What is the minimum energy required to launch a satellite of mass $m$ from the surface of a planet of mass $M$ and radius $R$ into a circular orbit at an altitude of $2R$?

  • A
    $\frac{5GmM}{6R}$
  • B
    $\frac{2GmM}{3R}$
  • C
    $\frac{GmM}{2R}$
  • D
    $\frac{GmM}{3R}$

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