We are nearly ready to determine the final state vector (position and velocity vectors) of the satellite. Several final vectors and terms are required. First, we need an intermediate vector that will be determined using the following equation: Y_{i} = N_{22}r_{32}  N_{32}r_{22 }Y_{j} = N_{32}r_{12}  N_{12}r_{32 }Y_{k} = N_{12}r_{22}  N_{22}r_{12} Y_{i} =
7.2727036 x 10^{9} km^{3} Next, we need a handy value to "tidy up" the loose values determined in the previous step: W = [ m / (N_{1}N_{2}) ]^{1/2} W = 3.7649279 x 10^{6} km^{1}·s^{1} Finally, the velocity vector can be found by using the following equation: v_{i} =
W [ Y_{i} / r_{2} + N_{13} ] v_{i} =
3.8589872 km/s Finally, the entire "state vector" satellite orbit elements are known and are stated in their entirety below. The epoch of this state vector corresponds to the second observation of the satellite.


SITE MAP  
Step 13: Velocity Vector Was Last Modified On September 23, 2013 