1. The problem statement, all variables and given/known data Find the energy required to launch a satellite from Earth into circular orbit at radius 5Re in units of joules. Msat = 1000 kg Me = 5.98e24 kg Re = 6.37e6 G = 6.67259e-11 2. Relevant equations F = GMm/(r^2) 3. The attempt at a solution I'm thinking somehow using conservation of forces, ending up with (mv^2)/r, and that v can be used to find final kinetic energy, which can be added to potential energy found using mgh, where g = GM/(r^2). I don't know how to get there though.