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Calculate the speed required for a satellite moving in a circular orbit 550.0 km above the surface of the Earth. (mEarth = 5.98 × 1024 kg , rEarth = 6.38 × 106 m)

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Brayden

  1. m v^2/R = m g there = G m M / R ^ 2
    m cancels of course
    so
    v^2 = G M/R
    R = 6.38*10^6 + 0.550 *10^6
    M = 5.98*10^24
    G= 6.67 *10^-11

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    Anonymous

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