Class / Patent application number | Description | Number of patent applications / Date published |
342357580 | Integrity monitoring, fault detection or fault isolation of space segment) | 45 |
20100265132 | Method of Amending Navigation Data of a Global Navigation System - In a method for reducing the adverse effect of clock frequency jumps on a user-position determination device in a global navigation system, a plurality of space vehicles each having a clock, transmit position determination information to the position determining device. If a sufficient number of such navigation signals from a first group of space vehicles having clocks in which no jump occurs are available for this purpose, and if a calculated integrity risk is acceptable, position determination is performed using those navigation signals. If not, however, the position determination device receives navigation signals from space vehicles of a second group with clocks in which jumps can occur. The latter signals are combined with signals from the first group in a manner which takes into account possible jumps, and the process is repeated. | 10-21-2010 |
20100289696 | Method and device for estimation of the integrity risk in a satellite navigation system - A method for estimating an integrity risk in a satellite navigation system includes receiving a plurality of navigation signals at a user system from at least one satellite, the plurality of navigation signals including data relative to the integrity of the satellite navigation system; and estimating the integrity risk using the data in the at least one user system. The estimating further includes forming a plurality of intervals of an integration variable of an integral function, estimating a maximum of the integrity risk for each interval, comparing the maximum of each interval to find an overall maximum of all the intervals; and using the overall maximum as an estimate of the integrity risk. | 11-18-2010 |
20100328149 | System and/or Method for Determining Sufficiency of Pseudorange Measurements - The subject matter disclosed herein relates to a system and method for determining a sufficiency of measurements for locating positions. In one example, although claimed subject matter is not so limited, a process to improve accuracy of pseudorange measurements may be terminated in response to a weighting of quantitative assessments of at least some of such pseudorange measurements. | 12-30-2010 |
20100328150 | NAVIGATION SYSTEM WITH ERROR-DETECTION ON DOPPLER FREQUENCIES OF SATELLITE SIGNALS - A navigation system for detecting error on Doppler frequencies of a plurality of satellite signals measured by the navigation system is disclosed herein. The navigation system includes an offset calculator for calculating offsets of the Doppler frequencies of the satellite signals during a predetermined time period and calculating an average value of the offsets. The navigation system further includes an error detecting unit coupled to the offset calculator. The error detecting unit compares the offsets of the Doppler frequencies of the satellite signals with the average value of the offsets and determines whether the satellite signals are unavailable according to corresponding comparison results. | 12-30-2010 |
20110025558 | DEVICE AND METHOD FOR THE REAL-TIME MONITORING OF THE INTEGRITY OF A SATELLITE NAVIGATION SYSTEM - The invention relates to a calculation device providing means for estimating an indication of integrity of a satellite navigation system, including a means for estimating in real time, by measuring data calculated by the navigation system, an indication of integrity of the system with respect to very low-probability location errors, the device including a means for receiving data calculated by the location system, a means for estimating a model of distribution of location errors, a means for estimating parameters characterizing the distribution model, a calculation means applying the extreme values theory as a function of the parameters characterizing the distribution model enabling the modeling of the distribution of very low-probability location errors, a means for estimating in real time an indication of integrity for very low-probability location errors, and a means for transmitting in real time an indication of integrity. | 02-03-2011 |
20110084878 | METHODS AND APPARATUSES FOR SELECTIVELY VALIDATING SATELLITE POSITIONING SYSTEM MEASUREMENT INFORMATION - Methods and apparatuses are provided that may be implemented in various electronic devices to identify suspect measurements for use in a position/velocity/time estimation filter and provide corresponding validated measurements that may be either operatively re-weighted in some manner or operatively one-sided isolated in some manner when subsequently considered by the position/velocity/time estimation filter. | 04-14-2011 |
20110122022 | METHOD FOR PROTECTING A RADIO NAVIGATION RECEIVER USER AGAINST ABERRANT PSEUDO-RANGE MEASUREMENTS - The present invention relates to a method for protecting a radionavigation receiver user in relation to aberrant pseudo-range measurements. In the method, a measurement error is detected by a statistical estimation scheme based on calculating the residuals of the measurements. This method makes it possible, in particular, in a manner which is autonomous of any ground segment (therefore implementing a RAIM functionality) to boost the performance of an off-the-shelf receiver (termed “primary”) without any integrity function, to detect possible errors contaminating measurements on input to the calculation of the position, through the use of a robust estimation statistical algorithm, that is to say one truly unaffected by measurement errors, and implementing a dynamic criterion, and to calculate a robust correction for the position provided by the primary receiver by excluding such an error if it is detected. | 05-26-2011 |
20110169693 | INTEGRITY COMMUNICATION IN A SATELLITE NAVIGATION SYSTEM - Embodiments of the invention are directed to a method for integrity communication in a satellite navigation system having a space segment with several satellites transmitting navigation signals for reception and evaluation by use systems for position determination, and a ground segment with several observation stations that, in their totality, monitor the satellites and their signals, and including at least one transmitting station. The method includes detecting errors that one of have or could have occurred in a determination of a pseudo-range between the satellites and the observation stations and could influence the integrity of the satellite navigation system, forming, from the detected errors, three error budgets for respectively different categories of errors that one of have or could have occurred in the determination of the pseudo-range between the satellites and the observation stations, transmitting the three error budgets one of per ground station or for a group of ground stations with a navigation signal of at least one satellite to the use systems, and receiving the navigation signal and estimating the integrity of the satellite navigation system by evaluating the error budget contained in the received navigation signal | 07-14-2011 |
20110181465 | MULTI-CONSTELLATION GLOBAL NAVIGATION SATELLITE SYSTEM AUGMENTATION AND ASSISTANCE - A multi-constellation GNSS augmentation and assistance system may include a plurality of reference stations. Each reference station may be adapted to receive navigation data from a plurality of different global navigation satellite systems and to monitor integrity and performance data for each different global navigation satellite system. An operation center may receive the integrity and performance data transmitted from each of the plurality of reference stations. A communication network may transmit a message from the operation center to navcom equipment of a user for augmentation and assistance of the navcom equipment. | 07-28-2011 |
20110205112 | METHOD AND DEVICE OF SATELLITE NAVIGATION SYSTEM'S INTEGRITY CONTROL - This invention relates to domain of space activity and can be used for the Earth satellite aided radio navigation, particularly, for control (monitoring) the system integrity without attendance of means of the ground control complex and globally allocated reference stations. A technical result of the claimed technical solution is the responsiveness enhancement of a user's notification about navigation signal uncertainty; cutting-down of expenditures for solving the task of system's integrity control considering the lack of globally allocated ground-based control and monitoring complexes; elimination of additional radio links; increase of reliability of the system's integrity control, growth of reliability. The device for realizing the method of navigation satellite system's integrity control comprises a transmitter-receiver unit, a computer, a navigation signal generator, a navigation signal source, a range measuring instrument, an unit for computing the range to other reference satellites of the navigation satellite system, an unit for comparison of estimated range with the measured one, control unit and decision-making unit. | 08-25-2011 |
20110210890 | SYSTEM FOR MONITORING A SATELLITE CONSTELLATION OF A POSITIONING SYSTEM - The present disclosure relates to a monitoring system which comprises at least one monitoring satellite placed in orbit at a lower altitude than that of the satellites of the satellite constellation so as to be capable of receiving the positioning signals emitted towards the Earth by said satellites, and which comprises a processing unit intended for verifying the integrity of said received positioning signals, using position information that is separate from said signals for this purpose. | 09-01-2011 |
20110291887 | NAVIGATION SYSTEM INTEGRITY - A method for modelling integrity of a filtered global navigation satellite system, by calculating component navigation system error distributions for a set of fault conditions and a fault free condition, and determining overall navigation error distribution by forming a mixture distribution from these component navigation system error distributions. The mixture distribution may be determined by weighted summation of navigation system error (NSE) distributions with weightings determined according to prior probabilities for the fault conditions. Once the overall NSE mixture distribution is determined in this way, it can be used to derive one or more statistical quantities relevant to the integrity of the navigation system such as the probability of exceeding given alert limits in a desired coordinate geometry. | 12-01-2011 |
20110316737 | RAIM Algorithm - Methods and apparatus for implementing a receiver autonomous integrity monitoring (RAIM) algorithm are provided. The RAIM algorithm is for determining an integrity risk in a global navigation satellite system (GNSS) by processing several ranging signals received from satellites of the GNSS. The algorithm involves determining several integrity risks at an alert limit for different fault conditions of the ranging signals, and determining an overall integrity risk at the alert limit from the determined several integrity risks. | 12-29-2011 |
20120013505 | METHOD AND DEVICE FOR DETECTING AND EXCLUDING SATELLITE MALFUNCTIONS IN A HYBRID INS/GNSS SYSTEM - According to a first form, the invention relates to a method for monitoring the integrity of position information outputted by a hybridization device that includes a bank ( | 01-19-2012 |
20120038511 | COMPUTING OF ROBUST AND IMPROVED SIGNAL-IN-SPACE ACCURACY PARAMETERS IN A REGIONAL OR GLOBAL NAVIGATION SATELLITE SYSTEM - Method, computer program to implement method, storage medium to store the program and apparatus for computing Signal-in-Space Accuracy (SISA) parameters in a regional or Global Navigation Satellite System (GNSS). The method includes at least of: determining individual Signal-in-Space Error (SISE) vectors; mapping individual SISE vectors to a service area; accumulating empirical sample sets; processing density functions of estimations of accumulated sample sets; individually overbounding density functions in one of an overbounding sense related to the regional or GNSS or in a paired overbounding with excess mass sense; and selecting a worst case according to predefined requirements. | 02-16-2012 |
20120062418 | METHOD AND SYSTEM OF CALCULATION FOR THE EVALUATION OF THE PRECISION PERFORMANCE OF A SATELLITE NAVIGATION SYSTEM - A method and a system calculates the low probability events for the evaluation of the precision performance of a satellite navigation system, and makes it possible to certify the precision performance of a satellite navigation system for high levels of requirement by modelling events of low probability on the basis of the implementation of the theory of extreme values conjointly with the use of a chart for evaluating precision performance. | 03-15-2012 |
20120146851 | METHOD AND APPARATUS FOR DETERMINING AN INTEGRITY INDICATING PARAMETER INDICATING THE INTEGRITY OF POSITIONING INFORMATION DETERMINED IN A GLOBAL POSITIONING SYSTEM - The present invention relates to a method and an apparatus for determining an integrity indicating parameter (e.g. an integrity risk IR or a protection level PL) indicating the integrity of positioning information determined from positioning information signals disseminated from a plurality of space vehicles SAT | 06-14-2012 |
20120182182 | RECOVERY FROM POSITION AND TIME OUTLIERS IN POSITIONING - A mobile device may use one or more outlier detectors to detect likelihoods that an outlier condition exists for a satellite positioning system (SPS) position fix. In some implementations, an outlier detector may compare a computed position fix to an element of assistance data to generate an outlier likelihood. A decision to perform a recovery operation may be made based, at least in part, on a generated outlier likelihood. In some implementations, a computed reliability of the position fix may also be considered in making a recovery decision. | 07-19-2012 |
20120286993 | Method for Detecting the Distortion of a GNSS Signal - A method for detecting the distortion of a GNSS signal transmitted by at least one GNSS satellite and received by at least one GNSS receiver, said distortion being caused by a GNSS signal generation defect, includes at least the following steps: a step for determining at least one autoregressive parametric model of the GNSS signal at the output of a correlation stage that said GNSS receiver includes; a step for computing at least one linear prediction error e(n) between said output signal of the correlation stage and said autoregressive parametric model; at least one step for comparing the linear prediction error to a detection threshold; and, a step for deciding on the distortion of the transmitted GNSS signal in the case where the linear prediction error exceeds said detection threshold. | 11-15-2012 |
20130009817 | SATELLITE NAVIGATION SYSTEM FAULT DETECTION BASED ON BIASED MEASUREMENTS - Example embodiments disclosed herein provide for a method for detecting a fault in a receiver for a satellite navigation system. The method includes calculating a plurality of measurement residuals corresponding to a position solution and combining the plurality of measurement residuals to form a test statistic. The method also includes calculating a threshold corresponding to the test statistic, wherein calculating the threshold includes selecting the threshold to be a value from a non-central chi squared distribution of possible test statistics that corresponds to a desired probability of false alarm. The test statistic is compared to the threshold and if the test statistic is larger than the threshold, performing at least one of: outputting an alarm indicative of a fault in the position solution and discarding the position solution. | 01-10-2013 |
20130088387 | APPARATUS AND METHOD FOR MONITORING MALFUNCTIONING STATE OF GLOBAL POSITIONING SYSTEM (GPS) SATELLITE - Provided is an apparatus for monitoring a malfunctioning state of a global positioning system (GPS) satellite, the apparatus comprising: an orbit computing unit to compute an orbit of a geostationary satellite; a data receiver to receive GPS data from the GPS satellite; a data correction unit to correct an error in a clock error value of the GPS data; a first computing unit to compute a data pseudorange between the GPS satellite and a base station based on the corrected GPS data; a second computing unit to compute a geographical distance between the GPS satellite and the base station; and a determining unit to determine a malfunctioning state of the GPS satellite by comparing the data pseudorange and the geographical distance. | 04-11-2013 |
20130162472 | METHOD FOR DETERMINING A PROTECTION SPACE IN THE EVENT OF TWO SIMULTANEOUS SATELLITE FAILURES - The present invention relates to a method for determining a protection space in the event of two faulty measurements of a pseudo-range between a satellite and a receiver for receiving signals transmitted by various satellites in a radio-navigation constellation, characterized in that said method includes the steps of: (a) determining, on the basis of the pseudo-ranges measured by the receiver, a test variable representative of the likelihood of a fault; (b) estimating, for each pair of pseudo-ranges from among the pseudo-ranges measured by the receiver and from the expression of the thus-obtained test variable, a set of minimum-bias pairs detectable for a given missed detection probability; (c) expressing, for each pair of pseudo-ranges, the estimated set of detectable minimum-bias pairs in the form of an equation defining an ellipse associated with the pair of pseudo-ranges in question; (d) expressing the equation of each ellipse in parametric coordinates and expressing each detectable associated minimum-bias pair on the basis of a single parameter; (e) projecting each of the thus-parameterized detectable minimum-bias pairs over at least one subspace of R3; (f) calculating, for each subspace and for each bias pair, the maximum position error induced by the bias pair; (g) selecting, for each subspace, the maximum from among all of the calculated maximum position errors, and transmitting the results of said selection outward. The present invention also relates to an integrity-monitoring system and to a vehicle therefor. | 06-27-2013 |
20130169478 | METHOD AND DEVICE FOR DETECTING AND EXCLUDING MULTIPLE SATELLITE FAILURES IN A GNSS SYSTEM - According to a first aspect, the invention relates to a method for checking the integrity of position information output by a satellite (GNSS) positioning device ( | 07-04-2013 |
20130229304 | RECEIVING METHOD AND RECEIVING APPARATUS - In a baseband process circuit unit, a demodulation unit demodulates a received satellite signal which carries a navigation message to obtain a demodulated data. Further, an error bit detection unit detects an error bit from among the demodulated data using a parity code included in the demodulated data. An inconsistent bit detection unit detects an inconsistent bit by comparing the demodulated data with prescribed comparison data. An adoption determination unit determines whether or not to adopt the demodulated data, based on a difference between the error bit and the inconsistent bit. In addition, a correction unit corrects the demodulated data, in a case where the demodulated data is determined to be adopted by the adoption determination unit. | 09-05-2013 |
20130249734 | METHOD FOR DETECTING AND EXCLUDING MULTIPLE FAILURES IN A SATELLITE - The present invention relates to a method for detecting and excluding at least one pseudo-range measured between a satellite and a receiver for receiving signals transmitted by different satellites of a radio-positioning constellation when said pseudo-range is faulty, characterized in that said method includes the steps of: (a) determining an estimation of the position of the receiver from the pseudo-ranges measured by the receiver, (b) estimating, from the thus-estimated position, biases in the measured pseudo-ranges; (c) processing the thus-obtained biases in order to derive a value representative of the probability of a fault for each pseudo-range; (d) preselecting, on the basis of the resulting values, a given number of pseudo-ranges which are most likely to be faulty; (e) determining, for each combination of pseudo-ranges from among the thus-preselected pseudo-ranges, a value of a test variable representative of the likelihood the combination is faulty; (f) selecting, on the basis of the values of the thus-obtained test variables, at least one combination of pseudo-ranges which are most likely to be faulty; and (g) comparing the test variable associated with the selected combination with a predetermined threshold, and transmitting the signals to the receiver or outward on the basis of the result of said comparison. The invention also relates to an integrity-monitoring system and to a vehicle therefor. | 09-26-2013 |
20130335267 | DETECTING METHOD OF GPS CLOCK SIGNAL JUMP USING CARRIER PHASE MEASUREMENTS IN REAL-TIME - Provided is a method of detecting GPS clock signal jump, comprising a data obtaining step of obtaining GPS carrier phase measurements from a GPS receiver and satellite orbits from IGS to detect the GPS clock signal jump; a GPS clock bias calculating step of eliminating errors included in the data obtained from the data obtaining step and calculating GPS clock bias; a Teager energy calculating step of applying a Teager energy operator to the GPS clock bias calculated with respect to each satellite in the GPS clock bias calculating step and calculating Teager energy to determine whether the GPS clock jump is occurred; and a GPS clock jump detecting step of checking whether a Teager energy is larger than a threshold value. Therefore, the present invention can effectively detect the GPS clock signal jump in real-time. | 12-19-2013 |
20140043188 | GLOBAL POSITIONING SYSTEM RADIOMETRIC EVALUATION - Methods and devices for the analysis of global positioning system (GPS) data are described. The methods and devices comprise several metrics to analyse GPS data, such as tracking coverage, signal to noise ratio, multipath noise, positioning and receiver clock, troposphere and data noise. | 02-13-2014 |
20140062778 | CYCLE SLIP DETECTION - Systems and methods for detecting and displaying cycle slips are provided. In one example method, a first L1 signal and a second L2 signal may be received. The coarse/acquisition code from the L1 signal may be extracted and may be monitored to detect a phase shift in the code. In response to detecting a phase shift in the code, a data bit of the L1 signal may be monitored for a predetermined length of time to detect a change in the data bit. A cycle slip may be detected in response to detecting a change in the data bit during the predetermined length of time. In another example, a cycle slip may be detected in response to detecting a change between a phase of the L1 signal and a phase of the L2 signal. | 03-06-2014 |
20140097984 | SYSTEM AND METHOD FOR MONITORING INTEGRITY OF A GLOBAL NAVIGATION SATELLITE SYSTEM - A system and method for monitoring integrity of a Global Navigation Satellite System (GNSS) are provided. Integrity of a GNSS location is assessed based on a comparison of the GNSS location with one or more locations received from at least one other GNSS. Integrity of the GNSS location is also assessed based on a comparison of the GNSS location with one or more locations obtained from signals generated by one or more known located emitters. Integrity of the GNSS location is also assessed based on a comparison of the GNSS location with historical data, which may include contextual information of recent GNSS locations of a user equipment, measurements made by an inertial navigation system of the user equipment, and prior measurements made by the user equipment during similar paths. An integrity warning is outputted when one or more of the integrity assessments indicate a loss of integrity of GNSS. | 04-10-2014 |
20140111377 | Manipulation Resilient Time Distribution Network - Disclosed herein is a system for detecting manipulation of a global time source such as a Global Navigational Satellite System (GNSS) signal and mitigating against such manipulation. A plurality of receivers with geographical diversity receive GNSS signals, and calculate a time signal to be distributed to consuming devices. The receivers also communicate calculated time signals with other receivers. The receivers compare the time signals, and when a difference between the time signals exceeds a predetermined threshold, the receivers indicate that manipulation is likely. Such indication is shared across the network of receivers. The indication is further shared with consuming devices of the time signal from the compromised receiver. A second time signal that is not compromised may be shared with the consuming devices and/or used by the consuming devices. The consuming devices may modify their behavior when in receipt of the indication. | 04-24-2014 |
20140232595 | SYSTEM AND METHOD FOR WIRELESS COLLABORATIVE VERIFICATION OF GLOBAL NAVIGATION SATELLITE SYSTEM MEASUREMENTS - Systems and methods are disclosed herein for verifying the quality of global navigation satellite system (GNSS) measurements. The system includes a GNSS receiver, a wireless communications device, and a fault detection processor. The GNSS receiver includes a GNSS antenna for receiving signals from a plurality of global navigation satellites and a processor for calculating a ranging measurement for each of the global navigation satellites from the GNSS receiver to the global navigation satellite. The wireless communications device receives ranging measurements from at least one other GNSS receiver. The fault detection processor performs a fault detection algorithm to determine if there is an anomaly affecting the ranging measurements of the GNSS receiver and the at least one other GNSS receiver. | 08-21-2014 |
20140247185 | Detection of Manipulated Satellite Time Signals - Disclosed herein is a system for detecting manipulation of a GNSS signal and mitigating against such manipulation. A GNSS receiver receives GNSS signals from a plurality of GNSS satellites, and calculates event times for each GNSS satellite. The GNSS receiver then compares a next event time for a particular GNSS satellite with an expected next event time for the particular GNSS satellite. If the difference between the expected next event time and the next event times exceeds a predetermined threshold, then the GNSS receiver indicates that signal integrity may be compromised. | 09-04-2014 |
20140266880 | Method and apparatus for determining device location - A satellite-based positioning system (SPS) signal processing technique re-samples a received series of PRN sequences from an SPS satellite to align them with a nominal sampling rate for a corresponding series of perfect reference PRN replica sequences. | 09-18-2014 |
20140292574 | SELECTED ASPECTS OF ADVANCED RECEIVER AUTONOMOUS INTEGRITY MONITORING APPLICATION TO KALMAN FILTER BASED NAVIGATION FILTER - A method of advanced receiver autonomous integrity monitoring of a navigation system is discussed and two modifications facilitating its implementation in a hybrid navigation system are disclosed. In the first approach, relations describing the effect of unmodeled biases in pseudo-measurement on the Kalman filter state estimate are analytically derived and their incorporation into the integrity monitoring algorithm is described. The method comprises receiving a plurality of signals transmitted from spaced-based satellites, determining a position full-solution and sub-solutions, specifying a pseudorange bias, computing a transformation matrix for the full-solution and all sub-solutions using a Kalman filter, computing a bias effect on an error of filtered state vectors of all sub-solutions, and adding the effect to computed vertical and horizontal protection levels. In the second approach, a modification for computationally effective calculation of the protection levels of hybrid navigation systems based on both integrity and non-integrity assured pseudorange error descriptions is disclosed. | 10-02-2014 |
20140313077 | METHOD AND SYSTEM FOR DETECTING ANOMALIES ON SATELLITE NAVIGATION SIGNALS AND HYBRIDIZATION SYSTEM COMPRISING SUCH A DETECTION SYSTEM - A method for detecting anomalies on satellite navigation signals consists in extracting the code error values delivered at the output of the N code discriminators, and comparing the extracted code error values with a same first threshold value corresponding to an acceptable maximum code error value and assigning a confidence index to each navigation signal received on each reception channel i, the confidence index depending on the result of the comparison carried out on the code error values. | 10-23-2014 |
20140354474 | Determining Ionospheric Time Delays for Global Positioning System (GPS) Receivers Using Multiple Carrier Frequencies - The disclosed method for determining atmospheric time delays involves receiving at least two signals, where the signals each have a different carrier frequency. The method further involves amplifying each of the signals with a respective amplifier for each of the signals to produce amplified signals. Also, the method involves digitizing each of the amplified signals with a respective analog to digital converter (ADC) for each of the amplified signals to produce digital signals. In addition, the method involves correlating each of the digital signals with a code using a respective correlator for each of the digital signals to determine the time group delay differential between the signals. Further, the method involves calculating, with at least one processor, the time group delay coefficient of the signals by using the time group delay differential. The time group delay coefficient is used to correct for the atmospheric time delays in the signals. | 12-04-2014 |
20150048973 | SYSTEM AND METHOD FOR DETECTING FALSE GLOBAL NAVIGATION SATELLITE SYSTEM SATELLITE SIGNALS - Disclosed is a system and method for detecting false Global Navigation Satellite System (GNSS) satellite signals. False GNSS satellite signals can be used malevolently to take control of a body such as a vehicle or ship that is using GNSS satellite signals for navigation. In some embodiments a GNSS attitude system is used to detect the false GNSS satellite signals. The GNSS attitude system measures the code or carrier phase of the GNSS satellite signals at two or more antennas to detect the false GNSS satellite signals. In some embodiments the attitude system computes first measured and second estimated carrier phase differences in order to detect the false GNSS satellite signals. The attitude system may compute the attitude of a baseline vector between the two antennas. Once false GNSS satellite signals are detected, the method can include preventing the attitude determining system from outputting position or location data. | 02-19-2015 |
20150145724 | ARCHITECTURES FOR HIGH INTEGRITY MULTI-CONSTELLATION SOLUTION SEPARATION - A method comprises receiving a plurality of signals from a plurality of space-based satellites, wherein the plurality of space-based satellites comprises at least one space-based satellite from each of a plurality of Navigation Satellite System (NSS) constellations. The method also comprises determining, in a first domain, a first plurality of sub-solutions based on a respective sub-set of the plurality of signals, each respective sub-set in the first domain chosen according to a characteristic defining the first domain; and determining, in a second domain, a second plurality of sub-solutions based on a respective sub-set of the plurality of signals, each respective sub-set in the second domain chosen according to a characteristic defining the second domain. The method further comprises determining if an error is present in the navigation system based on the first plurality of sub-solutions and on the second plurality of sub-solutions. | 05-28-2015 |
20150362597 | Ephemeris Extension - Apparatus has at least one processor and at least one memory having computer-readable code stored thereon which when executed controls the at least one processor: to store a model with parameters for extending ephemeris data for a first satellite; to receive first ephemeris data from the first satellite, the first ephemeris data relating to clock error data and/or orbit data for the first satellite at a first time; to receive second ephemeris data from the first satellite, the second ephemeris data relating to clock error data and/or orbit data for the first satellite at a second time; to use the model to predict clock error data and/or orbit data for the first satellite at the second time; to calculate a measure of deviation between the predicted clock error data and/or orbit data for the first satellite at the second time and the clock error data and/or orbit data for the first satellite at the second time as described in the second ephemeris data; to use the measure of deviation to determine whether there is a fault in the model or parameters of the model; and on a positive determination, to refrain from using ranging signals originating from the first satellite in positioning the receiver apparatus. | 12-17-2015 |
20160084962 | SYSTEM FOR EXCLUDING A FAILURE OF A SATELLITE IN A GNSS SYSTEM - The invention proposes a system for excluding a failure of a satellite suitable for a hybrid navigation system and which operates even in case of degraded geometry of the constellation of satellites. The hybrid system according to the invention comprises a plurality M of hybridization filters (SFH | 03-24-2016 |
20160116597 | APPARATUS FOR RECEIVING NAVIGATION SIGNAL AND OPERATING METHOD OF THE SAME - The present invention provides a navigation signal receiving apparatus, including: a first navigation information generating unit which receives at least one navigation signal; and a second navigation information generating unit which receives the at least one navigation signal, compares reference information generated based on a first navigation signal with measurement information generated based on the at least one navigation signal to determine whether the at least one navigation signal includes a second navigation signal, estimates normal measurement information using the reference information when the at least one navigation signal includes the second navigation signal, and controls the first navigation information generating unit to trace the first navigation signal which is included in the at least one navigation signal based on the normal measurement information. | 04-28-2016 |
20160154109 | Multi-Constellation GNSS Integrity Check for Detection of Time Signal Manipulation | 06-02-2016 |
20160154110 | METHOD FOR INTEGRITY MONITORING OF SATELLITE MEASUREMENTS | 06-02-2016 |
20160178752 | NAVIGATION AND INTEGRITY MONITORING | 06-23-2016 |
20160195617 | METHOD OF MULTIPLE SATELLITE MEASUREMENT FAILURE DETECTION AND ISOLATION FOR GNSS | 07-07-2016 |