$A$ satellite of mass $m$ revolving in a circular orbit of radius $r$ around the Earth has kinetic energy $E$. Then its angular momentum will be

The ratio of energy required to raise a satellite to a height $h$ above the earth's surface to that required to put it into the orbit at the same height is ($R=$ radius of earth).

$A$ 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 $9 R_E$?

$A$ skylab of mass $m \ kg$ is first launched from the surface of the earth into a circular orbit of radius $2R$ (from the centre of the earth) and then it is shifted from this circular orbit to another circular orbit of radius $3R$. The minimum energy required to shift the lab from the first orbit to the second orbit is:

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

If the kinetic energy of a satellite is $6 \times 10^9 \ J$,what will be its potential energy and total energy?