(c) The period of revolution of a satellite at a height $h$ from the surface of earth is given by
$\ \ \ \ \ \ \ \ \ \ \ \ \ \ \ \ T = 2\pi\sqrt{\frac{\left( R_{e} + h \right)^{3}}{gR_{e}^{2}}}$
$Given,\ \ T_{m} = 1$ lunar month,
$\therefore\ \ \ \ \ \ \ T_{sat} = 2\pi\sqrt{\frac{\left( R + \frac{h}{2} \right)^{2}}{gR^{2}}}$
$\Longrightarrow \ \ \ \ T_{sat} = \frac{1}{2^{3/2}}$
$\ \ \ \ \ \ \ T_{moon} = 2^{- 3/2}$ lunar month