The invention relates to a method and system for validating the graphical generation of symbols to display, comprising a graphical generation of symbols to display to form a video stream comprising a plurality of rasters, comprising a pixel generation, with the attribution of at least one associated symbol attribute for each pixel contributing to one of said symbols. The method comprises, for at least one raster of said video stream: obtaining at least one reference symbol attribute associated with at least one symbol to be monitored; identifying pixels having the reference symbol attribute(s), during a scan of the pixels of said raster in a predetermined course direction, these pixels contributing to said at least one symbol to be monitored, and calculating associated characteristic information; validating the display of the symbol(s) to be monitored based on the calculated characteristic information and of source information associated with said symbols to display.

An acoustic air data system includes first and second acoustic transmitters, an array of acoustic receivers, and control circuitry. The array is positioned to receive first and second acoustic signals. The control circuitry determines time difference of arrival (TDOA) of the first and second acoustic signals. The control circuitry determines, for each of a first and second set of acoustic receiver pairs, a signal velocity of the first and second acoustic signals, respectively, based on a distance between an inner acoustic receiver and an outer acoustic receiver and a corresponding TDOA for each pair of acoustic receivers. The control circuitry estimates one or more of wind angle, speed of sound, Mach number, and true airspeed of the airflow about the exterior of the vehicle based on parameters of a best fit circle.

Boundary information associated with a three-dimensional (3D) flying space is obtained, including a boundary of the 3D flying space. Location information associated with an aircraft is obtained, including a location of the aircraft. Information is presented based at least in part on the boundary information associated with the 3D flying space and the location information associated with the aircraft, including by presenting, in a display, the boundary of the 3D flying space and an avatar representing the aircraft at the location of the aircraft.

Computer-implemented methods, systems, and program products are provided that assist in aspects of aerial surveying, including selective display of planned flight path segments, marking of ground conditions, monitoring coverage of a planned flight path, and providing guidance information for aircraft navigation, including speed and turns.

Disclosed are systems, methods, and non-transitory computer-readable medium for providing a safe landing for a vehicle. The method may include: displaying, on one or more displays, a vehicle, an intended landing zone, and a real-time flight path of the vehicle as the vehicle approaches the intended landing zone; receiving data related to one or more of the vehicle, the flight path of the vehicle, the intended landing zone, and an obstacle; determining the proximity of the vehicle relative to the center of the intended landing zone based on the received data; displaying the proximity of the vehicle relative to the center of the intended landing zone; displaying the obstacle when present; displaying an alert when the vehicle deviates in proximity to the center of the intended landing zone and/or approaches the obstacle; and upon determining a failure to respond to the alert computing flight controls to modify landing.

An automated avionics system for determining a modified descent path of an aircraft includes a memory operable to store a database of flight information related to a flight plan and a processor operably coupled with the memory. The processor is operable to receive an indication to initiate descent of the aircraft associated with a position of the aircraft, receive information related to the flight plan from the database, and based on the information received, perform modifications to the path of descent. The processor is further operable to, based on a comparison of an original position of descent and the indicated position, determine a modified position of descent for the aircraft and calculate a modified path of descent, the modified path of descent complying with the of altitude constraint(s) of the flight plan.

Systems and methods are provided for an avionics interface of an aircraft. Sensors of the aircraft may convey information that can be used in the generation of one or more of the avionics interfaces. An avionics interface may include navigation information, engine instrument information, and communication information. Such information may be provided in visually distinct regions of the interface. An avionics interface may show an angle of attack of the aircraft in a visually incorporated manner with a navigation display. In some instances, the avionics interface may be variable to match pilot preference.

Disclosed is a method of guiding the pilot of an aircraft for the alignment maneuver, including: determining at a first instant an occurrence close to the alignment maneuver and triggering the display of a first symbol on the screen; updating the position of the first symbol on the horizon according to the updated value of the aircraft heading; when the alignment maneuver is to begin, moving a second symbol on the screen from the position of the first symbol, the direction of the displacement with respect to the horizon being determined depending on the direction of the crosswind with respect to the runway and the value of the displacement being determined depending on the difference between the current dynamic sideslip of the aircraft and a current dynamic sideslip setpoint value calculated for the aircraft.

Disclosed is a method for identifying a landing zone and for displaying on a head-up display system onboard an aircraft, a symbol conforming to the landing zone, the aircraft being apt to fly over a terrain and to land on the landing zone of the terrain. The aircraft is a helicopter, a drone or an electric aircraft with vertical take-off and landing. The method includes at least the following steps:—a hovering phase of the aircraft over the landing zone and acquisition of the geographical position of the landing zone;—a flight of the aircraft towards the landing zone and display on the head-up display system, of a symbol conforming to the landing zone at the measured geographic position.

A device includes a unit for defining evaluation criteria relating to the aircraft and to its flight, a unit for predicting an energy status of the aircraft at the end of a given segment of a flight trajectory, a unit for verifying whether at least one event will occur on the given segment, and a unit for identifying at least one action to be performed on given segment and the position where this action must be performed on this segment, the purpose of an action being to generate a change of flight configuration of the aircraft leading to a modification of the energy of said aircraft. The device is configured to form a predicted energy trajectory, from a current position of the aircraft to the end of the flight trajectory, the predicted energy trajectory indicating all identified actions and positions along the flight trajectory where these actions must be performed.