Aerospace Engineering > GATE 2011 > Orbital Parameters
An elliptic orbit has its perigee at 400 km above the Earth's surface and apogee at 3400 km above
the Earth's surface. For this orbit, the eccentricity and semi-major axis respectively are (assume
radius of Earth = 6400 km)
the Earth's surface. For this orbit, the eccentricity and semi-major axis respectively are (assume
radius of Earth = 6400 km)
Correct : a
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