Abstract: Disclosed is a method, means for and computer program for enhancing range and azimuth resolution in a two-dimensional (2D) image generated by a frequency modulated continuous-wave (FMCW) radar for providing enhanced situational awareness in autonomous approach and landing guidance (AALG) system by forming and displaying a two-dimensional (2D) model of landing conditions from received range and azimuth real beam radar (RBR) signals by rendering one or more target locations and amplitudes in both range and azimuth, selecting a region of interest from the displayed 2D model to enhance the one or more target locations in the selected region of interest, selectively applying range and azimuth resolution enhancement using a first and second beamforming approach or applying azimuth only resolution enhancement by using just the second beamforming approach to obtain an one or more accurate target location estimations and combining the enhanced one or more target locations to render an enhanced 2D image.

Abstract: A pulse radar is provided with a filter for eliminating a transmission waveform interfered with an answering signal from a received waveform, and a harmonic detector or a phase delay detector for detecting arrival and end of the answering signal reflected on a target.

Abstract: The invention relates to a method for assisting the piloting of an aircraft in the vicinity of a landing or takeoff point, by: determining the locus of entry and/or exit points for a given approach and/or departure altitude that are not safe for reaching the landing and/or takeoff point; and presenting a diagram including said locus on a display device.

Abstract: A method, system and computer program is disclosed for reducing range and angular ambiguities in a target data matrix output from a real beam monopulse radar sensor within a single beam for use in terrain morphing applications employed by brownout take-off and landing aid systems. One or more range bins are calculated to selectively determine one or more range segments from one or more targets of interest. Range resolution enhancement processing is employed to the selectively determined one or more range segments to obtain a range of target scatter locations. A monopulse angle bin is estimated from the obtained range of target scatter locations and one or more control inputs. Elevation and azimuth angular binning is applied to the estimated monopulse angle bin to obtain a smaller coverage area among one or more possible target areas.

Abstract: Using a radar to detect a known target likely to be positioned at approximately a predetermined height close to other targets, these other targets also being positioned at approximately the predetermined height. A first phase of detecting the known target is carried out by performing an azimuth scan. When the known target has been detected at a certain distance Di at a certain azimuth angle ?az, a second detection phase is carried out at said azimuth angle ?az and at an elevation angle ?EL corresponding to that of an object situated at said distance Di at the predetermined height. The target is said to be detected if it is detected at the elevation angle ?EL at a distance D approximately equal to the distance Di.

Abstract: The present invention is a method for obtaining a localizer deviation and a glide slope deviation for an aircraft. The method may include directing electromagnetic signals from a weather radar system of an aircraft towards a runway. The method may further include receiving return signals in response to the directed signals. The method may further include, based on the received return signals, determining an azimuth angle for the aircraft relative to the runway, determining an elevation angle for the aircraft relative to the runway, and determining a range for the aircraft relative to the runway. The method may further include based on the azimuth angle, the elevation angle, and the range, calculating the localizer deviation and the glide slope deviation for the aircraft.

Abstract: A method of identifying a runway is disclosed. A first scan of an area of ground known to include a runway is performed. The first scan is accomplished using a weather radar system at a predetermined position. A first image is obtained from the first scan. The first image is stored in a memory. A second scan of an area of ground proposed to include the runway is performed. The second scan is accomplished using a weather radar system at what is believed to be the predetermined position. A second image is obtained from the second scan. The first image is retrieved from the memory. It is determined whether features in the first image correlate to features in the second image. A runway confirmation signal is sent to a pilot of the aircraft when there is a substantial certainty of correlation between the first and second images.

Abstract: An aircraft radar system includes a radar antenna and a processing device. The processing device receives returns from the radar antenna associated with the scan. The processing device uses the returns from the scan for use in both incursion detection and weather phenomenon detection. A method for using the returns from the scan for both incursion detection and weather phenomenon detection is also disclosed.

Abstract: The subject of the invention is a method of aiding the piloting of an aircraft (3), which is intended to aid the piloting of the aircraft during an autonomous approach to a landing runway (P) for the purpose of landing, said aircraft comprising at least one locating means (10, 12), wherein: a) an estimated instant of arrival of the aircraft on the runway is determined; b) a prediction of the performance of said locating means of the aircraft at least at this instant of arrival is determined; and c) on the basis of said performance of the locating means and of characteristics of said approach, at least one minimum decision height (Hmin) corresponding to this instant of arrival is determined, above which the aircraft is protected from the risks of collision with the environment when it is guided automatically onto an approach axis (A) corresponding to said approach. The invention also relates to a device for implementing this method.

Abstract: An apparatus for aligning an aircraft with an area on the ground is provided. The apparatus includes an aircraft having an on-board landing system, the on-board landing system configured to record an image of an area on the ground. The apparatus also includes a location marker on the area of the ground, and a stored image showing at least a portion of the area of the recorded image. The on-board landing system is configured to obtain information from the location marker and use the information to align the recorded image with the stored image.

Abstract: A method for landing an aircraft includes determining the aircraft's deviation from its approach path so as to define a first point of the aircraft's heading. A first straight line passing through the first point and through a second point defining the ground orientation of the approach path is displayed, by a head-up display, on a horizon line with a heading scale. The first straight line represents a ground plot of the approach path. A first assistance gate is displayed such that the first straight line passes through the first assistance gate when the aircraft is aligned on the approach path. A second straight line, parallel with the horizon line and passing through the first point, is displayed and represents a plot on the ground of the origin of the approach path. A second assistance gate is displayed under the horizon line and represents the slope of the approach path.

Abstract: A pulse radar is provided with a filter for eliminating a transmission waveform interfered with an answering signal from a received waveform, and a harmonic detector or a phase delay detector for detecting arrival and end of the answering signal reflected on a target.

Abstract: A method for guiding the approach and landing of an aircraft is provided. The method involves receiving navigation information from the aircraft, receiving navigation information from an aircraft carrier, integrating the navigation information from the aircraft with the navigation information from the aircraft carrier to determine a relative velocity and a relative position between the aircraft and the aircraft carrier, and propagating the relative velocity and the relative position forward in time for navigation purposes.

Abstract: An imaging system for a rotary aircraft having a millimeter wave imager with visible or infrared overlay. The system includes an active millimeter wave imaging system comprising a millimeter wave transmitter and a millimeter wave phased array receiver for producing millimeter wave images of a landing region, a second imaging system operating at visible or infrared wavelengths to produce visible or infrared images of the landing region, and a processor programmed with a see and remember algorithm for overlaying the visible or infrared images and the millimeter wave images and to save at least one good high-resolution visible or infrared image in case of a brownout event begins to obscuring the visible or infrared images wherein in case of the brownout event the millimeter wave images are overlaid on the at least one good visible or infrared image and not obscured visible or infrared images.

Abstract: A landing-control device is provided having a new structure for carrying out landing control of an aircraft. A detecting unit 10 detects at least a relative altitude from a landing surface to an aircraft. A parameter-generating unit 20 is constructed by a neural network having a feedback loop which receives a detection value detected by the detecting unit 10 and outputs a landing-control parameter of the aircraft, an output of a first node among plural nodes constituting the neural network being input to a second node different from the first node. A controlling unit 30 controls the aircraft based on the control parameter output from the parameter-generating unit 20.

Abstract: A method and system for providing a bearing from a vehicle to a transmitting station are described. The method includes accessing a database to obtain transmitter position information for the transmitter, obtaining vehicle position information based on a GPS signal, and generating the bearing from the vehicle to the station utilizing the transmitter position information and the vehicle position information. The system includes a database storing transmitter position information identifying a position of the transmitter, a GPS receiver obtaining vehicle position information identifying a current position of the vehicle based on a GPS signal, and a controller generating a bearing from the vehicle to the transmitter utilizing the transmitter position information and the vehicle position information.

Abstract: The subject of the invention is a method of aiding the piloting of an aircraft (3), which is intended to aid the piloting of the aircraft during an autonomous approach to a landing runway (P) for the purpose of landing, said aircraft comprising at least one locating means (10, 12), wherein: a) an estimated instant of arrival of the aircraft on the runway is determined; b) a prediction of the performance of said locating means of the aircraft at least at this instant of arrival is determined; and c) on the basis of said performance of the locating means and of characteristics of said approach, at least one minimum decision height (Hmin) corresponding to this instant of arrival is determined, above which the aircraft is protected from the risks of collision with the environment when it is guided automatically onto an approach axis (A) corresponding to said approach. The invention also relates to a device for implementing this method.

Abstract: Systems and methods for displaying ground obstructions on a visual display are disclosed. In an embodiment, a ground proximity warning system includes at least one aircraft sensor system operable to acquire aircraft data and a ground proximity warning computer coupled to the aircraft sensor system to process the aircraft data that generates ground proximity warning data corresponding to a sensed ground obstruction. An indicating system including a visual display device then presents an image of a visual symbol corresponding to the sensed ground obstruction. At least one of the computer and the visual display device is controllable to selectively display the visual symbol.

Abstract: The invention relates to a method of detecting obstacles on board an aircraft while in the vicinity (44) of a touchdown point (27, 42), the method comprising the following operations: selecting/determining a path (41) to be followed by the aircraft overflying the touchdown point; the aircraft overflying the touchdown point following the overflight path, and during the overflight recording signals/data delivered by an on-board rangefinder observing a portion of space extending below the aircraft; analyzing the rangefinder data to detect the presence of obstacles and to determine their positions in a terrestrial frame of reference, where appropriate to determine their dimensions; and recording the detected obstacle position data, and dimensions, if any, in a memory.

Abstract: An apparatus for detecting clutter blocks and an interference source for dynamically establishing a clutter map includes a clutter block detecting module accumulates a plurality of range cell data of each detecting area, and compares the accumulated value with a clutter block level to define the position of a clutter block; a interference source detecting module accumulates all range cell data in each radar beam area, and compares the accumulated value with an interference source reference level to detect whether any interference source exists; and a clutter map establishing module saves the clutter maps on different beam areas in three memory blocks. When one clutter map cell is extracted, the clutter map cells on different beam areas neighboring with the beam area saving extracted clutter map cell are also extracted. The largest value among the extracted clutter map cells is being a clutter threshold value of a detected target.

Abstract: An avionics system includes a display device that is viewable by a user of an aircraft and a processor in operable communication with the display device. The processor is configured to display a digital terrain having a digital landmark thereon on the display device, the digital terrain being representative of an actual terrain and the digital landmark being representative of an actual landmark on the actual terrain, and display a plurality of position indicators over the digital terrain such that a line extending through the plurality of position indicators intersects the digital landmark, the position indicators being a fixed digital terrain distance apart as measured over the digital terrain.

Abstract: A system for aiding the landing of an aircraft on a runway uses an angular vertical position of the aircraft and includes at least one landing aid radio. In a stand-alone manner, the position of the aircraft in latitude and longitude is determined, and the position of the threshold of the runway in latitude and longitude is determined. A computing unit corrects, on the basis of positions of the aircraft and of the threshold of the runway, the angular vertical position of the aircraft. The corrected angular vertical position is used to aid the landing of the aircraft.

Abstract: Stochastic models of aircraft flight paths and a method for deriving such models from recorded air traffic data. Each stochastic model involves identifying the flight plan for one or more aircraft; identifying important parameters from each flight plan, such as aircraft type, cruise altitude, and airspeed; optionally identifying flight plan amendments for each flight; representing each route of flight as a series of navigational fixes; representing at least one aircraft flight parameter probabilistically; modeling realistic differences in at least one dimension between each planned route of flight and the flight path as it might actually be flown; and communicating the modeled deviations or simulated flight paths to the user. At least one aircraft flight parameter is represented as a random variable with a particular statistical distribution, such as a normal (Gaussian), Laplacian, or logistic distribution; or with a more complex algorithm containing one or more random elements.

Abstract: The speed dependent variable display system for a computer-implemented moving-map vehicle display system includes a data conversion module for converting a vehicle speed input signal to a distance range value; and, an application module for utilizing the distance range value, vehicle position information, vehicle direction of movement information, and input geographical information to provide scaled output geographical information. The scaled output geographical information is utilized to provide a situational awareness display which is optimized in accordance with the vehicle's position, direction of movement and speed. A display apparatus receives the scaled output geographical information to provide an optimized situational awareness display for a moving-map vehicle display system.

Abstract: A monopulse precision landing or other land-based radar system uses an array antenna and a beamformer to produce sum, azimuth difference and elevation difference beams relative to the array. The rows and columns of the array are skewed relative to the horizontal for tending to reduce the effects of multipath propagation on altitude estimates. A coordinate converter converts target information from the skewed antenna coordinates to ordinary vertical and horizontal coordinates.

Abstract: A method and device for carrying out switchover on a radio frequency landing system of an aircraft between a first input of a radio frequency receiver, which input is connected to a first antenna disposed on a lower part of the aircraft and receives a first signal, and a second input of the radio frequency receiver, which input is connected to a second antenna disposed on an upper part of the aircraft and receives a second signal. On initialization, switchover occurs to the input whose signal exhibits the highest level. After the initialization phase, a first value of a parameter, in relation to the aircraft, and a second value of this same parameter, in relation to the runway, are determined. The difference between these first and second values is computed, and switchover occurs to one of the first and second inputs as a function of this difference.

Abstract: A method and system for visually guiding an aircraft in its landing approach to a runway having an approach area equipped with approach lights operable in off, low, medium, and high intensity states. The lights are communicated with a secondary side of a transformer, which has a primary side with low, medium, and high taps that correspond to the light states. Off, low, medium, and high lighting intensity requests correspond to the low, medium, and high states of the plurality of lights. AC power is switched between the transformer taps in response to a request for an increase in lighting intensity. Power is sequentially applied to the taps by supplying the power to the low tap for a first predetermined time interval before supplying the power to the medium tap.

Abstract: A method of increasing positional awareness of a pilot of an aircraft during a landing approach of the aircraft. First data from a navigational aid is received. The first data is analyzed to determine a first position of the aircraft at a predetermined time. Second data is received. The second data is independent of the first data. The second data is analyzed to determine a second position of the aircraft at the predetermined time. The first position of the aircraft and the second position of the aircraft are compared, and the pilot is alerted to a difference between the first position of the aircraft and the second position of the aircraft. The second data may be displayed in a form that is convenient for the pilot to view during landing.

Abstract: A method and device for determining a vertical position cue of an aircraft while landing in the presence of a lateral alignment beam, which is emitted from the ground and provides an indication of the aircraft's lateral alignment with respect to a landing strip, may include detecting the lateral alignment beam with aircraft equipment. On the basis of cues relating to the detected lateral alignment beam and of predetermined cues, an axis of approach of the aircraft is determined. Additionally, the actual position and a preset position of the aircraft, which corresponds to the position the aircraft would have if it were on the approach axis, are determined. On the basis of the actual and preset positions of the aircraft, the vertical deviation of the aircraft, representing the vertical position cue, is computed.

Abstract: A method of guiding an aircraft in the final approach phase including imaging the ground using an imaging system onboard the aircraft to obtain an image, analyzing the image to detect an airport area, detecting an airport area and selecting a runway for landing, tracking the selected runway during the approach of the aircraft by visually tracking the selected runway in the image supplied by the imaging system, and tracking the runway when the aircraft is very close to the ground by analyzing the image supplied by the imaging system to determine the position of the aircraft relative to the runway.

Abstract: The advantage of flexible multi-axis robot systems and robot cell-unit systems being further extended by providing electric and electronic E-POOL networks, consisting of multiblock individual computer units, central computers, board computers, satellite units, antenna units, open and contact protected under floor and upper floor current and communication supply lines.

Abstract: An airborne radar system is disclosed. The airborne radar system comprises a radar antenna, radar circuitry coupled to the radar antenna, and a runway database comprising runway location information. The airborne radar system also comprises a processing device retrieving from the runway database, runway location information for a runway being approached by an aircraft, based on the location of the aircraft, and directing a radar beam defined by a polygon which represents the runway and which is derived from the runway information, the processing device determining whether there are any obstacles on the runway.

Abstract: In order to provide a method for locating moving objects that will allow high precision in position determination and thus largely eliminate sorting errors, and also to provide a device suitable for executing the method, it is envisaged that on at least one defined location within the reading range of an interrogator (16) arranged in a stationary position, an interference pulse, which influences a response signal transmitted by a transponder (20) carried by a moving object (12) in response to a signal transmitted by the interrogator (16), is exerted on the object (12), and a position of the object (12) is determined in dependence on a time when the influence of the response signal occurred.

Abstract: Deriving inertial-aided deviations for autoland systems during GPS signal interruptions involving an inertial reference system and a GPS landing system can include converting position coordinates of an aircraft from the inertial reference system to runway, lateral, and vertical coordinates. After this conversion, the method calibrates runway distance and lateral distance based on the converted position coordinates from the inertial reference system using runway distance and lateral distance from the GPS landing system with a third-order calibration filter when the aircraft is below a first height above terrain and calibrates vertical distance based on the converted position coordinates from the inertial reference system using vertical distance from the GPS landing system with a second-order calibration filter when the aircraft is below the first height above terrain.

Abstract: The method allows switchover between a first input (5) of a radiofrequency receiver (4) of the radiofrequency landing system (1), which input is connected to a first antenna (2) disposed on a lower part of the aircraft and receives a first signal, and a second input (6) of the radiofrequency receiver (4), which input is connected to a second antenna (3) disposed on an upper part of the aircraft. On initialization, switchover occurs to the input (5, 6) whose signal exhibits the highest level, and, after the initialization phase, a first value of a parameter, in relation to the aircraft, and a second value of this same parameter, in relation to the runway, is determined, the difference between these first and second values is computed, and switchover occurs to one of the first and second inputs (5, 6), as a function of this difference, and, moreover, one hysteresis loop around the switching values is provided.

Abstract: A monopulse precision landing or other land-based radar system uses an array antenna and a beamformer to produce sum, azimuth difference and elevation difference beams relative to the array. The rows and columns of the array are skewed relative to the horizontal for tending to reduce the effects of multipath propagation on altitude estimates. A coordinate converter converts target information from the skewed antenna coordinates to ordinary vertical and horizontal coordinates.

Abstract: An airport display device including a display including at least one window, a database including data related to an airport, a selector configured to select a degree of zoom for the airport to be displayed from a plurality of different degrees of zoom, a control unit connected to the display, the database and the selector and configured to control the display to display in the at least one window the airport according to a scale value representative of the degree of zoom selected by the selector, and a changing unit configured to change the scale value representative of the degree of zoom.

Abstract: A method, avionics apparatus and computer program for determining a terminal flight path, including access to aircraft position information provided by a Global Positioning System (GPS) receiver. The method apparatus and computer program determine an Intended Touchdown Point (ITP), which is the desired landing location on an intended runway; determine a Current Touchdown Point (CTP), which is where the aircraft will land given its current glidepath and is a function of the current trajectory, configuration and engine thrust; determine a correspondence of the CTP and ITP and generate an output signal as a function of the correspondence, which is displayed on a cockpit display device, annunciated on a cockpit speaker, or both.

Abstract: A system and method for measuring and predicting information on the position of approaching aircraft are disclosed. The system features a processor, an interrogating antenna, a receiving antenna, and a data link. The processor schedules interrogations and suppression pulses. Both of the antennas and the data link are in signal communication with the processor. The interrogating antenna transmits interrogations to a plurality of approaching aircraft. At least some of the interrogations include suppression pulses. The receiving antenna comprises at least three fixed, broad azimuth, array elements. The receiving antenna receives replies from each of the plurality of approaching aircraft and communicates the replies to the processor. The processor determines a state for each of the plurality of approaching aircraft based on the replies. The data link communicates information on the state of each of the plurality of approaching aircraft from the processor.

Abstract: A millimeter wave beacon includes a millimeter wave transmitter that produces at least one signal and plurality of antennas, coupled to the millimeter wave transmitter, that each emit millimeter wave radiation in response to the at least one signal. In one embodiment, the antennas are constructed and oriented to produce an overlapping signal field in which millimeter wave radiation emitted from multiple of the antennas can be detected. The millimeter wave radiation can be pulsed to encode various information of interest. Determination of the direction of approach to the beacon is facilitated by multiple antennas transmitting signals having different pulse encodings and/or different frequencies.

Abstract: A computer generated pilot instruction system for providing spatial information to a pilot corresponding to the difference between the actual landing fight path and optimal landing flight path.

Abstract: An aircraft guidance system uses radar imaging to verify airport and runway location and provide navigation updates. The system is applicable to flight operations in low visibility conditions.

Abstract: A method and apparatus that permit military aircraft operators to use the civilian Aircraft Addressing and Reporting System (ACARS) technology while ensuring data security.

Abstract: A computer generated pilot instruction system for providing spatial information to a pilot corresponding to the difference between the actual landing fight path and optimal landing flight path.

Abstract: In an aircraft flight information display system, a viewing surface of the display presents an observer with a view of the flight space forward of the aircraft. The viewing surface includes a section displaying a translucent plane of flight of the aircraft along its lateral axis having as an upper bound a line transverse to the lateral axis. The portion of the flight space upward of the plane of flight of the aircraft is displayed as a second section of the flight space above the line. Information of the features of terrain in the flight space, flight parameters of the aircraft and TCAS information is processed to form images of the terrain and traffic in relation to the translucent plane of flight of the aircraft. Terrain and traffic features are rendered in different colors according to their location with respect to the plane of flight. A series of ring-like indicia are displayed in the translucent plane to indicate the distance ranges in the plane of flight of the aircraft.

Abstract: The present invention is a method of deriving a ground speed of an aircraft on a descent along a flight path. A vertical speed signal is produced as a function of an altitude signal and a vertical acceleration signal. The vertical speed signal is transformed to a nominal ground speed signal based upon a glide slope defined by a glide slope beam. A correction is produced based on a glide slope deviation rate representative of deviation of the aircraft from the glide slope. The nominal ground speed signal is corrected with the correction to produce a corrected ground speed signal. The corrected ground speed signal is filtered with a horizontal acceleration signal and a runway heading signal to produce a smoothed ground speed signal.

Abstract: A ground-based, precision aircraft landing system provides CAT I precision approach and landing guidance. The aircraft elevation position is determined by measuring differential carrier phase and time-of-arrival of the aircraft ATCRBS transponder reply. The transponder reply is received at a plurality of sensor antenna locations where it is then conveyed to a sensor, demodulated and digitized. The data is transmitted to a central processor where calibration and multipath corrections are applied. Aircraft transponder diversity antenna switching is isolated from the jitter and colored noise of transponder reply multipath by correlating differential phase jumps measured between separate sensor antennas. An estimate of the diversity antenna separation is maintained by Kalman filter processing; the estimated separation is used to correct the differential phase measurement data of aircraft elevation.

Abstract: The invention deals with a surveillance system for terrestrial navigational and landing systems, in which the navigational signals being transmitted for aeroplanes or other airborne objects by the navigational and airport landing systems are received and evaluated by a ground-based receiving and control facility. In this system: the receiving and control facility is equipped with a plurality of additional receiving stations; these additional receiving stations operate in the frequency range of the navigational signals; the additional receiving stations are arranged geographically distributed within the transmitting range of the navigational or airport landing system; the signals recorded by the additional receiving stations are forwarded to a central evaluating unit.

Abstract: An aircraft guidance system uses radar imaging to verify airport and runway location and provide navigation updates. The system is applicable to flight operations in low visibility conditions.

Abstract: The system and method of the present invention provides a record of the performance of an aircraft engine. A plurality of sensors sense engine conditions and generate engine data. A ground data link unit is positioned within the aircraft and receives the engine data and stores the engine data within an archival data store. A wideband spread spectrum transmitter that can be part of a transceiver downloads the engine data to a ground based spread spectrum receiver that can be part of a transceiver, and receives the wideband spread spectrum communication signal from the aircraft. It demodulates the wideband spread spectrum communication signal to obtain the engine data.