Abstract: Devices and methods for aiding a large area search for objects. A searcher transmits interrogation signals of long range relative to the return range to be received by a device at the target object. The target device responds with a ping signal modified to be more easily found by means of information contained in the interrogation signal. The information may be in the nature of the received signal or data encoded and embedded. The target device may use a microprocessor to do complex operations using the information from the interrogation signal and other information. Detection of a weak ping is facilitated by such means as being beamed in the direction of the interrogation, arriving at a predictable time, or having parameters adapted to values requested by the searcher. The object is then intercepted with help of the ping or other signals from the device.

Abstract: Alerting systems and methods for an enhanced approach monitor are provided. The system is configured to: determine a missed approach altitude (MAA), an intended configuration, and target approach speed, each being related to the intended approach procedure and aircraft specific data. At a decision point defined as a co-occurrence of (a) the RT distance is substantially equal to or less than a distance threshold, and (b) the RT altitude is substantially equal to the MAA, the system identifies go-around scenarios, such as when (i) the RT speed exceeds the target approach speed, or (ii) the RT configuration is not equal to the intended configuration, or (iii) an RT approach path angle exceeds the target angle. The system issues a go-around alert based on whether the aircraft can perform a go-around operation, as determined based on aircraft performance data and terrain data.

Abstract: Provided are enhanced flight guidance systems and methods for an aircraft. The method includes recognizing when the aircraft is in manual operation and an active flight path is different than the planned flight path. An interrupt is received and categorized as one of (i) obstacle, (ii) equipment/fuel, or (iii) pilot health monitor. A managed mode begins, including identifying a rejoining leg of the planned flight path at which to rejoin and a location on the rejoining leg at which to rejoin. A recapture path strategy is selected from (i) lateral, (ii) vertical, and (iii) mixed lateral and vertical. A recapture path to the location on the rejoining leg is computed. The computed recapture path includes speed targets and configuration requirements at dedicated points along the recapture path. Aircraft state data along the recapture path is predicted and guidance controls for the aircraft along the recapture path are generated.

Abstract: An electronic device, a method and computer readable medium for multimodal authentication are disclosed. The method includes receiving a request for authentication, facial signature data generated based on an input from a radar source of the electronic device, and facial image data generated based on an input from a camera of the electronic device. The method also includes identifying an illumination condition and a sensor condition associated with the electronic device. The method additionally includes assigning a weight associated with the camera and the radar source based on the illumination condition and the sensor condition. The method further includes granting the request when at least one of the facial signature data and the facial image data are within a threshold of similarity with a preregistered facial data associated with the weight.

Abstract: Systems and methods for associating critical flight reference data with a flight path vector symbol are provided. The system displays a continuously updated image with a symbol for a flight path vector. The system displays a first readout arrangement, in which the airspeed indicator and the altitude indicator are (i) each located in relationship to boundary edges of the display device, and (ii) their locations are substantially static. The system detects a deviation between the flight path vector and the heading, and when the deviation exceeds a threshold, the system toggles to a second readout arrangement, in which the airspeed indicator and the altitude indicator are (i) each located a distance measured from the flight path vector, and (ii) dynamically change location responsive to movement of the flight path vector.

Abstract: An aircraft flight control system comprises a set of primary computers, each configured to compute a flight order dependent on at least one aircraft flight parameter and intended for an aircraft control surface actuator remote controller. Each computer participates in command mode within a first virtual command/monitor pair and in monitor mode within a second virtual command/monitor pair. Each computer determines a consolidated flight parameter value as a function of a flight parameter value acquired by this computer and of flight parameter values received from the other computers, using a consolidation algorithm commonly used by all primary computers to each determine a consolidated flight parameter value, and compute the intended flight order for the remote controller as a function of the consolidated flight parameter value, according to a unique computation whose result is used by the computer both when acting in command mode and when acting in monitor mode.

Abstract: Systems, methods, and devices are provided herein for controlling one or more movable objects via a graphical user interface. A method for controlling a movable object may be provided. The method may comprise obtaining one or more parameters of a target object, and generating a motion path for the movable object based on the one or more parameters of the target object. The motion path may comprise a plurality of spatial points that are defined relative to the one or more parameters of the target object. The plurality of spatial points may be configured to be on one or more planes.

Abstract: Various technologies described herein pertain to labeling sensor data generated by autonomous vehicles. A computing device identifies candidate path plans for an object in a driving environment of an autonomous vehicle based upon sensor data generated by sensor systems of the autonomous vehicle. The sensor data is indicative of positions of the object in the driving environment at sequential timesteps in a time period. Each candidate path plan is indicative of a possible maneuver being executed by the object during the time period. The computing device generates a weighted directed graph based upon the candidate path plans. The computing device determines a shortest path through the weighted directed graph. The computing device assigns a maneuver label to the sensor data based upon the shortest path, wherein the maneuver label is indicative of a maneuver that the object executes during the time period.

Abstract: A system and method for providing automatic from-waypoint updating includes determining when a flight plan has been received that includes rendering a lateral map image that includes an aircraft icon and a flight leg to be captured. A variable position user input device supplies a signal representative of its position. A processor processes the signal from the variable position user input device and commands a display device to render a trajectory line graphic that (a) extends from the aircraft icon in a direction that corresponds to the position of the variable user input device and (b) intersects the at least one flight leg to be captured. The flight plan is automatically updated to designate the waypoint at the start of the at least one flight leg as a from-waypoint.

Abstract: A method for detecting objects comprising radiation-absorbent material includes transmitting signals of two different frequencies to a target location and receiving an intermodulation product from the target location. The signals are transmitted via separate antennas connected with respective transmitters. The intermodulation product is received by a receiving antenna connected with a receiver and arranged to receive the intermodulation product reradiated from the target location. The intermodulation product comprises a harmonic of the two signals.

Abstract: In some examples, a system includes a radar device configured to transmit first X-band radar signals in a weather mode and receive first return X-band radar signals in the weather mode. In some examples, the radar device is further configured to transmit second X-band radar signals in a landing mode and receive second return X-band radar signals in the landing mode. In some examples, the system also includes processing circuitry configured to detect, in the weather mode, weather formations based on the first return X-band radar signals. In some examples, the processing circuitry is further configured to determine, in the landing mode, a position of a transponder based on the second return X-band radar signals received by the radar device and determine a location of a runway based on the position of the transponder.

Abstract: Systems and methods for tracking a target depression angle relative to a reference location. In accordance with some embodiments, the system comprises a set of algorithms and pilot displays that use data from an onboard navigation system to calculate an asset's location relative to a reference location, allowing for precise control of relative geometry for the purposes of system measurement and performance assessment. The system provides a pilot with tracking error and steering cues along a flight profile, allowing for closed-loop tracking of target depression angle (body axis elevation) while sweeping look angle (body axis azimuth) relative to a static or dynamic reference location.

Abstract: A device can receive information that identifies an airspace voxel that represents a three-dimensional portion of airspace during a particular time period. The device can associate one or more airspace parameters with the airspace voxel. The one or more airspace parameters can represent one or more conditions that relate to flight through the airspace voxel during the particular time period. The device can receive one or more flight parameters regarding a potential flight plan of an aircraft through a plurality of airspace voxels, including the airspace voxel, during the particular time period. The device can analyze the one or more flight parameters and a plurality of airspace parameters, associated with the plurality of airspace voxels, using one or more airspace rules. The device can output a recommendation regarding the potential flight plan based on analyzing the one or more flight parameters and the plurality of airspace parameters.

Abstract: A beacon (110) for a ranging system includes an electronic scanned array (ESA) antenna and a transceiver. The ESA antenna is configured to emit a separate radio frequency (RF) phased-array narrow beam (140) for each of a plurality of segments of an arc, and receive from an end user node (130) a response signal based on at least one of the RF phased-array narrow beam (140). Each segment of the arc is scanned at a specified time interval. The transceiver is configured to transmit a pulsed signal via the RF phased-array narrow beam (140), and receive the response signal.

Abstract: A radar system provides information relating to a three-dimensional field of surveillance (FoS) having a volume exceeding one cubic kilometre. The radar system includes a radar transmitter and radar receiver arranged to provide persistent surveillance of the FoS. Each radar return signal received within a sequence of time periods is processed. An associated signal information is stored in a memory in association with information identifying at least one of a respective beam in which that return signal was received and a respective receiver element at which that respective return signal was received.

Abstract: A three-dimensional path finding system bifurcates path finding operations between horizontal paths and vertical paths. Horizontal paths are identified according to the Theta* algorithm that produces direct, efficient paths that are viable in a horizontal plane. Vertical paths are identified according to the A* algorithm that produces paths that are viable for an aircraft changing altitude. The horizontal and vertical components are combined to produce a viable, efficient path in three dimensions.

Abstract: A system and related method for monitoring the performance of one or more autonomous unmanned aircraft (UA) includes a flight assistant for periodically determining the viability of an aircraft flight command, flight, or mission by comparing expected flight segment configuration and performance against at least actual performance. The flight assistant may trend actual performance as a function of differences in expected position and actual position and determine whether a flight command, flight, or mission may be performed or continued according to a hierarchy of user selectable detected anomalies or safety concerns. The flight assistant may report to an operator, controller, pilot, or monitor a rate of deviation, size of deviation, or change in the rate of deviation in accordance with a hierarchy based at least in part on flight segment, altitude, proximity to people or things.

Abstract: Apparatus and associated methods relate to determining, based on a detected portion of a projected pulse of quasi-optical energy backscattered by water particles within a divergent projection volume of a cloud atmosphere, properties of the backscattering water particles. The pulse of quasi-optical energy is projected into the divergent projection volume of the cloud atmosphere. The divergent projection volume is defined by an axis of projection and an angle of projection about the axis of projection. The portion of the projected pulse of optical energy backscattered by water particles within the divergent projection volume of the cloud atmosphere is received and detected. Various properties of the backscattering water particles, which can be determined from the detected portion of the projected pulse backscattered by water particles can include particle density and/or particle size.

Abstract: An aircraft control system and method to optimize aircraft control based on noise abatement volumes. A noise abatement component computes optimal flight and engine control based on a line-of-sight distance to minimize direct operating cost (DOC) while complying with community noise regulations.

Abstract: A method and system for assisting guidance of an aircraft along a runway approach axis. The method includes acquiring a position deviation between a current position of the aircraft and the approach axis, determining an angle between a longitudinal axis of the aircraft and the approach axis, and determining a lateral offset of the trajectory of the aircraft likely to result from a maneuver of alignment of the longitudinal axis of the aircraft with the runway during the landing of the aircraft. A lateral trajectory correction is computed as a function of the lateral trajectory offset. This position deviation is corrected by adding the lateral trajectory correction to it. This position deviation is transmitted to the device for guiding the aircraft.

Abstract: A system and related method for monitoring the performance of one or more autonomous unmanned aircraft (UA) includes a flight assistant for periodically determining the viability of an aircraft flight command, flight, or mission by comparing expected flight segment configuration and performance against at least actual performance. The flight assistant may trend actual performance as a function of differences in expected position and actual position and determine whether a flight command, flight, or mission may be performed or continued according to a hierarchy of user selectable detected anomalies or safety concerns. The flight assistant may report to an operator, controller, pilot, or monitor a rate of deviation, size of deviation, or change in the rate of deviation in accordance with a hierarchy based at least in part on flight segment, altitude, proximity to people or things.

Abstract: A vehicle data collection method is disclosed. The method comprises receiving vehicle data, determining that an internet connection is not available, storing the vehicle data, determining that an internet connection has become available, and transmitting the vehicle data based at least in part on the determination that an internet connection has become available.

Abstract: The disclosed embodiments relate to automated generation a flight log and a squawk list file. A computer records a preliminary flight log data file (PFLDF), and automatically generates a preliminary squawk list file (PSLF) that includes a plurality of squawk events recorded while an aircraft is in flight. A portable wireless communication device executes a software application, which can cause a display to display each squawk event from the PSLF for review. An input system receives an input for each particular squawk event. These inputs for each particular squawk event can be an edit input, an approval input, or a removal input. When all squawk events in the PSLF have been reviewed, the processor can generate a final flight log and a final squawk list file (FSLF) that includes each of the squawk events from the PSLF that have been reviewed and approved for inclusion in the final squawk list.

Abstract: Systems and methods can be utilized to align or provide targeting for a platform. One alignment system and method can receive first electronic data indicative of attitude of the platform and can receive second electronic data related to a position on the platform. The alignment system and method can provide third electronic data indicative of an adjusted attitude of the platform in response to the first electronic data and a slope vector or terrain data. The targeting system and method can use position differencing between a platform and a remote observer to aim at a target.

Abstract: Various avionics systems may benefit from the proper handling of diversity with respect to antennas. For example, systems and methods for remote L-band smart antenna distance measuring equipment may benefit from being prepared to provide diversity against interference, such as a multipath interference. A method can include determining which antenna of a plurality of antennas of an aircraft is preferred for communication with respect to distance measuring equipment. The method can also include selecting the antenna based on the determination.

Abstract: An automatic take-off and landing control device for an aircraft is provided. The control device comprises at least two of at least one local tracking device adapted for receiving at least one local signal from at least one local ground station and for determining a position of the aircraft based on the local signals, at least one GNSS tracking device adapted for receiving a GNSS signal and for determining a position of the aircraft based on the GNSS signal; and at least one camera device adapted for observing an environment of the aircraft and for determining a position of the aircraft based on the camera signal.

Abstract: Various embodiments that pertain to surface non-uniformity detection through use of radio waves are described. A vehicle can transmit radio waves to an area the vehicle is traveling to, such as a road in front of an automobile. The automobile can receive and process returned radio waves to determine if the road has a non-uniformity, such as a significant pothole or speed bump. If the road has the non-uniformity, then a driver of the automobile can be alerted so the driver can decide if evasive action should be taken and take such action if appropriate.

Abstract: A low cost, all weather, high definition RF radar system for an autonomous vehicle is described. The high definition RF radar system generates true target object data suitable for imaging, scene understanding, and all weather navigation of the autonomous vehicle. The high definition RF radar system includes a pair of independent orthogonal linear arrays. Data from both linear arrays is fed to a processor that performs data association to form true target detections and target positions. A Boolean association method for determining true target detections and target positions reduces many of the ghosts or incorrect detections that can produce image artifacts. The high definition RF radar system provides near optimal imaging in any dense scene for autonomous vehicle navigation, including during visually obscured weather conditions such as fog.

Abstract: A method of route planning for a vehicle proceeding from a current location to a destination in a planning space is provided. The method includes generating a destination-rooted tree from global information that provides cost-to-go routing to the destination from multiple locations in the planning space, generating a vehicle-rooted tree using local information from the current location out to a sensing horizon and determining a local destination at the sensing horizon. The local destination corresponds to minimal cost-to-go routing obtained from the destination-rooted tree.

Abstract: Systems and methods for performing distance and velocity measurements, such as by using carrier signals, are disclosed. A measurement method may include transmitting a first signal from an originator device to a transponder device and determining a carrier phase of the first signal at the transponder device. The measurement method may also include transmitting a second signal from the transponder device to the originator device and determining a carrier phase of the second signal at the originator device. The measurement method may include estimating a relative distance between the originator device and the transponder device using the carrier phase of the first carrier signal, the carrier phase of the second carrier signal. The method may also include estimating the relative distance using a frequency difference. The method may include using an adjusted relative distance to determine a total distance between the originator device and the transponder device.

Abstract: A reflection controller for modifying electromagnetic reflections from a surface includes a conducting patch being positioned proximate to an electromagnetically reflecting surface. The floating conducting patch includes an electrical conductor at a floating potential positioned on a dielectric substrate where at least one of a dielectric thickness, dielectric constant, or the dimensions of the electrical conductor are chosen to reduces retro-reflection of incident radiation.

Abstract: The invention relates to a method of analyzing flight data recorded during N flights of at least one aircraft, by means of a flight data recorder of an aircraft, the data being grouped together by flight i in a signature vector of the flight Xi of size d, the components of which correspond to data recorded during said flight i of the aircraft, a flight i being thus defined by the signature vector Xi, the method comprising the following steps: Gaussian kernel entropy component analysis of the flight signatures Xi to obtain a zone of normal flights and classifying the flight signatures Xi with respect to their distance to said zone; determining, for each flight i, an abnormality score zi defined by the distance of a flight signature Xi with respect to the zone of normal flights; detecting, as a function of the abnormality score zi, at least one abnormal flight.

Abstract: Mechanisms for identifying obstacles in a landing zone are disclosed. A first polarization elevation angle matrix is generated based on reflected radar signals having a first polarization sense. A second polarization elevation angle matrix based on reflected radar signals having a second polarization sense that differs from the first polarization sense is generated. The first polarization elevation angle matrix and the second polarization elevation angle matrix are integrated to form an integrated elevation angle matrix that identifies first scatterers and second scatterers with respect to the landing zone.

Abstract: A system and apparatus assists pilots and flight crews in determining the best course of action at any particular point inflight for any category of emergency. The system monitors a plurality of static and dynamic flight parameters including atmospheric conditions along the flight path, ground conditions and terrain, conditions aboard the aircraft, and pilot/crew data. Based on these parameters, the system may provide continually updated information to the pilot or crew about the best available landing sites or recommend solutions to aircraft configuration errors. In case of emergency, the system may provide the pilot with procedure sets associated with a hierarchy of available emergency landing sites (or execute these procedure sets via the autopilot system) depending on the specific nature of the emergency.

Abstract: A method includes controlling a plurality of rotors to cause a plurality of antennas to traverse a flight path. Traversing the flight path includes concurrent translation of a body in a horizontal plane and rotation of the body about an axis. The plurality of rotors is coupled to the body. The method also includes, while traversing the flight path, receiving a first phase measurement of a first signal via a first antenna of a plurality of antennas and receiving a second phase measurement of the first signal via a second antenna of the plurality of antennas. The method further includes determining position information related to a location of the transmitter based at least in part on the first phase measurement and the second phase measurement.

Abstract: An interferometric inverse synthetic aperture radar (IFISAR) is described that can provide a height measurement of moving objects on a surface using a small radar aperture. The IFISAR includes a two-dimensional antenna array including a plurality of elements that are configured to receive a plurality of return signals carrying energy of a transmitted RF signal that are reflected from the target. A first antenna group and a second antenna group of the plurality of elements respectively located at opposite ends of the array are enabled, and a third antenna group of the plurality of elements located between the first antenna group and the second antenna group are disabled. A processor of the IFISAR is operatively coupled to the plurality of elements and configured to determine height characteristics of the target according to interferometric processing of the return signals received by the first antenna group and the second antenna group.

Abstract: Some implementations provide techniques and arrangements for distance measurements between computing devices. Some examples determine a distance between devices based at least in part on a propagation time of audio tones between the devices. Further, some examples determine the arrival time of the audio tones by performing autocorrelation on streaming data corresponding to recorded sound to determine a timing of an autocorrelation peak indicative of a detection of an audio tone in the streaming data. In some cases, cross correlation may be performed on the streaming data in a search window to determine a timing of a cross correlation peak indicative of the detection of the audio tone in the streaming data. The location of the search window in time may be determined based at least in part on the timing of the detected autocorrelation peak.

Abstract: A method for detecting a failure of at least one sensor on board an aircraft is provided. The method includes implementing an anemo-inertial loop including obtaining a computed horizontal speed, based on an integration of a measured horizontal acceleration and obtainment of a short-term anemo-inertial speed from the computed horizontal speed; developing at least one intermediate loop parameter based on a deviation between the short-term anemo-inertial speed and the anemometric speed or the airspeed; and observing a failure detection parameter obtained from an intermediate parameter of the anemo-inertial loop and determining the presence of a failure on one of the sensors of the aircraft, based on the value of the observed failure detection parameter.

Abstract: A radar apparatus includes a retrieval unit, an estimation unit, a calculation unit, and a determination unit. The retrieval unit retrieves a strong reflection object based on a signal strength which a frequency spectrum of a beat signal generated by mixing a transmission signal which is frequency-modulated and emitted and a reception signal which is formed in the transmission signal is reflected on a target indicates. The estimation unit estimates an estimation orientation which is an orientation of a target assumed to be present around the strong reflection object, based on a relative distance to the strong reflection object. The calculation unit calculates power which is the signal strength for the estimation orientation by generating an orientation spectrum in the estimation orientation based on a frequency component corresponding to the relative distance. The determination unit determines whether there is the target in the estimation orientation based on the power.

Abstract: A ground-based videometrics guiding method for aircraft landing or unmanned aerial vehicles recovery is provided. The method comprised the following steps: setting videos(1,2,3,4,5,6) near the landing area of the aircraft or unmanned aerial vehicles; real-time imaging the aircraft or unmanned aerial vehicles during their final approaches; and real-time measuring the trajectory, velocity, acceleration, post and other motion parameters of the aircraft or unmanned aerial vehicles by analyzing the video images and using videometrics technology, so as to provide guiding information for the aircraft landing or unmanned aerial vehicles recovery.

Abstract: Navigation aid method for determining, by an instruction giver, the path of an aircraft initially following a predetermined path in an approach phase and upon which are defined a safety altitude and an alarm limit, said aircraft including a navigation system of the INS/GNSS type including a satellite information receiver and at least one inertial unit producing position information, said method including determining a future path; estimating predicted protection radii on the future path are estimated, starting at the calculation time in the case of a critical situation, in terms of position information, which starts at the calculation time; calculating a limit time after which the predicted protection radius is greater than or equal to the alarm limit; and calculating a limit time after which the predicted protection radius is greater than or equal to the alarm limit.

Abstract: Methods and compositions for preventing opposing ILS systems on a single runway from becoming active at the same time. A physical interlock system employs a physical switch element that may activate a first ILS system or an opposing second ILS system, but is not capable of permitting, and may prevent, opposing ILS systems from being active simultaneously. Also included are methods for preventing opposing ILS systems on a single runway from becoming active, comprising the use of a physical switch preventing activating signals from being sent to opposing ILS systems at the same time.

Abstract: According to one aspect of the present invention, a radar system is provided which accurately measures the surface profile in a wide sector beneath and forward of a helicopter, to aid low level transit and landing in poor visibility. This uses an electronic beam synthesis technique to form multiple beams directed at the area of interest, each measuring the distance to the first reflected signal received by each beam. These distances represent the profile of the ground and any objects on the ground. A processor then compares the measured profile with the ideal ground profile for safe landing. If the deviations from straight and level exceed the specified requirement for safe landing, or if sufficient rotor clearance is not detected, then a warning is given to the operator. A display will show the measured ground profile highlighting the unsafe regions, allowing the operator to seek a safe region to land.

Abstract: A system for maneuvering an aircraft for operations in connection with a sea-going vessel, the vessel having a designated area for landings and sling-load operations. Each of the aircraft has a navigation unit (INU) comprising a GPS receiver and an inertial navigation unit. The INU's are updated by data from the GPS receivers and the data from the shipboard unit's GPS receiver and INU are transmitted to the aircraft. The aircraft performs RTK calculations to determine a vector to the shipboard GPS antennas and modifies the vector with data from the INU's.

Abstract: Methods and systems for visually organizing aviation or aeronautical charts with color emphasis and de-emphasis features selected by a user.

Abstract: Methods are provided for presenting procedure information for an airport on a display device onboard an aircraft. A method comprises displaying a map on a display device and displaying a briefing panel overlying a portion the map. The briefing panel includes a plurality of segments, wherein each segment is associated with a type of procedure information for the airport.

Abstract: A transponder, able to equip a cooperative target facing a Doppler radar, includes at least one receiving antenna able to receive a signal transmitted by said radar and a transmitting antenna able to retransmit a signal. The signal received by the receiving antenna is amplitude-modulated before being retransmitted by the transmitting antenna to produce a variation of the radar cross-section of the target, the variation triggering a frequency shift between the signal transmitted and the signal received by the radar comparable to a Doppler echo. The transponder applies notably to the field of radars, more particularly for collaborative systems also operating at low velocity or nil velocity. It applies for example to assisted take-off, landing and deck-landing of drones, in particular rotary-wing drones, as well as manned helicopters.

Abstract: A method for producing a sensor-supported, synthetic view for landing support of helicopters under brown-out or white-out conditions is provided. A virtual 3-D representation of the landing zone is continuously created from 3-D data of the intended landing zone recorded during the landing approach and a monitoring routine is available to ensure that no 3-D data that was produced under brown-out or white-out conditions is considered in the representation. As soon as the monitoring routine detects that 3-D data has been recorded under brown-out or white-out conditions, an additional radar sensor is activated to continuously produce distance and/or Doppler data of potential objects entering the landing zone, the objects being displayed to a pilot of the landing helicopter in the synthetic view.

Abstract: A method and a system for displaying an airport or runway moving map with traffic information on a display screen in the cockpit or flight deck of an aircraft. Symbology representing surface and near-surface aircraft and surface vehicle traffic and associated traffic data are filtered to prevent or limit clutter on the display screen. Traffic symbology is automatically and manually filtered to display only relevant traffic. Traffic data is selectively displayed and displayed as/when relevant or needed. The displayed traffic information may be derived from automatic dependent surveillance-broadcast, traffic information system-broadcast, automatic dependent surveillance-rebroadcast, traffic collision avoidance system or other source.

Abstract: A method and system for providing taxiway navigational information to a crewmember of an airplane taxiing at an airport. An airport taxiway navigation system (“ATNS”) that executes on an onboard computer system that displays a map of the taxiways of an airport, receives the name of each taxiway of the taxi route specified by the taxi clearance, and highlights the taxiways on a displayed map to provide a visual indication of the cleared taxi route for the crewmembers.