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A spacecraft in an elliptical orbit around earth has perigee radius of 7,900 km and apogee radius of 73,000 km, what is its semi-major axis?

A spacecraft in an elliptical orbit around earth has perigee radius of 7,900 km and apogee radius of 73,000 km, what is its semi-major axis? Correct Answer 40,450 km

Given, Apogee radius (ra) = 73,000 km Perigee radius (rp) = 7,900 km Semi-major axis (a) = (ra + rp) / 2 = (73,000 + 7,900) / 2 = 40,450 km

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