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 Details

    • 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