Satellite Orbit and Ephemeris Determination using Inter Satellite Links
Satellite Orbit and Ephemeris Determination using Inter Satellite Links Satellite Orbit and Ephemeris Determination using Inter Satellite Links
Orbit ComputationInter Satellite LinksRadial [m] Along Track [m] Cross Track [m]50 x 50 0 0.01 030 x 30 0.04 0.34 0.0115 x 15 0.91 4.53 0.1910 x 10 4.2 67.6 2.85 x 5 43.7 762 7.62 x 2 330 1.4 km 62.1J2-Propagator (2 x 0) 1.1 km 33 km 21 kmKepler (0 x 0) 7.8 km 175 km 49.3 kmJGM-2 (70 x 70) 0.30 4.26 0.06GEM-T3 (50 x 50) 0.11 0.48 0.02GRIM4-S4 (66 x 66) 0.29 4.35 0.02Deviated JGM-3 0.05 0.23 0.02Table 4-6 1250 km LEO 6 hoursThe next figure show the results obtained for a medium earth orbit (MEO). The chosen orbitof approximately 20200 km orbit altitude with 55° inclination represents a generic GPS orbit,which is the most appropriate for navigation satellites. It has been propagated using a 5 x 5gravity model, and compared to the reference orbit using the full 70 x 70 model.Page 42R. Wolf
Inter Satellite LinksOrbit Computation1.00.80.6RadialAlong TrackCross TrackOrbit Error [m]0.40.20.0-0.220:52:30.000 05:12:30.000 13:32:30.000UTC [hours:minutes:seconds]Figure 4-2 Orbit Error of MEO with 5 x 5 gravity model after 1 dayHere also the orbital period can also be seen in the error behaviour. The following tablesindicates the 1σ error after one day and after six hours of prediction, for different gravitymodels.R. Wolf Page 43
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<strong>Orbit</strong> Computation<strong>Inter</strong> <strong>Satellite</strong> <strong>Links</strong>Radial [m] Along Track [m] Cross Track [m]50 x 50 0 0.01 030 x 30 0.04 0.34 0.0115 x 15 0.91 4.53 0.1910 x 10 4.2 67.6 2.85 x 5 43.7 762 7.62 x 2 330 1.4 km 62.1J2-Propagator (2 x 0) 1.1 km 33 km 21 kmKepler (0 x 0) 7.8 km 175 km 49.3 kmJGM-2 (70 x 70) 0.30 4.26 0.06GEM-T3 (50 x 50) 0.11 0.48 0.02GRIM4-S4 (66 x 66) 0.29 4.35 0.02Deviated JGM-3 0.05 0.23 0.02Table 4-6 1250 km LEO 6 hoursThe next figure show the results obtained for a medium earth orbit (MEO). The chosen orbitof approximately 20200 km orbit altitude with 55° inclination represents a generic GPS orbit,which is the most appropriate for navigation satellites. It has been propagated <strong>using</strong> a 5 x 5gravity model, <strong>and</strong> compared to the reference orbit <strong>using</strong> the full 70 x 70 model.Page 42R. Wolf
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