Suppose we want to launch satellite into a geosynchronous orbit IE a satellite w

Question

Suppose we want to launch satellite into a geosynchronous orbit IE a satellite with a period of 24 hours. What should the radiance of its orbit be? I don't really need the answer on this one I just need to figure out how to get there. :) Please give explanation instead of just writing down numbers. Suppose we want to launch satellite into a geosynchronous orbit IE a satellite with a period of 24 hours. What should the radiance of its orbit be? I don't really need the answer on this one I just need to figure out how to get there. :) Please give explanation instead of just writing down numbers.

Explanation / Answer

According to kepler's laws...

T^2 = 4*pi^2*r^3/(G*M) .....

r^3 = T^2*G*M/(4*pi^2) = (24*3600)^2*6.67*10^-11*5.97*10^24/(4*3.142^2)

r^3 = 75275785710*10^12.....

r = 4222.32*10^4 m = 42223.26 km

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