|Code Listing by Darin Koblick|
Convert ECI (CIS, Epoch J2000.0) Coordinates to WGS 84 (CTS, ECEF) Coordinates. This function has been vectorized for speed.
Example Function Call:
>> [r_ECEF v_ECEF] = ECItoECEF(JD,r_ECI,v_ECI);
JD is the Julian Date vector [1 x N] (units are in days)
r_ECI is the position vector [3 x N] (any units are permitted)
v_ECI is the velocity vector [3 x N] (any units are permitted)
Convert orbital elements to a state vector, or a state vector back to orbital elements.
Most readily available Keplerian orbital element conversion utilities do not address circular or parabolic orbits. This set of routines will address the...
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