If $R$ is the radius of orbit of a satellite,then the kinetic energy of the satellite 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 the Earth of mass $M$ and radius $R$ into a circular orbit at an altitude of $2R$ from the surface of the Earth is:

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

In a satellite,if the time of revolution is $T$,then the kinetic energy $(K.E.)$ is proportional to:

$A$ satellite of mass $m$,initially at rest on the Earth,is launched into a circular orbit at a height equal to the radius of the Earth. The minimum energy required is