A satellite in an orbit around Earth has velocities between Vmin=V-V0 and Vmax=V+V0. Find the eccentricity of the orbit.
where mu = reduced mass = m1m2/m1+m2
The Attempt at a Solution
I know all this formulas for eccentricity, but they all involve disctances/or energy, but not velocities! I don't even know how to start solving this.... Any help/hints?
Thank you very much in advance!