SpacecraftCovariance.SetStateSigmasInFrame(String, Array) Method

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Description

Sets the Spacecraft covariance, converting from the specified input Attitude Reference Frame to the ICRF. The input sigmas are used as the Square Root of the diagonal of the input covariance. This method only works in conjunction 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.SetStateSigmasInFrame(	String inputReferenceFrame,
	Array inputStateSigmasInFrame)

Arguments

inputReferenceFrame

Description:

The attitude reference frame of the input state sigmas array.

Valid Values:

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

inputStateSigmasInFrame
Description:	The input state sigmas array, in the user-specfied attitude reference frame.
Required Size:	3 to 8

Syntax

mySpacecraftCovariance1.SetStateSigmasInFrame(myString1, myArray1);