The potential energy of a satellite of mass $m$ and revolving at a height $R_e$ above the surface of earth where $R_e =$ radius of earth, is 

  • A

    $-m\, g\, R_e$

  • B

    $\frac{{ - m\,g\,{R_e}}}{2}$

  • C

    $\frac{{ - m\,g\,{R_e}}}{3}$

  • D

    $\frac{{ - m\,g\,{R_e}}}{4}$

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