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## Homework Statement

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 10
^{6}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?

## Homework Equations

Period=2pir/T

PE=G(mM/r)

KE=(1/2)(m)(v^2)

## 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!

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