SpacecraftODProperties.STM Property



This property has been Deprecated. Please use (Spacecraft.Propagator AsType Integrator).STM instead.


Returns the State Transition Matrix. The matrix is always a square where the length of each side is determined by the total number of properties being estimated or considered.


The general definition for the State Transition Matrix that maps the covariance from one time to another is






= State Transition Matrix that maps the covariance at one time to the covariance at a later time

      = State vector containing the estimable properties of the Spacecraft object that are being estimated or considered.


This is best illustrated through a simple example.  Consider a Spacecraft for which the position components are being estimated and the other estimable properties are being ignored.  In this case, the state vector will consist of the 3 position vector components: X, Y, and Z.  The State Transition Matrix is then a 3 x 3 square matrix given by




The method used to calculate these partial derivatives is determined by the CovariancePropagationMethod property.


Timing Precision Mode

This page describes functionality in millisecond timing precision mode.




Matrix of number





myMatrix1 = mySpacecraftODProperties1.STM;


See also

SpacecraftODProperties Object

Orbit Determination Guide