Abstract: A system, method, and computer program product are provided for estimating a distance to an object. The system includes a transmitter for transmitting RF signals from a location of an object. The system further includes measurement equipment, including a receiver, for receiving the transmitted RF signals as corresponding received RF signals and measuring a plurality of phase differences at different frequencies between the transmitted RF signals and the corresponding received RF signals. The system also includes a processor. The processor is configured to calculate corrected phases by resolving one or more ambiguities from the plurality of phase differences. The processor is further configured to obtain a characteristic curve using the corrected phases. The processor is also configured to provide an estimate of the distance based on the characteristic curve and the corrected phases.

Abstract: Methods and apparatus are described for processing a set of GNSS signal data derived from code observations and carrier-phase observations at multiple receivers of GNSS signals of multiple satellites over multiple epochs, the GNSS signals having at least two carrier frequencies, comprising: forming an MW (Melbourne-Wübbena) combination per receiver-satellite pairing at each epoch to obtain a MW data set per epoch, and estimating from the MW data set per epoch an MW bias per satellite which may vary from epoch to epoch, and a set of WL (widelane) ambiguities, each WL ambiguity corresponding to one of a receiver-satellite link and a satellite-receiver-satellite link, wherein the MW bias per satellite is modeled as one of (i) a single estimation parameter and (ii) an estimated offset plus harmonic variations with estimated amplitudes.

Abstract: This aircraft navigation assistance system comprises an inertial navigation module adapted for providing first positional information from accelerometric and gyrometric measurements, and a module adapted for determining second positional information from satellite positioning data. The system is characterized in that it comprises means for estimating a first localization of the aircraft at a time of estimation on the basis of first positional information determined from accelerometric and gyrometric measurements at said time of estimation and second positional information determined from positioning data received prior to said time of estimation, said first localization being determined independently from any positioning data received in a time interval preceding said time of estimation, advantageously equal to a time to alert.

Abstract: Computer-implemented methods and apparatus are presented for processing data collected by at least two receivers from multiple satellites of multiple Global Navigation Satellite Systems (GNSS), where at least one GNSS is Frequency Division Multiple Access (FDMA). Data sets are obtained which comprise a first data set from a first receiver and a second data set from a second receiver. The first data set comprises a first FDMA data set and the second data set comprises a second FDMA data set. At least one of a code bias and a phase bias may exist between the first FDMA data set and the second FDMA data set. At least one receiver-type bias is determined, to be applied when the data sets are obtained from receivers of different types. The data sets are processed, based on the at least one receiver-type bias, to estimate carrier floating-point ambiguities. Carrier integer ambiguities are determined from the floating-point ambiguities.

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: A method and system for estimating the position comprises measuring a first carrier phase of a first carrier signal and a second carrier phase of a second carrier signal received by a location-determining receiver. A primary real time kinematic (RTK) engine or receiver data processing system estimates a primary integer ambiguity set associated with at least one of the measured first carrier phase and the measured second carrier phase. A quality evaluator determines if a primary integer ambiguity set is resolved correctly to the predefined reliability rate during an earlier evaluation period. A secondary real time kinematic (RTK) engine or receiver data processing system estimates a secondary integer ambiguity set associated with at least one of the measured first carrier phase and the measured second carrier phase during a later period following the earlier evaluation period.

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: A method implements hybrid type simulation serving to validate an inertial unit of a moving body on board an angular movement simulator by comparing a trajectory of the moving body as calculated in a real navigation environment with at least one reference trajectory.

Abstract: A method and system for designing an impingement film floatwall panel system for a combustion chamber for a gas turbine engine comprising the steps of creating an impingement film floatwall panel knowledge base of information. The knowledge base has a plurality of design rule signals with respect to a corresponding plurality of parameter signals of associated elements of impingement film floatwall panels for a combustion chamber, wherein the knowledge base comprises at least one data value signal for each one of the plurality of design rule signals. The steps also include entering a desired data value signal for a selected one of the plurality of parameter signals of an associated element of the impingement film floatwall panels and comparing the entered desired data value signal for the selected one of the plurality of parameters with the corresponding at least one data value signal in the knowledge base for the corresponding one of the plurality of design rule signals.