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!