A satellite, moving in an elliptical orbit, is 1440 km above Earth's surface at its farthest point and 180 km above at its closest point. Calculate (a) the semimajor axis and (b) the eccentricity of the orbit.

Explanation

To solve the problem of finding the semi-major axis and eccentricity of a satellite's elliptical orbit, we will follow these steps:

### Given Data:
- Height at the farthest point (apogee) = 1440 km
- Height at the closest point (perigee) = 180 km
- Radius of the Earth (R) = 6378 km

### Step 1: Calculate the Distances from the Center of the Earth
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