If $R$ is the radius of orbit of a satellite,then the kinetic energy of the satellite is

When a satellite going round the Earth in a circular orbit of radius $r$ and speed $v$ loses some of its energy,then $r$ and $v$ change as:

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

The minimum energy required to launch a satellite of mass $m$ from the surface of a planet of mass $M$ and radius $R$ into a circular orbit at an altitude of $2R$ is

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 $m$ rotates around the Earth in a circular orbit of radius $R$. If the angular momentum of the satellite is $J$,then its kinetic energy $(K)$ and the total energy $(E)$ of the satellite are: