A flight management system includes a communications system configured to receive weather data from a remote source, a display system configured to generate an output for a flight display of an aircraft, and at least one processor with a non-transitory processor-readable medium storing processor-executable code. The output includes weather information based on the received weather data. The processor-executable code causes the processor to receive a user input from a user interface element of the aircraft where the user input requests updated weather information. The processor-executable code causes the processor to retrieve, via the communications system and in response to the user input, updated weather data from the remote source; calculate a departure or arrival performance flight parameter based at least in part on the updated weather data; and provide, via the display system, an output for the flight display of the aircraft where the output includes the flight parameter.

The system as described collects and utilizes weather data sensor information in order to rapidly collect and update weather forecasts using real-time weather data collected at high rates of frequency, and use this collected high frequency weather data to rapidly correct and update the weather forecasts generated by the system.

The system as described collects and utilizes weather data sensor information in order to rapidly collect and update weather forecasts using real-time weather data collected at high rates of frequency, and use this collected high frequency weather data to rapidly correct and update the weather forecasts generated by the system.

A method for a gas turbine engine includes calculating an inlet airflow distortion value at a reference area within an airflow duct and in front of a fan of the gas turbine engine. The inlet airflow distortion value is indicative of an air pressure of an air vortex at the reference area caused by a set of crosswind conditions. The calculating is based on a ratio between an inlet airflow static air pressure in the reference area and a total ambient air pressure. The inlet airflow distortion value is compared to a threshold corresponding to a permissible amount of inlet airflow distortion at the reference area for the set of crosswind conditions, and, based on the comparison indicating that the inlet airflow distortion exceeds the threshold, an inlet airflow distortion notification is provided. A system for a gas turbine engine and a method for a gas turbine engine are also disclosed.

A method for a gas turbine engine includes calculating an inlet airflow distortion value at a reference area within an airflow duct and in front of a fan of the gas turbine engine. The inlet airflow distortion value is indicative of an air pressure of an air vortex at the reference area caused by a set of crosswind conditions. The calculating is based on a ratio between an inlet airflow static air pressure in the reference area and a total ambient air pressure. The inlet airflow distortion value is compared to a threshold corresponding to a permissible amount of inlet airflow distortion at the reference area for the set of crosswind conditions, and, based on the comparison indicating that the inlet airflow distortion exceeds the threshold, an inlet airflow distortion notification is provided. A system for a gas turbine engine and a method for a gas turbine engine are also disclosed.

Systems and methods are provided for indicating wake turbulence on an avionic display. The system comprises a display device that is onboard an aircraft and a controller in communication with the display device. The controller configured to, by a processor: receive data that includes information relating to a wake turbulence generated by another aircraft, determine a location on a runway of the wake turbulence based on the received data, and render a visual element on a display device onboard the aircraft that is in communication with the controller that is configured to display information relating the determined location on the runway of the wake turbulence, wherein the information is displayed in relation to a takeoff environment of the aircraft.

Systems and methods are provided for indicating wake turbulence on an avionic display. The system comprises a display device that is onboard an aircraft and a controller in communication with the display device. The controller configured to, by a processor: receive data that includes information relating to a wake turbulence generated by another aircraft, determine a location on a runway of the wake turbulence based on the received data, and render a visual element on a display device onboard the aircraft that is in communication with the controller that is configured to display information relating the determined location on the runway of the wake turbulence, wherein the information is displayed in relation to a takeoff environment of the aircraft.

Unmanned Aerial Vehicles also known as UAVs or Drones, either autonomous or remotely piloted, are classified as drones by the US Federal Aviation Administration (FAA) as weighing under 212 pounds. The system described herein details Autonomous Flight Vehicles (AFV) which weigh over 212 pounds but less than 1,320 pounds which may require either a new classification or a classification such as Sport Light Aircraft, but without the requirement of a pilot due to the safe autonomous flight system such as the Safe Temporal Vector Integration Engine or STeVIE. Safe Autonomous Light Aircraft (SALA) are useful as drone carriers, large scale air package or cargo transport, and even human transport depending on the total lift capability of the platform.

Unmanned Aerial Vehicles also known as UAVs or Drones, either autonomous or remotely piloted, are classified as drones by the US Federal Aviation Administration (FAA) as weighing under 212 pounds. The system described herein details Autonomous Flight Vehicles (AFV) which weigh over 212 pounds but less than 1,320 pounds which may require either a new classification or a classification such as Sport Light Aircraft, but without the requirement of a pilot due to the safe autonomous flight system such as the Safe Temporal Vector Integration Engine or STeVIE. Safe Autonomous Light Aircraft (SALA) are useful as drone carriers, large scale air package or cargo transport, and even human transport depending on the total lift capability of the platform.

A system and method for selectively preventing an alert mode implemented in an enhanced ground proximity warning system (EGPWS) from generating an alert includes retrieving from a cruise altitude data source, using the EGPWS, cruise altitude data that is indicative of a cruise altitude of an aircraft, and retrieving from a take-off altitude data source, using the EGPWS, take-off altitude data this is indicative of a take-off altitude of the aircraft. The cruise altitude data and the take-off altitude data are processed in the EGPWS to determine if the cruise altitude is below the altitude from which the aircraft is taking off. When the cruise altitude is below the altitude from which the aircraft is taking off, the alert mode implemented in the EGPWS is prevented from generating the alert until the aircraft is at the cruise altitude.