Kinematic orbit determination of low Earth orbiting satellites, using satellite-to-satellite tracking data and comparison of results with different propagators
Independent thesis Advanced level (degree of Master (Two Years)), 20 credits / 30 HE creditsStudent thesisAlternative title
Kinematisk banbestämning av LEO-satelliter med STS-data (Swedish)
The GPS data from Challenging Mini-satellite Payload (CHAMP) is used for its orbit determination for the epoch day of January 1st 2002. The orbit of CHAMP is computed from the GPS data and ionospheric effects are removed by frequency combination.
Further, the orbits of CHAMP for the same epoch day are computed using the satellite tool kit (STK) employing simplified general perturbations (SGP4) and a high precision orbit propagator (HPOP). Results from both techniques (GPS computed orbit and STK computed orbit) are compared.
Furthermore, orbits computed using GPS data are also compared with jet propulsion laboratory’s published CHAMP spacecraft orbit and we have found that root mean square difference in ECEF position X component is below 0.01km other than some spikes at poles. The standard deviation of the difference in ECEF position X coordinate is 11.7m.
The accuracy of our computed satellite positions (using GPS data) is about 12 metres for other than polar areas. However there are some occasional spikes, especially at poles, having maximum errors (about 0.055 km).
Place, publisher, year, edition, pages
2014. , 75 p.
, TRITA-GIT EX, 14-001
GPS, Orbit Computation, STK, SGP4, HPOP
Other Natural Sciences
IdentifiersURN: urn:nbn:se:kth:diva-142627OAI: oai:DiVA.org:kth-142627DiVA: diva2:703788
Subject / course
Master of Science - Electrophysics
KTH, Stockholm (English)
Horemuz, Milan, Univ. lektor
Sjöberg, Lars, Professor