1. The problem statement, all variables and given/known data A satellite of mass m, initially at rest on the earth, is launched into a circular orbit at a height equal to radius of the earth. What is the the minimum energy required for this purpose? 2. Relevant equations GMm/r^2 = mv^2/r PE at surface = -GMm/R PE at orbit = -GMm/r where r = 2R 3. The attempt at a solution I am not getting the logic, and I think my problem is more so related to circular motion, I mean if we launch a satellite ,then it will go up and if viewed from outside earth , follow an elliptical trajectory , then how does it get into a circular orbit?How does a force which is actually pulling it downward suddenly provide centripetal acceleration for rotational motion? How is the initial and final energy related. I did most of the problem but this has left me perplexed made me revisit circular motion but I didnt get the solution to my answer anywhere.