Class / Patent application number | Description | Number of patent applications / Date published |
701017000 | I.L.S. or radar guidance | 25 |
20090055038 | AUTONOMOUS AND AUTOMATIC LANDING SYSTEM FOR DRONES - The invention relates to an automatic aircraft landing guidance system having an electromagnetic detecting and locating device, positioned on the ground and a first multifunction transmitting/receiving radiofrequency beacon, on board each guided aircraft and transmitting in particular a continuous wave. The detecting and locating device uses the continuous wave transmitted by the beacon to perform a passive locating intended to improve the accuracy of the measurement of the angular position of the aircraft. It also comprises means for generating and periodically transmitting to the aircraft, via the beacon, information enabling said aircraft to rejoin an optimum landing path from its position. The invention applies more particularly to the guidance of autonomous and automatic aircraft such as drones in the approach and landing phase. | 02-26-2009 |
20100017053 | Consistent Localizer Captures - Systems and methods for performing localizer capture maneuvers are disclosed. In one embodiment, a method includes determining at least one instrument landing system (ILS) threshold of an aircraft, and establishing at least one final approach course (FAC) deviation threshold for the aircraft. The method further includes receiving at least one ILS localizer error, then calculating at least one FAC deviation. The at least one ILS localizer error is compared to the ILS threshold, and the at least one FAC deviation is compared to the FAC threshold. A standard capture maneuver is performed if the at least one ILS localizer error reaches its corresponding ILS threshold prior to the at least one FAC deviation reaching its FAC threshold. However, if the at least one FAC deviation reaches its corresponding FAC threshold prior to the at least one ILS localizer error reaching its corresponding ILS threshold, a modified capture maneuver is performed. | 01-21-2010 |
20100286852 | METHOD FOR AIRCRAFT LANDING ASSISTANCE USING GPS AND MLS IN CASE OF CALCULATED AXIAL APPROACH - In a method for aiding aircraft landing using a GPS and an MLS within the context of a computed axial approach, the method uses coordinates of an azimuth antenna and/or of an elevation antenna as a reference point for the computation of a position of the aircraft in a reference frame centered on the landing runway. This position of the aircraft is thereafter used to determine an angle of azimuth between a longitudinal axis of the landing runway and the aircraft. | 11-11-2010 |
20110106345 | LOW VISIBILITY LANDING SYSTEM - Examples of the present invention may include a low visibility landing system for guiding aircraft on landing approaches. The low visibility landing system may aid a pilot during landing in low visibility conditions such that an aircraft may descend to lower altitudes without visual contact with the runway than is possible with other landing systems. The system may use various navigational systems to produce a hybrid signal that may be more stable than individual signals of those navigational systems. The hybrid signal is compared to a predetermined landing approach plan to determine the deviation of the aircraft from the landing approach plan and to provide guidance to the pilot to get the aircraft back onto the landing approach plan. The system may also use multiple navigational systems to perform checks on an operation of a primary navigational system to ensure that the primary navigational system is operating accurately. | 05-05-2011 |
20110160941 | Broadband Multifunction Airborne Radar Device with a Wide Angular Coverage for Detection and Tracking, Notably for a Sense-and-Avoid Function - 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 centre 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. | 06-30-2011 |
20110231038 | AIRCRAFT LANDING SYSTEM USING RELATIVE GNSS - A method for confirming mobile base station integrity in a relative GNSS aircraft landing system, the method comprising: determining a relative position of a first GNSS antenna fixed to the mobile base station with respect to a second GNSS antenna also fixed to the mobile base station by processing signals from a GNSS satellite constellation; calculating a distance between the first GNSS antenna and the second GNSS antenna using the measured relative position; comparing a calculated distance to a known fixed distance; and confirming mobile base station integrity if the calculated distance is within a predetermined threshold of the known fixed distance. | 09-22-2011 |
20120065817 | LOW VISIBILITY LANDING SYSTEM AND METHOD - A low visibility landing system is provided for guiding aircraft on landing approaches. The low visibility landing system may aid a pilot during landing in low visibility conditions such that an aircraft may descend to lower altitudes without visual contact with the runway than is possible with other landing systems. The system may use various navigational systems to produce a hybrid signal that may be more stable than individual signals of those navigational systems. The hybrid signal is compared to a predetermined landing approach plan to determine the deviation of the aircraft from the landing approach plan and to provide guidance to the pilot to get the aircraft back onto the landing approach plan. The system may also use multiple navigational systems to perform checks on an operation of a primary navigational system to ensure that the primary navigational system is operating accurately. | 03-15-2012 |
20120265377 | Method for Enabling Landing on an Offset Runway - 1—Method for determining the distance of an aircraft from an offset runway ( | 10-18-2012 |
20130035810 | METHOD AND SYSTEM TO AUTONOMOUSLY DIRECT AIRCRAFT TO EMERGENCY-CONTINGENCY LANDING SITES USING ON-BOARD SENSORS - A system for autonomous direction of an aircraft to emergency/contingency landing sites incorporates a terrain mapping sensor and an onboard processor receiving terrain data from the terrain mapping sensor. The processor employs software modules for processing the terrain data to produce a terrain map and for creating a landing profile based on the terrain map. | 02-07-2013 |
20130041529 | AIRCRAFT VISION SYSTEM HAVING REDUNDANCY FOR LOW ALTITUDE APPROACHES - A vision system is provided for confirming continuously updated approach information from a global positioning system or an instrument landing system with that from an inertial navigation system. The approach information from the inertial navigation system is displayed when the global positioning system or the instrument landing system is unavailable or whose approach information is determined to be invalid. | 02-14-2013 |
20130066489 | Consistent Localizer Captures - Instrument Landing System (“ILS”) localizer captures have historically been prone to performance degradations based upon erroneous estimates of the localizer deviation and deviation rate. The angular nature of the ILS beam and the relatively narrow trusted linear course guidance sector of the beam are the primary causes of many such issues. It is highly desirable to convert the angular guidance data into a rectilinear form when used by an autopilot and/or flight director systems, the latter of which allows for more consistent stability and performance with respect to distance to runway threshold. Systems and methods disclosed herein are for accurately converting angular localizer data into rectilinear localizer data, thus allowing for improved localizer capture performance and stability. | 03-14-2013 |
20140249703 | METHODS AND SYSTEMS TO ACCURATELY DISPLAY LATERAL DEVIATION SYMBOLOGY IN OFFSET APPROACHES TO RUNWAYS - Systems and methods to accurately display lateral deviation symbology in offset approaches to runways is provided. A system for on-aircraft display of lateral deviation symbology for use in offset approaches comprises means for generating a conformal video display representation of an aircraft's current position, means for notifying a flight crew of the existence of an offset approach, means for displaying an extended runway center line, and means for displaying an approach line. | 09-04-2014 |
20140277857 | METHODS, SYSTEMS AND COMPUTER READABLE MEDIA FOR ARMING AIRCRAFT RUNWAY APPROACH GUIDANCE MODES - Methods, systems, and computer readable media are disclosed for direct arming aircraft runway approach guidance modes, for example and without limitation, for aircraft operational. In some aspects, a method for directly arming a runway approach guidance mode of an aircraft includes displaying on a display unit an airport, selecting the airport and selecting an active runway for final approach, displaying an path toward the selected final approach runway, selecting the final approach runway, displaying on the display unit at least one symbol associated with at least one runway approach guidance mode, and arming at least one of the at least one runway approach guidance mode. | 09-18-2014 |
20140288733 | SYSTEMS AND METHODS FOR REDUCING ERROR DETECTION LATENCY IN LPV APPROACHES - Systems and methods for reducing error detection latency in LPV approaches are provided. In certain embodiments, a method for navigational guidance includes calibrating inertial measurements acquired from an inertial navigation system with satellite-based augmentation system position measurements acquired from a satellite-based augmentation system to create corrected inertial navigation system positions. The method also includes determining whether the satellite-based augmentation system experienced a fault when the inertial measurements were calibrated with the satellite-based augmentation system position measurements. Further, when the satellite-based augmentation system did not experience a fault, the method includes monitoring the satellite-based augmentation system navigation position measurements based on the corrected inertial navigation system positions. | 09-25-2014 |
20140365045 | METHOD OF APPROACHING A PLATFORM - A method having a preparation stage for preparing an approach path ( | 12-11-2014 |
20150019051 | REAL-TIME FAULT DETECTION IN AN INSTRUMENT LANDING SYSTEM - An electronic system with real-time fault detection is provided. In one embodiment, the system includes analog circuitry, having a first input coupled to receive an input signal and a second input coupled to receive a test signal. The test signal is at an edge of a selected band that contains the input signal. The test signal is used to identify faults in the electronic system during operation of the electronic system. The electronic system further includes an analog to digital (A/D) converter coupled to an output of the analog circuitry. The A/D converter generates digitized spectrum. Digital circuitry is coupled to the output of the A/D converter. The digital circuitry processes the input signal from the band to provide an output for the system and processes the test signal to detect faults in the analog circuitry, the digital circuitry and the A/D converter. | 01-15-2015 |
20150032300 | DEVICE FOR DETERMINING LOCATION INFORMATION AND INERTIAL PRIMARY REFERENCES FOR AN AIRCRAFT - Device for determining location information, primary references consolidated for an aircraft, comprising a chain for determining location information comprising means for measuring radionavigation data, suitable means for consolidating, suitable means for computing parameters and suitable means for consolidating the parameters. The device also comprises a chain for determining inertial primary references comprising means for measuring inertial data, suitable means for consolidating, suitable means for computing parameters and suitable means for consolidating the parameters. The device finally comprises a chain for determining anemo-barometric data comprising means for measuring anemo-barometric data, suitable means for consolidating the measured anemo-barometric data, suitable means for computing parameters, and suitable means for consolidating the reference parameters. | 01-29-2015 |
20150081144 | METHOD AND A DEVICE FOR AIDING PILOTING OF AN AIRCRAFT DURING AN APPROACH PHASE FOR LANDING - A method and device for aiding piloting of an aircraft during an approach phase for the purpose of landing. The device includes a guidance system for guiding the aircraft according to a first guidance mode during an initial phase upstream of a transition point, then guiding the aircraft according to a second guidance mode during a terminal phase between the transition point and the landing, the device further including a computing system for automatically computing the coordinates of the transition point, the guidance system also configured for automatically disabling the second guidance mode upstream of the transition point. | 03-19-2015 |
20150362598 | ONBOARD AIRCRAFT LANDING SYSTEM, BASED ON A GNSS SYSTEM, WITH REDUNDANT AND DISSIMILAR ARCHITECTURE FOR HIGH INTEGRITY LEVEL - Device for receiving radio-navigation signals, for aiding the piloting of an aircraft, comprising a first master GNSS module and a second slave GNSS module which are dissimilar, the first master GNSS module comprising a first means for processing radio-navigation signals and a first means for computing guidance data (X | 12-17-2015 |
20160009410 | LIDAR-BASED SHIPBOARD TRACKING AND STATE ESTIMATION FOR AUTONOMOUS LANDING | 01-14-2016 |
20160012735 | INDEPENDENT INSTRUMENT LANDING SYSTEM MONITOR | 01-14-2016 |
20160093225 | LANDING SYSTEM FOR AN AIRCRAFT - A landing system of an aircraft, including: a site selector to select a candidate site using geographical reference point data for the site and current navigation data for the aircraft; a path generator to generate (a) a survey route within the vicinity of said candidate site using said geographical reference point data for the site, and (b) a route to said survey route and; a camera system to obtain images of the candidate site when said aircraft flys said survey route; a site detector controller to process the images to confirm the site by determining the images are of at least part of the candidate site; a tracker to track the site, once confirmed, relative to the aircraft based on the images to verify, and provide navigation data on, the candidate site; and a navigation and guidance system to land the aircraft on the site once the candidate site is verified using the navigation data. | 03-31-2016 |
20160104384 | Redundant Determination of Positional Data for an Automatic Landing System - An automatic landing system contains a control device for providing positional data for controlling an aircraft, a first position or range measuring device for detecting first positional data of the aircraft, a second position or range measuring device for detecting second positional data of the aircraft, and a sensor device for detecting sensor data from which a direction in which a landmark is located and/or a distance of the landmark to the aircraft can be determined. The control device may be configured to generate, based on the first positional data, a first hypothesis for the direction and distance of the landmark and, based on the second positional data, a second hypothesis for the direction and distance of the landmark. Moreover, the control device may be configure to confirm or discard the first hypothesis and the second hypothesis, respectively, using the sensor data detected by the sensor device. | 04-14-2016 |
20160144734 | SYSTEM AND METHOD FOR MANAGING UNMANNED AERIAL VEHICLES - A base station for automated battery pack or payload exchange and methods for using the same. The base station provides a landing surface for receiving a mobile platform and includes a manipulator controlled by a manipulator compartment for accessing resource storage. The base station is operable to ascertain a location of the mobile platform on the landing surface and move the manipulator to the mobile platform. Thereby, the base station system advantageously accommodates low-accuracy landing of the mobile platform and further enables extended and autonomous operation of the mobile platform without the need for user intervention for exchanging battery packs and payloads. | 05-26-2016 |
20190144111 | PORTABLE UNMANNED AERIAL VEHICLE APPROACH AND DEPARTURE ZONE PROTECTION PLATFORM | 05-16-2019 |