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$GmM \left( \frac{1}{R_1^2} - \frac{1}{R_2^2} \right)$
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