Example implementations relate to systems and techniques for coordinating and assigning aircraft and ground vehicles to runways to prevent wrong surface events and to minimize runway incursions. An aircraft initially receives instructions identifying a runway for use by the aircraft generated by an Air Traffic Control Tower (ATCT) and then subsequently receives a runway identification (ID) code transmitted by a sensor subsystem positioned proximate the runway, which is used by a runway-aircraft pairing management system. An onboard verification system of the aircraft then compares the runway ID code with the runway identified in the ground navigation instruction and uses an onboard transmitter to transmit a confirmation to the sensor subsystem positioned proximate the runway when the code and runway match. The aircraft then displays instructions for the aircraft to proceed with use of the runway.

A method for planning a vehicle trajectory is provided. The method comprises obtaining an edge map representation corresponding to one or more terrain images of a given area, and identifying a total number of edge pixels in each of a plurality of sub-regions of the edge map representation. The method further comprises determining a measurement probability density function (PDF) for each of the sub-regions based on the number of edge pixels with information content in each sub-region. The method then computes a trajectory cost for each of the sub-regions by dividing a user-selected scalar by a sum of: a user-selected value and the number of edge pixels with information content in each sub-region. Thereafter, the method selects a trajectory for navigation of a vehicle over the given area based on the trajectory cost for each of the sub-regions.

A computer implemented method of identifying anomalous flight data is provided. The method comprises: receiving a plurality of flight data units in a time series from each of a plurality of different flights, wherein each flight data unit comprises a value for each of a plurality of flight parameters at the same time point; mapping the flight data units as respective data points to a multi-dimensional space, wherein the dimensions of the multi-dimensional space comprise a dimension for each of the plurality of flight parameters; and identifying one or more anomalous flight data units in the received plurality of flight data units by applying a local outlier factor algorithm to the mapped flight data units. A method of maintaining an aircraft, a flight data analyzer, a computer program and a computer-readable storage medium is also provided.

A method of targeting, which involves capturing a first video of a scene about a potential targeting coordinate by a first video sensor on a first aircraft; transmitting the first video and associated potential targeting coordinate by the first aircraft; receiving the first video on a first display in communication with a processor, the processor also receiving the potential targeting coordinate; selecting the potential targeting coordinate to be an actual targeting coordinate for a second aircraft in response to viewing the first video on the first display; and guiding a second aircraft toward the actual targeting coordinate; where positive identification of a target corresponding to the actual targeting coordinate is maintained from selection of the actual targeting coordinate.

A system and method for high-confidence error overbounding of multiple optical pose solutions receives a set of candidate correspondences between 2D image features captured by an aircraft camera and 3D constellation features including at least one ambiguous correspondence. A candidate estimate of the optical pose of the camera is determined for each of a set of candidate correspondence maps (CMAP), each CMAP resolving the ambiguities differently. Each candidate pose estimate is evaluated for viability and any non-viable estimates eliminated. An individual error bound is determined for each viable candidate pose estimate and CMAP, and based on the set of individual error bounds a multiple-pose containment error bound is determined, bounding with high confidence the set of candidate CMAPs and multiple pose estimates where at least one is correct. The containment error bound may be evaluated for accuracy as required for flight operations performed by aircraft-based instruments and systems.

A vehicle management system includes a missile avoidance system that generates command for controlling at least one function of a vehicle. The missile avoidance system includes a maneuver control unit and a missile avoidance management unit. The maneuver control unit includes at least two control models. Each of the at least two control models generates the command for controlling the at least one function of the vehicle, and each of the at least two control models can be selectively put in an active state or an inactive state. The missile avoidance management unit selects one of the at least two control models and putts it in the active state. The maneuver control unit outputs the command for controlling the at least one function of the vehicle provided by the control model that is in the active state.

A vehicle control and interface system described herein assists an operator of an aerial vehicle with the operation of an aerial vehicle, including automated control of the aerial vehicle during flight. The system can generate a graphical user interface (GUI) on which lateral guidance and vertical guidance initiation elements are displayed. The system can conditionally disable the vertical guidance initiation element from operator interaction until at least the operator interacts with the lateral guidance initiation element (e.g., to prevent an undesirable roll maneuver during descent). If the operator interacts with the vertical guidance initiation element before engaging lateral guidance, the aerial vehicle may maintain a current altitude rather than climb or descend according to a target vertical guidance route. In this way, the GUI reformats elements based on the operational state of the aerial vehicle and reduces a risk of operational error.

An aircraft having an augmented reality flight control system integrated with and operable from the pilot seat and an associated pilot headgear unit, wherein the flight control system is supplemented by flight-assisting artificial intelligence and geo-location systems. Embodiments include an augmented reality flight control system incorporating real-world objects with virtual elements to provide relevant data to a pilot during aircraft flight. A translucent substrate is disposed in the pilot's field of view such that the pilot can see therethrough, and observe virtual elements displayed on the substrate. The system includes a headgear that is worn by the pilot. A flight assistance module is configured to receive data related to the aircraft and provide predictive assistance to the pilot during flight based on the received data based in part on a pilot profile having preferences related to the pilot.

A system includes a first sensor configured to detect an object within an air space, and output an observation signal indicative of the object within the air space. A second sensor is configured to track the object within the air space, and output a tracking signal of the object within the air space. A tracking control unit is in communication with the first sensor and the second sensor. The tracking control unit is configured to receive the observation signal from the first sensor. In response to receiving the observation signal from the first sensor, the tracking control unit is configured to operate the second sensor to track the object within the air space relative to an aircraft within the air space. The tracking control unit is also configured to determine a priority of actions to take in relation to the object based, at least in part, on the tracking signal received from the second sensor.

A method for landing an aircraft, which takes off and lands vertically, at a predetermined landing site defined by a circular marking that can be captured optically and has a circular outer contour utilizes a landing system. A camera arranged on the aircraft and directed to the landing site is used to capture images electronically, each of which represents a reproduction of the marking detected at least in sections. Each camera image is evaluated in a control device. The control device is used to fit a geometric object with at least one straight line, which has a predetermined line slope in relation to the camera image, into the reproduction in such a way that the line constitutes a tangent through a contact point to the marking detected at least in sections. The control device steers the aircraft in the direction of the contact point determined in this way.