The mean equator mean equinox coordinate
system evaluated at the epoch of the object.
| Name |
Dimension |
Type |
Description |
| Time |
DateFormat |
Real Number |
Time. |
| Semi-Major Axis |
DistanceUnit |
Real Number |
A measure of the size of the orbit. Orbits with
eccentricity less than 1 are ellipses, with major and minor axes
identifying the symmetry axes of the ellipse, the major axis being
the longer one. The value is half the length of the major
axis. |
| e * sin(omegaBar) |
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. |
| e * cos(omegaBar) |
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. |
| tan(i/2) * sin(raan) |
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. |
| tan(i/2) * cos(raan) |
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 Lon |
LongitudeUnit |
Real Number |
mean longitude is the sum:
right_ascension_of_the_ascending_node + argument_of_periapse +
mean_anomaly. A measure of the location within the orbit. |
| Direction |
Unitless |
Text |
The type of equinoctial elements. Retrograde has
its singularity at an inclination of 0 deg. Posigrade has its
singularity at an inclination of 180 deg. |
| Semi-Major
Axis Rate |
Rate |
Real Number or Text |
Rate of change of semi-major axis. Computed by
applying the variation of parameters equations of motion to the
perturbative acceleration. |
| e * sin(omegaBar) Rate |
Unitless Per Time |
Real Number or Text |
Rate of change of h. Computed by applying the
variation of parameters equations of motion to the perturbative
acceleration. |
| e * cos(omegaBar) Rate |
Unitless Per Time |
Real Number or Text |
Rate of change of k. Computed by applying the
variation of parameters equations of motion to the perturbative
acceleration. |
| tan(i/2) * sin(raan) Rate |
Unitless Per Time |
Real Number or Text |
Rate of change of p. Computed by applying the
variation of parameters equations of motion to the perturbative
acceleration. |
| tan(i/2) * cos(raan) Rate |
Unitless Per Time |
Real Number or Text |
Rate of change of q. Computed by applying the
variation of parameters equations of motion to the perturbative
acceleration. |
| Mean Lon Rate |
AngleRateUnit |
Real Number or Text |
Rate of change of mean longitude including the
osculating mean motion. Computed by applying the variation of
parameters equations of motion to the perturbative
acceleration. |
| Mean Lon
Perturb Rate |
AngleRateUnit |
Real Number or Text |
Rate of change of mean longitude excluding the
osculating mean motion. Computed by applying the variation of
parameters equations of motion to the perturbative
acceleration. |
| Mean Motion |
AngleRateUnit |
Real Number |
A measure of the osculating period of the orbit,
expressed as an angular rate. The value is 2pi rad /
orbit_period. |