Example usage for org.apache.commons.math3.geometry.euclidean.threed FieldVector3D FieldVector3D

Introduction

In this page you can find the example usage for org.apache.commons.math3.geometry.euclidean.threed FieldVector3D FieldVector3D.

Prototype

public FieldVector3D(final double a, final FieldVector3D<T> u) 

Source Link

Document

Multiplicative constructor Build a vector from another one and a scale factor.

Usage

From source file:org.orekit.forces.BoxAndSolarArraySpacecraft.java

/** {@inheritDoc} */
public FieldVector3D<DerivativeStructure> dragAcceleration(final AbsoluteDate date, final Frame frame,
        final FieldVector3D<DerivativeStructure> position, final FieldRotation<DerivativeStructure> rotation,
        final DerivativeStructure mass, final double density,
        final FieldVector3D<DerivativeStructure> relativeVelocity) throws OrekitException {

    // relative velocity in spacecraft frame
    final FieldVector3D<DerivativeStructure> v = rotation.applyTo(relativeVelocity);

    // solar array contribution
    final FieldVector3D<DerivativeStructure> solarArrayFacet = new FieldVector3D<DerivativeStructure>(
            solarArrayArea, getNormal(date, frame, position, rotation));
    DerivativeStructure sv = FieldVector3D.dotProduct(v, solarArrayFacet).abs();

    // body facets contribution
    for (final Facet facet : facets) {
        final DerivativeStructure dot = FieldVector3D.dotProduct(v, facet.getNormal());
        if (dot.getValue() < 0) {
            // the facet intercepts the incoming flux
            sv = sv.subtract(dot.multiply(facet.getArea()));
        }/*from ww  w  .ja  v a2 s . c om*/
    }

    return new FieldVector3D<DerivativeStructure>(sv.multiply(density * dragCoeff / 2.0).divide(mass),
            relativeVelocity);

}

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From source file:org.orekit.forces.BoxAndSolarArraySpacecraft.java

/** {@inheritDoc} */
public FieldVector3D<DerivativeStructure> dragAcceleration(final AbsoluteDate date, final Frame frame,
        final Vector3D position, final Rotation rotation, final double mass, final double density,
        final Vector3D relativeVelocity, final String paramName) throws OrekitException {

    if (!DRAG_COEFFICIENT.equals(paramName)) {
        throw new OrekitException(OrekitMessages.UNSUPPORTED_PARAMETER_NAME, paramName, DRAG_COEFFICIENT);
    }// w ww  . java 2  s.c  om

    final DerivativeStructure dragCoeffDS = new DerivativeStructure(1, 1, 0, dragCoeff);

    // relative velocity in spacecraft frame
    final Vector3D v = rotation.applyTo(relativeVelocity);

    // solar array contribution
    final Vector3D solarArrayFacet = new Vector3D(solarArrayArea, getNormal(date, frame, position, rotation));
    double sv = FastMath.abs(Vector3D.dotProduct(solarArrayFacet, v));

    // body facets contribution
    for (final Facet facet : facets) {
        final double dot = Vector3D.dotProduct(facet.getNormal(), v);
        if (dot < 0) {
            // the facet intercepts the incoming flux
            sv -= facet.getArea() * dot;
        }
    }

    return new FieldVector3D<DerivativeStructure>(dragCoeffDS.multiply(sv * density / (2.0 * mass)),
            relativeVelocity);

}

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From source file:org.orekit.forces.BoxAndSolarArraySpacecraft.java

/** {@inheritDoc} */
public FieldVector3D<DerivativeStructure> radiationPressureAcceleration(final AbsoluteDate date,
        final Frame frame, final FieldVector3D<DerivativeStructure> position,
        final FieldRotation<DerivativeStructure> rotation, final DerivativeStructure mass,
        final FieldVector3D<DerivativeStructure> flux) throws OrekitException {

    if (flux.getNormSq().getValue() < Precision.SAFE_MIN) {
        // null illumination (we are probably in umbra)
        return new FieldVector3D<DerivativeStructure>(0.0, flux);
    }/*from   w w w  .  ja  va2  s.  c o m*/

    // radiation flux in spacecraft frame
    final FieldVector3D<DerivativeStructure> fluxSat = rotation.applyTo(flux);

    // solar array contribution
    FieldVector3D<DerivativeStructure> normal = getNormal(date, frame, position, rotation);
    DerivativeStructure dot = FieldVector3D.dotProduct(normal, fluxSat);
    if (dot.getValue() > 0) {
        // the solar array is illuminated backward,
        // fix signs to compute contribution correctly
        dot = dot.negate();
        normal = normal.negate();
    }
    FieldVector3D<DerivativeStructure> force = facetRadiationAcceleration(normal, solarArrayArea, fluxSat, dot);

    // body facets contribution
    for (final Facet bodyFacet : facets) {
        normal = new FieldVector3D<DerivativeStructure>(mass.getField().getOne(), bodyFacet.getNormal());
        dot = FieldVector3D.dotProduct(normal, fluxSat);
        if (dot.getValue() < 0) {
            // the facet intercepts the incoming flux
            force = force.add(facetRadiationAcceleration(normal, bodyFacet.getArea(), fluxSat, dot));
        }
    }

    // convert to inertial frame
    return rotation.applyInverseTo(new FieldVector3D<DerivativeStructure>(mass.reciprocal(), force));

}

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From source file:org.orekit.forces.gravity.CunninghamAttractionModelTest.java

@Test
public void testStateJacobian() throws OrekitException {

    Utils.setDataRoot("regular-data:potential/grgs-format");
    GravityFieldFactory.addPotentialCoefficientsReader(new GRGSFormatReader("grim4s4_gr", true));

    // initialization
    AbsoluteDate date = new AbsoluteDate(new DateComponents(2000, 07, 01), new TimeComponents(13, 59, 27.816),
            TimeScalesFactory.getUTC());
    double i = FastMath.toRadians(98.7);
    double omega = FastMath.toRadians(93.0);
    double OMEGA = FastMath.toRadians(15.0 * 22.5);
    Orbit orbit = new KeplerianOrbit(7201009.7124401, 1e-3, i, omega, OMEGA, 0, PositionAngle.MEAN,
            FramesFactory.getEME2000(), date, mu);
    OrbitType integrationType = OrbitType.CARTESIAN;
    double[][] tolerances = NumericalPropagator.tolerances(0.01, orbit, integrationType);

    propagator = new NumericalPropagator(
            new DormandPrince853Integrator(1.0e-3, 120, tolerances[0], tolerances[1]));
    propagator.setOrbitType(integrationType);
    CunninghamAttractionModel cuModel = new CunninghamAttractionModel(itrf2008,
            GravityFieldFactory.getUnnormalizedProvider(50, 50));
    Assert.assertEquals(TideSystem.UNKNOWN, cuModel.getTideSystem());
    propagator.addForceModel(cuModel);/*from ww w.  j a  v  a2  s.  co m*/
    SpacecraftState state0 = new SpacecraftState(orbit);
    propagator.setInitialState(state0);
    try {
        DerivativeStructure one = new DerivativeStructure(7, 1, 1.0);
        cuModel.accelerationDerivatives(state0.getDate(), state0.getFrame(),
                new FieldVector3D<DerivativeStructure>(one, state0.getPVCoordinates().getPosition()),
                new FieldVector3D<DerivativeStructure>(one, state0.getPVCoordinates().getVelocity()),
                new FieldRotation<DerivativeStructure>(one.multiply(state0.getAttitude().getRotation().getQ0()),
                        one.multiply(state0.getAttitude().getRotation().getQ1()),
                        one.multiply(state0.getAttitude().getRotation().getQ2()),
                        one.multiply(state0.getAttitude().getRotation().getQ3()), false),
                one.multiply(state0.getMass()));
        Assert.fail("an exception should have been thrown");
    } catch (OrekitException oe) {
        Assert.assertEquals(OrekitMessages.STEPS_NOT_INITIALIZED_FOR_FINITE_DIFFERENCES, oe.getSpecifier());
    }
    cuModel.setSteps(1.0, 1.0e10);

    checkStateJacobian(propagator, state0, date.shiftedBy(3.5 * 3600.0), 40000, tolerances[0], 2.0e-7);
}

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From source file:org.orekit.forces.gravity.DrozinerAttractionModelTest.java

@Test
public void testStateJacobian() throws OrekitException {

    Utils.setDataRoot("regular-data:potential/grgs-format");
    GravityFieldFactory.addPotentialCoefficientsReader(new GRGSFormatReader("grim4s4_gr", true));

    // initialization
    AbsoluteDate date = new AbsoluteDate(new DateComponents(2000, 07, 01), new TimeComponents(13, 59, 27.816),
            TimeScalesFactory.getUTC());
    double i = FastMath.toRadians(98.7);
    double omega = FastMath.toRadians(93.0);
    double OMEGA = FastMath.toRadians(15.0 * 22.5);
    Orbit orbit = new KeplerianOrbit(7201009.7124401, 1e-3, i, omega, OMEGA, 0, PositionAngle.MEAN,
            FramesFactory.getEME2000(), date, mu);
    OrbitType integrationType = OrbitType.CARTESIAN;
    double[][] tolerances = NumericalPropagator.tolerances(0.01, orbit, integrationType);

    propagator = new NumericalPropagator(
            new DormandPrince853Integrator(1.0e-3, 120, tolerances[0], tolerances[1]));
    propagator.setOrbitType(integrationType);
    DrozinerAttractionModel drModel = new DrozinerAttractionModel(itrf2008,
            GravityFieldFactory.getUnnormalizedProvider(50, 50));
    Assert.assertEquals(TideSystem.UNKNOWN, drModel.getTideSystem());
    propagator.addForceModel(drModel);/*w  w  w. j  a  v  a2  s.co  m*/
    SpacecraftState state0 = new SpacecraftState(orbit);
    propagator.setInitialState(state0);
    try {
        DerivativeStructure one = new DerivativeStructure(7, 1, 1.0);
        drModel.accelerationDerivatives(state0.getDate(), state0.getFrame(),
                new FieldVector3D<DerivativeStructure>(one, state0.getPVCoordinates().getPosition()),
                new FieldVector3D<DerivativeStructure>(one, state0.getPVCoordinates().getVelocity()),
                new FieldRotation<DerivativeStructure>(one.multiply(state0.getAttitude().getRotation().getQ0()),
                        one.multiply(state0.getAttitude().getRotation().getQ1()),
                        one.multiply(state0.getAttitude().getRotation().getQ2()),
                        one.multiply(state0.getAttitude().getRotation().getQ3()), false),
                one.multiply(state0.getMass()));
        Assert.fail("an exception should have been thrown");
    } catch (OrekitException oe) {
        Assert.assertEquals(OrekitMessages.STEPS_NOT_INITIALIZED_FOR_FINITE_DIFFERENCES, oe.getSpecifier());
    }
    drModel.setSteps(1.0, 1.0e10);

    checkStateJacobian(propagator, state0, date.shiftedBy(3.5 * 3600.0), 40000, tolerances[0], 2.0e-7);

}

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From source file:org.orekit.forces.gravity.NewtonianAttraction.java

/** {@inheritDoc} */
public FieldVector3D<DerivativeStructure> accelerationDerivatives(final AbsoluteDate date, final Frame frame,
        final FieldVector3D<DerivativeStructure> position, final FieldVector3D<DerivativeStructure> velocity,
        final FieldRotation<DerivativeStructure> rotation, final DerivativeStructure mass)
        throws OrekitException {

    final DerivativeStructure r2 = position.getNormSq();
    return new FieldVector3D<DerivativeStructure>(r2.sqrt().multiply(r2).reciprocal().multiply(-mu), position);

}

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From source file:org.orekit.forces.gravity.NewtonianAttraction.java

/** {@inheritDoc} */
public FieldVector3D<DerivativeStructure> accelerationDerivatives(final SpacecraftState s,
        final String paramName) throws OrekitException {

    complainIfNotSupported(paramName);//w w w  .j  av  a 2  s. co  m

    final Vector3D position = s.getPVCoordinates().getPosition();
    final double r2 = position.getNormSq();
    final DerivativeStructure muds = new DerivativeStructure(1, 1, 0, mu);
    return new FieldVector3D<DerivativeStructure>(muds.divide(-r2 * FastMath.sqrt(r2)), position);

}

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From source file:org.orekit.forces.gravity.ThirdBodyAttraction.java

/** {@inheritDoc} */
public FieldVector3D<DerivativeStructure> accelerationDerivatives(final AbsoluteDate date, final Frame frame,
        final FieldVector3D<DerivativeStructure> position, final FieldVector3D<DerivativeStructure> velocity,
        final FieldRotation<DerivativeStructure> rotation, final DerivativeStructure mass)
        throws OrekitException {

    // compute bodies separation vectors and squared norm
    final Vector3D centralToBody = body.getPVCoordinates(date, frame).getPosition();
    final double r2Central = centralToBody.getNormSq();
    final FieldVector3D<DerivativeStructure> satToBody = position.subtract(centralToBody).negate();
    final DerivativeStructure r2Sat = satToBody.getNormSq();

    // compute relative acceleration
    final FieldVector3D<DerivativeStructure> satAcc = new FieldVector3D<DerivativeStructure>(
            r2Sat.sqrt().multiply(r2Sat).reciprocal().multiply(gm), satToBody);
    final Vector3D centralAcc = new Vector3D(gm / (r2Central * FastMath.sqrt(r2Central)), centralToBody);
    return satAcc.subtract(centralAcc);

}

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From source file:org.orekit.forces.maneuvers.ConstantThrustManeuver.java

/** {@inheritDoc} */
public FieldVector3D<DerivativeStructure> accelerationDerivatives(final AbsoluteDate date, final Frame frame,
        final FieldVector3D<DerivativeStructure> position, final FieldVector3D<DerivativeStructure> velocity,
        final FieldRotation<DerivativeStructure> rotation, final DerivativeStructure mass)
        throws OrekitException {
    if (firing) {
        return new FieldVector3D<DerivativeStructure>(mass.reciprocal().multiply(thrust),
                rotation.applyInverseTo(direction));
    } else {//from  ww  w.j av  a2  s.c o m
        // constant (and null) acceleration when not firing
        final int parameters = mass.getFreeParameters();
        final int order = mass.getOrder();
        return new FieldVector3D<DerivativeStructure>(new DerivativeStructure(parameters, order, 0.0),
                new DerivativeStructure(parameters, order, 0.0),
                new DerivativeStructure(parameters, order, 0.0));
    }
}

---

From source file:org.orekit.forces.maneuvers.ConstantThrustManeuver.java

/** {@inheritDoc} */
public FieldVector3D<DerivativeStructure> accelerationDerivatives(final SpacecraftState s,
        final String paramName) throws OrekitException {

    complainIfNotSupported(paramName);//from  w ww.  j av  a 2 s .c  o m

    if (firing) {

        if (THRUST.equals(paramName)) {
            final DerivativeStructure thrustDS = new DerivativeStructure(1, 1, 0, thrust);
            return new FieldVector3D<DerivativeStructure>(thrustDS.divide(s.getMass()),
                    s.getAttitude().getRotation().applyInverseTo(direction));
        } else if (FLOW_RATE.equals(paramName)) {
            // acceleration does not depend on flow rate (only mass decrease does)
            final DerivativeStructure zero = new DerivativeStructure(1, 1, 0.0);
            return new FieldVector3D<DerivativeStructure>(zero, zero, zero);
        } else {
            throw new OrekitException(OrekitMessages.UNSUPPORTED_PARAMETER_NAME, paramName,
                    THRUST + ", " + FLOW_RATE);
        }

    } else {
        // constant (and null) acceleration when not firing
        final DerivativeStructure zero = new DerivativeStructure(1, 1, 0.0);
        return new FieldVector3D<DerivativeStructure>(zero, zero, zero);
    }

}

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