1. The problem statement, all variables and given/known data A satellite is in an elliptic orbit around the Earth. Its speed at pedigree A is 8650 m/s. (a) Use conservation of energy to determine its speed at B. The radius of the Earth is 6380 km. Use conservation of energy to determine the speed at the apogee C. 2. Relevant equations KE= 0.5mv^2 PE = (-GmM)/r 3. The attempt at a solution Honestly, I'm completely stuck. All I have so far is: Total energy = 1/2mv^2 - (GmM)/r I'm assuming we need to find the energy at A and that will be equal to the energy at B and at C but I really have no idea of how to go about that.