An artificial satellite is in an elliptical orbit around the earth with aphelion of `6R` and perihelion of `2R` where `R` is radius of the earth `=6400km`. Calculate the eccentricity of the elliptical orbit.

Explanation

To find the eccentricity of the elliptical orbit of the artificial satellite, we can follow these steps:

### Step 1: Understand the definitions
- **Aphelion (rA)**: The farthest point from the Earth in the orbit, given as \( r_A = 6R \).
- **Perihelion (rP)**: The closest point to the Earth in the orbit, given as \( r_P = 2R \).
- **Semi-major axis (A)**: The average of the aphelion and perihelion distances.

### Step 2: Write the formulas for aphelion and perihelion
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