A spacecraft $($mass $=m)$ orbits a planet $($mass $=M)$ in a circular orbit $($radius $=R).$ What is the minimum energy required to send this spacecraft to a distant point in space where the gravitational force on the spacecraft by the planet is negligible?

$Gm\frac{M}{2R}$

$2$GmM$/(5$R$)$

GmM$/(4$R$)$

GmM$/(3$R$)$

$Gm\frac{M}{R}$