Satellite Constellation - Fundamentals of Global Positioning System Receivers: A Software Approach - page 49

actual elliptical satellite orbit must be used. To discuss the motion of the satellite
in the elliptical-shaped orbit, Kepler's laws are introduced. Three anomalies are
defined: the mean M , the eccentric E ,andthetrue ν anomalies. Mean anomaly
M and eccentricity e s are given from the navigation data of the satellite. Eccentric
anomaly E can be obtained from Equation (3.30). True anomaly ν can be found
from Equations (3.40) and (3.41). Finally, the receiving power at the user location
is estimated.

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