What 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 $2R$?

In a satellite,if the time of revolution is $T$,then the potential energy $(PE)$ is proportional to ..........

$A$ $400 \; kg$ satellite is in a circular orbit of radius $2 R_{E}$ about the Earth. How much energy is required to transfer it to a circular orbit of radius $4 R_{E}$? What are the changes in the kinetic and potential energies?

$A$ satellite of $10^3 \text{ kg}$ mass is revolving in a circular orbit of radius $2R$. If $\frac{10^4 R}{6} \text{ J}$ of energy is supplied to the satellite,it would revolve in a new circular orbit of radius: (use $g = 10 \text{ m/s}^2$,$R = \text{radius of earth}$) (in $R$)

In an orbit,if the time of revolution of a satellite is $T$,then the potential energy $(PE)$ is proportional to:

Two identical satellites $A$ and $B$ are orbiting the Earth at heights of $R$ and $2R$ respectively,where $R$ is the radius of the Earth. The ratio of the kinetic energy of $A$ to that of $B$ is: