Package org.orekit.propagation.integration

Interface FieldAbstractIntegratedPropagator.MainStateEquations<T extends CalculusFieldElement<T>>

Type Parameters:
T - type of the field element
Enclosing class:
FieldAbstractIntegratedPropagator<T extends CalculusFieldElement<T>>
public static interface FieldAbstractIntegratedPropagator.MainStateEquations<T extends CalculusFieldElement<T>>
Differential equations for the main state (orbit, attitude and mass).

  • Method Details

    • 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