1. The problem statement, all variables and given/known data I have a satellite with a mass of 250 kg, which I'm launching from Earth. This neglects air resistance/rotation of the planet etc. a. How much energy is needed to put the satellite in orbit at an altitude of 4.0 x 106 m? b. What would be the period of the satellite at that altitude? c. How much additional energy would be needed to put the satellite into a geosynchronous orbit? 2. Relevant equations Period=2pir/T PE=G(mM/r) KE=(1/2)(m)(v^2) 3. The attempt at a solution This is my first day doing orbital problems, so I'm really having trouble getting started! For a, I thought maybe I should calculate velocity then the kinetic energy using 1/2mv^2? And then add it to the potential energy of the satellite when it's orbiting, using PE=mgh?For b, I know a formula to find the period. For c, I've never seen a problem like that, but I assume I would put 24 hours into the period equation and start from there? Thank you in advance!