Abstract: The present invention includes a method for identifying a facility on the ground or at sea, the method being implemented on an airborne responder linked to at least two antennas, the method including a step of choosing a first transmission antenna and a step of transmitting an interrogation message from the chosen antenna. The method further includes testing whether a response has been received by the responder, and, if at least one response signal is received by at least one of the antennas, choosing a transmission antenna as a function of the response signal or signals received. If no response message is received, a different transmission antenna is chosen from the antenna that transmitted the last interrogation message. The method is repeated from the step of transmitting the interrogation message.

Abstract: A method for validating received positional data in vehicle surveillance applications wherein vehicles transmit positional data indicating their own position to surrounding vehicles. A a radio direction finding antenna arrangement of a receiving unit receives a signal carrying positional data indicating an alleged position of a vehicle, transmitted from a radio source. The bearing from the receiving unit to the radio source is estimated utilizing the radio direction finding antenna arrangement and the received signal. The distance between the receiving unit and the radio source is estimated based on the time of flight for a signal travelling there between at known speed. An estimated position of the radio source is calculated based on the estimated bearing and the estimated distance. A deviation value indicating the deviation/coincidence between the alleged position of a vehicle is determined according to the received positional data and the estimated position of the radio source.

Abstract: An apparatus and method to generate and detect virtual targets. Position information for one or more virtual targets is calculated onboard a vehicle from real position information obtained from GPS satellites or other external or internal sources. This virtual position information is coded, mixed with a carrier frequency, amplified, and radiated to a nearby test vehicle, such as an aircraft. The amplitude of the radiated signal is adjusted such that the signal containing the virtual position information is received by the test aircraft only. The radiated signal thus adjusted is below the detection threshold of any aircraft further away. The test aircraft decodes the signal and interprets the decoded virtual position information as real aircraft in its vicinity. The coded signals may be structured to comply with the requirements of the FAA's ADS-B system. The apparatus may be mounted on the test aircraft itself, or on a nearby aircraft.

Abstract: Systems and methods for creating a narrow vertical pathway of detection that permits the enforcement of a fixed “exclusion zone” that is narrow and does not widen with range. An advantage to this approach is that the zone or corridor does not widen with range, permitting a fixed exclusion zone that will ignore items that will pass above or below the wing. An exemplary system located on a vehicle includes at least two vertically separated antennas that receive radar reflection signals, a processor, and an output device. The processor receives the radar reflection signals received by the antennas, determines vertical position of any obstacles identified in the radar reflection signals and determines if the obstacles are within a predefined alert zone. The output device outputs an alert if any obstacle is within the alert zone. The predefined alert zone is related to a protruding portion of the vehicle.

Abstract: Systems and methods for providing improved situational awareness for an aircraft while taxiing. An exemplary method generates reflectivity data based on an associated emission at a transceiver located on an aircraft. At a processor, targets are determined if a portion of the generated reflectivity data is greater than a predefined threshold. Then, the analyzed targets are determined as to whether they are within a dynamically defined three-dimensional envelope. The envelope is based on wingtip light module speed and trajectory. On a display device, an indication of the nearest target is presented at the associated range to the nearest target.

Abstract: A ground crew collision-avoidance system includes a plurality of radar sensor modules that each emit a radar signal, receives at a radar detector radar return signals corresponding to reflections of the emitted signal from a ground object, and transmits radar information associated with the received radar signal reflections reflected from the ground object, wherein each of the plurality of radar sensor modules are uniquely located on a surface of an aircraft that is at risk for collision with a ground object while the aircraft is being towed; a gateway unit that receives the radar information transmitted from the radar sensor module and transmits information associated with the received radar information; and a ground crew alert indicator that receives the information transmitted by the gateway unit and that presents a graphical alert icon on a display. The display indicates a likelihood of collision between the aircraft and the ground object.

Abstract: In embodiments a system to generate a dual frequency, circularly polarized beam of rotating electromagnetic radiation comprises a first radiation source to generate a first radiation beam at a first frequency, a second radiation source to generate a second radiation beam at a second frequency, different from the first frequency, and a tee. In some embodiments the tee receives the first radiation beam and the second radiation beam, outputs a third radiation beam which represents a sum of the first radiation beam and the second radiation beam, and outputs a fourth radiation beam which represents a difference between the first radiation beam and the second radiation beam, wherein the third radiation beam and the fourth radiation beam are separated by a ninety-degree phase shift. The system further comprises a combiner to combine the third and fourth beams to produce an output beam. Other embodiments may be described.

Abstract: A multifunction airborne radar device includes a plurality of transmit antenna modules and/or receive antenna modules that are fixed relative to the aircraft, placed substantially over the surface of the aircraft so as to form transmit and receive beams, enabling targets to be detected for implementing a sense-and-avoid function. The airborne radar device may also comprise processing means for tracking the detected targets and for generating information sent to an air traffic control center and/or to a control device on board the aircraft. The processing device may also receive data relating to the aircraft, enabling the antenna beams to be adjusted and the tracking calculations to be refined.

Abstract: A non-scanning radar system is installed on an aircraft to detect and avoid bird strikes or collisions with other airborne hazards. Target amplitude, range, and Doppler tracking versus time are used to qualify the collision threat. Avoidance is based on a quick minor altitude change by the pilot or autopilot to exit the imminent bird or other airborne hazard altitude window. In one embodiment, a bistatic passive radar receiver antenna is used in conjunction with an existing geostationary satellite signal. Range and Doppler information are obtained via cross correlation processing of the hazard reflection signal with a direct path reference signal from the satellite.

Abstract: A proximity warning system for a helicopter (22) comprising at least two radar units (1-3), preferably three radar units (1-3) arranged to transmit microwaves and receive reflections of said microwaves from obstacles (10). The at least two radar units (1-3) are fixed next to a main rotor head(s) (20) of the helicopter (22) for horizontally scanning an entire environment of 360° around the helicopter (22), all of said at least two radar units (1-3) operating essentially at the same frequency.

Abstract: Methods and apparatus are provided for transmitting incursion alerts to a plurality of in-flight aircraft in accordance with preconfigured pilot preferences. The apparatus comprises a data store module containing data sets against which the pilot preferences are evaluated during flight, including weather, airspace and flight restrictions, ground delay programs, and air traffic information. The apparatus further includes a flight path module containing route and position information for each aircraft. An incursion alert processing module evaluates the flight path, data store, and pilot preferences and generates incursion alerts which are transmitted to each aircraft during flight, either directly or via ground based dispatchers or flight operations personnel.

Abstract: A vehicle can be controlled in a first autonomous mode of operation by at least navigating the vehicle based on map data. Sensor data can be obtained using one or more sensors of the vehicle. The sensor data can be indicative of an environment of the vehicle. An inadequacy in the map data can be detected by at least comparing the map data to the sensor data. In response to detecting the inadequacy in the map data, the vehicle can be controlled in a second autonomous mode of operation and a user can be prompted to switch to a manual mode of operation. The vehicle can be controlled in the second autonomous mode of operation by at least obtaining additional sensor data using the one or more sensors of the vehicle and navigating the vehicle based on the additional sensor data.

Abstract: A device and method aids the evaluation of a flight trajectory that is intended to be followed by an aircraft within a constrained environment. The method includes receiving information from a processing unit regarding stationary and moving obstacles, implementing a collision trial based on this information, and displaying any collision risks to the pilot on a display device in the cockpit. Consequently, a pilot can know within the constrained environment whether a flight trajectory needs to be modified to avoid potential collisions.

Abstract: Embodiments for displaying first and second images to a pilot of an aircraft are presented. The embodiments include, but are not limited to, obtaining a first image signal and a second image signal, commanding a display unit to display a first image on a display screen corresponding to the first signal, and computing an image moving velocity of the first image. The method further comprises estimating an image flow velocity for the second image based on the second image signal and comparing the image moving velocity of the first image to the image flow velocity of the second image. After the comparison, the display unit is commanded to display the second image overlaid on the first image, and commanding the display unit to establish an intensity of the second image within a predefined range based upon the comparison.

Abstract: A system and device is provided for formulating alerts of the items of equipment of an aircraft. The device includes a database of virtual objects representing the items of equipment for constructing a virtual model representative on the one hand of the topological configuration of the network of items of equipment and on the other hand of the configuration of the chain of functional applications implemented by the items of equipment, means for each virtual object to formulate a request for consulting the status of the functional application carried out by the item of equipment associated with the object and means for detecting alerts for formulating requests for consulting the status of each of the objects of the virtual model so as to detect anomalies of configuration of the topology of the network of items of equipment and of the chain of functional applications of the virtual model and to transmit the alerts associated with the anomalies. The device detects and manages the alerts of an aircraft.

Abstract: A obstacle detection system comprises a transmission antenna operable to radiate a radio frequency (RF) signal and a transmitter operable to control transmission of the RF signal from the antenna. The obstacle detection system also comprises a receiver antenna operable to receive a reflection of the RF signal; and processing circuitry operable to analyze a plurality of characteristics of a radar cross section (RCS) of the received reflection to identify an obstacle and one or more physical attributes of the obstacle.

Abstract: According to the invention, the device (1) comprises means (3) for detecting, during an altitude capture maneuver, the emission of a first type alarm by the anti-collision system (2) and means (4) for controlling the vertical speed of said airplane (AC), after the emission of such an alarm, until the triggering of the capture phase.

Abstract: A novel and non-trivial radar-based system, module, and method for presenting steering symbology on an aircraft display unit are disclosed. Hazard information acquired from a forward-looking aircraft radar system may be presented as hazard data to a symbology generating processor. A plurality of minimum turn angles may be determined based upon the boundary tangents of the hazard data. Data representative of steering symbology corresponding to a one or more minimum turn angles may be generated, where the symbology may take the form of textual symbology and/or non-textual symbology. Then, the steering symbology data may be provided to a presentation system for depiction of steering symbology on a tactical display unit and/or strategic display unit.

Abstract: Methods for flying multiple aircraft in a predetermined formation in which a relative navigation grid is emitted from at least one of the aircraft, a spatial relationship is calculated based on the emitted relative navigation grid, and a relative position of at least one aircraft is altered to position the aircraft in the predetermined formation when the spatial relationship does not conform with the predetermined formation.

Abstract: A device and method for secondary radar signal reception with quasi-dynamic or dynamic sectoring of a space to be monitored. The device includes at least one antenna assembly including antenna elements for the reception of transmitted secondary radar signals, a signal processing unit connected via a connection point to the antenna elements for the joint processing of received antenna signals, outputs associated with a couple matrix in the signal processing unit and individual receivers. The couple matrix includes adjustable coefficients for sectoring of the space to be monitored and for performing a superposition of the antenna signals using a multiplicative-additive combination of the received antenna signals. In the case of dynamic sectoring of the space, each receiver receives for each receipt telegram another weighted superposition of the antenna signals with certain couple coefficients, and in the case of quasi-dynamic sectoring the adjustable coefficients are fixed over a longer time period.

Abstract: An aircraft position synchronization system and methods for coordinating positioning of vehicles in motion are presented. A rabbit calculation module calculates a planned position on an orbit pattern of an aircraft in flight, and a planned position-time projection vector comprising a planned velocity vector of the planned position. A display module graphically displays the orbit pattern, the planned position and the planned velocity vector of the planned position moving in real-time along the orbit pattern. The display module further displays the planned position-time projection vector, an actual position of the aircraft, and an actual position-time projection vector of the aircraft based on a bank angle of the aircraft such that a user determines the planned position on the planned position-time projection vector of the aircraft in order to arrive at a predetermined position at a correct time. A rendezvous module coordinates the aircraft with a second aircraft in flight.

Abstract: A bistatic radar receiver is centrally located within an array of multiple bistatic transmitters at an airport to precisely determine bird positions and altitudes. Bird target reflections from multiple transmitters are received by the radar receiver. Target location is determined by the transmitter location, receiver location, and measured transmitter-to-target-to-receiver ranges. Target position and altitude accuracy is similar to GPS. The radar receiver antenna is composed of a vertical array of elements and rotated 360 degrees in azimuth. The output of each element is downconverted, digitized, and digitally beamformed to provide multiple simultaneous antenna beams each electronically scanned in elevation. When bistatic transmitters cannot be deployed, a narrow-azimuth wide-elevation transmit antenna beam is overlapped with a wide-azimuth narrow-elevation receive antenna beam electronically scanned in elevation to provide a composite narrow azimuth and elevation beamwidth.

Abstract: According to the invention, the device (1) comprises means (4) for adapting the altitude capture maneuver, means (5) for first detecting the emission of a first type alarm, means (6) for determining a first alarm threshold and means (7) for establishing an activation height threshold from said first alarm threshold and airplane vertical speed at the time of the alarm emission, so that, when the height separating said aircraft (AC) from the altitude set level is strictly higher than said height threshold at the time of the alarm emission, said adaptation means (4) are disabled.

Abstract: The invention is a method making it possible to calculate and monitor the provisional landing distance and the configuration of the aircraft and flight parameters during the changes in the landing phase manoeuvre. The method consists in determining the landing runway then in analyzing the configuration and the dynamic parameters of the aeroplane, the meteorological and airport data in order to assess, from a performance database, whether the planned braking is suitable and will stop the aeroplane before the end of the runway.

Abstract: In an embodiment, a coordinate determiner is operable to identify at least first and second surfaces that each approximately intersect an object, and to determine at least two approximate coordinates of the object from the first and second surfaces, where at least one of the surfaces is nonplanar. For example, if the coordinate determiner is disposed on a fighter jet having at least two short-baseline-interferometers (SBIs), then two surfaces may be the surfaces of two cones having two of the SBIs as respective vertices, the object may be a close-in target, and the coordinate determiner may determine the azimuth and elevation of the target from the cone surfaces. Furthermore, the coordinate determiner or another computation unit onboard the jet may determine the slant range of the target from the elevation and the altitude of the jet.

Abstract: A system and methods for onboard sense and avoidance of an object are disclosed. At least one transmitter and at least one transmitter location of the at least one transmitter are selected from a database of transmitters based on a vehicle location of a vehicle, and at least one total signal is received at the vehicle. The at least one total signal comprises a direct signal of at least one broadcast signal from the at least one transmitter, and a reflection signal comprising a reflection of the broadcast signal reflected off an object. An estimated object location of the object is estimated based on the at least one total signal, the at least one transmitter location, and the vehicle location.

Abstract: A radar device includes an antenna having at least two linear arrays of radiating elements being orthogonal to one another, a first array being used to focus a transmission beam in a first plane and a second beam being used to focus a reception beam in a second plane, orthogonal to the first plane. The focussing of the beam is obtained in the first plane by colored emission followed by a reception beam formation by computation, and in that the focussing of the beam is obtained in the second plane using reception beam formation by computation. The colored emission is carried out by combining antenna transmission sub-arrays in such a manner as to form a sum channel and a difference on reception channel according to the monopulse technique.

Abstract: An air traffic control system, for use by a human controller controlling a plurality of aircraft held vertically separated in a stack above a minimum stack level, the system comprising at least one processor, and a display device for the human controller, controlled by said at least one processor; further comprising: means for periodically inputting a value representative of local terrestrial air pressure conditions; means for periodically inputting an aircraft flight level reading representing an altitude defined by a reference air pressure measured on the aircraft; means for periodically generating a display on said display device comprising a plurality of flight levels vertically arranged; means for indicating in said display said plurality of aircraft, arranged in a vertical list ranked by flight level; said at least one processor being arranged, on reception of a new said value, to redetermine said minimum stack level and to vary said display so as to indicate changes to said minimum stack level.

Abstract: A process and a device for detecting aircrafts circulating in an air space surrounding an airplane is disclosed. The device (1A) comprises means (2, 3) for detecting an aircraft circulating in the air space surrounding the airplane and, in case of a detection, for determining a first position and a second position of the aircraft with respect to the airplane, and means (8A) for comparing said first and second positions so as to check whether they match.

Abstract: Systems and methods for providing vehicle-centric collision avoidance are disclosed. In one embodiment, a method includes determining a first flight trajectory for a first aircraft. The method also includes determining a second flight trajectory for a second aircraft. A distance between the first aircraft and the second aircraft at a first closest point of approach (CPA) is predicted. The predicted closest point of approach is then compared to a separation perimeter layer. The separation perimeter layer is configured to provide a minimum separation distance from the first aircraft to the second aircraft. When the predicted closest point of approach breaches the separation perimeter, the first flight trajectory is altered to provide collision avoidance.

Abstract: A surveillance and guidance method and system for use with autonomously guided, man-on-the-loop or man-in-the-loop guided vehicles where the presence of obstacles must be considered in guiding the vehicle towards a target includes a navigation system configured to determine the position of the vehicle on which it is equipped. A communication system is configured for data exchange between the vehicle, neighboring vehicles and ground stations. A surveillance system is configured to detect and locate fixed or moving targets and obstacles. A computer is configured to track the position of targets and obstacles and to provide guidance commands or 4D flight paths to perform collision avoidance with respect to traffic regulations and procedures, and operational airspace restrictions. Additional computer tasks include station keeping or interception of targets. A command and control system is configured to interact with a user interface and control the vehicle's actuators.

Abstract: Autonomous collision avoidance systems for unmanned aerial vehicles are disclosed. Systems illustratively include a detect and track module, an inertial navigation system, and an auto avoidance module. The detect and track module senses a potential object of collision and generates a moving object track for the potential object of collision. The inertial navigation system provides information indicative of a position and a velocity of the unmanned aerial vehicle. The auto avoidance module receives the moving object track for the potential object of collision and the information indicative of the position and the velocity of the unmanned aerial vehicle. The auto avoidance module utilizes the information to generate a guidance maneuver that facilitates the unmanned aerial vehicle avoiding the potential object of collision.

Abstract: Device and a method for locating a mobile object approaching a surface reflecting electromagnetic waves. The location device includes an emission antenna and a reception antenna. The emission antenna has one or more emission positions emitting a detection signal toward the mobile object. The reception antenna has at least one column of one or more reception positions, receiving a signal transmitted by the mobile object. An emission of the detection signal is activated on each emission position. An emission position that produces a detection by the reception antenna, of the signal of maximum energy transmitted by the mobile object, is selected to track the mobile object. One or more signals of maximum energy, received by one or more reception positions, are used to angularly locate the mobile object. The invention can be used to determine the position of an aircraft in the final landing phase for a guidance device.

Abstract: A telematics system in an asset network is provided. The telematics system includes one or more sensors configured to acquire data from multiple assets at different locations in the asset network. The telematics system also includes a transceiver configured to receive the data acquired from the one or more sensors. The telematics system further includes a data analysis system. The data analysis system includes a central data server configured to receive the data transmitted from the transceiver. The data analysis system also includes a processing circuitry configured to combine data, analyze combined data to detect trends, generate value added services based on the detected trends and distribute the value added services to multiple end users.

Abstract: A computer-implemented transportation information management system and method permits entry, recording, and transmission of operation and maintenance data related to FAA recordkeeping and recording requirements within an SQL database. A secure website permits entry and display of operation and maintenance data as well as facilitating data input using input devices such as a cellular telephone, a personal digital assistant, a personal computer, and a portable computer. The system outputs aircraft operation and maintenance data, automatic alerts of pilot flight and duty time limitations, and flight tracking and monitoring information via a spreadsheet, electronic mail message, text message, and a completed FAA mandatory reporting requirement forms to the aforementioned data input devices. Operation and maintenance data is automatically and continuously transferred to the FAA to populate FAA flight tracking data systems and air traffic control data system.

Abstract: The invention relates to a method of processing an image sensed by an image sensor on board an aircraft fitted with an obstacle-locator system, in which the position and the extent of a zone in the sensed image, referred to as the zone of interest, is determined as a function of obstacle location data delivered by the obstacle-locator system, after which at least one parameter for modifying the brightness of points/pixels in said zone of interest is determined to enable the contrast to be increased in said zone of interest, and as a function of said modification parameter, the brightness of at least a portion of the image is modified.

Abstract: An aircraft avian radar is implemented using multiple axial beam antennas mounted on an aircraft. Target range is determined by radar range. Target azimuth and elevation position is determined by triangulation. An end-fire array antenna composed of a series of monopole antenna elements enclosed inside a long thin protective cover fashioned in the form of a stall fence is mounted on the wings, tail, or fuselage to produce a low drag axial beam antenna pattern directed ahead of the aircraft. Other axial beam antenna choices include helical, pyramidal horn, and conical horn antennas mounted on or inside various forward facing surfaces of the aircraft.

Abstract: Embodiments of a process are provided suitable for implementation by an avionics display system deployed on a host aircraft and including a monitor. In one embodiment, the process includes the step of receiving air traffic data indicative of a first flight characteristic pertaining to a neighboring aircraft. The first flight characteristic is selected from the group consisting of: (i) the wake turbulence created by the neighboring aircraft, (ii) the current flight plan of the neighboring aircraft, and (iii) the airspace in which the neighboring aircraft's current detection position should reside to ensure that the neighboring aircraft's actual position resides within the an airspace currently assigned to the neighboring aircraft. A visual representation of the first flight characteristic is generated on the monitor.

Abstract: A method for registering a radar system. The method includes obtaining first values for a location of a target relative to the radar system using radar system initiated signals, obtaining geo-referenced location data for and from the target, obtaining second values for the location of the target relative to the radar system using the geo-referenced location data, computing location registration bias errors for the radar system using the first and second values, and registering the radar system using the computed location registration bias errors.

Abstract: A method and apparatus for searching and generating trajectory content in a navigation device are provided. The method includes establishing a predetermined search region from a current position; extracting information about first parcels included in the established search region and information about second parcels including information about links of specific trajectory content; and determining whether the specific trajectory content is included in the established search region by comparing the information about the first parcels with the information about the second parcels.

Abstract: A method and a navigation device are disclosed for sharing at least one location message with at least one other device. The navigation device includes a receiver to determine a signal strength of a traffic message channel at a location, a memory to store information representing the signal strength of a traffic message channel, and at least one processor to correlate the information stored in memory to compile a traffic message channel resource and select a traffic message channel based on the traffic message channel resource and a location associated with a navigation device. The method includes determining a signal strength of a traffic message channel at a location, storing information representing the signal strength of a traffic message channel, correlating the information stored in memory to compile a traffic message channel resource, and selecting a traffic message channel based on the traffic message channel resource and a location associated with a navigation device.

Abstract: The invention relates to a method and device to assist in navigation in an airport sector. The inventive method and device make it possible to automatically calculate the points of intersection between the path of the flight plan and the zones having speed limitations all around an airport and calculate a speed profile conforming to these limitations. The inventive method and device also make it possible to use an automatic guidance automatically defining flight instructions corresponding to the calculated speed profile. Furthermore, the invention calculates predictions concerning the flight parameters.

Abstract: Systems and methods for predicting when a weather anomaly (e.g., convective cell) will intersect with an aircraft. Direction of movement and velocity information for at least one weather anomaly are received at a processor from a radar system. An intercept point for the at least one weather anomaly is determined based on the received location, direction of movement and velocity information and location and current speed information for the aircraft. Then, a first indicator based on the intercept point is displayed on a display device.

Abstract: A rotary wing aircraft, a rotor blade and a horizon scanning system are provided. The rotary wing aircraft, for example, may include, but is not limited to, a mast, an engine configured to provide rotational force to the mast and a controller. The rotary wing aircraft may further include a rotor blade connected to the mast having a leading edge, a plurality of tubercles positioned on the leading edge of the rotor blade, and a sensor housed within at least one of the plurality tubercles communicatively connected to the controller.

Abstract: Processing is described for forming a synthetic aperture radar image of the region toward which a platform moves, and for extracting from this image the physical positions of scatterers in the region, including moving scatterers. The processing entails one-dimensional resampling of the received radar data that can be performed as the data are being collected, facilitating real-time operation. Various embodiments are disclosed.

Abstract: Accurate measurements of flight path obstructions are taken from a moving aerial platform. Platform position, including altitude, is combined with dynamic data including target distance and target elevation data to calculate obstruction height or altitude. An optical subsystem on the aerial platform images the obstructions and provides a video stream showing the obstructions. The video stream and aerial platform data are wirelessly communicated to a control terminal where an operator observes a presentation of obstructions and obstruction altitudes or heights. The operator can issue commands to the aerial platform.

Abstract: The invention relates to a method and device for limiting the number of alarms generated by an anticollision system on board an airplane according to which the duration of a phase of capture of a setpoint altitude by the airplane is adjusted so that a theoretical time for collision with an intruder aircraft is greater than a predetermined threshold, when the airplane is close to said setpoint altitude and air traffic exists in the environment of said airplane.

Abstract: The general field of the invention is that of viewing systems of the synthetic vision type SVS, for a first aircraft, the said system comprising at least one cartographic database of a terrain, position sensors, for the said aircraft, an air traffic detection system calculating the position and the danger rating of at least one second aircraft exhibiting a risk of collision with the said first aircraft on the basis of data originating from sensors or systems such as TCAS or ADS-B, an electronic computer, a man-machine interface means and a display screen, the computer comprising means for processing the various items of information originating from the database, sensors and interface means, the said processing means arranged so as to provide the display screen with a synthetic image of the terrain comprising a representation of the said second aircraft.

Abstract: The invention relates to the field of monitoring and aid to taxiing of an aircraft at an airport. The invention is a method of checking and monitoring the taxi plan and relates to a monitoring system comprising means for checking the pathway of the plan and means for signalling on the taxi aid the waiting time for the next clearance ahead of the aircraft along the pathway, the means for checking the pathway comprising a device for checking the pathway constraints and a device for checking the clearances, the device for checking the constraints making it possible to test and to display on the taxi plan the information descriptive of the constraints and the device for checking the clearances making it possible to check the clearances and to add the missing clearances to the taxi plan.

Abstract: A radioaltimeter (5) having a signal generator-receiver (10) and signal transceiver means (20) connected to the generator-receiver (10), and a display member (30), said transceiver means (20) comprising a transceiver main member (21) for sending a signal towards a ground (S) in order to determine the height (H) between said main member (21) and said ground (S), said display member (30) having main display means (31) for displaying said height (H). Furthermore, the radioaltimeter (5) includes switch means (40) together with a control unit (50), and secondary display means (32) of said display member (30).