Search in sources :

Example 1 with PropagatorsParallelizer

use of org.orekit.propagation.PropagatorsParallelizer in project Orekit by CS-SI.

the class Model method value.

/**
 * {@inheritDoc}
 */
@Override
public Pair<RealVector, RealMatrix> value(final RealVector point) throws OrekitExceptionWrapper {
    try {
        // Set up the propagators parallelizer
        final NumericalPropagator[] propagators = createPropagators(point);
        final Orbit[] orbits = new Orbit[propagators.length];
        for (int i = 0; i < propagators.length; ++i) {
            mappers[i] = configureDerivatives(propagators[i]);
            orbits[i] = propagators[i].getInitialState().getOrbit();
        }
        final PropagatorsParallelizer parallelizer = new PropagatorsParallelizer(Arrays.asList(propagators), configureMeasurements(point));
        // Reset value and Jacobian
        evaluations.clear();
        value.set(0.0);
        for (int i = 0; i < jacobian.getRowDimension(); ++i) {
            for (int j = 0; j < jacobian.getColumnDimension(); ++j) {
                jacobian.setEntry(i, j, 0.0);
            }
        }
        // Run the propagation, gathering residuals on the fly
        if (forwardPropagation) {
            // Propagate forward from firstDate
            parallelizer.propagate(firstDate.shiftedBy(-1.0), lastDate.shiftedBy(+1.0));
        } else {
            // Propagate backward from lastDate
            parallelizer.propagate(lastDate.shiftedBy(+1.0), firstDate.shiftedBy(-1.0));
        }
        observer.modelCalled(orbits, evaluations);
        return new Pair<RealVector, RealMatrix>(value, jacobian);
    } catch (OrekitException oe) {
        throw new OrekitExceptionWrapper(oe);
    }
}
Also used : OrekitExceptionWrapper(org.orekit.errors.OrekitExceptionWrapper) Orbit(org.orekit.orbits.Orbit) NumericalPropagator(org.orekit.propagation.numerical.NumericalPropagator) PropagatorsParallelizer(org.orekit.propagation.PropagatorsParallelizer) OrekitException(org.orekit.errors.OrekitException) Pair(org.hipparchus.util.Pair)

Example 2 with PropagatorsParallelizer

use of org.orekit.propagation.PropagatorsParallelizer in project Orekit by CS-SI.

the class HarmonicParametricAccelerationTest method doTestEquivalentManeuver.

private void doTestEquivalentManeuver(final double mass, final AttitudeProvider maneuverLaw, final ConstantThrustManeuver maneuver, final AttitudeProvider accelerationLaw, final HarmonicParametricAcceleration parametricAcceleration, final double positionTolerance) throws OrekitException {
    SpacecraftState initialState = new SpacecraftState(initialOrbit, maneuverLaw.getAttitude(initialOrbit, initialOrbit.getDate(), initialOrbit.getFrame()), mass);
    double[][] tolerance = NumericalPropagator.tolerances(10, initialOrbit, initialOrbit.getType());
    // propagator 0 uses a maneuver that is so efficient it does not consume any fuel
    // (hence mass remains constant)
    AdaptiveStepsizeIntegrator integrator0 = new DormandPrince853Integrator(0.001, 100, tolerance[0], tolerance[1]);
    integrator0.setInitialStepSize(60);
    final NumericalPropagator propagator0 = new NumericalPropagator(integrator0);
    propagator0.setInitialState(initialState);
    propagator0.setAttitudeProvider(maneuverLaw);
    propagator0.addForceModel(maneuver);
    // propagator 1 uses a constant acceleration
    AdaptiveStepsizeIntegrator integrator1 = new DormandPrince853Integrator(0.001, 100, tolerance[0], tolerance[1]);
    integrator1.setInitialStepSize(60);
    final NumericalPropagator propagator1 = new NumericalPropagator(integrator1);
    propagator1.setInitialState(initialState);
    propagator1.setAttitudeProvider(accelerationLaw);
    propagator1.addForceModel(parametricAcceleration);
    MultiSatStepHandler handler = (interpolators, isLast) -> {
        Vector3D p0 = interpolators.get(0).getCurrentState().getPVCoordinates().getPosition();
        Vector3D p1 = interpolators.get(1).getCurrentState().getPVCoordinates().getPosition();
        Assert.assertEquals(0.0, Vector3D.distance(p0, p1), positionTolerance);
    };
    PropagatorsParallelizer parallelizer = new PropagatorsParallelizer(Arrays.asList(propagator0, propagator1), handler);
    parallelizer.propagate(initialOrbit.getDate(), initialOrbit.getDate().shiftedBy(1000.0));
}
Also used : ParameterDriver(org.orekit.utils.ParameterDriver) Arrays(java.util.Arrays) AdaptiveStepsizeFieldIntegrator(org.hipparchus.ode.nonstiff.AdaptiveStepsizeFieldIntegrator) LOFType(org.orekit.frames.LOFType) Rotation(org.hipparchus.geometry.euclidean.threed.Rotation) AdaptiveStepsizeIntegrator(org.hipparchus.ode.nonstiff.AdaptiveStepsizeIntegrator) AttitudeProvider(org.orekit.attitudes.AttitudeProvider) PVCoordinates(org.orekit.utils.PVCoordinates) SpacecraftState(org.orekit.propagation.SpacecraftState) LevenbergMarquardtOptimizer(org.hipparchus.optim.nonlinear.vector.leastsquares.LevenbergMarquardtOptimizer) PositionAngle(org.orekit.orbits.PositionAngle) Utils(org.orekit.Utils) CartesianOrbit(org.orekit.orbits.CartesianOrbit) PropagatorsParallelizer(org.orekit.propagation.PropagatorsParallelizer) FramesFactory(org.orekit.frames.FramesFactory) KeplerianOrbit(org.orekit.orbits.KeplerianOrbit) ObservedMeasurement(org.orekit.estimation.measurements.ObservedMeasurement) LofOffset(org.orekit.attitudes.LofOffset) List(java.util.List) InertialProvider(org.orekit.attitudes.InertialProvider) RealFieldElement(org.hipparchus.RealFieldElement) CelestialBodyPointed(org.orekit.attitudes.CelestialBodyPointed) NumericalPropagator(org.orekit.propagation.numerical.NumericalPropagator) ConstantThrustManeuver(org.orekit.forces.maneuvers.ConstantThrustManeuver) PV(org.orekit.estimation.measurements.PV) DormandPrince853Integrator(org.hipparchus.ode.nonstiff.DormandPrince853Integrator) MultiSatStepHandler(org.orekit.propagation.sampling.MultiSatStepHandler) FieldNumericalPropagator(org.orekit.propagation.numerical.FieldNumericalPropagator) DormandPrince853FieldIntegrator(org.hipparchus.ode.nonstiff.DormandPrince853FieldIntegrator) Orbit(org.orekit.orbits.Orbit) FieldSpacecraftState(org.orekit.propagation.FieldSpacecraftState) ArrayList(java.util.ArrayList) FieldAbsoluteDate(org.orekit.time.FieldAbsoluteDate) DormandPrince853IntegratorBuilder(org.orekit.propagation.conversion.DormandPrince853IntegratorBuilder) FieldVector3D(org.hipparchus.geometry.euclidean.threed.FieldVector3D) NumericalPropagatorBuilder(org.orekit.propagation.conversion.NumericalPropagatorBuilder) FastMath(org.hipparchus.util.FastMath) FieldBoundedPropagator(org.orekit.propagation.FieldBoundedPropagator) Before(org.junit.Before) CircularOrbit(org.orekit.orbits.CircularOrbit) Constants(org.orekit.utils.Constants) DateComponents(org.orekit.time.DateComponents) Vector3D(org.hipparchus.geometry.euclidean.threed.Vector3D) Test(org.junit.Test) Field(org.hipparchus.Field) OrekitException(org.orekit.errors.OrekitException) CelestialBodyFactory(org.orekit.bodies.CelestialBodyFactory) TimeScalesFactory(org.orekit.time.TimeScalesFactory) Decimal64Field(org.hipparchus.util.Decimal64Field) TimeComponents(org.orekit.time.TimeComponents) Assert(org.junit.Assert) BatchLSEstimator(org.orekit.estimation.leastsquares.BatchLSEstimator) AbsoluteDate(org.orekit.time.AbsoluteDate) SpacecraftState(org.orekit.propagation.SpacecraftState) FieldSpacecraftState(org.orekit.propagation.FieldSpacecraftState) NumericalPropagator(org.orekit.propagation.numerical.NumericalPropagator) FieldNumericalPropagator(org.orekit.propagation.numerical.FieldNumericalPropagator) FieldVector3D(org.hipparchus.geometry.euclidean.threed.FieldVector3D) Vector3D(org.hipparchus.geometry.euclidean.threed.Vector3D) AdaptiveStepsizeIntegrator(org.hipparchus.ode.nonstiff.AdaptiveStepsizeIntegrator) PropagatorsParallelizer(org.orekit.propagation.PropagatorsParallelizer) DormandPrince853Integrator(org.hipparchus.ode.nonstiff.DormandPrince853Integrator) MultiSatStepHandler(org.orekit.propagation.sampling.MultiSatStepHandler)

Example 3 with PropagatorsParallelizer

use of org.orekit.propagation.PropagatorsParallelizer in project Orekit by CS-SI.

the class PolynomialParametricAccelerationTest method doTestEquivalentManeuver.

private void doTestEquivalentManeuver(final double mass, final AttitudeProvider maneuverLaw, final ConstantThrustManeuver maneuver, final AttitudeProvider accelerationLaw, final PolynomialParametricAcceleration parametricAcceleration, final double positionTolerance) throws OrekitException {
    SpacecraftState initialState = new SpacecraftState(initialOrbit, maneuverLaw.getAttitude(initialOrbit, initialOrbit.getDate(), initialOrbit.getFrame()), mass);
    double[][] tolerance = NumericalPropagator.tolerances(10, initialOrbit, initialOrbit.getType());
    // propagator 0 uses a maneuver that is so efficient it does not consume any fuel
    // (hence mass remains constant)
    AdaptiveStepsizeIntegrator integrator0 = new DormandPrince853Integrator(0.001, 100, tolerance[0], tolerance[1]);
    integrator0.setInitialStepSize(60);
    final NumericalPropagator propagator0 = new NumericalPropagator(integrator0);
    propagator0.setInitialState(initialState);
    propagator0.setAttitudeProvider(maneuverLaw);
    propagator0.addForceModel(maneuver);
    // propagator 1 uses a constant acceleration
    AdaptiveStepsizeIntegrator integrator1 = new DormandPrince853Integrator(0.001, 100, tolerance[0], tolerance[1]);
    integrator1.setInitialStepSize(60);
    final NumericalPropagator propagator1 = new NumericalPropagator(integrator1);
    propagator1.setInitialState(initialState);
    propagator1.setAttitudeProvider(accelerationLaw);
    propagator1.addForceModel(parametricAcceleration);
    MultiSatStepHandler handler = (interpolators, isLast) -> {
        Vector3D p0 = interpolators.get(0).getCurrentState().getPVCoordinates().getPosition();
        Vector3D p1 = interpolators.get(1).getCurrentState().getPVCoordinates().getPosition();
        Assert.assertEquals(0.0, Vector3D.distance(p0, p1), positionTolerance);
    };
    PropagatorsParallelizer parallelizer = new PropagatorsParallelizer(Arrays.asList(propagator0, propagator1), handler);
    parallelizer.propagate(initialOrbit.getDate(), initialOrbit.getDate().shiftedBy(1000.0));
}
Also used : DormandPrince853Integrator(org.hipparchus.ode.nonstiff.DormandPrince853Integrator) Arrays(java.util.Arrays) AdaptiveStepsizeFieldIntegrator(org.hipparchus.ode.nonstiff.AdaptiveStepsizeFieldIntegrator) LOFType(org.orekit.frames.LOFType) MultiSatStepHandler(org.orekit.propagation.sampling.MultiSatStepHandler) Rotation(org.hipparchus.geometry.euclidean.threed.Rotation) AdaptiveStepsizeIntegrator(org.hipparchus.ode.nonstiff.AdaptiveStepsizeIntegrator) FieldNumericalPropagator(org.orekit.propagation.numerical.FieldNumericalPropagator) DormandPrince853FieldIntegrator(org.hipparchus.ode.nonstiff.DormandPrince853FieldIntegrator) AttitudeProvider(org.orekit.attitudes.AttitudeProvider) Orbit(org.orekit.orbits.Orbit) FieldSpacecraftState(org.orekit.propagation.FieldSpacecraftState) PVCoordinates(org.orekit.utils.PVCoordinates) FieldAbsoluteDate(org.orekit.time.FieldAbsoluteDate) SpacecraftState(org.orekit.propagation.SpacecraftState) PositionAngle(org.orekit.orbits.PositionAngle) FieldVector3D(org.hipparchus.geometry.euclidean.threed.FieldVector3D) FastMath(org.hipparchus.util.FastMath) FieldBoundedPropagator(org.orekit.propagation.FieldBoundedPropagator) Utils(org.orekit.Utils) Before(org.junit.Before) CartesianOrbit(org.orekit.orbits.CartesianOrbit) Constants(org.orekit.utils.Constants) DateComponents(org.orekit.time.DateComponents) Vector3D(org.hipparchus.geometry.euclidean.threed.Vector3D) PropagatorsParallelizer(org.orekit.propagation.PropagatorsParallelizer) FramesFactory(org.orekit.frames.FramesFactory) KeplerianOrbit(org.orekit.orbits.KeplerianOrbit) Test(org.junit.Test) LofOffset(org.orekit.attitudes.LofOffset) Field(org.hipparchus.Field) InertialProvider(org.orekit.attitudes.InertialProvider) OrekitException(org.orekit.errors.OrekitException) RealFieldElement(org.hipparchus.RealFieldElement) CelestialBodyPointed(org.orekit.attitudes.CelestialBodyPointed) CelestialBodyFactory(org.orekit.bodies.CelestialBodyFactory) NumericalPropagator(org.orekit.propagation.numerical.NumericalPropagator) TimeScalesFactory(org.orekit.time.TimeScalesFactory) Decimal64Field(org.hipparchus.util.Decimal64Field) ConstantThrustManeuver(org.orekit.forces.maneuvers.ConstantThrustManeuver) TimeComponents(org.orekit.time.TimeComponents) Assert(org.junit.Assert) AbsoluteDate(org.orekit.time.AbsoluteDate) FieldSpacecraftState(org.orekit.propagation.FieldSpacecraftState) SpacecraftState(org.orekit.propagation.SpacecraftState) FieldNumericalPropagator(org.orekit.propagation.numerical.FieldNumericalPropagator) NumericalPropagator(org.orekit.propagation.numerical.NumericalPropagator) FieldVector3D(org.hipparchus.geometry.euclidean.threed.FieldVector3D) Vector3D(org.hipparchus.geometry.euclidean.threed.Vector3D) AdaptiveStepsizeIntegrator(org.hipparchus.ode.nonstiff.AdaptiveStepsizeIntegrator) PropagatorsParallelizer(org.orekit.propagation.PropagatorsParallelizer) DormandPrince853Integrator(org.hipparchus.ode.nonstiff.DormandPrince853Integrator) MultiSatStepHandler(org.orekit.propagation.sampling.MultiSatStepHandler)

Aggregations

OrekitException (org.orekit.errors.OrekitException)3 Orbit (org.orekit.orbits.Orbit)3 PropagatorsParallelizer (org.orekit.propagation.PropagatorsParallelizer)3 NumericalPropagator (org.orekit.propagation.numerical.NumericalPropagator)3 Arrays (java.util.Arrays)2 Field (org.hipparchus.Field)2 RealFieldElement (org.hipparchus.RealFieldElement)2 FieldVector3D (org.hipparchus.geometry.euclidean.threed.FieldVector3D)2 Rotation (org.hipparchus.geometry.euclidean.threed.Rotation)2 Vector3D (org.hipparchus.geometry.euclidean.threed.Vector3D)2 AdaptiveStepsizeFieldIntegrator (org.hipparchus.ode.nonstiff.AdaptiveStepsizeFieldIntegrator)2 AdaptiveStepsizeIntegrator (org.hipparchus.ode.nonstiff.AdaptiveStepsizeIntegrator)2 DormandPrince853FieldIntegrator (org.hipparchus.ode.nonstiff.DormandPrince853FieldIntegrator)2 DormandPrince853Integrator (org.hipparchus.ode.nonstiff.DormandPrince853Integrator)2 Decimal64Field (org.hipparchus.util.Decimal64Field)2 FastMath (org.hipparchus.util.FastMath)2 Assert (org.junit.Assert)2 Before (org.junit.Before)2 Test (org.junit.Test)2 Utils (org.orekit.Utils)2