Abstract: A system and method for predicting estimated times of arrival are disclosed. The system may include a controller configured to: receive a flight plan for an aircraft, define a ground path for the aircraft based on the flight plan with respect to an ellipsoidal model of Earth, and integrate along the ground path for each flight leg using an energy-based method to generate aircraft states. The integration may involve calculating ground speed, traversal time, fuel consumed, and gross weight of the aircraft, aggregating the traversal time of each integration step to determine a total traversal time for each waypoint, determining an estimated time of arrival at each waypoint based on the total traversal time, and directing a transmission indicative of the estimated time of arrival at each waypoint.

Abstract: A neural network model predicts a maximum altitude for an aircraft based on factors. The neural network model is trained using aircraft performance tables that include specified parameters and variable parameters. The specified parameters include a residual rate of climb (RROC) threshold and a maneuver margin threshold. The variable parameters include an aircraft gross weight, a temperature, a cruise airspeed, and a present altitude. The variable parameters change within the table while the specified parameters do not. The altitude is incremented and the gross aircraft weight is determined based on a climb profile using the energy method to determine fuel consumption. After these changes, it is determined whether the parameters fail criteria for the maximum altitude. If one of the criteria is not met, then the maximum altitude for the table is determined based on the parameters. The tables and maximum altitudes are used to train the neural network model.

Abstract: A system and method for computing and displaying a fuel optimal idle deceleration start point which minimizes the overall auto throttle movement keeping the throttle at idle detent throughout the maneuver thus minimizing the fuel burn and stress on engine. The need for speed brakes deployment is also reduced because the deceleration distance length is accordingly adjusted based on current parameters. The accurate solution takes into account the current condition such as aircraft weight, altitude and speed and environmental parameters such as wind and temperature. The computed deceleration start point is displayed on map/navigation and vertical display for enhanced flight crew awareness.

Abstract: A system includes a processing circuit onboard an aircraft and configured to determine an optimum cruise profile for the aircraft based on a flight plan, a characteristic of the aircraft, and an environmental characteristic. The processing circuit is also configured to determine an optimized cruise vertical path based on the optimum cruise profile and air traffic information of at least one other aircraft, and control an autopilot system of the aircraft to cause the aircraft to follow the optimized cruise vertical path.

Abstract: A system and method for computing and displaying a fuel optimal idle deceleration start point which minimizes the overall auto throttle movement keeping the throttle at idle detent throughout the maneuver thus minimizing the fuel burn and stress on engine. The need for speed brakes deployment is also reduced because the deceleration distance length is accordingly adjusted based on current parameters. The accurate solution takes into account the current condition such as aircraft weight, altitude and speed and environmental parameters such as wind and temperature. The computed deceleration start point is displayed on map/navigation and vertical display for enhanced flight crew awareness.

Abstract: A system includes a processing circuit onboard an aircraft and configured to determine an optimum cruise profile for the aircraft based on a flight plan, a characteristic of the aircraft, and an environmental characteristic. The processing circuit is also configured to determine an optimized cruise vertical path based on the optimum cruise profile and air traffic information of at least one other aircraft, and control an autopilot system of the aircraft to cause the aircraft to follow the optimized cruise vertical path.

Abstract: Present novel and non-trivial system, device, and method for generating a vertical path profile are disclosed. The vertical path profile generating system is comprised of a source of navigation data, a source of performance factors data, a vertical path generator (“VPG”) and a presentation system. The VPG may be configured to receive the navigation data representative of takeoff runway information; receive the performance data may be representative of aircraft performance factors; determine a first vertical path and/or second vertical path as a function of criteria employing the navigation data and the performance data; generate presentation data responsive to the determination; and provide the presentation data to one or more presentation devices comprised of, in part, a visual display unit configured to display a first takeoff path profile and/or a second takeoff path profile.

Abstract: A present novel and non-trivial system, device, and method for presenting winds aloft symbology on an aircraft display unit are disclosed. Symbology image data representative of a plurality of sets of winds aloft symbologies may be generated as a function of flight plan data and weather data; flight plan data representative flight plan comprised of a plurality of waypoints may be received along with weather data representative of winds aloft data corresponding to each waypoint. Each set of winds aloft symbologies may be comprised of winds aloft symbology corresponding to each waypoint of the flight plan at a single altitude and symbolize winds aloft at that altitude. When provided to a display unit, each set of winds aloft symbologies represented in the symbology image data may be presented in a series of increasing or decreasing altitudes, where the series is presented sequentially or simultaneously.