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]LEO 1 day 8.8 27.6 0.57LEO 6 hours 2.3 7.2 0.17MEO 1 day 78.6 211 3.6MEO 6 hour 7.2 35.5 3.6GEO 1 day 182 589 10.3GEO 6 hours 21.6 18.6 4.4IGSO 1 day 175 511 19IGSO 6 hours 23 26 12Table 4-13 Solar Radiation PerturbationIt can be seen that for all orbits, even for short term prediction, this perturbation has to beconsidered.4.3.4 Air DragThe following tables shows the orbit error due to neglecting air drag. Satellites in orbits above1000 km are hardly or not at all affected by air drag, thus being indicated in this table only forcompleteness. Unlike the other perturbations, the air drag error is not given as RMS value, butthe instantaneous value at the end of the indicated period. This is due to the secular nature ofair drag perturbation.Radial [m] Along Track [m] Cross Track [m]500 km LEO 70 6.4 km 2.5800 km LEO 1.96 199 0.11250 km LEO 0.09 6.2 0MEO 0 0 0GEO 0 0 0IGSO 0 0 0Table 4-14 Air Drag Perturbation after 1 DayPage 52R. Wolf
Inter Satellite LinksOrbit ComputationRadial [m] Along Track [m] Cross Track [m]500 km LEO 14 322 0.19800 km LEO 0.65 9.83 01250 km LEO 0.01 0.18 0MEO 0 0 0GEO 0 0 0IGSO 0 0 0Table 4-15 Air Drag Perturbation after 6 HoursThe following figures indicates the orbit error of a 800 km LEO neglecting air drag, over aprediction period of one day.0Orbit Error [m]-50-100-150RadialAlong TrackCross Track-20006:39:30.000 13:19:30.000 19:59:30.000UTC [hours:minutes:seconds]Figure 4-8 Orbit Error of 800 km LEO neglecting Air DragAir drag forces act in direction of the flight path, i.e. the along track error is affected most. Asa secondary effect, the orbit altitude decreases due to the dissipation of kinetic energy. TheR. Wolf Page 53
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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]LEO 1 day 8.8 27.6 0.57LEO 6 hours 2.3 7.2 0.17MEO 1 day 78.6 211 3.6MEO 6 hour 7.2 35.5 3.6GEO 1 day 182 589 10.3GEO 6 hours 21.6 18.6 4.4IGSO 1 day 175 511 19IGSO 6 hours 23 26 12Table 4-13 Solar Radiation PerturbationIt can be seen that for all orbits, even for short term prediction, this perturbation has to beconsidered.4.3.4 Air DragThe following tables shows the orbit error due to neglecting air drag. <strong>Satellite</strong>s in orbits above1000 km are hardly or not at all affected by air drag, thus being indicated in this table only forcompleteness. Unlike the other perturbations, the air drag error is not given as RMS value, butthe instantaneous value at the end of the indicated period. This is due to the secular nature ofair drag perturbation.Radial [m] Along Track [m] Cross Track [m]500 km LEO 70 6.4 km 2.5800 km LEO 1.96 199 0.11250 km LEO 0.09 6.2 0MEO 0 0 0GEO 0 0 0IGSO 0 0 0Table 4-14 Air Drag Perturbation after 1 DayPage 52R. Wolf
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