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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)

\[\begin {array} {1 1} (1)\;\frac{GMm}{R} & \quad (2)\;\frac{13 GMm}{14R} \\ (3)\;\frac{GMm}{7R} & \quad (4)\;\frac{GMm}{14R} \end {array}\]

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$(2)\;\frac{13 GMm}{14R} $
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