Satellite: Astrogator Maneuver Ephemeris Block Initial: 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. |
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