(adsbygoogle = window.adsbygoogle || []).push({}); 1. The problem statement, all variables and given/known data

see attachment #12.106

2. Relevant equations

V=R[tex]\sqrt{}(g/r)[/tex] (for a circular orbit)

where R is the radius of the earth and r is the radius of the orbit from the center of the earth

conservation of momentum for elliptical orbits:

V_{a}r_{a}=V_{b}r_{b}

3. The attempt at a solution

The first thing I did was find the velocity of the satellite while it is still in a circular orbit and came up with 1.46x10^{8}m/s. Now this is fine and dandy but I don't see where there is enough information to get the velocities in the elliptical orbit since the only equation I have for an elliptical orbit is listed above and I don't have V_{a}or V_{b}. I tried to pretend that the object also went into a circular orbit at B by another rocket boost. Hoping that I might be able to solve for something but to no avail. So I guess my question really is, what is another equation that also has V_{a}and V_{b}so I can solve simultaneously, or is there a way to eliminate one of the variables that I don't see?

Thanks!

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# Velocity of a satellite in an elliptical orbit

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