non-piloting configuration. The device further comprises a detection system for detecting the positions of the first and second control sticks; a first and second actuation system configured to generate respective first and second forces on the respective first and second control stick; and a control module configured to control the actuation system of the control stick which is in a non-piloting configuration such that the positions of the control sticks are identical.

Abstract: A control system is for a high lift assembly of an aircraft. The assembly is controllable in two aerodynamic configurations each with different lift. The control system includes a manual control device operable by a pilot of the aircraft. The manual control device includes at least one member movable relative to a base body. The movable member can be moved relative to the base body between a rest position, a first position and a second distinct position. The manual control device includes a resilient return device for the movable member in the rest position. The manual control device issues a signal when the movable member reaches either the first or second position, to move the high lift assembly between two of the aerodynamic configurations.

Abstract: A system for monitoring the operational status of an aircraft crew includes a unit for determining at least one pilot state based on first monitoring data of a high design assurance level and second monitoring data of a lower design assurance level. The determination unit includes a first evaluation module capable of obtaining a high-level pilot state from the first data, regardless of the second data; a second evaluation module capable of determining a low-level pilot state, from at least the second data; and a consolidation module for determining a consolidated pilot state. The consolidated pilot state is obtained as a function of the high-level pilot state and the low-level pilot state.

Abstract: An aircraft cabin includes at least one seat able to receive at least one passenger; at least one table arranged opposite the seat; and a safety device able to be mounted on the table, below the table or received in the table. The safety device includes a deployable protection assembly including an airbag deployable from a retracted idle configuration to a deployed safety configuration, and a system for controlling the deployment of the or each airbag, able to trigger the deployment of the airbag beyond a threshold deceleration value of the aircraft.

Abstract: An aircraft portion includes a fuselage oriented in a longitudinal direction, an airfoil made up of at least one pair of wings arranged on either side of the fuselage in a transverse direction orthogonal to the longitudinal direction, and an airfoil-fuselage junction fairing at the interface between the airfoil and the fuselage. The junction fairing has, in a vertical plane, a lower profile and, in a horizontal plane, a horizontal profile at the junction of the outer surface of the junction fairing with the convex side of each wing. The horizontal profile and/or the lower profile successively has, in the longitudinal direction, a convex front segment, a concave intermediate segment, and a convex rear segment.

Abstract: An aircraft computer file distribution system comprises a store (36) of aircraft computer files for loading into at least one aircraft device (12) that is onboard, mobile or replicated on the ground. The system includes a file manager (44), configured for identifying an aircraft configuration of the aircraft with which the aircraft device (12) is associated and a computer configuration of the aircraft device (12); defining, among the computer files in the computer file store (36), at least one computer file loadable into the aircraft device (12) according to the identified aircraft configuration and computer configuration; and activating a synchronization for remote distribution of at least one computer file to be loaded into the aircraft device (12) selected from the one or more computer files loadable into the aircraft device (12) based on the identified aircraft configuration and computer configuration.

Abstract: A standardized connection interface between aircraft equipment and a wireless data transmission network external to the aircraft includes a router. The router includes a mapping table between a plurality of connectivity link classes and one or more connectivity links associated with each connectivity link class. The router is configured to transmit the list of active connectivity link classes to each item of equipment, to establish a transmission of data between the piece of equipment and at least one wireless data transmission network (14A to 14E) through an active connectivity link, based on the list of active connectivity link classes and a list of connectivity link classes to which the piece of equipment is authorized to connect.

Abstract: An aircraft door mechanism includes an aircraft structure (14) delimiting an opening (24); an aircraft door (26) movable between a position closing off the opening (24) and a released position of the opening (24); and a guide system (28) for moving the door (26) between the closed off and released positions. The guide system (28) includes a main rail (46) that is fixed relative to the structure and a main carriage (48) mechanically connected to the door (26) and able to slide on the main rail (46) during the movement between said closed off and released positions. The main rail (46) is positioned between the door (26) and the structure during at least part of the movement of the door (26) between said closed off and released positions.

Abstract: A method is for detecting a blockage of a wind vane (12) of an aircraft, with the wind vane (12) including a support (20), a paddle (22) mounted rotating relative to the support (20) along an axis (A), a motor (28) able to exert a rotational torque on the paddle (22) along the axis (A), the motor (28) being connected to a processing unit (18). The method includes applying a predetermined blockage detection torque on the paddle (22) by the motor (28); measuring at least one piece of information representative of a resistance of the paddle (22) to the predetermined detection torque; and generating, via the processing unit (18), a blocking information signal, if a predetermined condition based on the representative information is verified.

Abstract: A separating element for a platform cabin comprises at least one leaf subjected to a return force toward its open position, and, for the or each leaf, a return member for returning the leaf toward its closed position and comprising a first end articulated at an articulation point movable jointly with the leaf. This return member also comprises a second end mounted movably relative to the partition between an active position and an inactive position, such that when the leaf is open and the second end is in the active position, the return member exerts, on the leaf, a return force returning the leaf toward its closed position, and when the leaf is open and the second end is in the inactive position, the return member is in a second configuration in which it does not exert a force returning the leaf toward its closed position.

Abstract: An aircraft enhanced vision system includes an electromagnetic sensor comprising at least one group of transmitters and at least one group of receivers. The electromagnetic sensor includes a waveform generation assembly powering each transmitter in order to generate the transmitted signal and a signal capture assembly to capture the signal received by each receiver after reflection off of the ground. The transmitters are distinct and spaced apart from the receivers, being arranged so as to form at least one virtual transmitter/receiver network extending in an elongation direction perpendicular to the observation direction from each transmitter/receiver combination between the group of transmitters and the group of receivers.

Abstract: An aircraft actuator torque limiter includes a disengageable torque transmitter between a rotary shaft and a driven member. The disengageable transmitter includes a friction pack including at least one contact member mounted secured in rotation with the rotary shaft and a complementary contact member, mounted secured in rotation with the driven member. The transmitter includes a clamp of the friction pack and a mover of the clamp, able to contract or expand differentially relative to the rotary shaft along the axis of rotation during a temperature variation. The clamp mover is made from a second material having a thermal expansion coefficient different from that of the first material forming the rotary shaft.

Abstract: Aircraft mission calculation system includes a first calculator configured to calculate a plurality of iso-displacement curves from a selected point, at a displacement range corresponding to several successive displacement increments of the aircraft from the selected point, the iso-displacement curves being obtained at the displacement range for a displacement of the aircraft to a given flight level from displacements of the aircraft at distinct flight altitude levels. The first calculator is configured to determine, based on iso-displacement curves up to the given flight level, obtained at distinct flight altitude levels, taken at the same displacement range of the aircraft, an extended iso-displacement curve at the given flight level maximizing the displacement of the aircraft from the geographical point of origin or minimizing the displacement of the aircraft toward the geographical destination point.

Abstract: An aircraft mission computing system includes an aircraft mission path computing engine, and a mission deck comprising a display and a display management assembly configured for displaying, on the display, at least one button for defining an operational specification of the mission. The computing engine is configured to be activated after defining the choice of operational specification using the definition button to determine at least one possible path of the aircraft based on the or each choice of defined operational specification using the or each definition button. The display management assembly is configured to display, on the display, after the activation of the computing engine, at least one outcome indicator providing mission feasibility information while respecting the or each operational specification choice.

Abstract: A ground proximity warning system for an aircraft includes a plurality of alarm generators, each able to generate an alarm by verifying evolution conditions of the aircraft specific to each alarm generator, the verification using data obtained from at least one measuring sensor of the aircraft. The ground proximity warning system includes a unit for selective deactivation of at least some of the alarm generators, able to be implemented during a search and rescue mission carried out by the aircraft, and an auxiliary alarm generator, capable of emitting a ground proximity alarm based on the safety height chosen for the search and rescue mission, when the selective deactivation unit is implemented.