Closed ronisbr closed 5 years ago
When converting from state vectors to Keplerian elements, the RAAN, argument of perigee, and true anomaly is NaN for equatorial orbits:
NaN
julia> sv_to_kepler( kepler_to_sv( Orbit(0.0, 42164e3, 0, 0, 0, 0, 0 ) ) ) Orbit ====================================== t = 0.00000 Semi-major axis = 42164.0000 km Eccentricity = 0.000000 Inclination = 0.0000 ˚ RAAN = NaN ˚ Arg. of Perigee = NaN ˚ True Anomaly = NaN ˚
Hence, the function rv_to_kepler must account for the special cases.
rv_to_kepler
When converting from state vectors to Keplerian elements, the RAAN, argument of perigee, and true anomaly is
NaN
for equatorial orbits:Hence, the function
rv_to_kepler
must account for the special cases.