If a satellite of mass $400 \, kg$ revolves around the earth in an orbit with speed $200 \, m/s$,then its potential energy is .......... $MJ$.

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

The energy required to take a satellite to a height $h$ above the Earth's surface (radius of Earth $R = 6.4 \times 10^3 \, km$) is $E_1$,and the kinetic energy required for the satellite to be in a circular orbit at this height is $E_2$. The value of $h$ for which $E_1 = E_2$ is:

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

Two satellites $A$ and $B$ having masses in the ratio $4: 3$ are revolving in circular orbits of radii $3r$ and $4r$ respectively around the earth. The ratio of total mechanical energy of $A$ to $B$ is.

The total energy of a satellite in a circular orbit at a distance $(R+h)$ from the centre of the Earth varies as [ $R$ is the radius of the Earth and $h$ is the height of the orbit from Earth's surface].