Navigation parameters estimation of satellite integrated astro-gnss navigation system
Moscow Aviation Institute (National Research University), 4, Volokolamskoe shosse, Moscow, А-80, GSP-3, 125993, Russia
AbstractIt is considered the estimation of navigation parameters accuracy provided by the integrated navigation system. The way of possible accuracy improving problem solution by special configuring Kalman’s filter is described. Illustrations of navigation system processing simulation results after special integrated filter configuring are shown.
Keywords:navigation; integrated system; astrosensor, gnss navigation system; Kalman filter; GLONASS; star tracker; geostationary orbit.