Question: MATLAB orbital elements problem. Find the classical orbital elements: a, e, i, , , , given the following position and velocity (inertial coordinates in geocentric

MATLAB orbital elements problem.

Find the classical orbital elements: a, e, i, , , , given the following position and velocity (inertial coordinates in geocentric equatorial frame) (for Earth, = 398600 km3/s2 ) MATLAB orbital elements problem. Find the classical orbital elements: a, e, i,

Use MATLAB to do the calculations. Draw a sketch of the orbit. Is the orbit circular or eliptical? Is the orbit prograde or retrograde?

2625 i + 15871 j + 3970 k km -2.677-0.6915 j + 4.160 k km/s 2625 i + 15871 j + 3970 k km -2.677-0.6915 j + 4.160 k km/s

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