A satellite is launched into a circular orbit close to the earth's surface. What additional velocity has new to be imparted to the satellite in the orbit to overcome the gravitational pull ?

Explanation

To solve the problem of determining the additional velocity that needs to be imparted to a satellite in a circular orbit close to the Earth's surface in order to overcome gravitational pull, we can follow these steps:

### Step 1: Understand the concept of orbital velocity
The orbital velocity (\(v_o\)) of a satellite in a circular orbit close to the Earth's surface can be calculated using the formula:
\[ v_o = \sqrt{g \cdot r} \]
where \(g\) is the acceleration due to gravity (approximately \(9.8 \, \text{m/s}^2\)) and \(r\) is the radius of the Earth (approximately \(6400 \times 10^3 \, \text{m}\)).
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