The total mechanical energy ($E$) of a satellite of mass $m$ revolving in a circular orbit of radius $r$ around a planet of mass $M$ is given by $E = -\frac{GMm}{2r}$.

1. Initial Energy: In the orbit of radius $R_1$, the total energy is $E_1 = -\frac{GMm}{2R_1}$.
2. Final Energy: In the orbit of radius $R_2$, the total energy is $E_2 = -\frac{GMm}{2R_2}$.
3. Energy Supplied: The additional energy required to transfer the satellite is the difference between the final and initial total energies: $\Delta E = E_2 - E_1 = \left( -\frac{GMm}{2R_2} \right) - \left( -\frac{GMm}{2R_1} \right)$ $\Delta E = \frac{GMm}{2R_1} - \frac{GMm}{2R_2} = \frac{1}{2}GMm \left( \frac{1}{R_1} - \frac{1}{R_2} \right)$.