OrbitStateClassical#

class ansys.stk.core.stkobjects.OrbitStateClassical#

Bases: IOrbitState

Classical (Keplerian) coordinate type.

Overview#

Properties

`coordinate_system_type`	Coordinate system being used.
`coordinate_system`	Get the coordinate system and coordinate epoch.
`size_shape_type`	Get or set the pair of elements used for specifying orbit size and shape.
`size_shape`	Get the size and shape of the orbit.
`orientation`	Get the orbit orientation.
`location_type`	Get or set the element used for specifying spacecraft location in the orbit at epoch.
`location`	Get the location of the spacecraft in the orbit at epoch.
`supported_coordinate_system_types`	Return an array of supported coordinate system types.
`state_epoch`	Smart epoch component allows the user to configure the state epoch explicitly or implicitly (using a pre-defined or custom time instant component).

Examples#

Set the initial state of a satellite and propagate

# Satellite satellite: Satellite object
keplerian = satellite.propagator.initial_state.representation.convert_to(OrbitStateType.CLASSICAL)
keplerian.size_shape_type = ClassicalSizeShape.ALTITUDE
keplerian.location_type = ClassicalLocation.TRUE_ANOMALY
keplerian.orientation.ascending_node_type = OrientationAscNode.LONGITUDE_ASCENDING_NODE

# Assign the perigee and apogee altitude values:
keplerian.size_shape.perigee_altitude = 500  # km
keplerian.size_shape.apogee_altitude = 600  # km

# Assign the other desired orbital parameters:
keplerian.orientation.inclination = 90  # deg
keplerian.orientation.argument_of_periapsis = 12  # deg
keplerian.orientation.ascending_node.value = 24  # deg
keplerian.location.value = 180  # deg

# Apply the changes made to the satellite's state and propagate:
satellite.propagator.initial_state.representation.assign(keplerian)
satellite.propagator.propagate()

Import detail#

from ansys.stk.core.stkobjects import OrbitStateClassical

Property detail#

property OrbitStateClassical.coordinate_system_type: CoordinateSystem#: Coordinate system being used.

property OrbitStateClassical.coordinate_system: OrbitStateCoordinateSystem#: Get the coordinate system and coordinate epoch.

property OrbitStateClassical.size_shape_type: ClassicalSizeShape#: Get or set the pair of elements used for specifying orbit size and shape.

property OrbitStateClassical.size_shape: IClassicalSizeShape#: Get the size and shape of the orbit.

property OrbitStateClassical.orientation: ClassicalOrientation#: Get the orbit orientation.

property OrbitStateClassical.location_type: ClassicalLocation#: Get or set the element used for specifying spacecraft location in the orbit at epoch.

property OrbitStateClassical.location: IClassicalLocation#: Get the location of the spacecraft in the orbit at epoch.

property OrbitStateClassical.supported_coordinate_system_types: list#: Return an array of supported coordinate system types.

property OrbitStateClassical.state_epoch: ITimeToolInstantSmartEpoch#: Smart epoch component allows the user to configure the state epoch explicitly or implicitly (using a pre-defined or custom time instant component).