Initial Conditions
An orbit may be defined given a state vector and reference
frame. Within eom, state vectors are composed of six parameters and an
associated epoch time. Using this definition, the state vector alone
typically will not be sufficient to accurately propagate an orbit. For
SP methods, additional information about how the state vector was fit will be
required
(Propagator Configuration).
State Vector Type
The state vector type indicates the coordinate system used to
specify state vector components.
CART
Cartesian coordinates composed of three position and three velocity
elements.
KEP_T
Keplerian elements composed of semimajor axis, eccentricity,
inclination, right ascension of the ascending node, argument of perigee,
and true anomaly. Only earth centered inertial reference frames may be
used with this option.
AngleUnits Degrees;
# Default units of DU for semimajor axis
# a e i o w v
KEP_T GCRF 4.1632 0.741 63.4 345.0 270.0 0.0;
Reference Frame
Not all settings taking a reference frame type accept all available
reference frames.
GCRF
Cartesian geocentric celestial reference frame
ITRF
Cartesian international terrestrial reference frame