Abstract: Methods and systems are provided for enhancing the functionality of an airborne separation assurance system (ASAS) by modifying it to cooperate with a required time of arrival (RTA) functionality. The system comprises an autopilot configured to execute a trajectory of an aircraft and a flight management system (FMS) in operable communication with the autopilot. The FMS includes a required time of arrival (RTA) system that is configured to determine an RTA aircraft trajectory of the aircraft based on a required time of arrival of the aircraft at a waypoint along the flight plan. The system also includes an airborne separation assurance system (ASAS) in operable communication with the RTA and is configured to determine a spacing trajectory based on a spacing interval from a first reference aircraft.

Abstract: Systems and methods for displaying a location reference indicator (LRI) associated with an ownship icon are provided. In various embodiments, an airport moving map (AMM) is displayed, and the ownship icon is displayed in the AMM, where the ownship icon represents the ownship. A degree of zoom of the AMM is determined. In response to a determination that the degree of zoom is not within a range of center referenced threshold values, a first LRI is displayed that indicates that the icon representing the ownship is not to scale with other objects displayed in the AMM. In response to a determination that the degree of zoom is within the range of center referenced threshold values, a second LRI is displayed.

Abstract: Systems and methods for displaying a location reference indicator (LRI) associated with an ownship icon are provided. In various embodiments, an airport moving map (AMM) is displayed, and the ownship icon is displayed in the AMM, where the ownship icon represents the ownship. A degree of zoom of the AMM is determined. In response to a determination that the degree of zoom is not within a range of center referenced threshold values, a first LRI is displayed that indicates that the icon representing the ownship is not to scale with other objects displayed in the AMM. In response to a determination that the degree of zoom is within the range of center referenced threshold values, a second LRI is displayed.

Abstract: In some examples described herein, a runway location is determined based on aircraft state information from at least one aircraft. For example, a processor may determine the coordinates of one or more points of a runway based on aircraft state information generated by one or more aircraft using the runway. In some examples, the processor may aggregate coordinates determined from the aircraft state information provided by a plurality of different aircraft in order to determine the location of the runway. The processor can be located onboard an aircraft providing the state information, onboard a different aircraft, or external to any aircraft.

Abstract: A diagnostic method performed onboard an aircraft is provided. The method obtains aircraft state data during landing of the aircraft, via a plurality of avionics and aircraft systems; and determines a landing surface friction condition based on the aircraft state data, using at least one of the plurality of avionics and aircraft systems. A method of evaluating landing surface data onboard an aircraft is also provided. The method receives landing surface friction condition data, prior to landing; computes a required landing distance, based on the received landing surface friction condition data; and when the required landing distance is more than a predetermined threshold, performs a designated task.

Abstract: Provided are methods and systems for the automatic calculation and presentation of data on a display device alerting a pilot that a change in flight plan is desirable, possible and administratively compliant under air traffic control protocol. The methods and systems may automatically request the flight clearance over a data link or the pilot may override the data link.

Abstract: In some examples, a processor is configured to control a ground obstacle collision alerting system of an aircraft to deactivate delivery of ground obstacle collision alerts in response to determining the aircraft is in a designated ground area. In some examples, the processor is configured to determine the aircraft is in the designated ground area based on user input, based on a geographic location of the aircraft, or both. The processor is further configured to control the ground obstacle collision alerting system to automatically reactivate the delivery of the ground obstacle collision alerts in response to determining the aircraft is outside of the designated ground area. In some examples, the processor is configured to determine the aircraft is outside of the designated ground area based on a geographic location of the aircraft, a ground speed of the aircraft, or both.

Abstract: In some examples described herein, a runway location is determined based on aircraft state information from at least one aircraft. For example, a processor may determine the coordinates of one or more points of a runway based on aircraft state information generated by one or more aircraft using the runway. In some examples, the processor may aggregate coordinates determined from the aircraft state information provided by a plurality of different aircraft in order to determine the location of the runway. The processor can be located onboard an aircraft providing the state information, onboard a different aircraft, or external to any aircraft.

Abstract: A high-integrity auto-guidance and control method for use in conjunction with an aircraft electric taxi drive system comprises obtaining taxi path data generating in a plurality of processors taxi path guidance and control information from the taxi path guidance data, and sending commands derived from the taxi path guidance and control information from one of the plurality of processors based on a predetermined priority scheme to at least one electric taxi controller.

Abstract: In some examples, a processor is configured to control a ground obstacle collision alerting system of an aircraft to deactivate delivery of ground obstacle collision alerts in response to determining the aircraft is in a designated ground area. In some examples, the processor is configured to determine the aircraft is in the designated ground area based on user input, based on a geographic location of the aircraft, or both. The processor is further configured to control the ground obstacle collision alerting system to automatically reactivate the delivery of the ground obstacle collision alerts in response to determining the aircraft is outside of the designated ground area. In some examples, the processor is configured to determine the aircraft is outside of the designated ground area based on a geographic location of the aircraft, a ground speed of the aircraft, or both.

Abstract: An auto-guidance and control method and system are provided for use in conjunction with an aircraft electric taxi system, wherein electric taxi guidance may be performed in a manual mode by a crew or in an auto-mode by an auto-guidance and control system. First, aircraft status data and airport feature data are accessed. A processor, in response to at least the aircraft status data and the airport feature data, generates taxi guidance information and renders the taxi guidance information on a display. A guidance route is manually navigated utilizing guidance information on the display in the manual mode. In the auto mode, taxi-path commands, generated by the processor, are applied to taxi path guidance controllers in the auto-mode.

Abstract: A high-integrity auto-guidance and control method for use in conjunction with an aircraft electric taxi drive system comprises obtaining taxi path data generating in a plurality of processors taxi path guidance and control information from the taxi path guidance data, and sending commands derived from the taxi path guidance and control information from one of the plurality of processors based on a predetermined priority scheme to at least one electric taxi controller.

Abstract: An auto-guidance and control method and system are provided for use in conjunction with an aircraft electric taxi system, wherein electric taxi guidance may be performed in a manual mode by a crew or in an auto-mode by an auto-guidance and control system. First, aircraft status data and airport feature data are accessed. A processor, in response to at least the aircraft status data and the airport feature data, generates taxi guidance information and renders the taxi guidance information on a display. A guidance route is manually navigated utilizing guidance information on the display in the manual mode. In the auto mode, taxi-path commands, generated by the processor, are applied to taxi path guidance controllers in the auto-mode.

Abstract: An auto-guidance and control method and system is provided for use in conjunction with an aircraft electric taxi system. Aircraft status data is obtained, and airport feature data accessed. A processor generates taxi path guidance and control information including at least taxi speed guidance information, and sends commands derived from the taxi speed guidance information by the processor directly to an electric taxi controller to regulate the taxi speed of the aircraft.

Abstract: An auto-guidance and control method and system is provided for use in conjunction with an aircraft electric taxi system. Aircraft status data is obtained, and airport feature data accessed. A processor generates taxi path guidance and control information including at least taxi speed guidance information, and sends commands derived from the taxi speed guidance information by the processor directly to an electric taxi controller to regulate the taxi speed of the aircraft.

Abstract: Methods and systems are provided for enhancing the functionality of an airborne separation assurance system (ASAS) by modifying it to cooperate with a required time of arrival (RTA) functionality. The system comprises an autopilot configured to execute a trajectory of an aircraft and a flight management system (FMS) in operable communication with the autopilot. The FMS includes a required time of arrival (RTA) system that is configured to determine an RTA aircraft trajectory of the aircraft based on a required time of arrival of the aircraft at a waypoint along the flight plan. The system also includes an airborne separation assurance system (ASAS) in operable communication with the RTA and is configured to determine a spacing trajectory based on a spacing interval from a first reference aircraft.