A satellite moves in a circular orbit around the earth at height `(R_(e))//2` from earth's surface where `R_(e)` is the radius of the earth. Calculate its period of revolution. Given `R = 6.38 xx 10^(6) m`.

Two identical satellites are orbitting in circular orbits around the earth at heights R and 3R respectively from the surface of the earth. The radius of the earth is R. How do you compare the periods of revolution of these two satellites?

A satellite is in an elliptical orbit around the earth with aphelion of 6R_E and perihelion of 3R_E , where R_E is the radius of the earth. The eccentricity of the orbit is

Two identical satellites are orbitting in circular orbits around the earth at heights R and 3R respectively from the surface of the earth. The radius of the earth is R. Define orbital velocity.

An earth satellite of mass m revolves in a circular orbit at a height h from the surface of the earth. R is the radius of the earth and g is acceleration due to gravity at the surface of the earth. The velocity of the satellite in the orbit is given by

An earth satellite of mass m revolves in a circular orbit at a height h from the surface of the earth. R is the radius of the earth and g is acceleration due to gravity at the surface of the earth. The velocity of the satellite in the orbit is given by