A 2000 kg satellite is orbitting the earth in a circular orbit with an altitude

Question

A 2000 kg satellite is orbitting the earth in a circular orbit with an altitude of 1800 km.


a) How much energy does it take just to get it to this altitude?


b) How much energy does it to put it in orbit once it has reached this altitude?


c) What is the ratio of the this change in potential energy to the change in kinetic energy? (i.e. what is (a)/(b)?)


d) What would this ratio be if the final altitude of the satellite were 5000 km?


e) What would this ratio be if the final altitude of the satellite were 3185 km ?

Explanation / Answer

a. energy= mgh=2000x9.8x1800x10^3= 3.528x10^10 j = 35.28 Gegajoules b.mv^2/r = mg energy=.5xmxv^2=.5xmxgxr=17.64 Gegajoules c. 2 d. 2 e. 2

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