A satellite is launched from a point close to the surface of the earth (radius R) with a velocity $$v = \sqrt{1.5}\ v_0$$, where $$v_0$$ is the velocity in a circular orbit. If the initial velocity imparted to the satellite is horizontal, the maximum distance from the surface of the earth during its revolution is

A

R

B

2R

C

3R

D

4R