PropagatorSGP4Segment#
- class ansys.stk.core.stkobjects.PropagatorSGP4Segment#
SGP4 propagator segment.
Overview#
Catalog number of the spacecraft, if created by a 2-line element set. |
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Rev. Number. Dimensionless. |
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Universal date and time at which the specified orbit elements are true. Dimensionless. |
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Angle between the angular momentum vector (perpendicular to the plane of the orbit) and the inertial Z-axis. Uses Angle Dimension. |
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Angle from the ascending node to the eccentricity vector (lowest point of orbit) measured in the direction of the satelliteβs motion. Uses Angle Dimension. |
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Angle from the inertial X-axis to the ascending node. Uses Angle Dimension. |
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Value between 1 and 0 representing the ellipticality of the orbit. Dimensionless. |
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A measure of the osculating period of the orbit, expressed as an angular rate. Uses AngleRate Dimension. |
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Angle from the eccentricity vector to a position vector where the satellite would be if it were always moving at its average angular rate. Uses Angle Dimension. |
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First time derivative of mean motion. Dimensionless. |
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Second time derivative of mean motion. Dimensionless. |
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Drag term for the satellite. |
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One-letter classification indicator. U - Unclassified, C - Classified, S - Secret. |
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International designation of the satellite. |
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Method used to switch between element sets. |
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How far apart the satellites are when switching occurs. |
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Get or set the time of the switch between one element set and a second set. Not used when the Switching Method is Disabled. |
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Enable/disable the segment. |
Import detail#
from ansys.stk.core.stkobjects import PropagatorSGP4Segment
Property detail#
- property PropagatorSGP4Segment.ssc_number: str#
Catalog number of the spacecraft, if created by a 2-line element set.
- property PropagatorSGP4Segment.epoch: float#
Universal date and time at which the specified orbit elements are true. Dimensionless.
- property PropagatorSGP4Segment.inclination: Any#
Angle between the angular momentum vector (perpendicular to the plane of the orbit) and the inertial Z-axis. Uses Angle Dimension.
- property PropagatorSGP4Segment.argument_of_periapsis: Any#
Angle from the ascending node to the eccentricity vector (lowest point of orbit) measured in the direction of the satelliteβs motion. Uses Angle Dimension.
- property PropagatorSGP4Segment.right_ascension_ascending_node: Any#
Angle from the inertial X-axis to the ascending node. Uses Angle Dimension.
- property PropagatorSGP4Segment.eccentricity: float#
Value between 1 and 0 representing the ellipticality of the orbit. Dimensionless.
- property PropagatorSGP4Segment.mean_motion: Any#
A measure of the osculating period of the orbit, expressed as an angular rate. Uses AngleRate Dimension.
- property PropagatorSGP4Segment.mean_anomaly: Any#
Angle from the eccentricity vector to a position vector where the satellite would be if it were always moving at its average angular rate. Uses Angle Dimension.
- property PropagatorSGP4Segment.mean_motion_dot: float#
First time derivative of mean motion. Dimensionless.
- property PropagatorSGP4Segment.motion_dot_dot: float#
Second time derivative of mean motion. Dimensionless.
- property PropagatorSGP4Segment.classification: str#
One-letter classification indicator. U - Unclassified, C - Classified, S - Secret.
- property PropagatorSGP4Segment.international_designator: str#
International designation of the satellite.
- property PropagatorSGP4Segment.switching_method: PropagatorSGP4SwitchMethod#
Method used to switch between element sets.
- property PropagatorSGP4Segment.range: float#
How far apart the satellites are when switching occurs.