[SOLVED] energy for circular orbit This one should be easy for you guys, I've been workin on it for a while and need pointed in the right direction. For starters, here's the question: Neglecting Earth's rotation, show that the energy needed to launch a satellite of mass m into circular orbit at altitude h is [(GMm)/R]*[(R+2h)/(2*(R+h))] where G is 6.67x10^-11, M=mass of the earth, R=radius of the earth I believe the problem has to do with conservation of energy, so I found the change in potential energy between the surface of the earth and height h. I think I need to find the change in kinetic energy from the surface and height h then add U and K to find the total energy. I did this and came up with an incorrect answer. Where am I going wrong? P.S. nice site!