1. The problem statement, all variables and given/known data An Earth (mass M) satellite of mass m is in a circular orbit of radius r1. It is moved to an orbit with a larger radius r2 by way of an intermediate elliptical orbit. This is achieved by firing rockets for a short period when it is in the inner orbit, and then firing the rocket again when it has reached the maximum distance from M. Determine the total mechanical energy for each of the three orbits and the energy increase for each orbit transfer. 2. Relevant equations I was not given any equations for this problem or any hints to what equations I need. I had a guess at using F = GMm/r2 3. The attempt at a solution I am completely lost on this one. I know I am supposed to equate some equations, but I don't know which ones or how to go about it. I am sure somethings cancel out somewhere. Please help.