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

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SUMMARY

The discussion focuses on calculating a satellite's altitude and orbital period using Kepler's laws and the principles of circular motion. The satellite travels at a speed of 4505 m/s, and the relevant equation for determining the period is T² = (4π²/GMe)r³, where G is the gravitational constant (6.67 x 10^-11) and Me is the Earth's radius (6378.1 km). Participants emphasize the importance of consistent units when applying these equations, as incorrect unit usage leads to inaccurate results.

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  • Knowledge of gravitational constant (G) and Earth's mass (Me)
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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.
 
Last edited:
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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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