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Homework Statement
Assuming that the satellite's orbit is circular, show that its orbital period P at large distances (r>>a) is given by the expression:
P=[(4pi/GM)^(1/2)] r^(3/2) (1-(3/4)((a^2)/(4r^2)) J(subscript2))
Comment on the behavious of P in the limits as r approaches infinity
2relevant equations
g=(GM/(a^2))[-1-(3/2) J(subscript2)]
The Attempt at a Solution
omega^2 r =(GM/(a^2))(-1-(3/2)J(subscript 2))
(2pi/T)^2=(GM/(a^2))(-1-(3/2)J(subscript 2))
T=((4pi^2)/GM)^(1/2) sqrt [((a^2)r)/(m-(3/2)J2 -1)]