org.orekit.propagation.integration

Interface AbstractIntegratedPropagator.MainStateEquations

Enclosing class:

AbstractIntegratedPropagator

public static interface AbstractIntegratedPropagator.MainStateEquations

Differential equations for the main state (orbit, attitude and mass).

Method Summary

Methods

Modifier and Type	Method and Description
double[]	computeDerivatives(SpacecraftState state) Compute differential equations for main state.

Method Detail

computeDerivatives

double[] computeDerivatives(SpacecraftState state)
                            throws OrekitException

Compute differential equations for main state.

Parameters:

state - current state

Returns:

derivatives of main state

Throws:

OrekitException - if differentials cannot be computed