The orbital velocity of an artificial satellite in a circular orbit just above the earth's surface is v0. For a satellite orbiting at an altitude of half of the earth's radius, the orbital velocity is
1
\(\left(\sqrt{\left(\frac{2}{3}\right)}\right) \mathrm{v}_{0}\)
2
\(\rm \frac{2}{3} v_{0}\)
3
\(\rm \frac{3}{2} v_{0}\)
4
\(\sqrt{\left(\frac{3}{2}\right)} \mathrm{v}_{0}\)