SpacecraftCovariance.SetCovarianceInFrame(String, Matrix) Method

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Description

Sets the covariance of the spacecraft state in the inertial reference frame, after converting from the specified attitude reference frame. This method is only used with the Cartesian element set.

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

SpacecraftCovariance.SetCovarianceInFrame(	String inputReferenceFrame,
	Matrix inputCovarianceInFrame)

Arguments

inputReferenceFrame

Description:

The attitude reference frame of the input covariance matrix.

Valid Values:

Value	Label
"ICRF"	ICRF
"VNB"	VNB
"LVLH"	LVLH
"GEODETIC"	GEODETIC
"UVW"	UVW
"RIC"	RIC

inputCovarianceInFrame
Description:	The input covariance matrix, in the user-specfied attitude reference frame.

Syntax

mySpacecraftCovariance1.SetCovarianceInFrame(myString1, myMatrix1);