$A$ launching vehicle carrying an artificial satellite of mass $m$ is set for launch on the surface of the earth of mass $M$ and radius $R$. If the satellite is intended to move in a circular orbit of radius $7R$,the minimum energy required to be spent by the launching vehicle on the satellite is (Gravitational constant $= G$)
- A$\frac{GMm}{R}$
- B$\frac{13GMm}{14R}$
- C$\frac{GMm}{7R}$
- D$\frac{GMm}{14R}$
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