SpacecraftCovariance.SetStateSigmasInFrame Method

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.

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.

Overload List

Signatures	Return Value	Description
SpacecraftCovariance.SetStateSigmasInFrame(CoordinateSystem coordinate_system, Array inputStateSigmasInFrame)	None	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.
SpacecraftCovariance.SetStateSigmasInFrame(String inputReferenceFrame, Array inputStateSigmasInFrame)	None	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.

SpacecraftCovariance.SetStateSigmasInFrame Method

Description

Overload List