The additional kinetic energy to be provided to a satellite of mass $m$ revolving around a planet of mass $M$,to transfer it from a circular orbit of radius $R_1$ to another of radius $R_2$ $(R_2 > R_1)$ is:

• A
  $GmM \left( \frac{1}{R_1} - \frac{1}{R_2} \right)$
• B
  $2GmM \left( \frac{1}{R_1} - \frac{1}{R_2} \right)$
• C
  $\frac{1}{2}GmM \left( \frac{1}{R_1} - \frac{1}{R_2} \right)$
• D
  $GmM \left( \frac{1}{R_1^2} - \frac{1}{R_2^2} \right)$