n

 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)

In order to find the True Anomaly at the prediction time t, we will first need to find the Eccentric Anomaly E(t) using Kepler's Equation, then use the value of E(t) to determine the True Anomaly. Since the eccentricity for this particular orbit is nearly 0, the Mean Anomaly and the Eccentric Anomaly should be nearly equal to each other. Please be aware that Kepler's Equation can only be used with angles in terms of radians (not degrees)!

M(t) = E(t) - esinE(t)

For an easier time, use a Kepler's Equation solver from the Internet or a root-finding code. You should arrive at the following value:

You can convert the determined Eccentric Anomaly to degrees using the following equation:

E(t) (degrees) = [ E(t) (radians) ] [ 180o / p ]

E(t) = 78o.94226825

You can now determine the True Anomaly using the equation below. Since the eccentricity for this orbit is nearly 0, the Mean Anomaly, Eccentric Anomaly and the True Anomaly should be similar (but not exactly equal) to each other.

cosn(t) = (cosE(t)-e) / (1 - ecosE(t))

n(t) = 78o.95065818

BACK TO STEP #3

PROCEED TO STEP #5

 SITE MAP Step 4: Finding the True Anomaly Was Last Modified On June 25, 2012