Abstract: Methods and systems for guiding an aircraft are disclosed herein. An example method includes determining, via a processor, a difference between an estimated time of arrival and a required time of arrival of an aircraft. The example method also includes determining if the difference exceeds a threshold time. The example method further includes determining a deviation between a predicted four-dimensional flight trajectory of the aircraft and a measured four-dimensional flight trajectory of the aircraft during flight if the difference does not exceed the threshold time. The example method also includes generating a speed command to reduce the deviation and updating a flight plan of the aircraft based on the speed command.

Abstract: Example systems and methods for controlling aircraft arrivals at a waypoint are disclosed. An example method for controlling aircraft arrivals at a merging waypoint includes defining a tie waypoint at a first distance from the merging waypoint and generating a first parameter set of flight instructions for aircraft arriving at the tie waypoint. The first parameter set includes an aircraft speed instruction for a target separation between a first aircraft arriving at a target waypoint downstream of the tie waypoint and a second aircraft arriving at the target waypoint. The example method includes defining a diversionary flight path at a second distance from the merging waypoint. The second distance is less than the first distance. The method also includes generating a second parameter set of flight instructions for the aircraft arriving at the diversionary flight path.

Abstract: A method for controlling aircraft time of arrival at a flight trajectory waypoint decouples the various parts of the flight for flight plan, speed scheduling, and trajectory predictions. Adjustments to the speed during a first cruise phase of the flight reduce the deviations between the actual and estimated arrival times throughout the flight, and particularly reduce the amount of speed adjustments necessary during the later descent phase.

Abstract: A method for controlling aircraft time of arrival at a flight trajectory waypoint decouples the various parts of the flight for flight plan, speed scheduling, and trajectory predictions. Adjustments to the speed during a first cruise phase of the flight reduce the deviations between the actual and estimated arrival times throughout the flight, and particularly reduce the amount of speed adjustments necessary during the later descent phase.

Abstract: Example systems and methods for controlling aircraft arrivals at a waypoint are disclosed. An example method for controlling aircraft arrivals at a merging waypoint includes defining a tie waypoint at a first distance from the merging waypoint and generating a first parameter set of flight instructions for aircraft arriving at the tie waypoint. The first parameter set includes an aircraft speed instruction for a target separation between a first aircraft arriving at a target waypoint downstream of the tie waypoint and a second aircraft arriving at the target waypoint. The example method includes defining a diversionary flight path at a second distance from the merging waypoint. The second distance is less than the first distance. The method also includes generating a second parameter set of flight instructions for the aircraft arriving at the diversionary flight path.

Abstract: Methods and systems for guiding an aircraft are disclosed herein. An example method includes determining, via a processor, a difference between an estimated time of arrival and a required time of arrival of an aircraft. The example method also includes determining if the difference exceeds a threshold time. The example method further includes determining a deviation between a predicted four-dimensional flight trajectory of the aircraft and a measured four-dimensional flight trajectory of the aircraft during flight if the difference does not exceed the threshold time. The example method also includes generating a speed command to reduce the deviation and updating a flight plan of the aircraft based on the speed command.

Abstract: The present invention relates to methods of controlling the flight path of an aircraft to follow as closely as possible a predetermined four-dimensional flight path, such as when flying continuous descent approaches. A method of controlling an aircraft to follow a predetermined four-dimensional flight path is provided that comprises monitoring an actual along-track position and an actual vertical position of the aircraft relative to corresponding desired positions on the predetermined flight path. Throttle commands are generated based on deviations of the actual vertical position of the aircraft from the desired vertical position. Elevator commands are generated based on the deviation of the actual along-track position from the desired along-track position and on the deviation of the actual vertical position from the desired vertical position.

Abstract: The present invention relates to continuous descent approaches that ensure the greatest certainty in arrival time. The continuous descent approach is flown by maintaining an aerodynamic flight path angle, thereby allowing a ground speed to be followed with greater accuracy. An improvement is described that accounts for turns made during continuous descent approaches that may otherwise cause a drift away from the desired ground speed, and hence arrival time. A correction to the aerodynamic flight path angle is used that produces a compensatory change in the potential energy of the aircraft upon completing the turn to balance the anticipated drift in kinetic energy.

Abstract: Guiding an aircraft to follow a four-dimensional flight path during a descent with a nominal thrust setting corresponding to idle thrust or non-idle thrust includes monitoring actual along-track position and actual vertical position of the aircraft relative to corresponding desired positions on the flight path, generating control commands based on deviations of the actual vertical position of the aircraft from the desired vertical position, and generating elevator commands based on the deviation of the actual along-track position from the desired along-track position, wherein generating control commands includes, if the deviation of the actual vertical position from the desired vertical position indicates that the aircraft is too low, generating a throttle command to increase the thrust setting to above nominal thrust, and generating a speed brake command to deploy speed brakes when the deviation of the actual vertical position from the desired vertical position indicates that the aircraft is too high.

Abstract: The present invention relates to methods of controlling the flight path of an aircraft to follow as closely as possible a predetermined four-dimensional flight path, such as when flying continuous descent approaches. A method of controlling an aircraft to follow a predetermined four-dimensional flight path is provided that comprises monitoring the actual along-track position and the actual vertical position of the aircraft relative to the corresponding desired positions on the predetermined flight path. The aircraft's elevators are used to correct deviations of the along-track position and the aircraft's throttle is used to correct deviations of the vertical position.

Abstract: The present invention relates to methods of controlling the flight path of an aircraft to follow as closely as possible a predetermined four-dimensional flight path, such as when flying continuous descent approaches. A method of controlling an aircraft to follow a predetermined four-dimensional flight path is provided that comprises monitoring an actual along-track position and an actual vertical position of the aircraft relative to corresponding desired positions on the predetermined flight path. Throttle commands are generated based on deviations of the actual vertical position of the aircraft from the desired vertical position. Elevator commands are generated based on the deviation of the actual along-track position from the desired along-track position and on the deviation of the actual vertical position from the desired vertical position.

Abstract: The present invention relates to continuous descent approaches that ensure the greatest certainty in arrival time. The continuous descent approach is flown by maintaining an aerodynamic flight path angle, thereby allowing a ground speed to be followed with greater accuracy. An improvement is described that accounts for turns made during continuous descent approaches that may otherwise cause a drift away from the desired ground speed, and hence arrival time. A correction to the aerodynamic flight path angle is used that produces a compensatory change in the potential energy of the aircraft upon completing the turn to balance the anticipated drift in kinetic energy.