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

A satellite in an orbit around Earth has velocities between Vmin=V-V0 and Vmax=V+V0. Find the eccentricity of the orbit.

2. Relevant equations

rmin=l^2/(Gm1m2*mu*(1+e))

E=(Gm1m2)^2*mu*(e^2-1)/2l^2

where mu = reduced mass = m1m2/m1+m2

3. 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!

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# Satellite in an orbit around Eart

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