An aircraft includes at least one sensor, an altitude actuator, a memory device, and an electronic controller. The at least one sensor is configured to detect altitude of the aircraft, current position of the aircraft and speed of the aircraft. The altitude actuator is configured to change the altitude of the aircraft. The memory device is configured to store predetermined terrain data of an area. The electronic controller is configured to estimate a future position of the aircraft based on a detected current position of the aircraft and a detected speed of the aircraft. The electronic controller is further configured to control the altitude actuator based on the future position, a detected altitude of the aircraft and the predetermined terrain data.

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.

Methods and systems are provided for assisting operation of a vehicle deviating from a desired manner of operation, such as an aircraft deviating from a planned trajectory. One method involves identifying a current aircraft altitude, identifying a current aircraft configuration, determining a recommended flight path from the current aircraft altitude for satisfying an upcoming constraint associated with a reference descent strategy based at least in part on the current aircraft configuration in response to a deviation between the current aircraft altitude a target altitude according to the reference descent strategy, and providing an output influenced by the recommended flight path. The recommended flight path includes a recommended vertical profile and a recommended speed profile, and the recommended flight path is configured to vary at least one of a kinetic energy or a potential energy of the aircraft along the recommended flight path en route to the upcoming constraint.

An approach assistance method includes: an initial calculation step for calculating a reference path and the application of a stabilization test for determining whether the reference path makes the landing possible; modification steps implemented in a sequence and applying predefined modification rules and applying the stabilization test after each modification; and a transmitting step including transmitting the reference path to the human pilot, to an autopilot and/or to a traffic management system as soon as the reference path passes the stabilization test.

Systems and methods for providing trajectory amendments are provided. In one embodiment, a method can include receiving, by one or more first computing devices, a plurality of parameters associated with an aircraft. The method can further include determining, by the one or more first computing devices, a trajectory amendment associated with the aircraft based at least in part on the plurality of parameters. The method can include determining, by the one or more first computing devices, a projected operations value associated with the trajectory amendment. The method can further include providing, by the one or more first computing devices to one or more second computing devices of an operator associated with the aircraft, a set of data identifying the trajectory amendment and the projected operations value associated with the trajectory amendment.

Methods and apparatus are provided for transmitting re-routing options to a plurality of in-flight aircraft in accordance with preconfigured pilot preferences. The apparatus comprises a data store module containing data sets against which the pilot preferences are evaluated during flight, including weather, airspace and flight restrictions, ground delay programs, and air traffic information. The apparatus further includes a flight path module containing route and position information for each aircraft. An incursion alert processing module evaluates the flight path, data store, and pilot preferences and generates incursion alerts which are transmitted to each aircraft during flight. Upon receipt of an incursion alert or, alternatively, independent of an incursion alert, the pilot may request re-routing options. Once received and reviewed, the pilot selects the optimum re-routing option, and an associated micro flight plan is uplinked and loaded into the FMS (Flight Management System).

A system and method for displaying a current state and a future state of a vehicle on a display associated with the vehicle are provided. The method includes: receiving flight plan data for a selected flight plan and a plurality of legs associated with the selected flight plan from a source of flight plan data; determining, with a processor, a current state of the vehicle with respect to one of the plurality of legs based on sensor data; determining, with the processor, a current target state for the vehicle with respect to one of the plurality of legs based on the flight plan data; determining a divergence of the current state based on a difference between the current state and the current target state; and generating a user interface for display that illustrates the divergence of the current state with respect to the one of the plurality of legs.

A laser navigational system for a vehicle having a lighting assembly configured for emission of light. A lens array assembly receives incoming light from the lighting assembly and changes the direction of the incoming light received from the lighting assembly such that the outgoing light emanating from the lens array assembly is collimated in a first direction but diverges along a different, second direction. A scanning unit aligns with the lighting assembly to direct the collimated beam in two orthogonal directions. The lighting assembly, the lens array assembly and the scanning unit are configured to direct the light to form a visual beacon that guides navigation of the vehicle to a location.

A system is provided that includes a controller including one or more processors disposed onboard an aircraft. The controller is configured to be operably connected to multiple subsystems on the aircraft. The controller receives operating parameters from one or more of the subsystems during a flight of the aircraft. The controller is configured to analyze the operating parameters to determine an abnormal operating condition of the aircraft. The controller is further configured to transmit a display message to a display device onboard the aircraft. The display message provides multiple responsive actions to the abnormal operating condition. The responsive actions are prioritized on the display device to indicate to the flight crew that one or more of the responsive actions are recommended over one or more other responsive actions in the display message.

Systems and methods for presenting an RTA waypoint with associated time constraints. The system includes a flight management system (FMS) providing an assigned flight plan with a plurality of waypoints; a display device configured to render a current location and trajectory of the aircraft in a navigation display and in a vertical display; and a controller circuit. The system locates the RTA waypoint among the plurality of waypoints, as a function of the flight plan and the current location and trajectory of the aircraft. The system identifies a time constraint associated with the RTA waypoint. The system uses the time constraint to determine a type, from among an “at”, a “before”, and an “after”, for the RTA waypoint; and, assigns a preprogrammed visual encoding scheme for the type to the RTA waypoint. The system presents the RTA waypoint, using the visual encoding scheme, on the display device.