Package org.orekit.propagation

Interface FieldPropagator<T extends CalculusFieldElement<T>>

    • Method Detail

      • getMultiplexer

        FieldStepHandlerMultiplexer<T> getMultiplexer()
        Get the multiplexer holding all step handlers.
        Returns:
        multiplexer holding all step handlers
        Since:
        11.0

      • getEphemerisGenerator

        FieldEphemerisGenerator<T> getEphemerisGenerator()
        Set up an ephemeris generator that will monitor the propagation for building an ephemeris from it once completed.

        This generator can be used when the user needs fast random access to the orbit state at any time between the initial and target times. A typical example is the implementation of search and iterative algorithms that may navigate forward and backward inside the propagation range before finding their result even if the propagator used is integration-based and only goes from one initial time to one target time.

        Beware that when used with integration-based propagators, the generator will store all intermediate results. It is therefore memory intensive for long integration-based ranges and high precision/short time steps. When used with analytical propagators, the generator only stores start/stop time and a reference to the analytical propagator itself to call it back as needed, so it is less memory intensive.

        The returned ephemeris generator will be initially empty, it will be filled with propagation data when a subsequent call to either propagate(target) or propagate(start, target) is called. The proper way to use this method is therefore to do: 

           FieldEphemerisGenerator<T> generator = propagator.getEphemerisGenerator();
   propagator.propagate(target);
   FieldBoundedPropagator<T> ephemeris = generator.getGeneratedEphemeris();
        Returns:
        ephemeris generator

      • getInitialState

        FieldSpacecraftState<T> getInitialState()
        Get the propagator initial state.
        Returns:
        initial state

      • resetInitialState

        void resetInitialState​(FieldSpacecraftState<T> state)
        Reset the propagator initial state.
        Parameters:
        state - new initial state to consider

      • addAdditionalStateProvider

        void addAdditionalStateProvider​(FieldAdditionalStateProvider<T> additionalStateProvider)
        Add a set of user-specified state parameters to be computed along with the orbit propagation.
        Parameters:
        additionalStateProvider - provider for additional state

      • getAdditionalStateProviders

        List<FieldAdditionalStateProvider<T>> getAdditionalStateProviders()
        Get an unmodifiable list of providers for additional state.
        Returns:
        providers for the additional states

      • isAdditionalStateManaged

        boolean isAdditionalStateManaged​(String name)
        Check if an additional state is managed.

        Managed states are states for which the propagators know how to compute its evolution. They correspond to additional states for which an additional state provider has been registered by calling the addAdditionalStateProvider method. If the propagator is an integrator-based propagator, the states for which a set of additional derivatives provider has been registered by calling the addAdditionalDerivativesProvider method are also counted as managed additional states.

        Additional states that are present in the initial state but have no evolution method registered are not considered as managed states. These unmanaged additional states are not lost during propagation, though. Their value are piecewise constant between state resets that may change them if some event handler resetState method is called at an event occurrence and happens to change the unmanaged additional state.

        Parameters:
        name - name of the additional state
        Returns:
        true if the additional state is managed

      • getManagedAdditionalStates

        String[] getManagedAdditionalStates()
        Get all the names of all managed states.
        Returns:
        names of all managed states

      • getAttitudeProvider

        AttitudeProvider getAttitudeProvider()
        Get attitude provider.
        Returns:
        attitude provider

      • setAttitudeProvider

        void setAttitudeProvider​(AttitudeProvider attitudeProvider)
        Set attitude provider.
        Parameters:
        attitudeProvider - attitude provider

      • getFrame

        Frame getFrame()
        Get the frame in which the orbit is propagated.

        The propagation frame is the definition frame of the initial state, so this method should be called after this state has been set, otherwise it may return null.

        Returns:
        frame in which the orbit is propagated
        See Also:
        resetInitialState(FieldSpacecraftState)

      • propagate

        FieldSpacecraftState<T> propagate​(FieldAbsoluteDate<T> target)
        Propagate towards a target date.

        Simple propagators use only the target date as the specification for computing the propagated state. More feature rich propagators can consider other information and provide different operating modes or G-stop facilities to stop at pinpointed events occurrences. In these cases, the target date is only a hint, not a mandatory objective.

        Parameters:
        target - target date towards which orbit state should be propagated
        Returns:
        propagated state

      • propagate

        FieldSpacecraftState<T> propagate​(FieldAbsoluteDate<T> start,
                                  FieldAbsoluteDate<T> target)
        Propagate from a start date towards a target date.

        Those propagators use a start date and a target date to compute the propagated state. For propagators using event detection mechanism, if the provided start date is different from the initial state date, a first, simple propagation is performed, without processing any event computation. Then complete propagation is performed from start date to target date.

        Parameters:
        start - start date from which orbit state should be propagated
        target - target date to which orbit state should be propagated
        Returns:
        propagated state