Examples with MultiSatStepHandler org.orekit.propagation.sampling.MultiSatStepHandler used on opensource projects

Example 1 with MultiSatStepHandler

use of org.orekit.propagation.sampling.MultiSatStepHandler 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));
}

Example 2 with MultiSatStepHandler

use of org.orekit.propagation.sampling.MultiSatStepHandler 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));
}