Adaptive Kalman Filters for Orbit Estimation of Navigation Satellites for DGPS Applications
نویسنده
چکیده
The navigation problem associated with terminal aircraft guidance refers to position determination of an individual vehicle with respect to some point local to the environment as is the case with aircraft landing systems. This paper presents results for a relative navigation filter that achieves CAT3-level precision from a customized navigation satellite receiver's data message and the NORAD SDP4/SDP8 algorithm to establish the measured data. This work uses a precise, robust Unscented Kalman Filter (UKF) that is based on a realistic measurement model and a nonlinear propagation model. The UKF is based on the Unscented Transformation (UT) and provides a derivative free alternative to Extended Kalman filtering (EKF). Preliminary results indicate the method is particularly suitable for estimating the orbit ephemeris of navigation satellites such as GPS, Galileo and GLONASS. These estimates serve to generate pseudo-range corrections in an interoperable differential GNNS application.
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