Package 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

Modifier and Type	Method	Description
double[]	computeDerivatives(SpacecraftState state)	Compute differential equations for main state.
default void	init(SpacecraftState initialState, AbsoluteDate target)	Initialize the equations at the start of propagation.

Method Detail

init

default void init(SpacecraftState initialState,
                  AbsoluteDate target)

Initialize the equations at the start of propagation. This method will be called before any calls to computeDerivatives(SpacecraftState).

The default implementation of this method does nothing.

Parameters:

initialState - initial state information at the start of propagation.

target - date of propagation. Not equal to initialState.getDate().

computeDerivatives

double[] computeDerivatives(SpacecraftState state)

Compute differential equations for main state.

Parameters:

state - current state

Returns:

derivatives of main state