The minimum energy required to launch a satellite of mass m from the surface of earth of mass M and radius R in a circular orbit at an altitude of 2R from the surface of the earth is:
1
\(\rm \frac{5GmM}{6R}\)
2
\(\rm \frac{2GmM}{3R}\)
3
\(\rm \frac{GmM}{2R}\)
4
\(\rm \frac{GmM}{3R}\)