Description
Sets the Cartesian state of the CelestialObject in the specified frame, referenced from the CentralBody. This requires that the CelestialObject uses a TwoBody propagator, and will error if other propagators are used.
Timing Precision Mode
This page describes functionality in millisecond timing precision mode. Millisecond timing precision mode is deprecated and will be removed in a future release. We recommend that you migrate your Mission Plans to nanosecond timing precision mode.
Click here to see the documentation for this object in nanosecond timing precision mode.
Method Signature
Arguments
epoch
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Description:
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The epoch at which the CelestialObject's state is evaluated.
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state
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Description:
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array containing the Cartesian Elements
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Required Size:
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6
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referenceFrame
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Description:
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The reference frame in which the state elements will be evaluated.
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Valid Values:
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Value
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Label
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1
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ICRF
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2
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Mean of J2000 Earth Ecliptic
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3
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Mean of 1950 Earth Equator
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4
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Mean of Date Earth Equator
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5
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True Equator Mean Equinox
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6
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True of Date Earth Equator
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7
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TIRF
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8
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Earth Fixed
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9
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Moon Fixed (Principle Axis Rotating)
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10
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Moon Principle Axis - Inertial at J2000
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11
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Moon Principle Axis - Inertial at Epoch
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12
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Moon Mean Earth - Rotating
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13
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Moon Mean Earth - Inertial at J2000
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14
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Moon Mean Earth - Inertial at Epoch
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15
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CIRF
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16
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Specify any CelestialObject.ReferenceFrameId
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Syntax
myCelestialObject1.SetCartesianState(myVariable1, myArray1, myVariable2);
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See also
CelestialObject Object
CelestialObject.SetCartesianState
CelestialObjects Guide
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