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Masschaos
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Homework Statement
Consider a satellite in a circular, low-Earth orbit; that is, its
elevation above the Earth’s surface is h ≪ R⊕. Show that the orbital period P for such a satellite is approximately P=C(1+ 3h/[2R⊕]).
Homework Equations
P2 = (4pi2)/(GM) * a^3. (G - gravitational constant, M - mass of the Earth (in this case) and a = semi-major axis)
The Attempt at a Solution
Well, the semi-major axis will be: a = h + R⊕.
I've also picked up that a useful representation of a will be: a = R⊕(1 + h/R⊕)
This means our equation because P2 = (4pi2)/(GM) * (R⊕(1 + h/R⊕))^3.
Now we just want P, so P = (2pi/√GM) * (R⊕(1 + h/R⊕))^(3/2).
This obviously doesn't leave me with much. I've picked up from a few lectures that it may have something to do with Taylor series, but I'm severely stumped.