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

$A$ planet is moving in an elliptical orbit around the sun. If $T, V, E$,and $L$ stand respectively for its kinetic energy,gravitational potential energy,total energy,and magnitude of angular momentum about the centre of force,which of the following is correct?

If the radius of an orbiting satellite is decreased,then its kinetic energy

Write an equation of total energy of a satellite. Why is the total energy of a satellite negative?

Initially, a satellite of $100 \ kg$ is in a circular orbit of radius $1.5 R_E$. This satellite can be moved to a circular orbit of radius $3 R_E$ by supplying $\alpha \times 10^6 \ J$ of energy. The value of $\alpha$ is . . . . . . .
(Take Radius of Earth $R_E = 6 \times 10^6 \ m$ and $g = 10 \ m/s^2$)

$A$ 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 $9 R_E$?