For a satellite,if the time of revolution is $T$,then its $K.E.$ is proportional to

$A$ satellite is orbiting the Earth. If its orbital radius is reduced to half of its initial value,then the percentage change in its total energy is: (in $\%$)

For a satellite orbiting around the earth in a circular orbit,the ratio of potential energy to kinetic energy at the same height 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

An artificial satellite moving in a circular orbit at a distance $h$ from the centre of the Earth has a total energy $E_0$. Then,its potential energy is

$A$ 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 ($G$ is the gravitational constant).