Abstract
Global positioning system (GPS) observables can be used to compute the orbits of low earth orbiting (LEO) satellites using kinematic approach. Data from GPS receiver, installed onboard the LEO satellite is used for this purpose. In present paper, GPS data from challenging Mini-satellite Payload (CHAMP) is used for its orbit determination. The ionospheric effects on GPS raw data are removed by frequency combination technique. Furthermore, the CHAMP orbit computed using the GPS data are compared with jet propulsion laboratory’s (JPL) published CHAMP spacecraft orbit for same epochs. The root mean square difference in Earth centered Earth fixed (ECEF) Coordinates and JPL computed coordinates are compared. The standard deviations of the differences in ECEF coordinates (JPL results – GPS computed results) is presented. CHAMP orbits computed by JPL have accuracy of centimeter level. Therefore the difference in results of GPS data computed orbits and JPL computed orbits can also be referred as observed error in our method. On this basis, accuracy of our method is analyzed. The observed standard deviation of difference/errors is about 11m.

Muhammad Zaheer. (2015) Kinematic Orbit Determination of Low Earth Orbiting Satellites using GPS Observables, Journal of Space Technology , Volume 5, Issue 1.
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