Package org.orekit.propagation.integration

Interface FieldAbstractIntegratedPropagator.MainStateEquations<T extends org.hipparchus.RealFieldElement<T>>

Enclosing class:

FieldAbstractIntegratedPropagator<T extends org.hipparchus.RealFieldElement<T>>

public static interface FieldAbstractIntegratedPropagator.MainStateEquations<T extends org.hipparchus.RealFieldElement<T>>

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

Method Summary

Modifier and Type	Method	Description
T[]	computeDerivatives(FieldSpacecraftState<T> state)	Compute differential equations for main state.
void	init(FieldSpacecraftState<T> initialState, FieldAbsoluteDate<T> target)	Initialize the equations at the start of propagation.

Method Detail

init

void init(FieldSpacecraftState<T> initialState,
          FieldAbsoluteDate<T> target)

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

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

T[] computeDerivatives(FieldSpacecraftState<T> state)

Compute differential equations for main state.

Parameters:

state - current state

Returns:

derivatives of main state