A satellite undergoes an elliptic orbit about the Earth of mass M, with maximum distance 6R and minimum distance 3R from the Earth's centre. (a) Show that twice the minimum velocity v(min) = the maximum velocity v(max) = (2/3)*sqrt(GM/R) (b) Show eccentricity = 1/3 We are told that we can assume the orbit is described by 1/r = (1 + e*cos(Theta))/L where where r is the distance from the Earth’s centre, e is the eccentricity with 0 ≤ e < 1 and l = h^2/GM for constant h, the angular momentum per unit mass How I started off was using the conservation of angular momentum and from that got v(max) = 2*v(min) . Tried conservation of energy but got nowhere there. Also tried other equations but I'm not getting anywhere! If anyone could show me a solution I would be so grateful :) Thank you.