computeGroundTrack

computes the ground track of a satellite given including the nodal precession (unoptimized version)

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Declaration

 [lat, lon] = computeGroundTrack(semi_major_axis, e, incl, RAAN, omega, M0, t)

Parameters

• semi_major_axis Semi-major axis [km]
• e Eccentricity (0 for circular, >0 for elliptical)
• incl Inclination [degrees]
• RAAN_0 Right Ascension of Ascending Node [rad]
• argPerigee Argument of perigee [rad]
• M0 Initial mean anomaly at t = 0 [rad]
• t Time vector [s]

Returns

• lat Latitude (deg) vector corresponding to times in t
• lon Longitude (deg) vector corresponding to times in t

Discussion