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Period of a low-Earth orbit.

  1. Jul 31, 2012 #1
    1. The problem statement, all variables and given/known data
    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⊕]).


    2. Relevant equations
    P2 = (4pi2)/(GM) * a^3. (G - gravitational constant, M - mass of the earth (in this case) and a = semi-major axis)


    3. 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.
     
  2. jcsd
  3. Jul 31, 2012 #2

    Dick

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    Good guess. It is taylor series. (1+x)^(3/2)=1+3x/2+3x^2/8+... for x small. Truncate to the linear term. Does that help?
     
  4. Aug 1, 2012 #3
    Oh yes, I do see. That is almost exactly what is required.
    I don't suppose you'd know any reason for keeping it to the linear term?
    Perhaps because h << R the other terms become negligible. I think that is reasonable!
    Thank you very much.
    That was much simpler than I thought.
     
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