Inthispaper, usingtheinformationobtained in thestartracker, strap down inertial navigationsystempositioningerror in suborbital flightisreduced. In this regard, the position error equations of different channel in inertial navigation are modeled and error share of each sensor in position and attitude determination drifts are investigated. In continue celestial navigation and utilizing star tracker in attitude determination and positioning on different frames are considered. Then new equation of inertial navigation aiding by attitude determined with star tracker are introduced. According to the new equations, attitude and position in navigation and inertial frame were calculated again and comparing with the parameters obtained by inertial navigation, considerable reducing position error, especially in the height channel, is shown.

Keywords: Inertial navigation, Celestial Navigation, Star Tracker, Attitude Determination, Navigation Error, Error Analysis

Full-Text [PDF 7583 kb]   (3082 Downloads)