In a satellite,if the time of revolution is $T$,then $KE$ is proportional to

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:

$A$ satellite of mass $m$ is in a circular orbit of radius $2R_E$ around the Earth. The energy required to transfer it to a circular orbit of radius $4R_E$ is (where $M_E$ and $R_E$ are the mass and radius of the Earth,respectively).

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

$A$ satellite has kinetic energy $K$, potential energy $V$, and total energy $E$. Which of the following statements is true?