A satellite is in an elliptical orbit around the earth with aphelion of `6 R` and perihelion of `2 R` where `R = 6400 km` is the radius of the earth. Find accentricity of the orbit. Find the velocity of the satellite at apogee and perigee. What should be done if this satellite has to be transferred to a circular orbit of radius `6R`? `[G = 6.67 xx 10^(-11) SI` units and `M = 6 xx 10^(24) kg]`

Explanation

To solve the problem step by step, we will follow the given requirements:

### Step 1: Find the Eccentricity of the Orbit

The eccentricity \( e \) of an elliptical orbit can be calculated using the formula:

\[
e = \frac{R_a - R_p}{R_a + R_p}
...