1. The problem statement, all variables and given/known data A 1 500kg satellite is in orbit 250km above earth's surface. What minimum additional energy is needed to place this satellite in a new stable orbit 800km above earth's surface? 2. Relevant equations W = delta Ep = -GMm(1/r2-1/r1) Ep = -GMm/r Ek = GMm/2r or 1/2mv^2 3. The attempt at a solution I tried using the work formula = -GMm (1/2r2-1/2r1, but I get the wrong answer. The answer is 3.41 x 10^9J. I thought to change the radius of orbit from one to another is the change in potential energy which is work?