Abstract: A high-precision time synchronization (HTS) system and method using virtual atomic clocks (VACs) includes: providing an implementation of VAC generation method: accessing the high-precision time service provided by the WPT system, solving receiver clock offsets and reconstructing reference stations observations; providing a rapid HTS method: using the VAC information to realize rapid HTS by means of pseudorange or carrier phase CV time transfer; obtaining a HTS system using VACs, including a real-time observations receiving and distributing module, a differential corrections receiving and decoding module, a local clock solving module, a GNSS observations reconstruction module, and a VAC data broadcasting module.

Abstract: A method of determining three-dimensional attitude is provided. The method includes measuring a carrier phase of each satellite signal received at plurality of spaced antenna. A carrier phase difference between the measured carrier phase for each satellite signal from each satellite received at each antenna is determined. The integrity of the integer ambiguity resolution relating to the carrier phase difference is assured by applying a least-square-error solution using differential carrier phase measurements with applied integer ambiguities between at least two of the plurality of antennas and observing measurement residuals after the least-square-error solution is computed and applying an instantaneous test, an interval test and a solution separation function. Three-dimensional attitude is determined from the carrier phase differences upon completion of the integer ambiguity resolution and the assurance of integrity of the integer ambiguity resolution.

Abstract: The invention relates to a method for computing a bound B up to a given confidence level 1??, of an error in a state vector estimation KSV of a state vector TSV of a physical system as provided by a Kalman filter. The method decomposes the errors of the Kalman solution as a sum of the errors due to each of the measurement types used in the filter, In addition, the contribution of each type of measurement is bounded by a multivariate t-distribution that considers the error terms from all the epochs processed. Then, the method implements three main operations: computing a probability distribution of the measurement errors for each epoch and measurement type; summing the previous distributions to obtain a global distribution that models the Kalman solution error; and computing the error bound B for a given confidence level from the resulting distribution.

Abstract: In a system and method for navigating a moving object according to signals from satellite, a moving object receives satellite navigation signals from a number of satellites. The moving object also receives moving base data from a moving base. The received moving base data includes satellite measurement data of the moving base. At the moving object a relative position vector of the moving object relative to the moving base is determined, based on the received moving base data and the received satellite navigation signals. The moving object sends a signal reporting information corresponding to the relative position vector.

Abstract: An amount of propellant remaining in an orbiting satellite can be estimated in a more accurate manner than is possible with conventional approached. Pressure and temperature telemetry data received from the satellite can be analyzed using a maximum likelihood estimation approach that reconstructs a predicted tank pressure signal using the temperature data and determines a pressurant volume necessary to make the reconstructed pressure signal match the received pressure signal. Drift of the pressure data received from pressure transducers in the satellite can also be addressed using the current subject matter, as can issues including but not limited to inaccessible propellant due to satellite spin, tank expansion under pressure, and the like. Independent determinations of the amounts of propellant remaining can be made using moment of inertia calculations in situations in which an axis of spin of the satellite is known a priori.

Abstract: An automatic-piloting system configured for being set on a receiver aircraft and for controlling operations of in-flight refuelling of said receiver aircraft, comprising: first detection means, set on the receiver aircraft and configured for acquiring first geometrical information associated to a first detection area and a second detection area belonging to a tanker aircraft, the first and second detection areas being linked together by a geometrical relation known to the automatic-piloting system; processing means, configured for determining, on the basis of the first geometrical information acquired, first position information associated to a relative position of the receiver aircraft with respect to the tanker aircraft; and an automatic-pilot device coupled to the processing means and configured for varying flight parameters of the receiver aircraft on the basis of the first position information.

Abstract: Aspects of the disclosure relate generally to localizing mobile devices. In one example, a first location method associated with a first accuracy value may be used to estimate a location of the mobile device. A confidence circle indicative of a level of confidence in the estimation of the location is calculated. The confidence circle may be displayed on a mobile device. When other location methods become available, the size of the displayed confidence circle may be expanded based on information from an accelerometer of the client device or the accuracy of the other available location methods. This may be especially useful when the mobile device is transitioning between areas which are associated with different location methods that may be more or less accurate.

Abstract: A method is provided for processing data in an influencing device, whereby the influencing device is connectable to a vehicle control unit and to a data processing unit. If the influencing device receives a first trigger or a second trigger, the first trigger is checked for a valid assignment to a function implemented in the hardware or software. If there is a valid assignment, the assigned function is started. A first address and/or a second address and/or the value are checked for a valid assignment to a first sub-function or a second sub-function. Depending on the called sub-function, the value is checked and/or manipulated and depending on the result of the check, the checked value and/or the manipulated value are sent by the influencing device to the vehicle control unit and/or to the data processing unit and/or stored in the memory of the influencing device.

Abstract: Provided is a method of performing time synchronization using a navigation device. The method includes: (a) performing time synchronization between a GPS satellite and a navigation device by receiving GPS signals by a navigation device from at least one GPS satellite; (b) establishing an interface between the navigation device and a time-using device; (c) setting conditions for transmitting time information to the navigation device; and (d) performing time synchronization between the navigation device and the time-using device by transmission of time information from the navigation device to the time-using device.

Abstract: A method of determining a GPS position fix is disclosed together with a corresponding GPS receiver and server for the same. The method comprising the steps of: (i) providing standard GPS ephemeris corresponding to that transmitted by a GPS satellite; (ii) providing supplemental GPS ephemeris including at least one parameter describing the fluctuation over time of at least one satellite orbit parameter of standard GPS ephemeris; (iii) measuring psuedoranges to GPS satellites; and (iv) determining a GPS position fix from both the standard and supplemental GPS ephemeris provided in steps (i) and (ii) respectively and the psuedoranges measured in step (iii).

Abstract: Device for aiding the navigation and guidance of an aircraft, and system comprising such a device. The device (1) comprises at least three independent channels and it comprises at least one computer (2) which contains means (4) for storing and means (6, 7) for calculating positions and deviations.

Abstract: A method is provided for augmenting GPS data using an in-vehicle vision-based module. A vehicle position is determined utilizing position-related data obtained from a position module. A position error is estimated on a periodic basis. A determination is made whether the position error estimate exceeds a first predetermined error threshold. Tracking data is generated for the vehicle over a course of travel utilizing captured images from the in-vehicle vision based module. The tracking data is integrated with the position-related data to estimate the vehicle position in response to the position error estimate exceeding the first predetermined error threshold. A determination is made whether the position error estimate decreases below a second predetermined error threshold. The vehicle position is re-determined using only the position-related data when the position error estimate decreases below the second predetermined error threshold.

Abstract: The navigation system described here utilizes GPS and Galileo satellite signals combined with Inertial Navigation Systems (INS), where a Coupled Antenna (CAN) provides both GNSS and Inertial Measurement Unit (IMU) data to a Highly Integrated GNSS-Inertial (Hi-Gi) receiver. Such receiver makes use of a high fidelity relation between GNSS unprocessed Correlator Output (COUT) I and Q data and the user trajectory, and inertial sensor data, which in turn are combined within a Kalman Filter (KF). The KF determines the navigation solution that is also used to provide feedback to the receiver demodulation signal processing stage, thus eliminating the need of dedicated structures such as Delayed Locked Loops (DLL) and Phase Locked Loops (PLL), allowing a significant improvement in navigation performance.

Abstract: An auxiliary satellite positioning system is applied to a first satellite positioning apparatus. The auxiliary positioning system includes a detection module, a transmission interface and a positioning module. A second satellite positioning module having a satellite data can be detected by the detection module via a wireless transmission protocol. The satellite data can be transmitted by the transmission interface to the first satellite positioning module from the second satellite positioning module. The satellite data can be used by the positioning module to implement a satellite positioning action.

Abstract: A method and apparatus for determining protection levels in a satellite navigation system includes the following steps: (1) determining an integrity risk at the alert limit for a plurality of application situations—for example, starting from approaches in category I (Category I precision approach) up to the operation “oceanic enroute;” (2) determining an interval of the alert limits between the largest set of alert limits which produces too high an integrity risk, and the smallest set of alert limits which produces an acceptable integrity risk; and (3) carrying out an interval nesting for the interval of the alert limits that was determined in the previous step, the integrity risk between the horizontal and the vertical being divided in the same way as it is obtained from the relationship between these integrity risks in the largest set of alert limits.

Abstract: In a method for providing integrity information for users of a global navigation system, which comprises several space vehicles like satellites transmitting information to a device for position detection, the transmitted information comprises first information from the global navigation system about the accuracy of a signal in space error SISE of a faulty space vehicle, and second information whether or not the global navigation system assesses the faulty space vehicle as faulty. The invention is based on the assumption how exact a fault can be detected, so that performance the global navigation system can be increased; and no unfounded assumption is used which improves the quality of service.

Abstract: The present invention relates to a reinforced slide chassis structure of an audio/video system, more particularly, to a reinforced slide chassis structure of an audio/video system for a motor vehicle, capable of preventing deteriorations in the slide chassis by reducing a total weight of the slide chassis yet reinforcing a deformation-sensitive portion of the slide chassis.