$A$ 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

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

$A$ launching vehicle carrying an artificial satellite of mass $m$ is set for launch on the surface of the earth of mass $M$ and radius $R$. If the satellite is intended to move in a circular orbit of radius $7R$,the minimum energy required to be spent by the launching vehicle on the satellite is ($G$ is the gravitational constant).

Given below are two statements:
Statement $I:$ If $E$ be the total energy of a satellite moving around the earth,then its potential energy will be $\frac{E}{2}$.
Statement $II:$ The kinetic energy of a satellite revolving in an orbit is equal to the half the magnitude of total energy $E$.
In the light of the above statements,choose the most appropriate answer from the options given below.

$A$ 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 $9 R_E$?

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 $2R$?