SpacecraftODProperties.STM Property 
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DescriptionThis 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
where
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.
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