pymgp.tleorb.tle2orb#

pymgp.tleorb.tle2orb(tle, t, propagation='J2')[source]#

Compute satellite orbital elements from NORAD Two Line Elements.

Compute satellite orbital elements from NORAD Two Line Elements at times t, using basic orbit propagation (with J2).

Parameters:
tlenamed tuple

Named tuple with two line elements for a single satellite

tarray_like, float, with shape (n,)

Array with serial date numbers in UT1.

propagation{‘J2’, ‘NOJ2’, ‘SGP4’}, optional

Propagation method to for the orbital elements:

J2    Include secular effects of J2, but nothing else (default). This gives
      acceptable results for plotting purposes and planning computations
NOJ2  Ignores effect of J2 on orbit propagation. Should only be used for 
      educational purposes
SGP4  SGP4 orbit propagator of NORAD. Not implemented yet
Returns:
orbndarray with shape (n,6)

Array with rows of orbital elements ‘[semi-major axis (m), eccentricity (-), inclination (rad), right ascension of ascending node (rad), argument of periapsis (rad]) and true anomaly (rad)]’ at time ‘t[i]’.

See also

tleget, tleread, tle2vec
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