Class KeplerianPropagator

    • Constructor Detail

      • KeplerianPropagator

        public KeplerianPropagator​(Orbit initialOrbit)
        Build a propagator from orbit only.

        The central attraction coefficient μ is set to the same value used for the initial orbit definition. Mass and attitude provider are set to unspecified non-null arbitrary values.

        Parameters:
        initialOrbit - initial orbit
        See Also:
        KeplerianPropagator(Orbit, AttitudeProvider)
      • KeplerianPropagator

        public KeplerianPropagator​(Orbit initialOrbit,
                                   double mu)
        Build a propagator from orbit and central attraction coefficient μ.

        Mass and attitude provider are set to unspecified non-null arbitrary values.

        Parameters:
        initialOrbit - initial orbit
        mu - central attraction coefficient (m³/s²)
        See Also:
        KeplerianPropagator(Orbit, AttitudeProvider, double)
      • KeplerianPropagator

        public KeplerianPropagator​(Orbit initialOrbit,
                                   AttitudeProvider attitudeProv)
        Build a propagator from orbit and attitude provider.

        The central attraction coefficient μ is set to the same value used for the initial orbit definition. Mass is set to an unspecified non-null arbitrary value.

        Parameters:
        initialOrbit - initial orbit
        attitudeProv - attitude provider
      • KeplerianPropagator

        public KeplerianPropagator​(Orbit initialOrbit,
                                   AttitudeProvider attitudeProv,
                                   double mu)
        Build a propagator from orbit, attitude provider and central attraction coefficient μ.

        Mass is set to an unspecified non-null arbitrary value.

        Parameters:
        initialOrbit - initial orbit
        attitudeProv - attitude provider
        mu - central attraction coefficient (m³/s²)
      • KeplerianPropagator

        public KeplerianPropagator​(Orbit initialOrbit,
                                   AttitudeProvider attitudeProv,
                                   double mu,
                                   double mass)
        Build propagator from orbit, attitude provider, central attraction coefficient μ and mass.
        Parameters:
        initialOrbit - initial orbit
        attitudeProv - attitude provider
        mu - central attraction coefficient (m³/s²)
        mass - spacecraft mass (kg)
    • Method Detail

      • resetIntermediateState

        protected void resetIntermediateState​(SpacecraftState state,
                                              boolean forward)
        Reset an intermediate state.
        Specified by:
        resetIntermediateState in class AbstractAnalyticalPropagator
        Parameters:
        state - new intermediate state to consider
        forward - if true, the intermediate state is valid for propagations after itself
      • createHarvester

        protected AbstractMatricesHarvester createHarvester​(String stmName,
                                                            RealMatrix initialStm,
                                                            DoubleArrayDictionary initialJacobianColumns)
        Create the harvester suitable for propagator.
        Overrides:
        createHarvester in class AbstractPropagator
        Parameters:
        stmName - State Transition Matrix state name
        initialStm - initial State Transition Matrix ∂Y/∂Y₀, if null (which is the most frequent case), assumed to be 6x6 identity
        initialJacobianColumns - initial columns of the Jacobians matrix with respect to parameters, if null or if some selected parameters are missing from the dictionary, the corresponding initial column is assumed to be 0
        Returns:
        harvester to retrieve computed matrices during and after propagation