Satellite Orbit and Ephemeris Determination using Inter Satellite Links

Orbit ComputationInter Satellite LinksThird body attraction has to be modelled, regardless of the application (but especially fornavigation satellites). The errors introduced by neglecting these contributing forces are farfrom being negligible.4.3.3 Solar Radiation PressureThe following figures shows the orbit error due to direct solar radiation pressure for theinvestigated orbits. Obviously the LEO is affected less by (neglecting) solar radiation, due tothe fact that the exciting force (=solar radiation pressure) has a slowly varying geometry.80706050RadialAlong TrackCross TrackOrbit Error [m]403020100-10-2019:12:30.000 01:52:30.000 08:32:30.000UTC [hours:minutes:seconds]Figure 4-5 Orbit Error of 1250km LEO neglecting Solar Radiation PressurePage 50R. Wolf