Abstract: An aircraft operational state monitoring system is provided that includes a module for acquiring a logic state of a plurality of components of the aircraft, the components belonging to airplane systems. The aircraft operational state monitoring system includes a module for determining the operability status of a plurality of macroscopic functions of the aircraft, each macroscopic function being defined independently of the components and airplane systems necessary for the performance of the macroscopic function, the operability status being determined based on logic states of the plurality of components between an operational status and at least one nonoperational status. The aircraft operational state monitoring system includes a display and at least one graphic display management assembly on the display, configured for displaying, on the display, summary indicators of the operability status of the macroscopic functions of the aircraft.

Abstract: A lightning protection system of an aircraft includes a wall defining an inner surface and an outer surface. The outer surface is configured to come into contact with a mass of air located around the aircraft. The lighting protection system also includes at least two electrically conductive lighting traps received in holes traversing the wall and at least one strip with pellets having an electrically insulating substrate and electrically conductive pellets spaced apart from one another on the electrically insulating substrate. The strip with pellets is fastened on the wall by the two lightning traps. The strip with pellets is attached on the inner surface of the wall.

Abstract: A task management system of an aircraft crew during a mission includes a task sequencing module configured to acquire a first list of procedure tasks for normal and special missions to be performed during the mission, a second list of abnormal, emergency and deferred procedure tasks, to be performed in case of defect and/or failures, and a third list of additional tasks resulting from entries by the crew. The task sequencing module is configured for defining a priority order and/or a planning order between the tasks to be performed immediately from among the tasks of the first list, the second list and the third list. The display management assembly is configured to display a first overall task sequencing window including tasks from the first list, the second list and the third list ranked according to the priority order and/or according to the planning order.

Abstract: A dynamic determination method for determining the position of a stopping point of an aircraft on a landing strip and related system includes determining a first table of average time from touchdown of the aircraft as a function of the ground speed, based on an average deceleration profile of the aircraft; determining a first deceleration profile adapted to the current conditions, based on an engine thrust computed for each ground speed from the average time determined in the first table; determining a second table of time adapted to the current conditions based on the first deceleration profile; determining a second deceleration profile adapted to the current conditions, based on an engine thrust computed for each ground speed from the time determined in the second table; and computing the position of the stopping point from the second adapted deceleration profile.

Abstract: A system for purging an aircraft fuel reservoir includes a body (48) configured to be assembled on the aircraft fuel reservoir (16) and a valve (50), received in the body (48), and having a released configuration of an outlet channel (70) and a tight closed configuration of the outlet channel (70). The system further comprises a transport pipe (44) secured to the body (48), the transport pipe (44) being configured to be fluidly connected to a fuel supply pipe (20) configured to supply an energy producing device. The transport pipe (44) extends at least between a fuel suction inlet (52) and a discharge outlet (54), the suction inlet (52) being configured to emerge in the aircraft fuel reservoir (16) and the discharge outlet (54) being configured to emerge in the supply pipe (20) when the body (48) is mounted on the aircraft fuel reservoir (16).

Abstract: A display device for displaying information relative to a flight by an aircraft is provided. The information includes information relative to an energy variation of the aircraft, the energy variation being expressed by a variable representative of that energy variation. The display device is configured to show, on a viewing screen, an energy variation symbol representative of a current value of the variable. The display device is configured to further show at least one energy variation bound symbol representative of a threshold value of the variable, the threshold value corresponding to an authorized acceleration bound for the aircraft to keep or bring the speed of the aircraft in or toward a predefined usage speed range.

Abstract: A display device for displaying information relative to a flight by an aircraft is provided. The information includes information relative to an energy variation of the aircraft, the energy variation being expressed by a variable representative of that energy variation. The display device is configured to show, on a viewing screen, an energy variation symbol representative of a current value of the variable. The display device is configured to further show at least one energy variation bound symbol representative of a threshold value of the variable, the threshold value corresponding to an authorized acceleration bound for the aircraft to keep or bring the speed of the aircraft in or toward a predefined usage speed range.

Abstract: A device for managing the mechanical energy of an aircraft, having a light system, includes a support defining a guide; at least one control lever for varying the mechanical energy of the aircraft, mounted moving through the guide; and at least one position sensor detecting the position of the control lever in the guide, configured to create position information for the position of the control lever in the guide intended to be sent to a flight control unit of the aircraft. The device also includes at least one light strip extending on the support along at least part of the travel of the control lever in the guide; and a control unit of the at least one light strip, configured to display at least one light indication at least at one given point of the lighted position ramp calculated as a function of a movement context of the aircraft.

Abstract: A device for managing the mechanical energy of an aircraft, with a force application system on a control lever, includes a support defining a guide; a moving control lever for controlling varying a mechanical energy variation of the aircraft, mounted moving through the guide; and at least one position sensor detecting the position of the moving lever in the guide, configured to create position information for the position of the moving lever in the guide intended to be sent to a flight control unit of the aircraft. The device also includes an active force applicator for applying a force on the moving lever, configured to generate a force applied on the moving lever. The force depends on the position of the moving lever in the guide.

Abstract: An aircraft mission computing system includes a computing engine for computing aircraft trajectories during a mission that comprises a trajectory computing module capable of computing a mission trajectory between the geographical point of origin and the geographical destination point as a function of the airplane performance and operational mission specifications. The trajectory computing module is configured to compute at least one iso-movement curve of the aircraft, in particular at least one isochronous curve and/or at least one fuel iso-consumption curve from at least one point of the trajectory and is able to determine at least one other point of the trajectory on the iso-movement curve of the aircraft.

Abstract: A system for displaying information related to a flight of an aircraft and an associated method are provided. The display system comprises a dynamic synthesis image generating module, configured to generate at least two successive transition synthesis images between an image according to a first type of perspective and an image according to a second type of perspective, or between an image according to a second type of perspective and an image according to a first type of perspective, respectively, and to command the display thereof at successive transition moments.

Abstract: A device for managing the mechanical energy of an aircraft, having an energy management auxiliary system, includes a support defining a guide, a centralized control lever for varying the energy of the aircraft, at least one position sensor detecting the position of the centralized control lever in the guide. The position sensor is configured to create position information for the position of the centralized control lever in the guide intended to be sent to a flight control unit of the aircraft. The device also includes an auxiliary support; for the or each motor of the aircraft, an individual control lever for the individual propulsion of the motor, mounted movably in the auxiliary support; and at least one auxiliary position sensor detecting the position of the or each individual lever configured to generate information intended to be sent to the flight control unit of the aircraft.

Abstract: An observation system for an aircraft, related aircraft and method are provided. The observation system includes an observation assembly deployable between a retracted inner position and a deployed outer position outside a passage opening and a deployment mechanism of the observation assembly. The system includes a hatch, mounted moving between a position closing off the passage opening and a position clearing the passage opening, and a mechanism for maneuvering the hatch between the closing off position and the clearing position. The system also includes a conjugating assembly between the mechanism for deploying the observation assembly and the mechanism for maneuvering the hatch, active over at least part of the movement of the observation assembly between the retracted position and the deployed position, to move the hatch from the closing off position to the clearing position during the movement.

Abstract: A device for waking up a crew member resting on an aircraft includes a processing unit configured to detect current development parameters of the aircraft and/or to detect a state of consciousness of at least one other active crewmember. The processing unit is also configured to activate an apparatus for waking up the resting crew member, when at least one predetermined condition for waking up the resting crew member on one or several current parameters of the aircraft and/or on a parameter representative of the state of consciousness of the at least one other active crew member is satisfied.

Abstract: A piloting assistance system of a platform, and associated method are provided. The system includes a first detector for detecting a windshear able to generate a first alert that the platform is approaching a windshear zone; a second detector for detecting a windshear able to generate a second alert indicating the presence of the platform in the windshear zone; and a guider of the platform. The guider is able to automatically select a first guidance mode when a first alert is generated by the first detector, and to automatically select at least one second guidance mode different from the first guidance mode when a second alert is generated by the second detector. The system includes an information device able to display unified windshear alert information and/or unified information for implementation of a guidance mode, shared by the first alert and the second alert.

Abstract: A display device for displaying information relative to a flight by an aircraft is provided. The information includes information relative to an energy variation of the aircraft, the energy variation being expressed by a variable representative of that energy variation. The display device is configured to show, on a viewing screen, an energy variation symbol representative of a current value of the variable. The display device is configured to further show at least one energy variation bound symbol representative of a threshold value of the variable, the threshold value corresponding to an authorized acceleration bound for the aircraft to keep or bring the speed of the aircraft in or toward a predefined usage speed range.

Abstract: An assembly for implementing an aircraft trajectory includes a flight management system including a viewer, and a display application, on the viewer, for navigation data of the aircraft including waypoints of the aircraft along a trajectory. The flight management system includes an application for recovering tactical track monitoring data, the display application being able to display, dynamically on the viewer, a tactical track positioning symbol corresponding to the or each tactical track being monitored, the position of the positioning symbol being updated by the display application as a function of position data of the aircraft and tactical track monitoring data corresponding to the tactical track, received from a data acquisition apparatus, via a data transmission system.

Abstract: A system for controlling a trajectory of an aircraft on the ground, includes a determining module configured to determine a current trajectory of the aircraft on the ground including a series of waypoints planned for an element of the aircraft with unchanged conditions of the lateral movement devices of the aircraft, and at least one limit trajectory, including a series of limit waypoints that may be reached by the element by actuating at least one lateral movement device. The system includes a display assembly comprising a viewer configured to display a view (200) of a runway portion located near the aircraft, and a display generating module configured to display, on the viewer, a current trajectory curve (202) representative of the current trajectory and at least one limit curve (204a, 204b, 206a, 206b) representative of the limit trajectory, superimposed on the view (200).

Abstract: A hatch for closing an opening provided through an aircraft structure, related structure and method are provided. The hatch includes an inner sealing partition, intended to be mounted sealably on an aircraft structure and a locking assembly releasable from the inner partition on the structure. The hatch includes a valve for balancing pressure between an inner surface of the inner partition intended to be placed in an inner volume of the aircraft and an outer surface of the inner partition, intended to communicate with the outside of the aircraft. The valve is movable by a user between a closed sealing position and an open pressure balancing position. The releasable locking assembly is immobilized in its locking configuration when the valve is its closed sealing position.