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(B) For a satellite in a circular orbit of radius $r$ around the Earth of mass $M$, the potential energy $U$ is given by $U = -\frac{G M m}{r}$.The ki

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$2 E$

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(B) For a satellite in a circular orbit of radius $r$ around the Earth of mass $M$, the potential energy $U$ is given by $U = -\frac{G M m}{r}$.The kinetic energy $K$ of the satellite is given by $K = \frac{G M m}{2 r}$.The total energy $E$ is the sum of potential and kinetic energy:$E = U + K = -\frac{G M m}{r} + \frac{G M m}{2 r} = -\frac{G M m}{2 r}$.Comparing the expressions for $U$ and $E$:$U = -\frac{G M m}{r}$$E = -\frac{G M m}{2 r}$Therefore, $U = 2 	imes (- \frac{G M m}{2 r}) = 2 E$.Wait, let us re-evaluate: $U = -\frac{G M m}{r}$ and $E = -\frac{G M m}{2 r}$.Thus, $U = 2 E$ is incorrect. The correct relation is $U = 2 E$ if $E$ were defined differently, but here $U = 2 E$ is not correct. Let's re-check: $U = -\frac{G M m}{r}$ and $E = -\frac{G M m}{2 r}$.So, $U = 2 	imes (-\frac{G M m}{2 r}) = 2 E$. Actually, $U = 2 E$ is correct because $2 	imes (- \frac{G M m}{2 r}) = - \frac{G M m}{r} = U$.

An artificial satellite moves in a circular orbit around the earth. The total energy of the satellite is given by $E$. The potential energy of the satellite is

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