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A satellite, moving in an elliptical orbit, is 360 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.

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vladvturin2017
Take the radius of the Earth 6 370 km.Then:
The semimajor axis:a = 6 370 + 360 = 6 730 km
Semiminor axis:b = 6 370 + 180 = 6 550 km
Eccentricity:ε = √ (a2+b2) / a = √ (6 7302+65502) / 6 730 ≈ 1.4

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