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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Software Description<strong>Inter</strong> <strong>Satellite</strong> <strong>Links</strong>Assuming C /N 0 to be - for a given link technique - approximately a function of the inversesquare of the geometric distance (equation 5.3-8), we obtainNKC0C / N=20 dEq. 5.3-12Where the parameter K C/N0 still has to be determined. By assuming a (rather pessimistic) C/N 0 of 30 dB Hz for a GPS satellite close to the horizon (elevation ~ 0°) which would have arange of approximately 25 000 km, we obtain the link budget dependent factor K C/N0 byCNK0CN0C / NdB,Hz= 1003= 30dB=KHzC / N( 25000km)= 6.25 ⋅1017= 10 ⋅ log0210⎛⎜⎝CN0⎞⎟⎠Eq. 5.3-135.3-9 <strong>and</strong> 5.3-10 have been evaluated <strong>using</strong> the parameter values indicated above, but withthree different integration time constants T I . The results has been plotted. Figure 5-3 <strong>and</strong> 5-4show the results for the code range <strong>and</strong> carrier noise.86Ti = 2 msTi = 20 msTi = 200 msD = 30 mCode Noise [m]4200 10000 20000 30000 40000Distance [km]Figure 5-3 Code Noise vs. RangePage 78R. Wolf
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