A 1700 kg satellite is orbitting the earth in a circular orbit with an altitude of 1800 km. a) How much energy does it take just to get it to this altitude? . . . Ok, I just need help getting the setup on this first part. The amount of energy need to get to this altitude would the sum of the initial potential and kinetic energies, right? So -GMm/r + .5mv^2 = total energy? where r= Radius of earth + altiude (m) I can figure out the velocity using escape velocity equation, but I get this big negative answer. Thats not right, so whats the right way to do this?