The orbital period of a geostationary satellite is (in $\,h$)

$A$ satellite $S$ is moving in an elliptical orbit around the Earth. The mass of the satellite is very small compared to the mass of the Earth.

$A$ body is moving in a low circular orbit about a planet of mass $M$ and radius $R$. The radius of the orbit can be taken to be $R$ itself. Then the ratio of the speed of this body in the orbit to the escape velocity from the planet is

Consider two satellites $S_{1}$ and $S_{2}$ with periods of revolution $1\, hr$ and $8\, hr$ respectively,revolving around a planet in circular orbits. The ratio of the angular velocity of satellite $S_{1}$ to the angular velocity of satellite $S_{2}$ is:

Assuming that the earth is revolving around the sun in a circular orbit of radius $R$,the angular momentum is directly proportional to $R^{n}$. The value of $n$ is

$A$ satellite is revolving around a planet in a circular orbit close to its surface. Let $\rho$ be the mean density and $R$ be the radius of the planet. Then the period of the satellite is ($G=$ universal constant of gravitation).