Embodiments of the disclosure are directed to a convertible rotor aircraft CRA able to convert between airplane and helicopter flight modes during flight, comprising a tillable proprotor assembly TPA comprising a proprotor. Optionally, the CRA comprises a flight control module FCM configured to control the TPA to reverse direction of thrust generated by the proprotor relative to the TPA when the TPA transitions between a first orientation for helicopter flight and a second orientation for airplane flight. Optionally, the CRA comprises a deployable guard for the proprotors, configured to have a stowed state and a deployed state, wherein: the guard in the deployed state is controlled to be configured as a partially air-permeable barrier.

An enhanced flight vision system for an aircraft includes an image acquisition system configured to acquire images of the surroundings outside the aircraft and a display system configured to receive images produced by the image acquisition system and to display these images on a display in the cockpit of the aircraft. The display system is configured to acquire information about the flight path angle of the aircraft when approaching a runway, to calculate a difference between the flight path angle of the aircraft and a nominal angle and to deactivate the display of the images received from the image acquisition system on the display when the absolute value of the difference is greater than a first angular value.

In a server device, an acquisition unit acquires information generated by a first detection unit and a second detection unit through a network. An identification unit identifies a wind condition and the state of flight of an aerial vehicle on the basis of the information acquired by the acquisition unit. More specifically, the identification unit identifies the wind direction and the wind speed, which indicate the wind condition, and the position, the flight direction, and the flight speed of the aerial vehicle, which indicate the state of flight of the aerial vehicle. The estimation unit estimates a landing area where the aerial vehicle is likely to land according to the wind condition and the state of flight of the aerial vehicle which have been identified.

The invention relates to a method for validating at least one position stored in a database of an aircraft comprising a satellite positioning system, the database containing at least one radionavigation beacon position, a runway threshold position, and a displaced runway threshold position on a runway, on which the aircraft is intended to land, the validation of said at least one position comprising a consistency check between at least: a signal received by the aircraft from a radionavigation beacon associated with said at least one position, and the position of the aircraft provided by the satellite positioning system, and the value of the position stored in the database.

The invention relates to a method for validating at least one position stored in a database of an aircraft comprising a satellite positioning system, the database containing at least one radionavigation beacon position, a runway threshold position, and a displaced runway threshold position on a runway, on which the aircraft is intended to land, the validation of said at least one position comprising a consistency check between at least: a signal received by the aircraft from a radionavigation beacon associated with said at least one position, and the position of the aircraft provided by the satellite positioning system, and the value of the position stored in the database.

A method and system for determining a position error of an aircraft. The system comprises a set of collection modules implemented in an iterative manner, including an offset collection module, a position vector collection module, a set of sequentially implemented computation modules, including an angular alignment bias computation module, an observable position bias computation module and a position error computation module. The system thus allows a position error to be determined that is used to perform a landing in good conditions.

A method and system for determining a position error of an aircraft. The system comprises a set of collection modules implemented in an iterative manner, including an offset collection module, a position vector collection module, a set of sequentially implemented computation modules, including an angular alignment bias computation module, an observable position bias computation module and a position error computation module. The system thus allows a position error to be determined that is used to perform a landing in good conditions.

A method for aiding in the piloting of an aircraft landing on a runway comprises determining current flight conditions of the aircraft, determining a first approach distance using the current flight conditions, determining a current aircraft position and selection of a first point on a cockpit screen that is a function of the current position of the aircraft, selecting a second point in proximity to the landing runway, and controlling the display on the cockpit screen, of a first circular arc centered on the second point and whose radius is a function of the first approach distance, the first circular arc intersecting at a third point with a straight line passing through the first point and through the second point and the length of a part of the first circular arc situated between the third point and a first end of the first circular arc, comprising a predetermined length.

A method for aiding in the piloting of an aircraft landing on a runway comprises determining current flight conditions of the aircraft, determining a first approach distance using the current flight conditions, determining a current aircraft position and selection of a first point on a cockpit screen that is a function of the current position of the aircraft, selecting a second point in proximity to the landing runway, and controlling the display on the cockpit screen, of a first circular arc centered on the second point and whose radius is a function of the first approach distance, the first circular arc intersecting at a third point with a straight line passing through the first point and through the second point and the length of a part of the first circular arc situated between the third point and a first end of the first circular arc, comprising a predetermined length.

Systems and methods to improve controllability of an aerial vehicle responsive to degraded operational conditions are described. For example, one or more propeller blades of an aerial vehicle may be modifiable between two or more configurations. The configurations may include a low torque configuration suitable for normal operational conditions, and a high torque configuration suitable for degraded operational conditions. Various aspects or portions of a propeller blade may be modified to increase torque generated by the propeller blade due to drag or air resistance. The additional generated torque may then be used as a source of additional torque to improve controllability of the aerial vehicle responsive to degraded operational conditions.