Abstract: A navigation system for use with moving vehicles includes target points proximate to a rendezvous site located on a first moving vehicle. One or more transmitters associated with the target points broadcast time-tagged target point positioning information. A navigation unit on a second moving vehicle utilizes a camera with known properties to capture images that include the target points. The navigation unit processes the image that corresponds in time to the positioning information, to determine the relative position and orientation of the rendezvous site at the second vehicle. The navigation unit utilizes the relative position and orientation and an absolute position and orientation of the rendezvous site calculated from the target position information and calculates an absolute position and orientation corresponding to the second vehicle.

Abstract: Among other things, positioning a magnetic instrument on a pedestrian; positioning an inertial instrument on a foot of a pedestrian; receiving positioning signals at the pedestrian; aligning the inertial instrument based in part on the received positioning signals; calibrating the magnetic instrument using the inertial instrument; and tracking the pedestrian using the calibrated magnetic instrument and the inertial instrument.

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

Abstract: 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.

Abstract: A system and method for detecting global positioning system (GPS) spoofing attacks includes collecting GPS readings along with inertial navigational system (INS) readings as a ground truth, and sequentially testing the GPS readings and INS readings through the use of a sequential probability ratio testing (SPRT) process.

Abstract: A method of improving position determination of a device using locally measured movement. A first position fix of a Global Navigation Satellite System (GNSS) receiver system of a device is accessed. A second position fix of the GNSS receiver system is accessed at a time subsequent to the first position fix. Locally measured device movement information is obtained from at least one sensor, that is in a known physical relationship to the device, for a time period after the first position fix and no later than the second position fix, wherein the at least one sensor comprises an image capture device. The quality of measurement of the second position fix is improved by disciplining the second position fix based on the locally measured device movement information.

Abstract: A positioning system operates by first determining that a user is pedestrian, and then estimating a speed of the user. Having tracked a first signal from one radio transmitter whose position is known, the system attempts to detect additional signals from the one transmitter, in a search space such that the first signal and the or each additional signal are consistent with the estimated speed of the user and with one or more of the signals having been reflected off a reflector in the vicinity of the user. One or more detected additional signals from the one transmitter are then tracked, and candidate measurements, derived from the first signal and the one or more detected additional signals, are provided for use when estimating the position and/or velocity of the user.

Abstract: A drive assist system includes: wireless communication devices on first and second vehicles. The wireless communication device on the first vehicle includes: a distance calculation device for calculating a satellite positioning distance between the first and second vehicles; and a difference calculation device for calculating a distance difference between the satellite positioning distance and a distance to the second vehicle obtained by a ranging sensor in the first vehicle.

Abstract: Apparatus for determining a positioning error includes: database for storing grid cells separated by each pCell ID and WLAN environment information matched to grid cells; information receiving unit for receiving terminal WLAN environment information from mobile communication terminal; identification information checking unit for checking AP identification information included in terminal WLAN environment information; triangulating unit for calculating triangulation coordinate value by performing triangulation with AP position estimation information corresponding to AP identification information; grid cell positioning unit for selecting one or more grid cells corresponding to AP identification information and calculating grid cell coordinate value based on coordinate value corresponding to grid cell selected; and error determining unit for comparing triangulation coordinate value and grid cell coordinate value and determining whether there is positioning error in any one of triangulation coordinate value and g

Abstract: Systems and methods are disclosed for determining a geographic position of a mobile communications terminal operable in a wireless communications network. According to one embodiment, a first estimated position of the mobile communications terminal may be calculated based on pseudo-range measurements related to a plurality of signals received from transmitters of a global navigation satellite system. Moreover, a second estimated position of the mobile communications terminal may be calculated based on information provided by the wireless communications network. The first estimated position may be analyzed to derive an indication of whether at least one of the pseudo-range measurements is affected by errors. If at least one of the pseudo-range measurements is affected by errors at least one third estimated position may be calculated based on a sub-set of pseudo-range measurements and evaluated against the first estimated position.

Abstract: A quasi tightly coupled (QTC) aided INS (AINS) process has an inertial navigator system with a loosely-coupled AINS Kalman filter that constructs INS-GNSS position measurements, a GNSS position engine that computes a position fix from observables and an externally provided a priori position and position VCV matrix. An INS position seeding process in which the externally provided a priori position to the GNSS position engine is an antenna position computed from the INS position and attitude solution. An observable subspace constraint (OSC) process computes an OCS matrix that suppress the components of the GNSS position error due to a poor geometry in the GNSS position solution in the IG position measurement constructed by the AINS Kalman filter and that multiplies the OSC matrix and the IG position measurement and measurement model matrix to suppress uncorrected component of the GNSS position error in the IG position measurement and measurement model.

Abstract: A positioning device capable of detecting three-dimensional move trace including a GPS module, an acceleration detecting module, and a computing unit is illustrated. The GPS module acquires global position information of the positioning device. The acceleration detecting module continuously detects three-dimensional acceleration based on movements of the positioning device, and calculates three-dimensional vectors of the positioning device accordingly. The computing unit is coupled with the GPS module and the acceleration detection module. The computing unit generates plane position information according to the global position information and a plurality of short three-dimensional traces according to the three-dimensional vectors. The computing unit further generates a plurality of short-distance traces according to the plane position information and the plurality of three-dimensional traces, and provides a three-dimensional moving trace via combining the plurality of short-distance traces.

Abstract: A handheld GNSS device includes a housing, handgrips integral to the housing for enabling a user to hold the device, and a display screen integral with the housing. The device has a GNSS antenna and a communication antenna, both integral with the housing. The GNSS antenna receives position data from GNSS satellites. The communication antenna receives positioning assistance data from a base station. The GNSS antenna has a first antenna pattern, and the communication antenna has a second antenna pattern. The first and second antenna patterns are substantially separated. Coupled to the GNSS antenna, within the housing, is at least one receiver. Further, the device includes, within the housing, orientation circuitry for generating orientation data, imaging circuitry for obtaining image data, and positioning circuitry for determining a position for the point of interest based on the position data, the positioning assistance data, the orientation data, and the image data.

Abstract: A position calculating device of a moving object including a satellite positioning unit and an inertial positioning unit sets an influence level of measurement result 1 of the satellite positioning unit on measurement result 2 of the inertial positioning unit to a first level until a given condition is established after position calculation is started, and sets the influence level to a second level after the given condition is established. The position of the moving object is calculated by performing a coupling process of coupling measurement result 1 and measurement result 2 on the basis of the set influence level.

Abstract: A system is provided for collecting defect data of components in a passenger cabin of a vehicle that includes, but is not limited to a component identification device for identifying an affected component, and a malfunction selection device, connected to the component identification device, for selecting a malfunction of the identified component from a predefined quantity of component-specific malfunctions. The system includes, but is not limited to a locating device for acquiring a position of the affected component in the passenger cabin, with the aforesaid being connected to the component identification device. In this manner, by means of devices that are very simple to use, imprecise positioning information, component information and malfunction information can be avoided.

Abstract: A satellite positioning component calculates a first position associated with a navigation receiver at a first time. An inertial positioning component calculates a second position associated with the navigation receiver at the first time. A combination positioning component provides a reference position, combines the first position and the second position into a third position based on distances among the first position, the second position, and the reference position, and locates the navigation receiver according to the third position.

Abstract: A navigation system includes first receiver receiving satellite signals, second receiver receiving differential correction data from ground receivers, and processing device coupled to receivers.

Abstract: The subject matter disclosed herein relates to providing assistance information to a mobile station for performing position estimation operations.

Abstract: In a GPS composite navigation apparatus of a configuration having a GPS receiver, variation in an estimated position, an estimated velocity, and an estimated azimuth of a moving body when the moving body is not moving is resolved, and the GPS/INS integrated navigation system with good response characteristics from a stationary state to a moving state. A stationary detector for determining the stationary state of the moving body is provided, and when it is determined to be the stationary state by the stationary detector, a measurement model used for measurement-update of a Kalman filter is changed, while a changed amount of an error covariance matrix by the update is corrected.

Abstract: Various different techniques are used to determine a location of a device, including 3-dimensional (3D) mapping techniques as well as one or more of Global Navigation Satellite System (GNSS) techniques, wireless signal detection techniques, and inertial sensor techniques. The locations determined by these various techniques are combined to determine the location of the device and/or user of the device. In addition to the location of the device, an orientation or direction of view of the device and/or user of the device can optionally be determined as well.

Abstract: A location calculating method includes acquiring measurement information by receiving satellite signals from positioning satellites and storing the acquired measurement information in a storage unit in association with acquisition time, calculating movement information that includes a movement direction and a movement distance by using a detection result of a sensor unit that at least includes an acceleration sensor and storing the calculated movement information in the storage unit in association with calculation time, and calculating a location at desired time by using at least the measurement information of which the acquisition time satisfies a predetermined proximity time condition and the movement information of which the calculation time is between the acquisition time of the measurement information and the given desired time.

Abstract: Systems and methods for the selection of antennas in aircraft navigation systems are provided. In one embodiment, a navigation receiver system for an aircraft comprises: a first aircraft antenna that receives transmitter signals from fixed-location ground transmitters and a second aircraft antenna that receives transmitter signals from the fixed-location ground transmitters, wherein the first aircraft antenna has a first gain pattern that is different from a second gain pattern of the second aircraft antenna; a switch coupled to a first receiver and the first and second aircraft antenna; and a switch controller coupled to the switch. The switch controller operates the switch to electrically couple the first receiver to either the first or second aircraft antenna based on a determination of whether the first gain pattern or the second gain pattern provides higher gain in a direction of a first fixed-location ground transmitter of the fixed-location ground transmitters.

Abstract: A position calculation method and apparatus are described. The position calculation apparatus may include an inertial measurement unit and be configured to be coupled with at least one sensor unit for detecting a physical event for use in position calculation. The presence of and type sensor unit may identified, and the position processing to be undertaken may depend on this identification.

Abstract: A navigation system determines its usage mode. In some embodiments, a method comprises determining a usage mode of a navigation system based on at least one of an acceleration indicator, a speed indicator, and a magnet sensor. The usage mode is at least one of a pedestrian mode, a vehicular mode, an aerial mode, a train mode, and a marine mode. The method further comprises configuring a navigation subsystem based on the usage mode.

Abstract: A positioning method whereby inertial positioning data is calculated based upon measurements of an Inertial Navigation System. Virtual satellite ranging data is then generated based upon the inertial positioning data. The virtual satellite ranging data is then combined with received satellite ranging data from one or more satellites forming part of a Global Navigation Satellite System (GNSS). A GNSS positioning solution is then calculated based upon the combined received satellite ranging data and the virtual satellite ranging data.

Abstract: A method of determining an angular velocity of an aircraft includes measuring the angular velocity using at least one gyro delivering a measured angular velocity signal affected by stochastic noise; measuring the angular acceleration of the aircraft using at least one accelerometer delivering a signal representing the angular acceleration of the aircraft; and using a filtering complementary in a frequency domain to combine a sum of the measured angular velocity signal and the angular acceleration signal so as to obtain a hybrid estimated angular velocity signal with reduced stochastic noise.

Abstract: A positioning method and apparatus of an electronic device which comprises a Global Navigation Satellite System (GNSS) or Global Positioning System (GPS), and an Inertial Navigation System (INS), includes receiving a satellite signal through the GNSS. A location of the electronic device and a reliability of location information of the electronic device is determined based on the satellite signal provided by the GNSS using at least one of satellite information of the satellite signal and location information based on the determined location of the electronic device. An operational level of the INS is determined using the reliability of the location information of the electronic device; and compensating the location of the electronic device by operating the INS according to the determined operational level of the INS.

Abstract: A controlled access satellite navigation receiver has only incomplete knowledge of secret codes transmitted by satellites. This incomplete knowledge allows only intermittent position determination. Incomplete secret codes and the intermittent positions they provide are useful for authenticating navigation signals or controlling access to secret satellite services.

Abstract: A heading determination system comprises an inertial measurement unit (IMU) coupled with at least two GNSS receivers, each receiver paired with and receiving signals from a corresponding GNSS antenna, wherein the GNSS antennas are separated by an ultra-short baseline. The heading determination system receives signals broadcast by a plurality of GNSS satellites and calculates the phase difference in the signal seen among the separate GNSS antennas. Using this phase difference information, derived from comparing the signals received from a plurality of GNSS satellites, along with attitude data generated by the IMU, the heading determination system calculates a highly-accurate heading solution. A method is provided for determining a heading of a system including an IMU coupled with at least two GNSS receivers, with each receiver being paired with and receiving signals from a corresponding GNSS antenna and the antennas being separated by an ultra-short baseline.

Abstract: Inertial navigation systems for wheeled vehicles with constrained motion degrees of freedom are described. Various parts of the navigation systems may be implemented in a smart-phone.

Abstract: Embodiments of the invention provide a tightly-coupled integration filter for inertial sensor-assisted GNSS (global navigation satellite system) receiver. The inertial measurement unit (IMU) contains inertial sensors such as accelerometer, magnetometer, and/or gyroscopes. Embodiments include blending filter based on extended Kalman filter (EKF), which optimally integrates the IMU navigation data with all other satellite measurements (tightly-coupled integration filter). The proposed blending filter includes two states for estimating/compensating the speed scale-factor and the heading bias in the INS measurement.

Abstract: The present invention relates to estimating the attitude angles of an aircraft (1). The estimated attitude angles are generated by a device (9) that performs algorithmic integration on inertial measurements indicative of an angular velocity and of a linear acceleration. Horizontal components (34-39) of desired corrections are obtained by a linear combination of two horizontal components (32-33), with cross coefficients between said horizontal axes being continuous variable over time and dependent on the estimated rate of turn. As a result, the estimated attitude angles are stable, and the biases of the gyros continue to be estimated, including during stages during which the aircraft (1) is turning.

Abstract: A positioning apparatus, positioning method and storage medium are described. According to one implementation, a positioning apparatus includes a first positioning section, a second positioning section, a first calculating section, a control section and a specifying section. The first positioning section performs positioning of the positioning apparatus. The second positioning section performs positioning of displacement of the positioning apparatus. The first calculating section calculates a positioning accuracy of displacement. The control section controls measurement operation of the first and the second positioning sections based on the positioning accuracy calculated by the first calculating section. The specifying section specifies a present position of the positioning apparatus based on a measured result of the first and second positioning sections.

Abstract: Control systems and methods that provide a high degree of vertical measurement accuracy for a body in motion are disclosed. The systems employ an inertial sensor system for vertical measurement and a Global Navigation Satellite System that includes multipath reduction or attenuation to provide corrected vertical information for a moving body to the inertial sensor system. The combination of these systems enables the maintenance of an accurate vertical position for said body.

Abstract: There are situations where GPS signals are received from less than four satellites. In order to improve the GPS location availability, disclosed here are systems and methods for synthesizing GPS measurements, which, together with fewer than four available real GPS signals, can be used to calculate a position fix. In particular, GPS range measurements for lost satellites, which are satellites that were previously tracked but are now not tracked, are synthesized to improve GPS signal availability. The synthesized measurements are used along with real measurements to enable accurate position fix even when GPS satellite availability is poor. Different synthesized measurement generation schemes, depending on whether an INS/DR aiding system is available, are further described herein.

Abstract: A mobile navigation device operating in a first mode and a second mode is provided. In the first mode, a satellite positioning module is activated while a dead reckoning module is disabled. A processor calculates the coordinates of the mobile navigation device based on the satellite navigation signals received by the satellite positioning module. In the second mode, the satellite positioning module is disabled while the dead reckoning module is activated, and the processor updates the coordinates based on displacements and rotations detected by the dead reckoning module.

Abstract: A system and method for detecting global positioning system (GPS) spoofing attacks includes collecting GPS readings along with inertial navigational system (INS) readings as a ground truth, and sequentially testing the GPS readings and INS readings through the use of a sequential probability ratio testing (SPRT) process.

Abstract: The present application describes a computer-implemented method and system for obtaining position information for a moving mobile device with increased accuracy and reduced power consumption. The subject of the present application combines information from a GPS location sensor with information from MEMS devices such as an acceleration detector and a gyroscope using statistical analysis techniques such as a Kalman filter to estimate the location of the device with greater accuracy while using numerical methods such as the Newton-Raphson Method to minimize power consumption. Minimizing power consumption is possible because GPS signals sampled at a lower rate can conserve power, while GPS sampled at a lower rate and working together with MEMS devices can achieve the same level of location prediction accuracy as a GPS alone sampled at a higher rate.

Abstract: Providing indoor location, position, or tracking of a mobile computer is disclosed. Outdoor location, indoor location, and determined motion information is used to track the mobile computer indoors.

Abstract: A heading determination system using signals from a global navigation satellite system (GNSS) includes a rotator mechanism for rotating an array of GNSS antennas. The antenna array rotational orientation relative to a structure, such as a vehicle, can be determined by an angular sensor. By rotating the antennas, multipath error can be nullified. Greater GNSS guidance accuracy and heading determination can be achieved by reducing or eliminating multipath error. The system is also adapted for providing output corresponding to the tilt and roll angles for a mobile structure on which it is mounted using two antennas, with the rotation angle being at least 90°.

Abstract: A heading determination system comprises an inertial measurement unit (IMU) coupled with at least two GNSS receivers, each receiver paired with and receiving signals from a corresponding GNSS antenna, wherein the GNSS antennas are separated by an ultra-short baseline. The heading determination system receives signals broadcast by a plurality of GNSS satellites and calculates the phase difference in the signal seen among the separate GNSS antennas. Using this phase difference information, derived from comparing the signals received from a plurality of GNSS satellites, along with attitude data generated by the IMU, the heading determination system calculates a highly-accurate heading solution. A method is provided for determining a heading of a system including an IMU coupled with at least two GNSS receivers, with each receiver being paired with and receiving signals from a corresponding GNSS antenna and the antennas being separated by an ultra-short baseline.

Abstract: A GNSS receiver includes a radio frequency module and an antenna for acquiring and tracking signals from various satellites and demodulating them to an intermediate frequency or a baseband signal. The receiver also includes a processing unit for processing the demodulated signals to obtain a first position, velocity, and time (PVT fix) data and displays the data to a user. The receiver may include a memory unit for storing the obtained PVT fix. The receiver may further include one or more sensors for detecting a motion of the receiver and provide an index to the processing unit that determines a next position of the receiver based on the index during a coverage gap. The one or more sensors may include an accelerometer, a compass, or a combination thereof.

Abstract: A system and method for locating, tracking, and/or monitoring the status of personnel and/or assets (“trackees”), both indoors and outdoors, is provided. Tracking data obtained from various sources utilizing any number of tracking methods may be provided as input to a mapping application. The mapping application generates position estimates for trackees using a suite of mapping tools to make corrections to the tracking data. The mapping application further uses information from building data, when available, to enhance position estimates. Indoor tracking methods including, sensor fusion methods, map matching methods, and map building methods may be implemented to take tracking data from one or more trackees and compute a more accurate tracking estimate for each trackee. Outdoor tracking methods may be implemented to enhance outdoor tracking data by combining tracking estimates such as inertial tracks with magnetic data, compass data, and/or with GPS, if and when available.

Abstract: A process for determination of navigation parameters of a carrier by a hybridisation device comprising a bank (3) of Kalman filters, each working out a hybrid navigation solution from inertial measurements calculated by a virtual platform (2) and raw measurements of signals emitted by a constellation of satellites supplied by a satellite-positioning system (GNSS), characterised in that it comprises the steps of: determination for each satellite of at least one probability ratio between a hypothetical breakdown of given type of the satellite and a hypothetical absence of breakdown of the satellite, declaration of a breakdown of given type on a satellite as a function of the probability ratio associated with this breakdown and of a threshold value, estimation of the impact of the breakdown declared on each hybrid navigation solution, and correction of hybrid navigation solutions as a function of the estimation of the impact of the breakdown declared.

Abstract: In order to determine positional information, about a mobile robot, Real Time Kinematic (RTK) Global Satellite Navigation System (GNSS) measurement data are obtained by at least two GNSS receivers mounted on the mobile robot. Estimates of the covariance matrices of the measurement data are computed. The RTK GNSS measurement data are combined according to the covariance matrices to obtain enhanced positional information. The results may be fused with data from an IMU to obtain driftless attitude and/or localization information.

Abstract: To provide a GPS compound device having a configuration including a GPS receiver, that accurately determines abnormality in an output from the GPS receiver based on a difference between a GPS pseudorange measurement and a Doppler frequency measurement, when detecting the abnormality in the outputs from the GPS receiver, while avoiding continuation of the abnormality at the time of the abnormality determination resulting from estimation errors of the GPS pseudorange measurement and the Doppler frequency measurement. When the abnormality of the outputs from the GPS receiver are detected, an abnormal period is counted. When the count value is below a predetermined threshold, the outputs from the GPS receiver are treated as abnormal, and after it exceeded the threshold, the outputs from the GPS receiver are treated as normal. Thus, the abnormality of the outputs from the GPS receiver can be determined accurately.

Abstract: An Ultra-Tightly Coupled GPS-inertial navigation system for use in a moving agile platform includes a range residual extractor that uses best curve fitting of a third order polynomial for estimating range residual. The curve-fitted residual is used to update an error Kalman filter. The error Kalman filter includes correction for navigation solution, and IMU and GPS parameters. The navigation solution together with GPS parameter corrections are used in a Tracking Predictor to generate high-sampling-rate carrier and code replicas. The curve-fitting error covariance indicates signal to noise ratio for the tracked GPS signal and may be used for early indication of interference or jamming.

Abstract: Control systems and methods that provide a high degree of vertical measurement accuracy for a body in motion are disclosed. The systems employ an inertial sensor system for vertical measurement and a Global Navigation Satellite System that includes multipath reduction or attenuation to provide corrected vertical information for a moving body to the inertial sensor system. The combination of these systems enables the maintenance of an accurate vertical position for said body.

Abstract: Inertial navigation systems for wheeled vehicles with constrained motion degrees of freedom are described.

Abstract: A handheld GNSS device for determining position data for a point of interest is provided. The device includes a housing, handgrips integral to the housing for enabling a user to hold the device, and a display screen integral with the housing for displaying image data and orientation data to assist a user in positioning the device. The device further includes a GNSS antenna and at least one communication antenna, both integral with the housing. The GNSS antenna receives position data from a plurality of satellites. One or more communication antennas receive positioning assistance data related to the position data from a base station. The GNSS antenna has a first antenna pattern, and the at least one communication antenna has a second antenna pattern. The GNSS antenna and the communication antenna(s) are configured such that the first and second antenna patterns are substantially separated. Coupled to the GNSS antenna, within the housing, is at least one receiver.