A method of assisting in piloting an aircraft having a fuselage, the aircraft having a first side arrangement and a second side arrangement, which arrangements are disposed laterally on either side of the fuselage, and each of them participates in the movement of the aircraft. During an assistance phase, the method includes the following steps: measuring a value of a first ground clearance of the first side arrangement and a value of a second ground clearance of the second side arrangement; and displaying on a screen at least one symbol that varies as a function of the variation in the value of the first ground clearance and/or of the variation in the value of the second ground clearance.

A method for assisting a pilot to navigate an aircraft when taxiing is disclosed. A centre line of a route, conformal to outside scenery, is displayed on an eyes out screen associated with the pilot. A pictorial indication of the alignment of the undercarriage with the centre line is displayed on the eyes out screen. Further graphical information related to the navigation is displayed on the eyes out screen.

Various avionics systems may benefit from repeaters. For example, an ADS-B In traffic display repeater system may be useful for, for example, retrofit aircraft. A system, according to certain embodiments, can include a traffic awareness computer of an aircraft. The system can also include an aircraft interface device. The system can further include a data bus configured to convey data from the traffic awareness computer to the aircraft interface device. The data conveyed can be configured to permit repetition of one or more displays of a cockpit of the aircraft on a tablet computer.

A display system for an aircraft, comprising at least one first display unit; at least one second display unit; a control unit that is configured to control the at least one first display unit and the at least one second display unit; and a storage unit with a main memory that is configured to store at least one configuration file, wherein the at least one configuration file is useable by the control unit for configuration of the at least one first display unit and the at least one second display unit, and wherein the at least one configuration file defines at least one displayable parameter for the at least one first display unit and the at least one second display unit.

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.

A method for guidance and for assisting in following a trajectory for velocity-vector piloting of an aircraft includes a step of calculating, at all times, lateral and vertical offsets of the current position of the aircraft from a target trajectory, estimated by a flight management system, and then a joining heading and a joining gradient for the aircraft to join the trajectory depending on these offsets; and a following fourth step of displaying, in head-up or head-down form, a consistent guidance symbol centered on the calculated joining heading and the calculated joining gradient for joining the trajectory, on a piloting screen showing a velocity vector. The fourth step may display, in addition to the guidance symbol, one or more items of information anticipating the next trajectory break.

A low visibility aid device includes a main body having a front end, a back end, a middle section and an interior space. A mounting bracket extends outward from the main body for securing the device onto a manned aircraft for use during flight. A sensor suite is positioned within the main body to capture flight data information including audiovisual information, altitude information, attitude information and heading information of the aircraft during flight. A control unit having a wireless communication unit is positioned within the main body and selectively transmits the flight data information to a user device. A power generation unit generates power for use by the system components during device operation.

Disclosed are methods, systems, and a non-transitory computer-readable medium for generating and displaying a target altitude and a target speed for a vehicle to ensure sonic boom values remain within permissible threshold values. For instance, the method may include receiving speed data, altitude data, and flight path data for a flight path of the vehicle, and generating at least one of a target altitude and a target speed for each of one or more locations along the flight path based on the received speed data, altitude data, and flight path data, and a permissible threshold boom value for each of the one or more locations. The method may also include outputting the generated at least one of the target altitude and the target speed to a display system.

Methods and apparatus are provided for generating a runway landing alert for an aircraft. The method comprises establishing an altitude parameter and a safety envelope for a designated target runway of the aircraft. A track of the aircraft is monitored with reference to a centerline of the target runway. Any deviation by the aircraft from the centerline of the target runway is detected and determined if it is within a margin of error. If the deviation is within the margin of error, an altitude parameter is increased. If the aircraft is determined to still be maneuvering with respect to the centerline of the target runway, the altitude parameter is decreased. Otherwise, an alert is generated if the aircraft is outside of the safety envelope.

A method is disclosed for generating and displaying a location, time, amount of one or more transitions along a flight path of a vehicle to ensure sonic boom values remain within permissible threshold values. The method may include receiving speed data, altitude data, and flight path data, including environment data, for a flight path of the vehicle, and generating, for each of one or more transitions along the flight path of the vehicle, at least one of a transition location, of upcoming locations along the flight path, a transition time, and a transition amount, based on the received speed data, altitude data, and flight path data, and a permissible threshold boom value of the upcoming transitions along the flight path. The method may also include outputting the generated transition location, transition time, and transition amount for the one or more transitions to a display system.