An artificial satellite moving in a circular orbit around the earth has a total (kinetic + potential) energy $E_0$. Its potential energy is

The additional kinetic energy to be provided to a satellite of mass $m$ revolving around a planet of mass $M$ to transfer it from a circular orbit of radius $R_1$ to another of radius $R_2$ $(R_2 > R_1)$ is:

The minimum energy required to launch a satellite of mass $m$ from the surface of the Earth of mass $M$ and radius $R$ into a circular orbit at an altitude of $2R$ from the surface of the Earth is:

The additional kinetic energy to be provided to a satellite of mass $m$ revolving around a planet of mass $M$,to transfer it from a circular orbit of radius $R_1$ to another of radius $R_2$ $(R_2 > R_1)$ is:

$A$ satellite of mass $m$ is in a circular orbit of radius $3 R_E$ about the Earth (mass of Earth $M_E$,radius of Earth $R_E$). How much additional energy is required to transfer the satellite to an orbit of radius $9 R_E$?

The minimum energy required to launch a satellite of mass $m$ from the surface of a planet of mass $M$ and radius $R$ into a circular orbit at an altitude of $2R$ is