p

 Element Symbol Value Epoch to 05:54:21.171 UTC December 16, 2007 Inclination i 51o.9970 R.A. of the Ascending Node aW0 251o.0219 Eccentricity e 0.0001492 Argument of Perigee w0 33o.8641 Mean Anomaly at TLE Epoch Mo 326o.2322 Mean Motion n 12.62256095 orbits / solar day Propagation Time Dt 1.7677141 solar days Mean Anomaly at Time t M(t) 1.37777389 radians (78o.940629) True Anomaly at Time t n(t) 78o.95065818

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 = 2.97554x1015 km3 / day2

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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 SITE MAP Step 5: Finding the Perigee Distance Was Last Modified On January 02, 2012