ElementDelaunay#

class ansys.stk.core.stkobjects.astrogator.ElementDelaunay#

Delaunay elements.

Overview#

Properties

`mean_anomaly`	Get or set the angle from the eccentricity vector to a position vector where the satellite would be if it were always moving at its average angular rate (l). Uses Angle Dimension.
`arg_of_periapsis`	Get or set the angle from the ascending node to the eccentricity vector (lowest point of orbit) measured in the direction of the satellite’s motion and in the orbit plane (g). Uses Angle Dimension.
`raan`	Get or set the angle from the inertial X axis to the ascending node measured in a right-handed sense about the inertial Z axis in the equatorial plane (h). Uses Angle Dimension.
`delaunay_l`	Related to the two-body orbital energy. Defined as sqrt(GM * a). Uses AreaRate Dimension.
`semimajor_axis`	One-half the distance along the long axis of the elliptical orbit. Uses Distance Dimension.
`delaunay_g`	Get or set the magnitude of the orbital angular momentum. Defined as sqrt(GM * p). Uses AreaRate Dimension.
`semilatus_rectum`	Semi-latus Rectum. Uses Distance Dimension.
`delaunay_h`	Get or set the Z component of the orbital angular momentum. Defined as G cos(inc). Uses AreaRate Dimension.
`inclination`	Get or set the angle between the angular momentum vector (perpendicular to the plane of the orbit) and the inertial Z axis. Uses Angle Dimension.

from ansys.stk.core.stkobjects.astrogator import ElementDelaunay

property ElementDelaunay.mean_anomaly: Any#: Get or set the angle from the eccentricity vector to a position vector where the satellite would be if it were always moving at its average angular rate (l). Uses Angle Dimension.

property ElementDelaunay.arg_of_periapsis: Any#: Get or set the angle from the ascending node to the eccentricity vector (lowest point of orbit) measured in the direction of the satellite’s motion and in the orbit plane (g). Uses Angle Dimension.

property ElementDelaunay.raan: Any#: Get or set the angle from the inertial X axis to the ascending node measured in a right-handed sense about the inertial Z axis in the equatorial plane (h). Uses Angle Dimension.

property ElementDelaunay.delaunay_l: float#: Related to the two-body orbital energy. Defined as sqrt(GM * a). Uses AreaRate Dimension.

property ElementDelaunay.semimajor_axis: float#: One-half the distance along the long axis of the elliptical orbit. Uses Distance Dimension.

property ElementDelaunay.delaunay_g: float#: Get or set the magnitude of the orbital angular momentum. Defined as sqrt(GM * p). Uses AreaRate Dimension.

property ElementDelaunay.semilatus_rectum: float#: Semi-latus Rectum. Uses Distance Dimension.

property ElementDelaunay.delaunay_h: float#: Get or set the Z component of the orbital angular momentum. Defined as G cos(inc). Uses AreaRate Dimension.

property ElementDelaunay.inclination: Any#: Get or set the angle between the angular momentum vector (perpendicular to the plane of the orbit) and the inertial Z axis. Uses Angle Dimension.