A satellite, moving in an elliptical orbit, is 306 km above Earth's surface at its farthest...
A satellite, moving in an elliptical orbit, is 306 km above Earth's surface at its farthest point and 168 km above at its closest point. Calculate (a) the semimajor axis (in km) and (b) the eccentricity of the orbit.
Homework Answers
a = semimajot axis
e = eccentricity
Rf = farthest point = 306
Rc = closest point = 168
Rf = a(1 + e) eq-1
Rc = a(1 - e) eq-2
Rf/Rc = (1 + e) / (1 - e)
306 / 168 = (1 + e) / (1 - e)
e = 0.291
using eq-1
306 = a(1 + 0.291)
a = 237.03 km
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