The semi-major axis (a) of a satellite's orbit can be determined from its Mean Motion (n) by using Kepler's Third Law: a = [ m / (2pn)^{2} ]^{ 1/3} where m = The Gravitational Parameter = 2.97554x10^{15} km^{3} / day^{2} a = 7791.787473 kilometres from the Earth's Center The perigee distance (P) can now be found by using the following equation: P = a (1-e) P = 7790.624938 kilometres from the Earth's Center it is extremely
important to remember that these values refer to distances to the satellite from
the center of the Earth and NOT from the observer's location! |
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Step 5: Finding the Perigee Distance Was Last Modified On January 02, 2012 |