Determining Satellite's Altitude and Period Using Kepler's Laws

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To determine a satellite's altitude and orbital period, the discussion emphasizes using Kepler's laws and the equation T^2=(4π^2/GMe)r^3. The user initially attempted to apply this equation with values for gravitational constant G and Earth's mass Me but found their results incorrect. A key point raised is the importance of ensuring consistent units when performing calculations. The conversation highlights that understanding both circular motion and Kepler's laws is essential for solving the problem accurately.
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Homework Statement


A satellite moves in a circular orbit around Earth at a speed of 4505 m/s.

a) Determine satellite's altitude above surface of the Earth.
b) Determine the period of satellite's orbit.


Homework Equations


I'm not sure about equations for the altitude, but I know the period has something to do with Kelper's laws &

T^2=(4pie^2/GMe)r^3=KeR^3


The Attempt at a Solution


My attempt was to use the above equation with G=6.67x10^-11 & Me=6378.1
It wasn't right.
 
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I think this will probably have more to do with circular motion than Kepler's laws.
 
featherua08 said:
My attempt was to use the above equation with G=6.67x10^-11 & Me=6378.1
It wasn't right.
What units are those numbers in? You have to make sure the values you use are consistent with respect to units. Those numbers are not.
 

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