Understand that orbital period depends only on semi-major axis (Kepler's third law) — not on eccentricity — while eccentricity alone controls how much the orbit's closest and farthest points differ from the average radius.
Perigee
7000 kmApogee
7000 kmKepler's third law: T = 2π·√(a³/μ)Perigee: r_p = a·(1 − e)Apogee: r_a = a·(1 + e)Keep eccentricity at 0. Confirm perigee and apogee are exactly equal — a perfect circle.
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