SpacecraftCovariance.SetStateSigmasInFrame(CoordinateSystem, 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 nanosecond timing precision mode.

Click here to see the documentation for this object in millisecond timing precision mode.

Method Signature

SpacecraftCovariance.SetStateSigmasInFrame(	CoordinateSystem coordinate_system,
	Array inputStateSigmasInFrame)

Arguments

coordinate_system
Description:	A CoordinateSystem to define the reference frame of the input state sigmas.

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

Syntax

mySpacecraftCovariance1.SetStateSigmasInFrame(myCoordinateSystem1, myArray1);