DASSAULT AVIATION

A device including a display management system, configured to display on at least one of a first dedicated display area and a second dedicated display area, an alert indication corresponding to alert information received from an avionics central unit. It is configured to receive role information of the crew member present respectively on a first seat located in front of the first dedicated display area and on a second seat located in front of the second dedicated display area. The display management system is configured to display an alert indication corresponding to the received alert information, on at least one of the first dedicated display area and the second dedicated display area, defined based on the role information of the crew member present respectively in front of the first dedicated display area and the second dedicated display area.

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.

An improved aircraft vision system includes a display, a system for detecting inconsistencies between a displayed position of a synthetic depiction and the actual position on the display of a runway and/or of an approach lighting system. The inconsistency detection system includes a module for identifying a row of lights extending transversely to the runway, a system for characterising the at least one row of lights identified in order to determine a given position of the at least one row of lights relative to the runway from among a plurality of possible positions extending transversely to the runway and a calculation module configured to calculate an actual position on the display of the runway and/or approach lighting system using the determined position of the at least one row of lights.

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.

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.

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 ).

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.

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.

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.

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.