Description
Calculates and returns the covariance of a distribution of orbit states in the specified element set defined in the Spacecraft in the provided Formation. Also, populates the meanState argument with the computed mean state.
Timing Precision Mode
This page describes functionality in nanosecond timing precision mode.
Click here to see the documentation for this object in millisecond timing precision mode.
Method Signature
CovarianceUtilities.CalculateMeanAndCovariance(
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Formation formation,
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String covarianceElementSet,
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Array meanState)
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Arguments
formation
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Description:
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Formation object containing the states to use when computing the covariance.
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covarianceElementSet
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Description:
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Element set definition for which the covariance will be computed.
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Valid Values:
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Value
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Label
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"Cartesian"
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Cartesian Elements
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"Equinoctial"
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Equinoctial Elements
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"SGP4Equinoctial"
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SGP4Equinoctial Elements
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"NoradEquinoctial"
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NoradEquinoctial Elements (deprecated, use SGP4Equinoctial instead)
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meanState
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Description:
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The computed mean state associated with the covariance matrix.
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Return Value
Returns a covariance matrix.
Syntax
myMatrix1 = CovarianceUtilities.CalculateMeanAndCovariance(myFormation1, myString1, myArray1);
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See also
CovarianceUtilities Object
CovarianceUtilities.CalculateMeanAndCovariance
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