SpacecraftCovariance.GetStateSigmasInFrame(String) Method

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Description

Returns an array containing the square root of the diagonal elements of the spacecraft state in 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.GetStateSigmasInFrame(

String referenceFrame)

Arguments

referenceFrame

Description:

The attitude reference frame in which the state sigmas will be expressed.

Valid Values:

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

Return Value

Type:

Array of number

The value of the state sigmas from the converted Covariance matrix.

Syntax

myArray1 = mySpacecraftCovariance1.GetStateSigmasInFrame(myString1);