A satellite is designed to orbit Earth at an altitude above its surface that will place it in a gravitational field with a strength of 4.5N/kg.
a) Calculate the distance above the surface of Earth at which the satellite must orbit.
b) Assuming the orbit is circular, calculate the acceleration of the satellite and its direction.
c) At what speed must the satellite travel in order to maintain this orbit?
g=(G*Me)/r^2, where Me is Earth's mass
The Attempt at a Solution
For a), I've used the above equation, with given g value(4.5) substituted into the equation, and got 3.0 x 10^3km as my final answer but b) and c) is where I have the problem. In order to calculate the acceleration for b), I believe that I need to calculate the velocity(v=sqrt(G*Me/r)) first then substitute into (a = v^2/r). However, if I end up getting an answer for part b), didn't I just do c) as well? Because for c) I need to calculate the velocity as well.. I'd like to know whether or not I was wrong about this before I get in any further.
Thank you in advance for your comments.