Abstract: Systems, methods, and apparatus for sensor fault detection and identification using residual failure pattern recognition are disclosed. In one or more embodiments, a method for sensor fault detection and identification for a vehicle comprises sensing, with sensors located on the vehicle, data. The method further comprises performing majority voting on the data for each of the types of data to generate a single voted value for each of the types of data. Also, the method comprises generating, for each of the types of data, estimated values by using some of the voted values. In addition, the method comprises generating residuals by comparing the estimated values to the voted values. Further, the method comprises analyzing a pattern of the residuals to determine which of the types of the data is erroneous to detect and identify a fault experienced by at least one of the sensors on the vehicle.

Abstract: Systems and methods for enabling a pilot to select an automated response to an air traffic conflict alert. In accordance with one embodiment, the system includes updated displays, an updated autoflight mode control panel and high-level software logic in the autopilot, flight director and autothrottle to provide an expedited response. A mode control switch may be optionally included. In accordance with an additional option, the system may be configured to operate in a fully automated state in which the system responds automatically to the air traffic conflict event without needing the pilot to first accept the automated response before its execution.

Abstract: A system includes a memory and a processor. The memory is configured to store map data indicating positions of landmarks. The processor is configured to receive image data from an image sensor. The processor is also configured to determine, based on the image data, a first estimate of a position, relative to the image sensor, of a landmark identified in the map data. The processor is configured to determine orientation of the image sensor based on inertial measurement unit measurements. The processor is also configured to determine, based on position information, the orientation, and the map data, a second estimate of the position of the landmark. The processor is configured to determine position offset data based on a comparison of the first estimate and the second estimate. The processor is also configured to generate, based on the position offset data and the position information, an output indicating an adjusted position.

Abstract: Example implementations relate to autonomous airport runway navigation. An example system includes a first sensor and a second sensor coupled to an aircraft at a first location and a second location, respectively, and a computing system configured to receive sensor data from one or both of the first sensor and the second sensor to detect airport markings positioned proximate a runway. The computing system is further configured to identify a centerline of the runway based on the airport markings and receive sensor data from both of the first sensor and the second sensor to determine a lateral displacement that represents a distance between a reference point of the aircraft and the centerline of the runway. The computing system is further configured to control instructions that indicate adjustments for aligning the reference point of the aircraft with the centerline of the runway during subsequent navigation of the aircraft.

Abstract: Systems, methods, and apparatus for sensor fault detection and identification using residual failure pattern recognition are disclosed. In one or more embodiments, a method for sensor fault detection and identification for a vehicle comprises sensing, with sensors located on the vehicle, data. The method further comprises performing majority voting on the data for each of the types of data to generate a single voted value for each of the types of data. Also, the method comprises generating, for each of the types of data, estimated values by using some of the voted values. In addition, the method comprises generating residuals by comparing the estimated values to the voted values. Further, the method comprises analyzing a pattern of the residuals to determine which of the types of the data is erroneous to detect and identify a fault experienced by at least one of the sensors on the vehicle.

Abstract: A system includes a memory and a processor. The memory is configured to store map data indicating positions of landmarks. The processor is configured to receive image data from an image sensor. The processor is also configured to determine, based on the image data, a first estimate of a position, relative to the image sensor, of a landmark identified in the map data. The processor is configured to determine orientation of the image sensor based on inertial measurement unit measurements. The processor is also configured to determine, based on position information, the orientation, and the map data, a second estimate of the position of the landmark. The processor is configured to determine position offset data based on a comparison of the first estimate and the second estimate. The processor is also configured to generate, based on the position offset data and the position information, an output indicating an adjusted position.

Abstract: Example implementations relate to autonomous airport runway navigation. An example system includes a first sensor and a second sensor coupled to an aircraft at a first location and a second location, respectively, and a computing system configured to receive sensor data from one or both of the first sensor and the second sensor to detect airport markings positioned proximate a runway. The computing system is further configured to identify a centerline of the runway based on the airport markings and receive sensor data from both of the first sensor and the second sensor to determine a lateral displacement that represents a distance between a reference point of the aircraft and the centerline of the runway. The computing system is further configured to control instructions that indicate adjustments for aligning the reference point of the aircraft with the centerline of the runway during subsequent navigation of the aircraft.

Abstract: In one embodiment of a method for reducing vertical position errors of an aircraft, the displacement of the aircraft from a commanded vertical path may be determined. A determination may be made as to whether a magnitude of a vertical path error meets criteria. No more steps of the method may be followed if the vertical path error does not meet the criteria, while the vertical path error may be converted into a delta lift command if the vertical path error meets the criteria. The delta lift command may be limited. The delta lift command may be converted into lateral surface position commands for control surfaces. The lateral surface position commands may be communicated to lateral control surface actuators to move the control surfaces according to the lateral surface position commands.

Abstract: A system and method for providing guidance during a flare maneuver of an aircraft may include the steps of: (1) generating a primary flare command from a primary flare control law based on an altitude of the aircraft, (2) generating the secondary flare command from a secondary flare control law based on inertial vertical speed of the aircraft, and (3) generating an ultimate flare command by selecting one of the primary flare command when the aircraft is over regular terrain or the secondary flare command when the aircraft is over irregular terrain.

Abstract: A system and method for providing guidance during a flare maneuver of an aircraft may include the steps of: (1) generating a primary flare command from a primary flare control law based on an altitude of the aircraft, (2) generating the secondary flare command from a secondary flare control law based on inertial vertical speed of the aircraft, and (3) generating an ultimate flare command by selecting one of the primary flare command when the aircraft is over regular terrain or the secondary flare command when the aircraft is over irregular terrain.

Abstract: In one embodiment of a method to reduce vertical position errors of an aircraft, a disturbance input acting on the aircraft may be determined. The magnitude of the disturbance may be converted into a delta lift command if the magnitude of the disturbance is outside a criteria. The delta lift command may be post processed. The delta lift command may be converted into symmetric lateral surface position commands for control surfaces. The symmetric lateral surface position commands may be communicated to lateral control surface actuators to move the control surfaces according to the symmetric lateral surface position commands.

Abstract: An automatic landing system (ALS) includes an automatic landing module. The automatic landing module receives a radio altitude from a radio altimeter and any other sensor inputs for use by the automatic landing module and generates an ALS elevator command. The ALS also includes a runway slope compensation (RSC) module. The runway slope compensation module receives the ALS elevator command, the radio altitude and an inertial vertical speed from an inertial reference unit and generates an aircraft elevator command and at least one symmetric wing surface command. The aircraft elevator command and the at least one symmetric wing surface command are useable by an aircraft for runway slope compensation.

Abstract: In one embodiment of a method to reduce vertical position errors of an aircraft, a disturbance input acting on the aircraft may be determined. The magnitude of the disturbance may be converted into a delta lift command if the magnitude of the disturbance is outside a criteria. The delta lift command may be post processed. The delta lift command may be converted into symmetric lateral surface position commands for control surfaces. The symmetric lateral surface position commands may be communicated to lateral control surface actuators to move the control surfaces according to the symmetric lateral surface position commands.

Abstract: In one embodiment of a method for reducing vertical position errors of an aircraft, the displacement of the aircraft from a commanded vertical path may be determined. A determination may be made as to whether a magnitude of a vertical path error meets criteria. No more steps of the method may be followed if the vertical path error does not meet the criteria, while the vertical path error may be converted into a delta lift command if the vertical path error meets the criteria. The delta lift command may be limited. The delta lift command may be converted into lateral surface position commands for control surfaces. The lateral surface position commands may be communicated to lateral control surface actuators to move the control surfaces according to the lateral surface position commands.

Abstract: In one embodiment of a method to reduce vertical position errors of an aircraft, a disturbance input acting on the aircraft may be determined. The magnitude of the disturbance may be converted into a delta lift command if the magnitude of the disturbance is outside a criteria. The delta lift command may be post processed. The delta lift command may be converted into symmetric lateral surface position commands for control surfaces. The symmetric lateral surface position commands may be communicated to lateral control surface actuators to move the control surfaces according to the symmetric lateral surface position commands.