For a satellite orbiting very close to the surface of the Earth,what is the relationship between its escape velocity $(v_{e})$ and its orbital velocity $(v_{0})$?
- A$v_{e} = v_{0}$
- B$v_{e} = \sqrt{2} v_{0}$
- C$v_{e} = 2 v_{0}$
- D$v_{e} = \frac{v_{0}}{\sqrt{2}}$
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