تلخیص
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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