computeGroundTrackCircularOrbit

computes the ground track assuming a circular orbit

Declaration 

 [lat, lon] = computeGroundTrackCircularOrbit(semi_major_axis, e, incl, RAAN_0, 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]
  • omega 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