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
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<strong>Orbit</strong> Computation<strong>Inter</strong> <strong>Satellite</strong> <strong>Links</strong>The negative sign of the total trajectory energy is related to a body which is never leaving thegravity influence of the earth as the central body. Therefore the orbits of earth orbitingsatellites are represented by ellipses.4.1.1 Kepler <strong>Orbit</strong>sThe classical Kepler orbit is described by six parameters:aεimajor semiaxisnumerical eccentricityinclination of the orbital planeΩ right ascension of the ascending nodeω argument of perigeeT 0time of perigee crossingThe three Keplerian law are associated with the following equations:1. Keplerian law (orbit energy)v 22GM−rGM= −2aEq. 4.1-52. Keplerian law (rotational impact)h = r ⋅ v⋅cosγEq. 4.1-6with γ angle between the normal on the radius vector <strong>and</strong> the velocity vector3. Keplerian law (orbit period)22 4πEq. 4.1-73T = aGMTogether with the geometrical equations for the ellipse, the movement of a satellite in hisorbital plane can be described. In the following the equations are given only with a briefdescription.Page 20R. Wolf
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