Satellite: Astrogator Maneuver Ephemeris Block Final:
Equinoctial Elems
Calc Objects for the ephemeris of the
object, expressed in equinoctial elements. Each Calc Object allows
a choice of element type (Osculating elements, Kozai-Izsak Mean
elements, Brouwer-Lyddane Mean elements using only short period
terms, and Brouwer-Lyddane Mean elements using both short and long
period terms). The default is osculating. Each Calc Object allows a
choice of coordinate systems. The default is Earth Centered
Inertial.
| Name |
Dimension |
Type |
Description |
| Time |
DateFormat |
Real Number |
Time. |
| Equinoctial_h |
Unitless |
Real Number |
h = eccentricity *
sin(right_ascension_of_the_ascending_node + argument_of_periapse).
Equinoctial elements h and k together describe the shape of the
orbit and the location of the periapse. |
| Equinoctial_k |
Unitless |
Real Number |
k = eccentricity *
cos(right_ascension_of_the_ascending_node + argument_of_periapse).
Equinoctial elements h and k together describe the shape of the
orbit and the location of the periapse. |
| Equinoctial_p |
Unitless |
Real Number |
p = tan(inclination/2) *
sin(right_ascension_of_the_ascending_node). Equinoctial elements p
and q together describe the orientation of the orbit plane.
Retrograde orbits have a singularity at zero inclination, and
posigrade orbits have a singularity at 180 deg inclination. |
| Equinoctial_q |
Unitless |
Real Number |
q = tan(inclination/2) *
cos(right_ascension_of_the_ascending_node). Equinoctial elements p
and q together describe the orientation of the orbit plane.
Retrograde orbits have a singularity at zero inclination, and
posigrade orbits have a singularity at 180 deg inclination. |
| Mean_Longitude |
AngleUnit |
Real Number |
Not defined for this class of object. |
STK Programming Interface 11.0.1