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For a given orbit, the orbital elements are h = 112 km2/s, e = 1.6, i...

For a given orbit, the orbital elements are h = 112 km2/s, e = 1.6, i = 30 degrees, omega = 40 degrees, w = 60 degrees, and v = 30 degrees.

i. Find the position vector, r, and velocity vector, v, of a satellite in the perifocal coordinate system.

ii. Convert the position and velocity vectors obtained in part i to the geocentric-equatorial coordinate system

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